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    • 专利摘要:
    Gas turbine engine mechanism control system. The present invention relates to a distributed gas turbine engine mechanism control system. the gas turbine engine mechanism control system (36) comprising a motor mechanism controller (38) configured to control a plurality of parameters associated with the operation of a gas turbine engine mechanism system (10); and a plurality of remote interface units (40) communicatively coupled to the motor mechanism controller (38), wherein the remote interface unit is configured to receive an input signal from the motor mechanism controller (38) indicative of values. respective targets of at least one parameter of a plurality of parameters and the remote interface unit is configured to provide closed loop control of at least one parameter based on the input signal and feedback signals indicative of respective values measured from the at least one. least one parameter.
    公开号:BR102013007063A2
    申请号:R102013007063-7
    申请日:2013-03-26
    公开日:2018-11-21
    发明作者:Harry Kirk Mathews；Brent Jerome Brunell；Emad Andarawis Andarawis；R. Sheldon Carpenter；Samhita Dasgupta；Scott Douglas Waun；Simon Shlomo Lis；Sridhar Adibhatla
    申请人:General Electric Company；
    IPC主号:
    专利说明:

    (54) Title: GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (51) Int. Cl .: F02C 9/50.
    (30) Unionist Priority: 03/30/2012 US 13 / 436,184.
    (71) Depositor (s): GENERAL ELECTRIC COMPANY.
    (72) Inventor (s): HARRY KIRK MATHEWS JR .; BRENT JEROME BRUNELL; EMAD ANDARAWIS ANDARAWIS; R. SHELDON CARPENTER; SAMHITA DASGUPTA; SCOTT DOUGLAS WAUN; SIMON SHLOMO LIS; SRIDHAR ADIBHATLA.
    (57) Abstract: GAS TURBINE ENGINE CONTROL SYSTEM. The present invention relates to a distributed gas turbine engine control system. The gas turbine engine mechanism control system (36) comprising a motor engine controller (38) configured to control a plurality of parameters associated with the operation of a gas turbine engine mechanism system (10); and a plurality of remote interface units (40) communicatively coupled to the motor mechanism controller (38), the remote interface unit being configured to receive an input signal from the motor mechanism controller (38) indicative of values respective targets of at least one parameter of a plurality of parameters and the remote interface unit is configured to provide closed loop control of at least one parameter based on the input signal and feedback signals indicative of respective values measured from at least least one parameter.
    1/27 “GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM” Field of the Invention [001] The present invention relates to a distributed gas turbine engine mechanism control system.
    Background of the Invention [002] Gas turbine systems typically employ a motor engine controller, such as a full authority digital engine engine controller (FADEC), to control various parameters associated with the operation of the gas turbine system. For example, the engine engine controller can be configured to receive an input signal (for example, indicative of throttle setting, desired fuel mix, etc.) from a remote network and to adjust various operating parameters of the engine system. gas turbine based on the input signal. As an example, if the controller receives an input signal indicative of a desired throttle setting, the engine mechanism controller can rotate the compressor's propeller blades to a desired angle, adjust the fuel valve positions, and / or adjust the cooling air flow to the turbine blades to establish the desired throttle setting.
    [003] Certain motor mechanism controllers use a first control loop to calculate the target values of the operating parameters based on the input signal and a second control loop to adjust the operating parameters based on the target values. To facilitate control of operating parameters, multiple actuators can be communicatively coupled to the motor mechanism controller. In addition, the sensors can be communicatively coupled to the motor mechanism controller to provide feedback signals indicative of measured values from operating parameters, thereby enabling the motor mechanism controller to provide loop control.
    2/27 closed of actuators. In certain embodiments, the sensors can be arranged inside a motor mechanism controller housing and a line / tube can extend between each sensor and a respective component associated with the parameter. For example, the motor mechanism controller can be configured to control the compressor outlet pressure by adjusting a valve position based on a measured compressor outlet pressure. Consequently, a tube can extend from a pressure tap to an electronic pressure transducer inside the motor mechanism controller. In this configuration, the motor mechanism controller can monitor the compressor outlet pressure based on feedback from the electronic transducer and adjust the valve position until the measured pressure is substantially equal to a desired pressure.
    [004] As the number of parameters controlled inside the gas turbine system increases, the number of sensors inside the engine mechanism controller and the corresponding number of lines / tubes also increases. The increased number of sensors can increase the size of the motor mechanism controller housing, thereby increasing the difficulty associated with mounting the motor mechanism controller inside a motor mechanism nacelle. In addition, the increased number of lines / tube can increase the weight of the engine engine control system, thereby reducing vehicle performance. In addition, due to the fact that the sensors inside the motor mechanism controller are selected to measure the parameters associated with the particular motor mechanism configuration, modification of the motor mechanism configuration (for example, varying the number and / or type of parameters controlled) can request a remodeling and recertification of the motor mechanism controller. Consequently, the duration and costs associated with the development of a motor mechanism can
    3/27 be increased undesirably.
    Description of the Invention [005] In one embodiment, a gas turbine engine control system includes a motor engine controller configured to control multiple parameters associated with the operation of a gas turbine engine system. The gas turbine engine mechanism control system also includes multiple remote interface units communicatively coupled to the engine engine controller. The remote interface unit is configured to receive an input signal from the motor engine controller indicative of respective target values of at least one parameter and the remote interface unit is configured to provide closed loop control of at least one signal-based parameter input and feedback signals indicative of respective values measured from at least one parameter.
