• 专利附录
  • 专利说明
  • 权利要求
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    • 专利摘要:
    A pneumatic turbine starter (10) for starting an engine, having a housing (30) having an inlet (32), an outlet (34) and a flow passage (36) extending between the inlet (32) and the outlet (34) for circulating a flow of gas therein. A turbine element is pivotally supported in the housing (30) and is disposed in the flow passage to extract, by rotation, the mechanical power of the gas flow. A secondary supply port (148) is in fluid communication with the flow of pressurized gas into the housing.
    公开号:FR3069582A1
    申请号:FR1856793
    申请日:2018-07-23
    公开日:2019-02-01
    发明作者:Luis Angel Martinez；Rick L. Fiste；David Rawlins
    申请人:Unison Industries LLC；
    IPC主号:
    专利说明:

    PNEUMATIC TURBINE STARTER
    An aircraft engine, for example a gas turbine engine, cooperates, in normal operation, with a pneumatic turbine starter. Air turbine starters are usually mounted on the engine through a gearbox or other transmission system. The transmission transmits power from the starter to the engine to help start the engine. The internal members of the gas turbine engine 10 as well as the pneumatic turbine starter rotate with each other so that the pneumatic turbine starter is used to start the engine.
    According to a first aspect, the present invention relates to a pneumatic turbine starter comprising a casing having an inlet designed to receive a compressed gas, an outlet, and a flow passage extending between the inlet and the outlet for circulating therein a flow of compressed gas and a secondary supply orifice in fluid communication with the flow of compressed gas in the casing and capable of providing a secondary supply of compressed gas 20 coming from the casing.
    According to another aspect, the present invention relates to a method for operating a pneumatic turbine starter, the method comprising supplying compressed air to a pneumatic turbine starter which comprises at least one turbine element pivotally supported in a part of the pneumatic turbine starter, the mechanical power extraction of the compressed air via the turbine element (s), and the selective use of the compressed air supplied, originating from the pneumatic turbine starter , in a secondary application unrelated to the extraction of mechanical power via the turbine element (s).
    The invention will be better understood on detailed study of a few embodiments taken by way of nonlimiting examples and illustrated by the appended drawings in which:
    Figure 1 is a schematic perspective view of a turbine engine with an accessory drive housing and a starter according to an embodiment of the invention;
    Figure 2 is a perspective view of a starter usable in the engine system of Figure 1, according to an embodiment of the invention;
    Figure 3 is a sectional view of the starter of Figure 2 according to an embodiment of the invention;
    Figure 4 is a partially exploded view of the starter of Figure 2 according to an embodiment of the invention;
    Figure 5 is a perspective view of part of the starter 15 of Figure 2 according to an embodiment of the invention i;
    Figure 6 is an enlarged sectional view of a portion of the starter of Figure 2 according to an embodiment of the invention;
    Figure 7 is a partially cutaway perspective view of the starter of Figure 2 with an inlet valve in a second position according to an embodiment of the invention;
    Figure 8 is a sectional view of a portion of the starter of Figure 2 with portions in an engagement position according to an embodiment of the invention;
    Figure 8A is a perspective view of part of the starter of Figure 2 with parts in an engagement position according to an embodiment of the invention;
    Figure 9 is a sectional view of the part of the starter of Figure 8 illustrating the rotation according to an embodiment of the invention;
    Figure 10 is a sectional view of the part of the starter of Figure 8 illustrating the recoil according to an embodiment of the invention;
    Figure 11 is a sectional view of a starter portion of Figure 2 with a toothed pinion engaged according to one embodiment of the invention; and Figure 11A is a perspective view of part of the starter in the position illustrated in Figure 11 according to an embodiment of the invention.
    The present invention relates to a drive mechanism generating a kinetic movement, in the form of a rotary shaft coupled with rotary equipment. A pneumatic turbine choke is a non-limiting example. The starter can have several applications including, without limitation, starting a gas turbine engine, starting a piston engine, starting a ship engine or the like.
