• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    gas turbine system and method for operating gas turbine system. the invention relates to a gas turbine system comprising: gas turbine engine (101) for generating power, control unit (102) for controlling the gas turbine engine, data acquisition system (108) with a thermodynamic model unit (104) and a test sequence unit (105), sensing device (103) which is coupled to the gas turbine engine to measure a performance parameter (115) of the gas turbine engine, and a comparative unit (109). the thermodynamic model unit generates the computed performance parameter (113) based on a mechanical model (106) and a thermodynamic model (107) of the gas turbine engine. the test sequence unit generates test sequence data (114) comprising setpoint operating data and timing data with which a gas turbine engine cycle time is executable. the data acquisition system generates test control data (112) based on the test sequence data and is coupled to the control unit (102) to provide test control data to the control unit such that the turbine engine of gas is controllable based on the test control data. the comparative unit is coupled to the data acquisition system so that the measured performance parameter, measured by the sensing device, is comparable with the computed performance parameter.
    公开号:BR112015018471B1
    申请号:R112015018471-5
    申请日:2014-01-22
    公开日:2022-01-18
    发明作者:Samuel Bowler；Michael Smith；Andrew Yarwood
    申请人:Siemens Energy Global GmbH & Co. KG；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    [001] The present invention relates to a gas turbine comprising a test system and a method of operating a gas turbine with a test procedure. BACKGROUND TECHNIQUE
    [002] Industrial gas turbine engines are designed to produce mechanical or electrical energy. After a certain time of operation, for example after a repair or overhaul, test sequences under which gas turbine engines run at predefined operating points have to be conducted in order to verify that an industrial gas turbine engine still works correctly. Each operating point specifies a set of setpoints representing a state in which the motor is to run.
    [003] In conventional industrial gas turbine engines, a test sequence of a gas turbine engine is manually initiated. The operator controls the industrial gas turbine engine by a control device manually, so that the gas turbine engine operates with predetermined set points that are pre-set by a test cycle. The predefined test cycle is, for example, generated in the verification and performance tests of the industrial gas turbine engine.
    [001] Therefore, in order to conduct an industrial gas turbine engine test sequence, operators are required who initiate and control the test cycles manually. Furthermore, the test sequence that is predetermined under verification tests often does not match the values of measured operating parameters and environmental parameters to which the gas turbine engine is actually exposed. Some of the reasons for this deviation can be found in differences in climate (eg temperature or elevation) and fuel composition between where an industrial gas turbine is tested and where it is used on a daily basis.
    [002] US 4,821,217 discloses a programmable test station that automatically performs static tests of electrical and pneumatic systems of jet aircraft engines. The test station automatically simulates the systems to be tested on each engine and measures their response. A programmable data acquisition computer controls both stimuli and measurements, and generates data. A station is operably connected to a plurality of engines, simultaneously, and tests certain systems on each in accordance with the commands of the station's user.
    [003] US 4,389,710 discloses a test circuit to exercise and test the ability to operate anti-skid and automatic braking control circuits in an aircraft braking system. A digital processor communicates with an interface circuit associated with each anti-skid control circuit and automatic braking system valve actuators. Each interface circuit includes an analog switch receiving an electrical stimulus from the processor and applying the same to various test points in the non-skid control circuit or associated automatic braking system valve actuators. An analog selector is connected to various test points in the anti-skid control circuit and valve actuators of the automatic braking system to detect the electrical stimulus and pass such responses to the processor to determine the operational capability of the anti-skid and automatic braking control systems. .
    [004] US 5,521,824 discloses an engine tester using lead-lag control. An operator interface produces a control mode signal and a plurality of setpoints. The operators also include a test controller for receiving the control mode signal and a plurality of setpoints and responsively operating the motor tester. The test controller detects the operating characteristics of the motor tester. The test controller also selectively operates the motor tester parameters according to the control mode signal.
    [005] US 8,161,806 discloses a method for monitoring the performance parameters of an aircraft gas turbine engine during its operation. The method includes detecting the performance parameters, generating analog sensor outputs, and producing digital data by conditioning the analog sensor outputs with at least one hub unit that is mounted next to a motor.