    [006] In another embodiment, a gas turbine engine engine control system includes multiple remote interface units distributed throughout an entire gas turbine engine engine system. The remote interface unit includes an actuator configured to adjust a respective parameter associated with the operation of the gas turbine engine mechanism system, a sensor configured to emit a feedback signal indicating a measured value of the respective parameter and a coupled interface controller communicatively to the actuator and the sensor. The interface controller is configured to provide closed-loop control of the actuator based on the feedback signal. The gas turbine engine engine control system also includes a engine engine controller communicatively coupled to the remote interface unit. The motor mechanism controller is configured to instruct the interface controller to establish a target value for the respective parameter.
    4/27 [007] In an additional embodiment, a gas turbine engine control system includes a engine engine controller configured to control multiple parameters associated with the operation of a gas turbine engine system. The gas turbine engine mechanism control system also includes multiple remote interface units communicatively coupled to the engine engine controller. At least one remote interface unit includes at least one local loop closure module that has an interface controller. The at least one remote interface unit also includes an actuator communicatively coupled to the interface controller and configured to adjust a parameter. In addition, the at least one remote interface unit includes a sensor communicatively coupled to the interface controller and configured to emit a feedback signal indicating a measured value of a parameter. The interface controller is configured to provide closed-loop control of the actuator based on the feedback signal and an input signal from the motor mechanism controller indicative of a target value of a parameter.
    Brief Description of the Drawings [008] These and other features, aspects and advantages of the present invention will become better understood when the following detailed descriptions are read with respect to the accompanying drawings in which similar characters represent similar parts throughout the drawings, in which:
    Figure 1 is a block diagram of an embodiment of a turbine system that includes a distributed control system configured to adjust various operating parameters of the turbine system by means of multiple remote interface units distributed throughout the turbine system;
    Figure 2 is a block diagram of an implementation of a distributed control system that can be used inside the system
    5/27 of turbine of Figure 1;
    Figure 3 is a block diagram of an embodiment of a remote interface unit that can be employed within the distributed control system of Figure 2; and
    Figure 4 is a block diagram of an alternative embodiment of a remote interface unit that can be employed within the distributed control system of Figure 2.
    Description of Invention Realizations [009] One or more more specific realizations will be described below. In an effort to provide a concise description of these achievements, all the features of an actual implementation may not be described in the specification. It must be understood that in the development of any such real implementation, as in any engineering or model design, numerous specific implementation decisions must be made to achieve the specific goals of the developers, such as compliance with business and system-related restrictions, which may vary from one implementation to another. Furthermore, it must be understood that such an attempt at development can be complex and time-consuming, but it would nonetheless be a routine task of modeling, manufacturing and production for those of ordinary skill who have the benefit of this revelation.
    [010] When introducing elements of various achievements revealed in this document, the articles, “one, one”, “o, a” and “said, said” are intended to mean that there are one or more of the elements. The terms "who understands", "who includes," and "who has" are intended to be inclusive and mean that there may be additional elements in addition to the elements listed.
    [011] Achievements disclosed in this document can substantially reduce the weight and complexity of a
    6/27 motor mechanism for the distribution of remote interface units throughout a turbine system to provide local control of parameters associated with the operation of the turbine system. In certain embodiments, a gas turbine engine engine control system includes a engine engine controller configured to control multiple parameters associated with the operation of the gas turbine engine engine system. The gas turbine engine mechanism control system also includes multiple remote interface units communicatively coupled to the engine engine controller. The remote interface unit is configured to receive an input signal from the motor mechanism controller indicative of a target value of an operational parameter. The remote interface unit is also configured to provide closed loop control of the operating parameter based on the input signal and a feedback signal indicative of a measured value of the operating parameter. The remote interface units can be distributed throughout the gas turbine engine mechanism system to control a variety of operational parameters, such as valve position, propeller blade orientations and fluid pressures, among others. In certain embodiments, the remote interface unit includes an actuator configured to set the operating parameter and a sensor configured to output the feedback signal.
    [012] Due to the fact that remote interface units provide local control of operating parameters, the weight and complexity of the motor mechanism control system can be reduced substantially, compared to configurations in which the motor mechanism controller directly controls the operational parameters. For example, due to the fact that the sensors are communicatively coupled to the local remote interface units, lines / tubes that extend between components associated with each parameter and sensors
    7/27 mounted inside the motor mechanism controller are avoided, thereby reducing the weight of the motor mechanism control system. In addition, due to the fact that the sensors are not arranged inside the motor mechanism controller, the size of the motor mechanism controller can be reduced, thereby facilitating the assembly of the motor mechanism controller inside a nacelle. the motor mechanism. In addition, the number of controlled parameters can be adjusted by varying the number of remote interface units and / or the number of actuators / sensors inside each remote interface unit. Consequently, a single motor mechanism controller configuration can be employed to control the operation of a variety of motor mechanism configurations (for example, which have different numbers and / or types of operating parameters), thereby obviating the process remodeling and recertifies the engine engine controller for each engine engine configuration. As a result, engine engine development costs can be reduced significantly.
    [013] Referring now to the drawings, Figure 1 is a block diagram of an embodiment of a turbine system that includes a distributed control system configured to adjust various operating parameters of the turbine system through multiple distributed remote interface units throughout the turbine system. Although a turbine system is described below, it should be understood that the distributed control system can be used to adjust operating parameters inside other rotating machines or turbo machines, such as a compressor, a jet engine, a pump, or a steam turbine, for example. The illustrated turbine system 10 includes a fuel injector 12, a fuel supply 14 and a combustor 16. As illustrated, the fuel supply 14 directs a liquid fuel and / or gas
    8/27 fuel, such as natural gas, to the gas turbine system 10 through the fuel injector 12 into the combustor 16. As discussed below, the fuel injector 12 is configured to inject and mix the fuel with compressed air . Combustion 16 ignites and ignites the fuel-air mixture and then passes hot pressurized gas into a turbine 18. As will be understood, turbine 18 includes one or more stators that have fixed propeller blades or blades and one or more rotors that have blades that rotate in relation to the stators. The hot gas passes through the rotor blades of the turbine, thereby activating the rotor of the turbine to rotate. Engagement between the turbine rotor and an axis 19 causes the axis 19 to rotate, which is also coupled to various components throughout the gas turbine system 10, as illustrated. Eventually, the gas leaves the gas turbine system 10 via an exhaust fan 20.