    All directional indications (e.g. radial, upper, lower, up, down, left, right, side, front, back, up, down, above, below, vertical, horizontal, in clockwise, 20 counterclockwise) are used only for identification purposes to help the reader understand the invention and do not create any limit, in particular as to position, orientation or 1 ' use of it. The assembly instructions (e.g. fixed, coupled, connected or joined) must be interpreted in a broad sense) and, unless otherwise stated, may include intermediate elements between a series of elements and the movement of the elements relative to each other. In this way, the mounting instructions do not necessarily imply that two elements are directly connected and fixed with respect to each other. The example drawings are for illustrative purposes only and the dimensions, positions, order and relative sizes shown in the drawings appended to this description may vary.
    Within the meaning of the present description, the expression “forwards” or “upstream” refers to a fluid flowing towards the inlet, or to a member relatively closer to the inlet in comparison with another organ. The expression “backwards” or “downstream” refers to a direction towards the exit of a flow passage relative to the pneumatic turbine starter or to the position of a member relatively closer to ia output in comparison with another organ. In addition, within the meaning of the present description, the term “radial” or “radially” refers to a dimension extending between a central longitudinal axis of the engine and an outer periphery of the engine. It should also be understood that "a set" can comprise any number of the elements described respectively, or even comprise a single element.
    Considering FIG. 1, a starter motor or a starter 10 with a pneumatic turbine is mounted on a drive unit 12 for an accessory, or accessory gear box, with the acronym AGB in English terms, also called transmission casing, and both are shown schematically mounted on a turbine engine 14 such as a gas turbine engine. The turbine engine 14 has an air intake with a blower 16 which sends air into a high pressure compression zone 18. The air intake with a blower 16 and the high pressure compression zone are called collectively 'cold section' of the turbine engine 14 upstream of the combustion. The high pressure compression zone 18 supplies high pressure air to a combustion chamber 20. In the combustion chamber, the high pressure air is mixed with a fuel and burned. The hot compressed combustion gases pass through a turbine zone 22 before escaping from the turbine engine 14. As the compressed gases pass through the turbine zone 22, the turbine extracts rotational power from the flow of gases passing through the turbine engine 14. The high pressure turbine of the turbine zone 22 can be coupled with the compression mechanism (not shown) of the high pressure compression zone 18 via a shaft to supply power to the compression mechanism.
    The AGB 12 is coupled with the turbine engine 14, in the turbine area 22, by means of a mechanical PTO 26. The mechanical PTO 26 contains multiple pinions and means for mechanical coupling of AGB 12 with turbine engine 14. Under normal operating conditions, the PTO 26 transmits power from the turbine engine 14 to the AGB 12 to operate accessories of the aircraft, for example, but in no way limiting, fuel pumps, electrical systems, and cabin air conditioning controls. Often, the pneumatic turbine starter 10 is mounted near the AGB 12 and / or the PTO 26 of the turbine engine 14. For example, the pneumatic turbine starter 10 can be mounted either outside the. air intake zone containing the blower 16, i.e. on the gas generator near the high pressure compression zone 18.
    In operation, the pneumatic turbine starter 10 can be used to start the rotation of the engine. Although the pneumatic turbine starter 10 has been shown to be used in the context of an aircraft engine, it is understood that the present invention is not limited to this. The pneumatic turbine starter can be used in any suitable environment, including other desired mobile or non-mobile applications.
    Now considering Figure 2, an example of a pneumatic turbine starter 10 is shown in more detail. Overall, the pneumatic turbine starter 10 comprises a casing 30 having an inlet 32 and a set of outlets 34. A flow passage 36, represented diagrammatically by an arrow, extends between the inlet 32 and the set of outlets 34 to circulate therein a flow of fluid comprising, without limitation, a gas, compressed air or the like. The housing 30 may be composed of two or more than two parts combined with each other or may be formed in one piece. In the presented aspects of the invention, the casing 30 of the pneumatic turbine starter 10 generally has, arranged in series in line, an inlet system 38, a turbine section 40, a transmission box 42 and a drive section 44. The pneumatic turbine starter 10 can be formed using any material and according to any process including, in particular, the die-casting of metals with high mechanical strength and light such as aluminum, stainless steel, iron or titanium. The casing 30 and the gearbox 42 may have a thickness sufficient to ensure adequate mechanical rigidity without unnecessarily weighing down the starter 10 with pneumatic turbine and therefore the aircraft.