    [006] US 4,215,412 discloses real-time performance monitoring of an aircraft's gas turbine engines. The monitoring system includes a digital processor that uses a set of scalar coefficients and the current value of various performance parameters to predict the actual value of these performance parameters are monitored and compared with the predicted values to supply overhead signal deviation to monitor logic that provides an indication of faults with the digital processor.
    [007] EP 1 288 644 discloses a diagnostic method and a diagnostic system for turbine engines. The system assesses whether failures detected during testing of a gas turbine engine are related to engine performance issues or to some other abnormality unrelated to engine performance. An engine performance parameter is evaluated under a performance condition to generate a first set of current engine data which is then compared to a first set of previous engine data to determine if an abnormality exists.
    [008] EP 2175 336 A1 describes a method for monitoring the performance of a gas turbine engine over a period of time and compensating for the degradation experienced during that extended operation in order to maintain the most satisfactory performance.
    [009] EP 2 249 004 A2 describes methods and systems for automatically controlling the thrust output of a gas turbine engine to compensate for deterioration that can occur over time.
    [0010] EP 2 175 336 A1 and EP 2 249 004 A2 each disclose predictable models which, based on engine inlet conditions and a reference parameter such as fuel inlet, calculate the performance that can be obtained by a rated or reference motor. Measurements from the operating engine are then compared to equivalent predicted parameters from the model and used as a basis for adjusting one or more control parameters such as fuel system gains or pressure ratio limits, etc. SUMMARY OF THE INVENTION
    [0011] It may be an object of the present invention to provide an automatic test of an industrial gas turbine engine under real-time conditions.
    [0012] The present invention is a method for testing a gas turbine engine, typically prior to release to a customer, and can be performed automatically by closed-loop control to obtain target performance parameters, such as a power output, consumption of fuel or emissions. The present method is an analytical model that, taking into account measurements from the engine in operation, calculates thermodynamic parameters that cannot be measured directly, such as the combustor outlet temperature or normalized temperature (N/root (temperature of input)) These parameters are then fed back to the controller or control device where they are used in a closed loop to set a motor test operating point to give the parameter value corresponding to the specified value in a predefined test sequence.
    [0013] This objective can be solved by a gas turbine system and a method for operating a gas turbine system in accordance with the present invention.
    [0014] According to a first aspect of the present invention, a gas turbine system is presented. The gas turbine system comprises a gas turbine engine for generating power, a control unit for controlling the gas turbine engine, a sensor device, a comparative unit, a data acquisition system comprising a model unit thermodynamic and a test sequence unit.
    [0015] The sensor device is coupled to the gas turbine engine to measure a performance parameter of the gas turbine engine.
    [0016] The thermodynamic model unit generates performance parameter computed on the basis of a mechanical model of the gas turbine engine from a thermodynamic model of the gas turbine engine.
    [0017] A test sequence by itself can be designed by a qualified person or the test sequence unit and input to the control unit by a qualified person. The test sequence data comprising setpoint operating data and test schedule data with which a gas turbine engine cycle time is executable.
    [0018] The data acquisition system generates test control data on the basis of test sequence data. The data acquisition system is coupled to the control unit to provide the test control data to the control unit so that the gas turbine engine is controllable on the basis of the test control data.
    [0019] The comparative unit is coupled to the data acquisition system so that the performance parameter measured by the sensor device during or after the test cycle is completed is comparable with the computed performance parameter.
    [0020] The gas turbine engine comprises, for example, a compressor section, a combustion section and a turbine section. When operating the gas turbine engine, (mechanical) power is generated, which can be used to operate a generator to generate electrical power, for example.
    [0021] In order to control the gas turbine engine, the control unit is installed. The control unit can control, for example, the fuel valves to control the injection of fuel within the combustion section of the gas turbine engine.
    [0022] In addition, a brake unit for braking a gas turbine engine shaft can be coupled to the gas turbine engine, for example, in order to absorb power from the gas turbine. The control unit can control the brake unit to control the rotational speed of the gas turbine engine shaft, so directly or indirectly the mass of fluid flows through the gas turbine engine, for example. The control unit can control the brake load in addition to the rotating shaft speed in order to fix the operating point of the gas turbine engine.