    [014] A compressor 22 includes blades rigidly mounted to a rotor that is driven to rotate around axis 19. As air passes through the rotating blades, the air pressure increases, thereby supplying the combustor 16 with sufficient air for proper combustion. The compressor 22 receives air into the gas turbine system 10 through an air inlet 24. In addition, the shaft 19 can be coupled to a load 26, which can be fed by turning the shaft 19. How will it be understood, load 26 can be any suitable device that can use the power of the rotating outlet of the gas turbine system 10, such as the power generation plant or an external mechanical load. For example, charge 26 may include an electric generator, an airplane propeller, and so on. The air inlet 24 draws air 30 into the gas turbine system 10 by means of a suitable mechanism, such as a cold air inlet. Air 30 then flows through the blades of compressor 22, which supplies compressed air 32 to combustion 16. In particular, fuel injector 12 can inject air
    9/27 compressed 32 and fuel 14, as a mixture of fuel and air 34, into the combustor 16. Alternatively, compressed air 32 and fuel 14 can be injected directly into the combustion for mixing and combustion.
    [015] As illustrated, the turbine system 10 includes a distributed motor mechanism control system 36 that has a motor mechanism controller 38 and multiple remote interface units (RIU) 40 distributed throughout the turbine system 10. The controller motor mechanism 38 is configured to control multiple parameters associated with the operation of the turbine system 10. For example, the motor mechanism controller can be configured to receive instructions from a remote network and to control the operating parameters of the turbine system 10 based on the instructions. For example, if the engine engine controller 38 is instructed to establish a desired throttle setting, the engine engine controller 38 can send signals to remote interface units 40, instructing remote interface units 40 to adjust various parameters the turbine system 10 to achieve the desired throttle setting. For example, the engine mechanism controller 38 can instruct the remote interface unit 40 coupled to the compressor 22 to adjust a propeller blade angle of the compressor. The engine mechanism controller 38 can also instruct the remote interface unit 40 coupled to the combustion 16 to open valves that provide increased fuel flow to the combustion 16. In addition, the engine mechanism controller 38 can instruct the coupled remote interface unit 40 to turbine 18 opening valves that provide additional cooling air flow to the turbine blades. In this way, a desired throttle setting can be obtained while maintaining the efficiency of the turbine system. In the illustrated embodiment, the motor mechanism controller 38 is configured to receive
    10/27 instructions for an aircraft flight control system. However, it should be understood that the motor mechanism controller 38 can receive instructions from a terrestrial control network, or any other suitable system configured to provide instructions to the motor mechanism controller 38.
    [016] Each remote interface unit 40 inside the turbine system 10 is communicatively coupled to the motor mechanism controller 38 and configured to receive an input signal from the motor mechanism controller 38 indicative of a target value of an operational parameter . For example, the controller of the motor mechanism 38 can send an input signal to the remote interface unit 40 coupled to the compressor 22 indicative of a target propeller blade angle. Similarly, the engine mechanism controller 38 can send an input signal to the remote interface unit 40 coupled to the combustion 16 indicative of a fuel valve position. Each remote interface unit 40, in turn, is configured to provide closed loop control of the operational parameter based on the input signal and a feedback signal indicative of a measured value of the parameter. Consequently, if the engine mechanism controller 38 instructs the remote interface unit 40 coupled to the compressor 22 to rotate the compressor's propeller blades to a target angle, the remote interface unit 40 can instruct an actuator to rotate the propeller blades to the target angle based on a feedback signal from a sensor configured to measure the propeller blade angle. In addition, if the engine mechanism controller 38 instructs the remote interface unit 40 coupled to the combustor 16 to adjust a fuel valve to a target position, the remote interface unit 40 can instruct an actuator to adjust the valve to the target position based on a feedback signal from a sensor configured to measure position
    11/27 valve.
    [017] Certain remote interface units 40 include one or more local loop closure modules (LLCM) 42 configured to independently provide closed loop control of a respective operational parameter. For example, in the illustrated embodiment, the remote interface unit 40 coupled to the compressor 22 includes two local loop closure modules 42. As discussed in detail below, each local loop closure module 42 includes an interface controller configured to provide control closed-loop actuator based on a feedback signal from a sensor and the input signal from the motor mechanism controller 38. Each remote interface unit 40 can include 1,2,3, 4, 5, 6, 7, 8, 9, 10, or more local loop closure modules 42 to provide closed loop control of a corresponding number of operational parameters. Consequently, each remote interface unit 40 can control parameters associated with a component (for example, compressor 22, combustion 16, turbine 18, etc.) coupled to remote interface unit 40, thereby providing distributed control of the turbine system 10.