    As best seen in Figure 3, the inlet system 38 includes an inlet connector 46 which can be connected to any suitable conduit carrying a gas flow including, but not limited to, an air cart on the ground , an auxiliary generator or an inter-sample start using an already running engine. The inlet connector 46 is in fluid communication with an inlet plenum 48 which sends compressed air to the turbine section 40 via an inlet opening 50. An inlet valve 52 can selectively open and close the inlet opening 50. The inlet opening 50 is in alignment with the turbine section 40. More particularly, an axis of rotation 51 has been shown for the turbine section 40. The inlet opening 50 is aligned with the axis of rotation 51. Although the inlet connector 46 is oriented upwards, it is understood that the supply of air through the inlet opening 50 via the inlet valve 52 takes place in the alignment of the turbine section 40. This allows greater compactness of the starter 10 with pneumatic turbine.
    The inlet valve 52 can be any pneumatic inlet valve. The inlet valve 52 is disposed at least partially in the inlet opening 50 and is movable between an open position and a closed position. A pneumatic actuator can be used to bring the inlet valve 52 into its open position. The pneumatic power source for the actuator can be compressed air supplied, for example, by an auxiliary generator (APU), extract air from the compressor of another engine, from a carriage to the ground or whatever. In some cases, the compressed air supplied to the pneumatic turbine starter 10 and to the inlet valve 52 is not regulated and is at a pressure level higher than may be required for the operation of the pneumatic turbine starter 10. Certain inlet valves 52 can therefore also be designed in the form of a pressure regulator, thereby regulating the pressure of the air flow towards the pneumatic turbine starter.
    Compressed air can be introduced, at an orifice, into a cavity 56 present in a valve seat 58. Regardless of the specific source of compressed air, the supplied air pushes the inlet valve 52 to move it from the closed position to an open position (Figure 7). A biasing member 60 may be included to urge the inlet valve 52 to the closed position if compressed air is no longer supplied to the cavity 56. The biasing member 60 may be any mechanism suitable and has been shown here, by way of non-limiting example, in the form of a helical spring.
    If the inlet valve 52 is in the open position, compressed air is sent to the inlet plenum 48, passes through the inlet 32 of the housing, a flow channel 62, and leaves the housing 30 through the outlet assembly 34. The flow channel 62 comprises an axial flow portion 64 formed through a crown system 66 mounted in the casing 30, very close to the inlet 32. The crown system 66 comprises a central opening 68 and a set of injectors 70 spaced around its periphery (shown in detail in Figure 4), which are integral with and project radially from a surface of the crown system 66. An inlet of the flow channel 62 is formed by the central orifice 68 and the only outputs are those defined by the injectors 70 of the crown system 66.
    In the turbine section 40 there is a set of rotors or turbine elements. In the example illustrated, a first turbine element 72 and a second turbine element 74 form a twin turbine element and are mounted so as to be able to rotate in the casing 30 on the turbine section 40 and are arranged in the passage d flow 36 (FIG. 5) for extracting, by rotation, mechanical power from the flow of gas flowing in flow passage 36. The first turbine element 72 and the second turbine element 74 15 respectively define a first and a second stage of the turbine section 40. In particular, the first turbine element 72 and. the second turbine element 74 include wheels on the periphery of which are located, a number of blades or injectors. The injectors 76 of the first turbine element 72 are aligned with the injectors 70 of the crown system 66 and are spaced apart with respect to the interior surface of the casing 30. An intermediate crown 80 provided with injectors 82 can be interposed between the first turbine element 72 and the second turbine element 74. The injectors 78 of the second turbine element 74 may be aligned with the injectors 82 of the intermediate ring 80 and be spaced apart relatively to the interior surface of the casing 30.