    [0023] The data acquisition system is used to collect all necessary data of specific parameters in order to operate the gas turbine engine correctly and in order to control and test the gas turbine engine. The data acquisition system comprises the thermodynamic model unit and the test sequence unit, for example.
    [0024] The sensor device is coupled to the gas turbine engine to measure an operating parameter or to measure the performance parameter. The sensor device comprises, for example, a temperature sensor, for example a temperature sensor, a pressure sensor, an oxygen sensor, a speed sensor or any other sensors suitable for measuring the desired parameter.
    [0025] Operating parameter defines a parameter that is entered into the gas turbine engine to operate the gas turbine engine.
    [0026] The operating parameter is, for example, an amount of fuel, a mass flow of a volume of air flow, or amount of leaking air that has leaked from the gas turbine engine.
    [0027] The measured performance parameter defines the parameter which is emitted by the gas turbine engine while the gas turbine engine runs on the operating parameter. The measured performance parameter is, for example, a temperature of the gas turbine engine (for example, at a predefined location of the gas turbine engine, such as the combustion section or the turbine section), the pressure at a certain gas turbine engine location, gas turbine engine emissions, fuel consumption and/or gas turbine engine load, respectively.
    [0028] The thermodynamic model unit comprises, for example, a warehouse where the data of the mechanical model (simulation) of the gas turbine engines and the thermodynamic model (simulation) of the gas turbine engine are stored.
    [0029] The mechanical model of the gas turbine engine is, for example, a model that comprises the same dimensions and geometric constraints as the gas turbine engines so that a simulation of the mechanical model is possible.
    [0030] Consequently, the thermodynamic model comprises data of specific operating conditions of the gas turbine engine. For example, the thermodynamic model calculates on the basis of certain input (ie operating) parameters specific output (performance) parameters so that the operation of the gas turbine engine is simulated. For example, as an input value, an amount of fuel, the amount of injected air and a predefined amount of exhausted air, so that the thermodynamic model can calculate (e.g. under consideration of the mechanical model) the simulated performance parameter theoretical, such as the temperature, pressure or emission of gas turbine engines, for example at the turbine stage output.
    [0031] On the basis of the mechanical model and the thermodynamic model, the thermodynamic model unit generates the computed performance parameter.
    [0032] The computed performance parameter defines a simulated operating condition of a simulated operation of the gas turbine engine. The computed performance parameter is a computed and calculated parameter which is computed by the thermodynamic model unit on the basis of the measured or predefined operating parameter. In particular, the computed performance parameter is indicative of a computed (simulated) load, a computed (simulated) efficiency, a computed emission, a computed fluid flow characteristic through the gas turbine engine, a computed fuel consumption, a computed lambda value and/or a computed power curve.
    [0033] Therefore, the computed performance parameter, such as computed load, gives a simulated and theoretical indication under which input operating parameters such as fuel mass (such as fuel mass flow, etc.) The computed output performance must be obtained by the gas turbine engine theoretically, ie under normal conditions and/or under simulation conditions.
    [0034] The test sequence unit generates test sequence data comprising setpoint operating data and time schedule data with which the gas turbine engine cycle time is executable. In other words, in the test sequence unit, predefined test runs and test cycles are stored, which must be performed after certain operating times of the gas turbine engines in order to ensure correct and fault-free operation of the engine. of gas turbine.
    [0035] Test sequence data comprises setpoint operating data indicating, for example, gas turbine engine setpoint acceleration data, a gas turbine engine setpoint speed, and a predefined fuel type used by the gas turbine engine. In other words, setpoint operating data is control data that defines the setpoint that must be obtained by the gas turbine engine when running the test cycle.
    [0036] Time schedule data describes time frames where the gas turbine engine must run with the data setpoint operating data preset during the test cycle.
    [0037] The data acquisition system specifically collects computed performance parameters (measured or predefined), operating parameters, computed performance parameters and test sequence data and generates the test control data on the basis of these parameters.