    [018] An alternative embodiment of a remote interface unit 40 is coupled to the combustor 16. The remote interface unit 40 includes a multiple local loop closure module (MLLCM) 44 configured to provide multiple parameter closed loop control associated with the operation of the turbine system 10. As discussed in detail below, the multiple local loop closure module 44 includes an interface controller configured to provide closed loop control of multiple actuators based on feedback signals from multiple sensors. For example, the remote interface unit 40 may include multiple actuators configured to adjust a respective set of operating parameters and
    12/27 multiple sensors configured to send a respective set of feedback signals. In such embodiments, the interface controller of the multiple local loop closure module 44, which is communicatively coupled to each actuator and each sensor, is configured to provide closed loop control of the actuators based on the respective feedback signals. In this way, a single multiple local loop closure module 44 within remote interface unit 40 can control multiple operating parameters associated with a component (eg compressor 22, combustion 16, turbine 18, etc.) of the system turbine 10. Although the illustrated remote interface unit 40 includes a single multiple local loop closure module 44, it should be understood that additional local loop closure modules and / or multiple additional local loop closure modules can be included in realizations. remote interface unit alternatives 40.
    [019] As illustrated, another embodiment of a remote interface unit 40 is coupled to the turbine 18. The remote interface unit 40 includes two sets of smart actuators 46. Each set of smart actuators 46 includes an actuator configured to set an operational parameter of the turbine system 10 and a sensor configured to emit a feedback signal indicative of a measured value of the operational parameter. Each set of smart actuators 46 also includes an interface controller configured to provide closed-loop control of the actuator based on the feedback signal and the input signal from the motor mechanism controller 38 indicative of the parameter's target value. Certain remote interface units 40 may include 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, or more sets of smart actuators 46 to provide closed loop control of a corresponding number of operating parameters. Other remote interface units 40 may include at least one set
    13/27 of smart actuators 46, at least one local loop closure module 44, and / or at least one multiple local loop closure module 44.
    [020] Although three remote interface units 40 are employed in the illustrated embodiment, it should be understood that alternative motor mechanism control systems 36 may employ greater or lesser quantities of remote interface units 40. For example, in certain embodiments, the system motor mechanism control unit 36 may include 1, 2, 3, 4, 5, 6, 7, or more remote interface units distributed throughout the turbine system 10. In addition, it should be understood that remote interface units 40 can be mounted inside a variety of locations throughout the turbine system 10. For example, a remote interface unit can be mounted on an external surface of the compressor 22, within a turbine core 18, and / or between turbine 18 and combustor 16, for example. In certain embodiments, each component of the remote interface unit can be arranged within a single housing. Alternatively, sensors and / or actuators can be remotely mounted to the housing and communicatively coupled to the interface controller, which is arranged inside the housing. For example, a remote interface unit housing mounted on the outer surface of the compressor 22 can be communicatively coupled to a sensor mounted inside the turbine core.
    [021] As discussed earlier, each remote interface unit 40 includes a sensor configured to measure an operational parameter. Due to the fact that the sensors are not arranged inside the motor mechanism controller, line / tubes configured to transmit pressures / temperatures to the motor mechanism controller are avoided. Consequently, the weight of the motor mechanism control system 36 can be reduced. In addition, the size of the motor mechanism controller
    14/27 can be reduced due to the fact that the sensors are mounted inside the respective remote interface units 40, thereby facilitating the assembly of a motor mechanism controller inside a motor mechanism nacelle. In addition, the motor mechanism controller 38 can be used to control a variety of motor mechanism configurations by varying the type and / or number of remote interface units communicatively coupled to the motor mechanism controller. Consequently, the process of remodeling and recertifying the engine engine controller to vary the engine engine configurations is avoided, which reduces the costs of developing the turbine system.
    [022] Figure 2 is a block diagram of an embodiment of a distributed control system 36 that can be employed inside the turbine system 10 of Figure 1. In the illustrated embodiment, the motor mechanism controller 38 includes a control module motor mechanism 50 configured to control multiple parameters associated with the operation of the turbine system 10 and a power conditioning module 52 configured to supply electrical power to the motor mechanism control module 50 and remote interface units 40. In certain embodiments , the motor mechanism control module 50 and the energy conditioning module 52 are arranged inside independent housings positioned remotely from each other. Consequently, the motor mechanism control module 50 can be thermally isolated from the heat generated by the energy conditioning module 52. The reduced heat flow to the motor mechanism control module 50 can facilitate more compact spacing of electronic components, in this way, the size of the motor mechanism controller 38 is reduced. In addition, heat dissipation features, such as cooling vanes and / or a
    15/27 active fluid cooling system, can be avoided, thereby reducing the cost and complexity of the motor mechanism controller 38.
    [023] In the illustrated embodiment, the power conditioning module 52 is configured to supply electrical energy to a first electrical bus 54 and a second electrical bus 56. As will be understood, the first and second electrical buses 54 and 56 provide a system of redundant power distribution that increases the availability of the turbine system 10. As illustrated, the first and second electrical buses 54 and 56 are electrically coupled to an ignition exciter 58. Ignition exciter 58 is configured to generate a high voltage signal for a first igniter 60 and a second igniter 62. The igniters are configured to start combustion inside the combustion 16 during engine start procedures.
    [024] Electrical buses 54 and 56 are also electrically coupled to remote interface units 40 to provide redundant electrical power to remote interface units 40. In addition, a first communication bus 64 and a second communication bus 66 s extend between the engine mechanism control module 50 and each remote interface unit 40. Communication buses 64 and 66 are configured to provide redundant signals between the engine mechanism control module 50 and remote interface units 40. In the illustrated embodiment , a remote interface unit 40 includes two local loop closure modules 42 to provide redundant closed loop control of an operational parameter. As illustrated, the remote interface unit 40 is divided into a section of channel A and a section of channel B. Each channel is configured to independently control the same operational parameter, thereby providing redundant control. As
    16/27 illustrated, the first electrical bus 54 is coupled to channel section A and the second electrical bus 56 is coupled to channel section B. Consequently, if one channel is disabled due to an interruption in electricity, the other channel can continue the operation. Similarly, the first communication bus 64 is coupled to a communication module 68 in channel section A and the second communication bus 66 is coupled to a communication module 68 in channel section B. In this configuration, if a channel and disabled due to an interruption in one communication bus, the other channel can continue operation.