    The first turbine element 72 can be considered as a first stage rotor and the second turbine element 74 can be considered as a second stage rotor. Likewise, the crown system 66 can be considered as a first stator or a first distributor stage and the intermediate crown 80 can be considered as a second stator or a second distributor stage. The crown system 66 has been shown provided with sixteen injectors 70. The intermediate crown has been shown provided with twenty-four injectors 82. The first and second stages of injectors each have a greater number of injectors to what was usually found in starters of this size according to the prior art (respectively 14 and 22). The additional injectors 70, combined with a greater number of injectors 82, allow the pneumatic turbine starter 10 to consume more air and at a higher pressure compared to equipment according to the prior art. This allows a higher torque, of 70 psig or pound per square inch gauge in Anglo-Saxon tarnish, corresponding to around 482,632 kPa in SI unit, or 26% more than other starters according to the prior art. Although sixteen injectors 70 and twenty-four injectors 82 appear in the description, a greater or lesser number of injectors can be included on at least one of the crown systems 66, intermediate crown 80 or the like. For example, in no way limiting, the intermediate crown 80 comprises twenty-five injectors 82.
    The first turbine element 72 and the second turbine element 74 are coupled by means of an output shaft 90. More particularly, the first turbine element 72 and the second turbine element 74 may each comprise a central part forming hub 92 keyed onto a first part of the output shaft 90. The output shaft 90 is supported, so as to be able to rotate, by a pair of bearings 94.
    The output shaft 90 serves as a rotary input member for a gear train 96 disposed in an interior 98 of the gearbox 42. The gear train 96 can include any pinion system, including , in no way limiting, a planetary gear system or a pinion gear system. The output shaft 90 couples the gear train 96 with the first and second turbine elements 72, 74, which allows the transmission of mechanical power to the gear train 96. The interior 98 of the gearbox 42 may contain a lubricant (not shown) including, without limitation, a grease or an oil to ensure the lubrication or cooling of the mechanical parts contained therein, such as the gear train 96.
    A retaining element 100 may be mounted on the gearbox 42 and may be present to cover the interior 98 of the transmission box 42. The retaining element 100 may comprise a plate 102 provided with an orifice 104 through which the output shaft 90 can extend. Although the word “plate” has been used here, it will be understood that this part of the retaining element 100 is not necessarily planar. In the example illustrated, the plate 102 has, by way of non-limiting example, a non-planar or stepped profile.
    It will be understood that the retaining element 100 can have any suitable shape, profile, outline or other. In the example illustrated, a peripheral part can be mounted between the casing and the gearbox and the plate 102 comprises a central part which extends into the housing with the orifice 104 formed therein. The body or the plate 102 can comprise a frustoconical part. This is not necessarily the case and the retaining element 100 can be any retaining means designed to prevent or limit the escape of the lubricant from an interior of the transmission box 42. It will be understood that the output shaft 90 and retaining member 100 can provide fluid tightness.
    The retaining element 100 is able to hold the grease in the gearbox 42 for a lifetime of the gearbox. It is contemplated that when a lubricant such as grease is in the interior 98, the retainer 100 may retain the lubricant in the interior 98. This limits the migration of lubricants into the housing 30 and causes an improvement in the lubrication of the gears, so that the gearbox 42 does not dry, which was a problem in the systems according to the prior art. Furthermore, there is no need to add an additional amount during the lifetime of the system.
    An output of the gear train 96 can cooperate with a first end 106 of a drive shaft 108. The rotary drive shaft 108 can be produced with any material and according to any process including, in no way limiting, the extrusion or machining of high strength metal alloys such as those containing aluminum, iron, nickel, chromium, titanium, tungsten, vanadium or molybdenum. The diameter of the drive shaft 108 can be fixed or vary over the length thereof.
    In the transmission box 42 can be an orifice 110 through which the first end 106 of the drive shaft 108 can extend to mesh with the gear train 96. A second casing 112 can cooperate with the box transmission 42. The drive shaft 108 can be mounted in the second housing 112 so as to be able to rotate.