    [0038] The comparative unit is coupled to the data acquisition system so that the measured performance parameter measured by the sensor system during the test cycle is comparable with the computed performance parameters. If the measured performance parameter is similar to the computed performance parameter, proper operation of the gas turbine engine can be assumed.
    [0039] Therefore, the comparative unit verifies that the performance parameters measured after conducting the test cycle agree with the computed performance parameters that are computed and calculated by the thermodynamic model. Therefore, if a big difference occurs between the computed performance parameter and the measured performance parameter, the gas turbine engine is probably not working properly.
    [0040] Therefore, by the present invention, test control data are generated that not only comprise test sequence data that are predefined under laboratory and theoretical conditions, but also consider performance parameters computed from a thermodynamic model of the turbine engine. gas. Therefore, test control data can be tailored more exactly to the environmental conditions and the current operating state of the gas turbine engine so that specifically tailored test cycles can be driven by the gas turbine engine.
    [0041] For example, if the gas turbine engine operates at maximum power generation, a respective maximum power test can be conducted automatically. For example, the sensor device measures the generation of the data acquisition system. Then, the data acquisition system receives, from the thermodynamic model unit, the computed performance parameters that are indicative of a thermodynamic model of the gas turbine engine running under maximum power generation. In addition, the test sequence unit gives the test sequence data that comprises the setpoint operating data and the time schedule data that are required to test the gas turbine engine under maximum power generation. .
    [0042] Therefore, the test control data not only comprises the test sequence data, for example for a maximum power test, but also comprises the computed performance parameters of the gas turbine engine that must be obtained while running. under full power, for example.
    [0043] Furthermore, according to another exemplary embodiment, the thermodynamic model unit is coupled to the sensor device so that the thermodynamic model unit generates the computed performance parameters further on the basis of the measured operation parameters. Therefore, the thermodynamic model unit can receive information about the fuel injection volume, whereas the thermodynamic model unit can generate computed performance parameters, for example a computed load, which is theoretically obtainable by the gas turbine engine if the measured fuel injection volume is injected.
    [0044] According to another exemplary embodiment, a test sequence unit is coupled to the control unit so that the test cycle is automatically measurable.
    [0045] As described above, if the control unit activates the gas turbine engine under maximum power generation, the test sequence unit can automatically start a maximum power test of the gas turbine engine. It is no longer necessary that an operator can start a test cycle manually.
    [0046] According to another exemplary embodiment, the test sequence unit is coupled to the control unit so that the test cycle is manually initiated by an operator.
    [0047] According to another exemplary embodiment, a control device is coupled to the control unit whereby the control device is controllable by the control unit so that the gas turbine engine is adjustable according to the control data of test. As described above, the control device may be, for example, a control brake for applying a controlled load to the output shaft of the gas turbine engine so that, for example, together with controlling the rotational speed of the output of the gas turbine, a preset value of the gas turbine operating point can be fixed. In addition, or alternatively, the control device may comprise a fuel valve for controlling the supply of fuel to the gas turbine engine. Therefore, the amount of fuel can be adjusted exactly according to the test control data, for example.
    [0048] Next, a method for operating a gas turbine system in accordance with another aspect of the present invention is described. A gas turbine engine generates power, the gas turbine engine being controlled by a control unit. A gas turbine engine performance parameter is measured by a sensor device of a data acquisition system. Then, a computed performance parameter is generated on the basis of a mechanical model of the gas turbine engine and a thermodynamic model of the gas turbine engine by a thermodynamic model unit. The test sequence data is generated where the test sequence data comprises a setpoint operation data. Time schedule data with which the gas turbine engine cycle time is executable by the test sequence unit. Then, test control data is generated on the basis of the test sequence data by the data acquisition system. Test control data is provided to the control unit so that the gas turbine engine is controllable by the control unit on the basis of the test control data. The measured performance parameter, measured by the sensor device, is compared with the performance parameter computed by a comparative unit.
    [0049] In summary, by the present invention, the test control data not only comprises predefined test data, but also includes output performances (computed performance and/or computed operating parameter) from the thermodynamic model of the turbine engine. gas.
    [0050] The thermodynamic model can be run continuously during operation of the gas turbine engine by the thermodynamic model unit under consideration of the measured operating conditions. The thermodynamic model unit works independently from the control unit that controls the gas turbine engine.