    [025] In addition, channel section A includes a first local loop closure module 42 communicatively coupled to a first communication module 68 and channel channel B includes a second local loop closure module 42 coupled from communicative form to a second communication module 68. Communication modules 68 are configured to establish a communication link between an interface controller 70 in the local loop closure module 42 and the respective communication bus. Consequently, an input signal from the motor mechanism controller 38 can be sent to the local loop closure module 42 and a return signal can be sent from the local loop closure module 42 to the motor mechanism controller 38. For example, the input signal from the motor mechanism controller 38 can be indicative of a target value of an operational parameter. The return signal can be indicative of a measured value of the operational parameter, and / or an operational state of the local loop closure module 42. Consequently, the motor mechanism controller 38 can monitor the value of each operational parameter to determine whether a parameter exceeds a limit value, and / or to facilitate control of the turbine system 10. In addition, the engine mechanism controller 38 can monitor the health / condition
    17/27 operational of each component within the distributed motor mechanism control system 36.
    [026] As will be understood, a variety of communication protocols can be employed to establish a communication link between communication modules 68 and motor engine control module 50. For example, the first communication bus 64 and the second communication bus 66 can use a balanced digital multipoint network (for example, RS-485) to facilitate communication throughout the distributed motor mechanism control system 36. communication buses 64 and 66 can also employ other communication protocols wired or wireless. For example, if a wireless communication link is employed, reducing wiring can substantially reduce the weight and complexity of the distributed motor mechanism control system 36. In certain embodiments, communication modules 68 can be configured to communicate with the engine mechanism control module 50 via electrical busbars 54 and 56. For example, the engine mechanism control module 50 and communication modules 68 can be configured to modulate an electrical power signal in such a way that Inlet and retraining can be transmitted throughout the distributed motor mechanism control system 36, thereby preventing separate wired connections.
    [027] As discussed earlier, each local loop closure module includes an interface controller 70 configured to provide closed loop control of a parameter associated with the operation of the turbine system 10. In addition, each channel of the remote interface unit 40 includes a sensor 72 and an actuator 74 communicatively coupled to a respective interface controller 70. Actuator 74 is configured to set an operating parameter of the turbine system 10, sensor 72 is configured
    18/27 to output a feedback signal indicative of a measured value of the operating parameter and interface controller 70 is configured to provide closed loop control of actuator 74 based on the feedback signal and an input signal from the motor mechanism controller 38 indicative of a target value of the operational parameter. In the illustrated embodiment, the A 74 channel actuator and the B 74 channel actuator can be configured to adjust the same operating parameter (for example, compressor propeller blade angle, fuel valve position, fuel cooling valve position). air, etc.). Similarly, the sensor of channel A 72 and the sensor of channel B 72 can be configured to measure a heat of the same parameter. In certain embodiments, the A 72 channel sensor and the B 72 channel sensor may be arranged within a common housing and / or may include a common sensor element. In such embodiments, separate conductors can extend from the common sensor housing / element to each respective interface controller 70.
    [028] As an example, the motor mechanism control module 50 can send a signal indicative of a target value of an operational parameter to channel A section of the remote interface unit 40 via the first communication bus 64. The communication module of channel A 68 can receive the signal and transmit the target value to interface controller 70 inside the local loop closure module of channel A 42. Controller 70, in turn, can instruct actuator 74 to adjust the operational parameter until sensor 72 indicates that the target value is obtained. Interface controller 70 can then cyclically monitor the parameter value via a feedback signal from sensor 72 and instruct actuator 74 to compensate for any variations in the target value. In this way, the local loop closure module of channel A 42 can provide closed loop control of a parameter associated with the operation of the turbine system 10.
    19/27 [029] It should be understood that a variety of actuators 74 can be used throughout the turbine system 10. For example, the turbine system 10 can include linear mechanical, electromechanical, pneumatic and / or hydraulic and / or linear actuators. rotary actuators. Certain components of the turbine system 10 can be adjusted by a two-element electro-hydraulic actuator that uses fuel as the working fluid. As an example, propeller blades inside the compressor 22 can be coupled to a hydraulically driven element of an electro-hydraulic actuator. The hydraulically driven element is configured to adjust a propeller blade angle based on fuel pressure for the actuator element. The electro-hydraulic actuator also includes a second element configured to regulate fuel pressure for the hydraulically driven element. The second element can be an electrically controlled valve (for example, by means of a solenoid, stepper motor mechanism, etc.) communicatively coupled to interface controller 70. Consequently, interface controller 70 can adjust the angle of the blades compressor propeller by adjusting the fuel pressure to the hydraulically controlled element through actuation of the electrically controlled element. In certain embodiments, the remote interface unit 40 can be arranged inside the hydraulically driven element (for example, a fuel metering unit) to facilitate cooling of electronic components inside the interface controller 70, thereby , increases the longevity of the remote interface unit 40.
    [030] In certain embodiments, actuator 74 may be an electric torque motor and sensor 72 may be a position sensor, such as a linear differential differential transformer (LVDT). In such embodiments, controller 70 can instruct the electric torque motor to adjust a
    20/27 operational parameter until a position sensor indicates that a target value is obtained (for example, a component has been rotated through a desired angle, a component has been moved from a desired distance, etc.). The interface controller 70 can then cyclically monitor the parameter value by means of a feedback signal from the position sensor and instruct the electric torque motor to compensate for any variations in the target value.