    For example, a second end 116 of the drive shaft 108 can be mounted to rotate in a bearing device 118 supported and housed in an end casing 120. The end casing 120 can be mounted from any which way suitably on the second casing 112. The end casing 120 is formed and mounted so that its inner wall surface has a small concentric spacing with respect to the structure it contains and it has a butted and bolted end against the end of the second casing 112. The second casing 112 and the end casing 120 are fixed so as to be coaxial with the casing 30 and the second casing 112. In this way, the casing comprises a plurality of assembled sections with each other.
    The end casing 120 is cut at an outer end 122 to reveal part of the drive shaft 108 and a pinion 124 cooperating therewith. In the example illustrated, the end 122 can be considered as the bottom of the end casing 120 and can reveal a bottom of the drive shaft 108 and of the pinion 124. The end casing 120 also contains a clutch system 126 cooperating with the drive shaft 108. In the example illustrated, a groove 132 provided with a portion with a helical thread 134 (Figure 7) makes the drive shaft 108 and the system d 'clutch 126. The clutch system 126 may include any coupling means including, without limitation, gears, splines, a clutch mechanism or combinations thereof. In the example illustrated, the clutch system 126 comprises a clutch groove 136 having a helical internal thread 138 complementary to that of the part with helical thread 134. A second clutch element 140 can cooperate selectively with the groove 136 clutch via a serrated link 142. More particularly, the opposite or adjacent faces of the clutch groove 136 and of the second clutch element 140 are respectively provided with complementary inclined serrations 144 and 146 for transmission of torque, which can engage with each other (Figure 4). The serrations 144 and 146 are only a non-limiting example of the variety of sawtooth configurations for creating a connection by unidirectional freewheeling clutch.
    The pinion 124 is shown placed on the drive shaft 108 at the second end 116 in the immediate vicinity of an output side of the clutch system 126. More particularly, the pinion 124 is coupled or integrated with the second element 140 clutch. The pinion 124 is designed to be engaged with and separated from a toothed pinion 150 of the motor (Figure 7), for example in the coaxial direction of the drive shaft 108. The pneumatic turbine starter 10 is mounted in connection with the turbine engine 14 so that the drive shaft 108 is parallel to the teeth of the pinion on and delimits the peripheral limit of the toothed pinion 150 of the motor.
    A system for approaching or moving the pinion 124 away from the toothed pinion 150 of the motor can comprise a piston 128, an indexing system 130 and a solenoid valve 152. The solenoid valve 152 can be any suitable solenoid valve. In the example illustrated, the solenoid valve controls the air inlet into a port 154 connected to a closed end 156 of the second casing 112. The solenoid valve 152 can also control the air inlet into the operating port Valve 54.
    Figure 4 better illustrates that the housing 30 includes a peripheral wall 60 defining an interior 162 and an exterior 164. The outlet assembly 34 is located in a middle region of the housing, along the peripheral wall 160, after the second turbine element 74. In the example illustrated, the peripheral wall 160 is a cylindrical peripheral wall. The peripheral wall can be formed in any suitable manner, in particular with the possibility of having a wall thickness of 2.54 mm (0.100 inch). The outlet assembly 34 may extend over a portion of the periphery of the peripheral wall, it may in particular extend over 270 degrees or more of the periphery. In the example illustrated, the outlet assembly 34 includes a plurality of outlets or orifices spaced about 360 degrees around the periphery of the peripheral wall 160. The outlet assembly 34 shown comprises multiple rows of outlets, although it should be understood that this is not necessarily the case. Outlets 34 can be located, organized, or oriented to any suitable location and in any suitable manner. The outlet assembly 34 shown comprises exhaust orifices 34a and 34b of variable dimensions. These differences in dimensions may be of a purely aesthetic nature or may be used to satisfy other requirements, in particular by having dimensions creating small exhaust openings, by tapping screw holes, etc. In the example illustrated there are thirty-two large exhaust ports 34a and eight small exhaust ports 34b. It is contemplated that the exhaust ports 34a and 34b may have appropriate dimensions, including, but not limited to, that the large exhaust ports 34a may measure 15.875 millimeters (5/8 inch) and that the small exhaust ports 34b can measure 11,1125 millimeters (7/16 inch). It will be understood that, according to other possibilities, an exhaust port of only one dimension may be present, that additional dimensions may be present and that any number of orifices of various dimensions may be present. The outlets 34 may include any suitable ports to create a low resistance exhaust passage so that the gas leaves the air turbine starter 10. Although other shapes, profiles, possible contours can be used, round outlets 34 are shown as examples. Furthermore, it will be understood that the more the outlets 34 cover a large area, the lower the resistance opposed to the gas and the less back pressure there is. The back pressure can be measured between the second stage rotor and the exhaust. Aspects of the invention provide a back pressure of 1 psig (6.894757 kPa) or less. This is less than in prior art equipment which has a back pressure of up to 10 psig (68.94757 kPa).