    [0051] The outputs (computed performance parameter) from the thermodynamic model unit are based on a mechanical model of the gas turbine engine, the thermodynamic model of the gas turbine engine, and the measured and preset operating parameters of the gas turbine engine. gas turbine.
    [0052] Test control data comprising the set of operating points, for example, is uploaded to the control unit. The set of operating points (setpoint operating data) comprises, for example, a desired load (power) of the gas turbine engine that must be obtained under a certain operating mode of the gas turbine engine. The desired load can be specified as one of a selection of either one of the outputs (computed performance parameter) of the thermodynamic model or, for example, the sensor device. Also a ramp rate can be specified to allow control of a crossover operation between two specified operating states of the gas turbine engine. The test control data may also comprise, for example, information about the desired speed since gas turbine engine setpoint operating data must be obtained during the test cycle. The desired speed can be taken from the actual speed (measured operating parameter) measured by the sensor device or a corrected speed (computed performance parameter) which is an operating parameter computed from the thermodynamic model.
    [0053] In addition, the test control data may comprise information on which type of fuel the gas turbine engine should run under the test cycle, i.e. whether the gas turbine engine should run on gaseous fuel or fuel. liquid.
    [0054] Test sequence data further comprises time schedule information that defines how long the gas turbine engine should be held at the specified operating point (setpoint operating data). In addition, the test control data defines the operating conditions of the gas turbine and defines an increase, decrease or elimination of an operating state from a retention period.
    [0055] In addition, the data acquisition system can function as a part of a closed loop controller and periodically test control data is generated to drive test cycles. Therefore, the data acquisition system and the control unit act as a closed-loop controller working together. The method is a closed loop operable until the target performance parameters are obtained for the gas turbine. Thus, desirable performance parameters are obtained before releasing to a client.
    [0056] The data acquisition system generates or collects test control data or parameters which are then fed back to the controller or control device/unit where they are used in a closed loop to fix a motor test operating point to give the parameter value corresponding to the value specified in a predefined test sequence.
    [0057] It should be noted that the embodiments of the invention have been described with reference to different subjects. In particular, some embodiments have been described with reference to apparatus type embodiments while other embodiments have been described with reference to method type embodiments. However, one skilled in the art will glean from the above and the following description that, unless otherwise noted, in addition to any combination of aspects belonging to one type of subject with reference to different subjects, in particular between aspects of the embodiments of apparatus type and aspects of method type embodiments is considered to be described with this application. BRIEF DESCRIPTION OF THE DRAWINGS
    [0058] The aspects defined above and other aspects of the present invention are evident from the embodiment examples to be described hereinafter and are explained with reference to the embodiment examples. The invention will be described in more detail below with reference to exemplary embodiments, but to which the invention is not limited.
    [0059] The figure shows a schematic view of the gas turbine system according to an exemplary embodiment of the present invention. DETAILED DESCRIPTION
    [0060] The illustration in the drawing is schematic. Similar or identical elements are provided with the same reference signs.
    [0061] The figure shows the gas turbine system comprising the gas turbine engine 101 for generating power. Furthermore, the control unit 102 is shown to control the gas turbine engine 101. Furthermore, the data acquisition system 108 is shown comprising a thermodynamic model unit 104 and a test sequence unit 105.
    [0062] A sensor device 103 is coupled to the gas turbine engine 101 to measure a measured operating parameter 111 of the gas turbine engine 101.
    [0063] The thermodynamic model unit 104 generates computed performance parameters 113 on the basis of a mechanical model 106 of the gas turbine engine 101 and a thermodynamic model 107 of the gas turbine engine 101. The test sequence unit 105 generates test sequence data 114 comprising setpoint operating data and timing data with which a gas turbine engine 101 timing cycle is executable.
    [0064] Data acquisition system 108 generates test control data 112 on the basis of measured operation parameter 111, computed performance parameter 113 and test sequence data 114. Data acquisition system 108 is coupled to the control unit. control 102 to provide test control data 112 to control unit 102 so that gas turbine engine 101 is controllable on the basis of test control data 112.