    [031] Similar to communication buses 64 and 66, a variety of communication protocols can be used to establish a communication link between sensor 72 and interface controller 70 and between actuator 74 and interface controller 70. For For example, sensor 72 and / or actuator 74 can be communicatively coupled to interface controller 70 by one or more conductors, thereby facilitating the transmission of analog or digital signals. As will be understood, digital signals can be multiplexed, thereby enabling the transmission of multiple signals (for example, from one or more sensors 72, and / or one or more actuators 74) over a single bus. In addition, a wireless communication link can be employed to reduce wiring.
    [032] In certain embodiments, interface controller 70 is configured to monitor the operational status of the local loop closure module 42. If an anomaly is detected that could interfere with the operation of the local loop closure module, the interface 70 can instruct communication module 68 to send a signal to the motor mechanism control module 50 indicative of the anomaly. The motor mechanism control module 50 can then disable channel section A of remote interface unit 40 and instruct channel section B to control an operational parameter. Similarly, if the electrical energy for channel section A
    21/27 is broken and / or communication with the motor mechanism control module 50 is interrupted, the motor mechanism control module 50 can disable channel A section of remote interface unit 40 and enable channel section B.
    [033] In certain embodiments, channel section A and channel section B of remote interface unit 40 can be operated simultaneously. In such embodiments, a communication link 76 between the interface controller 76 can facilitate communication between the local loop closure modules 42. For example, the sensor of channel A 72 and the sensor of channel B 72 can simultaneously measure the same operational parameter. The interface controller 70 can compare the measured values with each other and identify discrepancies. If a discrepancy is detected (for example, the difference between measured values exceeds a threshold value), the interface controller 70 can select the appropriate measurement and / or report the discrepancy to the engine mechanism control module 50 for analysis / interpretation. If interface controllers 70 and / or the motor mechanism control module 50 determine that a sensor 72 is not producing accurate measurements, interface controllers 70 and / or the motor mechanism control module 50 can disable the respective channel of the remote interface unit 40 and instruct the other channel to provide closed loop control of the operational parameter.
    [034] In certain embodiments, each local loop closure module 42 is configured to operate at a higher frequency than the motor mechanism control module 50. For example, interface controller 70 can be configured to receive a feedback from sensor 72 and adjust actuator 74 to a frequency of about 5 Hz, 10 Hz, 25 Hz, 50 Hz, 100 Hz or more. Conversely, the motor mechanism control module 50 can send a signal indicating a target value of a
    22/27 operational parameter for the remote interface unit at a frequency of about 1 Hz, 2 Hz, or 3 Hz, for example. Due to the lower operating frequency of the motor mechanism control module 50, less data is sent through communication buses 64 and 66, compared to configurations in which a centralized motor mechanism controller receives signals from the sensors and adjusts the actuators in one higher frequency. Consequently, a lower bandwidth network can be employed, thereby reducing the cost of the motor mechanism control system.
    [035] Although the illustrated remote interface unit 40 includes two channels configured to control an operational parameter, it should be understood that alternative remote interface units may include greater or lesser amounts of channels to control one or more parameters associated with the operation of the system. turbine. For example, In certain embodiments, the remote interface unit 40 may include 1,2, 3, 4, 5, 6, or more channels to control an operational parameter. As previously discussed, more than one channel provides redundant control of the operational parameter, thereby increasing the availability of the turbine system 10. In addition, it should be understood that certain remote interface units 40 can be configured to control multiple operational parameters , with one or more channels associated with each parameter. For example, certain remote interface units can be configured to control 1, 2, 3, 4, 6, 8, 10, 15, 20, 25, 30, 35, 40, 50, or more parameters associated with the operation of the system. turbine 10. As an example, the remote interface unit can be configured to control more than 1.5, 10, 20, 30, 40, or more operational parameters.
    [036] In addition, although the illustrated remote interface unit 40 includes separate communication modules 68 to establish a
    23/27 communication between the motor mechanism control module 50 and the respective local loop closure module 42, it should be understood that certain remote interface units may include a single communication module to facilitate communication between the mechanism control module motor 50 and each local loop closure module 42. In additional embodiments, a remote interface unit 40 may include a communication module 68 for each local loop closure module associated with a particular operational parameter. In addition, certain local loop closure modules may include integrated communication modules, thus avoiding the communication module within the remote interface unit.
    [037] Each remote interface unit 40 can be configured particularly for anticipated environmental conditions. For example, remote interface units positioned within the higher temperature portions of the turbine system can be configured to operate effectively within the expected temperature range. For example, in low temperature environments, such as those adjacent to compressor 22, the electrical circuits of the remote interface unit 40 can be mounted on a silicon substrate. In higher temperature environments, such as those adjacent to combustor 16 or turbine 18, electrical circuits can be mounted on silicon on an insulating substrate (SOI). For example, an SOI substrate can include an insulating layer (for example, silicon dioxide) disposed between two layers of silicon. If the remote interface unit 40 is mounted inside the hotter regions of the turbine system 10, such as inside the turbine core 18, the electrical circuits can be mounted on a silicon carbide substrate or a nitride substrate. gallium to resist increased heat loads. In additional embodiments, the remote interface unit 40 can be actively cooled to facilitate operation in high temperature environments. Per
    24/27 example, fuel from the fuel supply 14 can pass through a heat exchanger attached to the remote interface unit 40 before flowing to the combustion 16, thereby reducing the operating temperature of the remote interface unit 40.