    FIG. 5 more clearly represents a retention grid or grid 166 disposed relative to the casing 30. The retention grid 166 may be located in the interior 162 of the casing 30, upstream of the outlet assembly 34. The grid retention 166 can be found very close to the second turbine element 74. More particularly, it can be located very close to the exhaust of the second turbine element 74 and axially between the second turbine element 74 and the outlet assembly 34. Although the retention grid 166 can be mounted from any which appropriate manner in the casing 30, it has been shown mounted on a bearing hub 168 of the bearing 94, which constitutes an axial retaining device designed to retain the retention grid 166 axially with respect to the casing 30. The retention grid 166 can extend to, abut against the peripheral wall forming the casing 30.
    The retention grid 166 can be produced in any suitable manner, in particular it can comprise a plate provided with openings 167, a perforated plate provided with openings 167, or a grating provided with openings 167. The retention grid 166 can be made of any suitable material including, without limitation, stainless steel and have openings of any size and have any percentage of open area. In the example illustrated, the retention grid 166 has 60% of open area to ensure better retention but without appreciable increase in the back pressure.
    Among other things, the retention grid 166, combined with the series of outlets 34 and their small dimensions, creates a winding passage for the gas to come out of the pneumatic turbine starter 10. The retention grid 166, in combination with the outlet assembly 34 and their small dimensions, reduces the risk of sparks, particles or other debris escaping from the casing 30. Figure 6 is an enlarged sectional view of part of the pneumatic turbine starter 10 representing an example of winding passage 170. The creation of such winding passages can be particularly useful if metal or other impurities enter the casing through the inlet 32. These debris can create sparks in the interior 162 of the casing 30 and the presence of the retention grid 166 as well as outlets 34 of small diameter obstructs the output of sparks from the casing 30. The retention grid 166 as well as outlets 34 of small diameter can also constitute several forms of mechanical retention in the event of failure of part of the starter 10 with pneumatic turbine.
    Figure 7 is a partially cutaway perspective view of the pneumatic turbine starter and. illustrates examples of dimensions for the starter 10 with pneumatic turbine. For example, a total length (L) of the air turbine starter 10 may be approximately less than 50 cm (19.7 inches). Furthermore, the length of the pneumatic turbine starter 10 from the mounting surface (at 112) of the engine to the rear end of the starter at the inlet 32 may be less than 39 cm (15.33 cm). The extension of the end 122 may be less than 9.7 cm (3.82 inches). By way of nonlimiting example, the diameter (Hl) of the pneumatic turbine starter 10, which globally includes the height with the exception of the inlet system 38, the solenoid valve 152 and the flexible hoses / accessories, can be equal to or less than 15.63 cm (6.15 inches), the cylindrical part of the casing 30 being able in particular to have a diameter of 14.6 cm (5.75 inches) or less. The height (H2), including the entry system, can be equal to or less than 17.17 cm (6.76 inches). The height (H3), including the solenoid valve 152, can be equal to or less than 23.5 cm (9.25 inches).