    [0065] As shown in the figure, thermodynamic model unit 104 is coupled to sensor device 103 so that thermodynamic model unit 104 generates computed performance parameter 113 additionally on the basis of measured operation parameter 111.
    [0066] Furthermore, the comparative unit 109 is coupled to the data acquisition system 108 so that a measured performance parameter 115 that is measured by the sensor device 103 after or during a test cycle is completed is comparable with the performance parameter 115 that is measured by the sensor device 103 after or during a test cycle. computed performance 113.
    [0067] In addition, a control device 110, such as a fuel valve for controlling the supply of fuel to the gas turbine engine 101 or a control brake for braking the gas turbine engine 101, is coupled to the engine. gas turbine 101. Control unit 102 controls control device 110 so that the operating point of gas turbine engine is adjustable in accordance with test control data 112 sent by data acquisition system 108.
    [0068] It should be noted that the term "comprising" does not exclude other elements or steps and "a" or "an" does not exclude a plurality. Also elements described in association with different modalities can be combined. It should also be noted that reference signs in the embodiments should not be interpreted as limiting the scope of the embodiments.
    权利要求:
    Claims (12)
    [0001]
    1. Gas turbine system, characterized in that it comprises a gas turbine engine (101) for generating power, a control unit (102) for controlling the gas turbine engine (101), a system for acquiring data (108) comprising a thermodynamic model unit (104) and a test sequence unit (105), a sensor device (103) which is coupled to the gas turbine engine (101) to measure a performance parameter ( 115) of the gas turbine engine (101), and a comparative unit (109), wherein the thermodynamic model unit (104) generates computed performance parameter (113) based on a mechanical model (106) of the turbine engine (101) and based on a thermodynamic model (107) of the gas turbine engine (101), the test sequence unit (105) generating test sequence data (114) comprising operating data of setpoint and time schedule data with which a gas turbine engine test cycle (101) is run The data acquisition system (108) generates test control data (112) based on the test sequence data (114) and computed performance parameters (113), the data acquisition system being data (108) is coupled to the control unit (102) to provide the test control data (112) to the control unit (102) so that the gas turbine engine (101) is controllable based on the data from test control (112), and the comparative unit (109) being coupled to the data acquisition system (108) so that the measured performance parameter (115) measured by the sensor device (103) is comparable to the computed performance parameter (113).
    [0002]
    2. Gas turbine system, according to claim 1, characterized in that the thermodynamic model unit (104) is coupled to the sensor device (103) so that the thermodynamic model unit (104) generates the computed performance parameter (113) additionally based on the measured operating parameter (111).
    [0003]
    3. Gas turbine system, according to claim 1 or 2, characterized in that the computed performance parameter (113) is indicative of at least one of a computed load, a computed effectiveness, a computed emission, a computed flow characteristic of fluid through the gas turbine engine (101), a computed fuel consumption, a computed lambda value, and a computed power curve.
    [0004]
    4. Gas turbine system according to any one of claims 1 to 3, characterized in that the measured performance parameter (115) is indicative of at least one of a measured temperature, a measured pressure, a measured speed , measured emissions, a measured fuel consumption and a measured load.
    [0005]
    5. A gas turbine system according to any one of claims 1 to 4, characterized in that the setpoint operating data comprises at least one of a turbine engine setpoint acceleration data gas (101), a set point speed of the gas turbine engine (101), and a type of fuel used by the gas turbine engine (101).
    [0006]
    6. Gas turbine system, according to any one of claims 1 to 5, characterized in that the test sequence unit (105) is coupled to the control unit (102) so that the test cycle is automatically startable.
    [0007]
    7. Gas turbine system according to any one of claims 1 to 6, characterized in that the test sequence unit (105) is coupled to the control unit (102) so that the test cycle is startable by an operator manually.
    [0008]
    8. Gas turbine system, according to any one of claims 1 to 7, characterized in that it also comprises a control device (110) that is coupled to the control unit (102), and the control device ( 110) is controllable by the control unit (102) so that the gas turbine engine (101) is adjustable in accordance with the test control data (112).