    [038] Due to the fact that the sensors are not arranged inside the motor mechanism controller, the size of the motor mechanism controller can be reduced, thus facilitating the assembly of the motor mechanism controller inside a nacelle the motor mechanism. In addition, the number of controlled parameters can be adjusted by varying the number of remote interface units and / or the number of actuators / sensors inside each remote interface unit. Consequently, a single motor mechanism controller configuration can be employed to control the operation of a variety of motor mechanism configurations (for example, which have different numbers and / or types of operating parameters), thereby obviating the process of remodel and recertify the engine engine controller for each engine engine configuration. As a result, engine engine development costs can be reduced significantly. In addition, the engine engine control system 36 can use common remote interface unit configurations to control each parameter associated with the operation of the turbine system 10. In such a configuration, the model and production cost can be further reduced by obviating the model / certification costs associated with developing multiple remote interface unit configurations.
    [039] Figure 3 is a block diagram of an embodiment of a remote interface unit 40 that can be employed within the distributed control system 36 of Figure 2. As illustrated, the remote interface unit 40 includes a set of actuators smart 46 that has a
    25/27 integrated communication module 68, interface controller 70, sensor 72 and actuator 74. Such set of smart actuators 46 can be used to control an operational parameter independently, or it can be used in conjunction with one or more sets of similar smart actuators 46 to provide redundant control of a parameter (ie, each set of smart actuators 46 serves as a channel for a control system with many channels). Remote interface units 40 that have a set of smart actuators 46 can be distributed throughout the turbine system 10 to control parameters close to the unit. For example, a remote interface unit 40 can be positioned adjacent to the propeller blades of the compressor 22 to control an angle of the propeller blades and another remote interface unit 40 can be positioned adjacent to the fuel value to control flow. of fuel for the combustor 16. By distributing the remote interface units throughout the turbine system, the weight and complexity of the engine mechanism control system can be reduced by obviating lines / tubes, which can be used in configurations that have sensors arranged inside the motor mechanism controller.
    [040] Although the illustrated remote interface units 40 include a single set of smart actuators 46, it should be understood that alternative remote interface units may include additional sets of smart actuators (for example, 1,2,3, 4, 5, 6 or more). In addition, it should be understood that certain remote interface units may include a set of smart actuators 46 and a local loop closure module 42 that has a separate sensor and a separate actuator. In addition, although the illustrated smart actuator set 46 includes an integrated communication module 68, it should be understood that alternative embodiments may employ a remote communication module
    26/27 (for example, configured to establish a communication link with multiple sets of smart actuators 46). In addition, although the illustrated smart actuator set 46 includes an integrated sensor 72, it should be understood that alternative embodiments can employ a remote sensor 72 to measure the value of a remote parameter to actuator 74.
    [041] Figure 4 is a block diagram of an alternative embodiment of a remote interface unit 40 that can be employed within the distributed control system 36 of Figure 2. In the illustrated embodiment, the remote interface unit 40 includes a module multiple local loop closure (MLLCM) 44 configured to provide multiple parameter closed loop control associated with the operation of the turbine system
    10. As illustrated, the multiple local loop closure module 44 includes an integrated communication module 68 and an interface controller 70. However, it should be understood that a remote communication module 68 can be employed in alternative embodiments. The remote interface unit 40 also includes multiple actuators 74 communicatively coupled to interface controller 70 and configured to adjust a respective set of parameters associated with the operation of the turbine system 10. In addition, the remote interface unit 40 includes a set corresponding number of sensors 72 communicatively coupled to interface controller 70 and configured to output respective feedback signals to interface controller 70. Interface controller 70 is configured to provide closed loop control of actuators 74 based on feedback signals and a input signal from the motor mechanism control module 50 (for example, received via communication module 78) indicative of a target value for each parameter. In this configuration, a single controller 70 within the remote interface unit 40 can control multiple operating parameters associated with the
    27/27 various components throughout the turbine system 10.
    [042] Although the illustrated embodiment includes four sensors 46 and four actuators 44, it should be understood that alternative designs may include larger or smaller amounts of sensors / actuators. For example, certain remote interface units 40 may include 1, 2, 3, 4, 5, 6, 7, 8, or more sensors 46 and a corresponding number of actuators 44. In addition, certain parameters can be determined by measuring multiple associated parameters related to the operation of the turbine system 10. For example, a fluid flow velocity can be determined by measuring a static pressure and a dynamic pressure by means of two pressure sensors. Consequently, interface controller 70 can be configured to determine a parameter based on feedback signals from multiple sensors. Controller 70, in turn, can instruct an actuator to adjust the parameter based on the determined value of the parameter.
    [043] This written description uses examples to reveal the invention, which includes the best way and also to enable a person skilled in the art to practice the invention, which includes making and using any devices or systems and executing any built-in methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
    1/5
    权利要求:
    Claims (15)
    [1]
    Claims
    1. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), characterized by the fact that it comprises:
    a motor mechanism controller (38) configured to control a plurality of parameters associated with the operation of a gas turbine motor mechanism system (10); and a plurality of remote interface units (40) communicatively coupled to the motor mechanism controller (38), the remote interface unit being configured to receive an input signal from the motor mechanism controller (38) indicative of values respective targets of at least one parameter of a plurality of parameters and the remote interface unit is configured to provide closed loop control of at least one parameter based on the input signal and feedback signals indicative of respective values measured from at least least one parameter.
    [2]
    2. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 1, characterized by the fact that the remote interface unit (40) comprises an actuator (74) configured to adjust at least one parameter and a sensor (72) configured to output feedback signals.