    Figure 7 also shows that aspects of the present invention include the fact that a secondary supply port or air supply port 148 may be included in the inlet system 38. It is contemplated that the starter 10 with pneumatic turbine can fulfill a dual function or purpose and also serve as a point of supply of pressurized air. More particularly, the air supply orifice 148 is connected to the flow of pressurized gas in the pneumatic turbine starter 10 and designed to provide a secondary supply of pressurized gas from the pneumatic turbine starter 10. The air supply port 148 may allow a user to access the pressurized air present in the plenum 48 of the housing 30, preferably when the inlet valve 52 is in the closed position. For example, according to a non-limiting aspect of the invention, the air supply orifice 148 can be designed with an interface to selectively constitute a pressurized air or gas supply orifice for another tool or pneumatic device. To this end, the air supply orifice 148 may constitute an orifice 148 designed to allow a user or an operator to receive or use the gas coming from the pressurized source via the pneumatic turbine starter 10, without intermediate structures, flow passages, fittings, additional interface converters or others. According to one aspect of the invention which is in no way limiting, the air supply orifice 148 may take the form of a 1.5875 cm (5/8 inch) orifice with an American standard conical thread (NPT). Although it is not shown, it will be understood that a plug may be present in the pneumatic turbine starter 10 and that such plugs may be designed to selectively close the secondary supply orifice 148.
    Figure 7 also shows the inlet valve 52 in the open position. During operation, the solenoid valve 152 can control a flow of air sent to the orifice 54, for example via a pipe (not shown). As air fills the cavity 56, the inlet valve 52 presses against the biasing member 60 and the inlet valve 52 comes into the open position shown in Figure 7. The air under pressure sent to the inlet plenum 48 then passes through the inlet 32 of the casing, a flow channel 62 and drives the first and second elements 72 and 74 of the turbine before exiting in a central zone of the casing 30 via the outlet assembly 34. Thus, when the inlet valve 52 is in the open position, compressed air can pass through the inlet valve 52 and enter the turbine section 40. The pressurized air strikes the first and second turbine elements 72 and 74 by rotating them at a relatively high speed.
    Since the inlet valve is described as being actuated by pressurized air, it can be considered as a pneumatic valve. However, it will be understood that other possible valve mechanisms and actuators may be used. If no more air is sent into the cavity 56, the biasing element 60 can return to its uncompressed state and return the inlet valve 52 to the closed position (Figure 3). When the inlet valve 52 is in the closed position, the flow of compressed air to the turbine section 40 can be prevented.
    In normal operation, when it is desired to start the turbine engine 14, the pinion 124 is moved to the right so that the pinion 124 meshes with the toothed pinion 150 of the engine. More particularly, when the first and second turbine elements 72 and 74 are driven, they rotate the output shaft 90. The output shaft 90 serves as an input for the gear train 96, which in turn does rotate the drive shaft 108. A torque is transmitted, via the groove 132, from the threaded part 134 to the gear system 126, to the pinion 124 by means of a spline connection, and finally to the toothed pinion 150 of the motor.
    As the engine 14 ignites and acquires autonomous operation, the toothed pinion 150 of the motor can drive the pinion at a speed greater than that of the drive shaft 108. The serrations 144 and 146 slip so that the air turbine starter is not driven at high engine speeds.
    The pneumatic turbine starter 10 is further designed to perform an indexing function if the pinion 124 abuts against one of the teeth of the toothed pinion 150 while it is actuated to the right to mesh. Figure 8 is a sectional view of part of the starter during meshing. It will be understood that the part of the pneumatic turbine starter 10 shown in FIGS. 8 to 11A is shown, for greater clarity, with the opening of the end casing 120 facing upwards.
    When air under pressure is introduced into the closed end 156 of the second casing 112 via the orifice 154, the piston 128, the indexing system 130, the clutch system 126 and the pinion 124 are pushed towards the casing d end 120 as indicated by arrow 172. Finally, it is assumed that the pinion 124 meshes with the toothed pinion of the motor. However, when an engagement occurs, the movement of the pinion 124 is opposed by the coming of the teeth in abutment against the teeth of the toothed pinion 150 of the motor. More particularly, the teeth of the pinion 124 strike the teeth of the toothed pinion 150 of the motor. Indexing takes place when the meshing between the pinion 124 and the toothed pinion 150 of the motor is not obtained at the first try.