    [0009]
    9. Gas turbine system according to claim 8, characterized in that the control device (110) comprises a control brake to controllably brake the gas turbine engine (101) and/or a valve of fuel to control the fuel supply to the gas turbine engine (101).
    [0010]
    10. Gas turbine system, according to any one of claims 1 to 9, characterized in that the data acquisition system (108) generates test control data that is fed back to the control device (110) for be used in a closed loop to set a motor test operating point to give the value of those parameters that correspond to the specified value in a predefined test sequence.
    [0011]
    11. Method for operating a gas turbine system, characterized in that it comprises the steps of generating power by a gas turbine engine (101), controlling the gas turbine engine (101) by a control unit (102). ), measuring a performance parameter (115) of the gas turbine engine (101) by a sensor device (103) of a data acquisition system (108), generating a computed performance parameter (113) based on a mechanical model (106) of the gas turbine engine (101) and a thermodynamic model (107) of the gas turbine engine (101) by a thermodynamic model unit (104), generated by a test sequence unit (105) test sequence data (114) comprising setpoint operating data and time schedule data with which a gas turbine engine test cycle (101) is executable, generate test control data (112) based on test sequence data (114) and performance parameters computed (113) by the system (108), providing the test control data (112) to the control unit (102) so that the gas turbine engine (101) is controllable by the control unit (102) based on the data (112), and comparing the measured performance parameter (115) measured by the sensor device (103) with the performance parameter computed (113) by a comparative unit (109).
    [0012]
    12. Method according to claim 11, characterized in that the method is a closed loop and operable until target performance parameters are reached for the gas turbine.
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    同族专利:
    公开号 | 公开日
    BR112015018471A2|2017-07-18|
    MX2015010140A|2015-12-17|
    KR20150114559A|2015-10-12|
    JP2016513202A|2016-05-12|
    KR102072349B1|2020-01-31|
    CN105074413A|2015-11-18|
    CA2898392C|2018-07-10|
    WO2014122013A1|2014-08-14|
    CN105074413B|2019-10-15|
    EP2954297B1|2018-12-26|
    KR20170109087A|2017-09-27|
    CA2898392A1|2014-08-14|
    EP2954297A1|2015-12-16|
    JP6403690B2|2018-10-10|
    EP2762852A1|2014-08-06|
    RU2015132521A|2017-03-13|
    RU2627617C2|2017-08-09|
    US10067035B2|2018-09-04|
    MX361552B|2018-12-10|
    US20150362405A1|2015-12-17|
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    法律状态:
    2018-11-13| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-04-07| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-04-13| B25A| Requested transfer of rights approved|Owner name: SIEMENS GAS AND POWER GMBH AND CO. KG (DE) |
    2021-10-05| B25D| Requested change of name of applicant approved|Owner name: SIEMENS ENERGY GLOBAL GMBH AND CO. KG (DE) |
    2021-10-13| B25G| Requested change of headquarter approved|Owner name: SIEMENS ENERGY GLOBAL GMBH AND CO. KG (DE) |
    2021-11-16| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2022-01-18| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 22/01/2014, OBSERVADAS AS CONDICOES LEGAIS. |
    2022-02-08| B25K| Entry of change of name and/or headquarter and transfer of application, patent and certificate of addition of invention: republication|Owner name: SIEMENS ENERGY GLOBAL GMBH AND CO. KG (DE) Free format text: RETIFICACAO DO DESPACHO (25.7) ? ALTERACAO DE SEDE PUBLICADO NA RPI NO 2649, DE 13/10/2021, QUANTO AO ITEM (71) ? DEPOSITANTE NO PARECER.ONDE SE LE: SIEMENS GAS AND POWER GMBH AND CO. KGLEIA-SE: SIEMENS ENERGY GLOBAL GMBH AND CO. KG |
    优先权:
    申请号 | 申请日 | 专利标题
    EP13154041.1|2013-02-05|
    EP13154041.1A|EP2762852A1|2013-02-05|2013-02-05|Automatic Testing System for a Gas Turbine|
    PCT/EP2014/051168|WO2014122013A1|2013-02-05|2014-01-22|Auto testing system for a gas turbine|
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