    [3]
    3. GAS TURBINE MOTOR MECHANISM CONTROL SYSTEM (36), according to claim 1 or 2, characterized by the fact that at least one remote interface unit (40) comprises a multiple local loop closure module ( 44) configured to provide closed loop control of a respective set among the plurality of parameters.
    [4]
    4. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 1, characterized by the fact
    2/5 that at least one remote interface unit (40) comprises a plurality of local loop closure modules (42) and the local loop closure module is configured to independently provide closed loop control of a respective parameter of a plurality of parameters.
    [5]
    5. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 4, characterized by the fact that the local loop closure module (42) is configured to provide closed loop control of the respective parameter by instructing an actuator (74) to adjust the respective parameter based on the feedback signals from a sensor (72).
    [6]
    6. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 4 or 5, characterized by the fact that at least two of the plurality of local loop closure modules (42) are configured to provide the redundant closed-loop control of at least one parameter.
    [7]
    7. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 1, characterized by the fact that at least one remote interface unit (40) comprises a set of intelligent actuators (46) that have a actuator (74) configured to adjust the at least one parameter, a sensor (72) configured to output feedback signals and an interface controller (70) communicatively coupled to the actuator (74) and sensor (72), being that the interface controller is configured to provide closed-loop control of at least one parameter.
    [8]
    8. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 1, characterized by the fact that the remote interface unit (40) comprises a control module
    3/5 communication (68) configured to receive the input signal from the motor mechanism controller (38).
    [9]
    9. GAS TURBINE MOTOR MECHANISM CONTROL SYSTEM (36) according to claim 1, characterized by the fact that the motor mechanism controller comprises a motor mechanism control module (50) configured to control the plurality of parameters and an energy conditioning module (52) configured to supply electrical power to the motor mechanism control module and to the plurality of remote interface units (40), the motor mechanism control module and the energy conditioning module they are arranged inside independent accommodations positioned remotely from each other.
    [10]
    10. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 1, characterized by the fact that the plurality of remote interface units (40) is distributed throughout the turbine engine mechanism system a gas (10).
    [11]
    11. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), characterized by the fact that it comprises:
    a plurality of remote interface units (40) distributed throughout a gas turbine engine mechanism system (10), the remote interface unit comprising an actuator (74) configured to adjust a respective parameter associated with the operation of the system gas turbine engine mechanism (10), a sensor (72) configured to emit a feedback signal indicative of a measured value of the respective parameter and an interface controller (70) communicatively coupled to the actuator and the sensor, being that the interface controller is configured to provide closed-loop control of the actuator based on the feedback signal; and
    4/5 a motor mechanism controller (38) communicatively coupled to the remote interface unit, the motor mechanism controller being configured to instruct the interface controller to establish a target value for the respective parameter.
    [12]
    12. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 11, characterized by the fact that at least one remote interface unit (40) comprises a set of intelligent actuators (46) and the actuator (74), the sensor (72) and the interface controller (70) are arranged inside the set of intelligent actuators.
    [13]
    13. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 12, characterized by the fact that at least one remote interface unit (40) comprises a plurality of local loop closure modules (42 ) and the local loop closure module comprises a respective interface controller configured to provide closed loop control of a corresponding parameter.
    [14]
    14. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), characterized by the fact that it comprises:
    a motor mechanism controller (38) configured to control a plurality of parameters associated with the operation of a gas turbine motor mechanism system; and a plurality of remote interface units (40) communicatively coupled to the motor mechanism controller (38), at least one remote interface unit comprising:
    at least one local loop closure module (42) that has an interface controller;
    an actuator (74) communicatively coupled to the controller
    5/5 interface and configured to adjust a parameter of a plurality of parameters; and a sensor (72) communicatively coupled to the interface controller and configured to emit a feedback signal indicative of a measured value of a parameter;
    wherein the interface controller is configured to provide closed-loop control of the actuator based on the feedback signal and an input signal from the motor mechanism controller indicative of a target value of a parameter.
    [15]
    15. GAS TURBINE ENGINE MECHANISM CONTROL SYSTEM (36), according to claim 14, characterized in that the at least one local loop closure module (42) comprises a configured communication module (68) to receive the input signal from the motor mechanism controller (38).
    1/3
    2/3
    W LU wgá << O§ w K § Ê>
    íQ z H <w fe m
    3/3
    - FOR MODULE OF
    CONDITIONING
    POWER
    - FOR MOTOR MECHANISM CONTROL MODULE
    RIU z — 46INTELLIGENT ACTUATOR.—COMMUNICATION MODULE __CONTROLLER | -__- SENSOR |___ ACTUATOR 1—
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    同族专利:
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    JP2013213497A|2013-10-17|
    US20130255220A1|2013-10-03|
    CA2810146A1|2013-09-30|
    CN103362653A|2013-10-23|
    EP2644869A2|2013-10-02|
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    法律状态:
    2018-11-21| B03A| Publication of an application: publication of a patent application or of a certificate of addition of invention|
    2018-12-04| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-01-22| B08F| Application fees: dismissal - article 86 of industrial property law|Free format text: REFERENTE A 6A ANUIDADE. |
    2019-05-07| B08K| Lapse as no evidence of payment of the annual fee has been furnished to inpi (acc. art. 87)|Free format text: REFERENTE AO ARQUIVAMENTO PUBLICADO NA RPI 2507 DE 22/01/2019. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/436,184|US9388744B2|2012-03-30|2012-03-30|Distributed gas turbine engine control system with remote interface units|
    US13/436,184|2012-03-30|
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