    Now considering FIG. 9, due to the force acting on the piston 128 and the indexing system 130, illustrated by an arrow 174, an internal mechanism in the indexing system 130 rotates inside the groove 136 d the serrated clutch as illustrated by arrow 176. Although the indexing system 130 can rotate at any angle, it is envisaged that the indexing system 130 rotates by about half a pinion tooth. It will be understood that the pinion 124 and the clutch groove 136. splines remain stationary during the indexing movement.
    After the engagement has taken place, the piston 128, the indexing system 130, the clutch system 126 and the pinion 124 are moved away from the end casing 120, as illustrated by an arrow 178 in FIG. 10. During this recoil, a spring 180 inside the indexing system 130 begins to re-index the pinion 124. The new position of the pinion is established as the spring is released during the recoil. Once the pinion 124 has rotated and achieved the desired indexing, the spring 180 pulls the drive shaft system 108 to return it to the complete recoil position and, under the action of the barrier air of the piston 128, the drive shaft 108 advances once again to engage the toothed pinion 150 of the engine. A new engagement is then attempted with the pinion 124 in a new position defined by the indexing. As illustrated in Figure 11, the pinion 124 can mesh properly with the toothed pinion 150 of the motor.
    The advantages associated with the starter described here include the impossibility of undesirable rearward drive of the starter for a turbine engine. The impossibility of driving backwards reduces wear on the parts described here, in particular the drive shaft and the output shaft. Reduced wear prolongs as to. it the lifetime of the parts. The starter described here reduces the cost of maintenance and facilitates repair. The starter engagement mechanism performs all normal shock absorption, indexing, freewheeling, automatic tooth separation, etc.
    The arrangement of the outlet assembly around the cylindrical peripheral wall 160 allows 360 degree exhaust from various orifices. In starters with fewer exhaust ports, the exhaust is more concentrated and the possibilities as to. the place where the starter or. the orientation of the assembly thereof without blocking or obstructing the orifices. Conversely, the set of outputs described above allows flexibility in mounting the starter 10 with a pneumatic turbine. It suffices to mount the pneumatic turbine starter 10 at various specific points, including the inlet 32 and the pinion 124. As the inlet system 38 can be made to rotate in any way as long as a flow of 'aligned air is created at the inlet 32, this allows many orientations of the starter 10 to pneumatic turbine.
    The present invention also allows more power to be extracted from the second stage. In prior art equipment, the power distribution is usually 70% of the power from the first stage (a stage is the combination of a stator and a rotor) and only 30% of that of the second floor. In the present invention, the power distribution is 54-46%. A combination of more injectors and an offset in the stator injectors allows greater power extraction in the second stage.
    A larger output shaft allows the transmission of the higher torque created by this extraction of increased power. More particularly, the present invention also allows the use of a drive shaft 108 of a larger diameter in a pinion according to the prior art. By way of non-limiting example, a diameter of 22.225 millimeters (7/8 inch) can be used, which constitutes an increase compared to usual shaft diameters. Such a larger shaft allows a greater distribution of the torque. It is possible to include in no way limiting aspects of the invention, according to which smaller shaft diameters (eg diameters less than 22,225 millimeters, ie 7/8 of an inch) can be used. Furthermore, it is also envisaged that a pinion according to the prior art can be modified by enlarging a central opening of the pinion, which is capable of receiving a 19.05 millimeter (3/4 inch) shaft in order to define an opening of larger dimensions. Once enlarged, a tree larger than 19.05 millimeters can then be inserted into or through the larger opening. The central opening can be enlarged in any suitable way, in particular by drilling or chemical attack.
    In addition, failure of conventional 19.05 millimeter (3/4 inch) diameter shafts is common, as operators may repeatedly seek to launch the pneumatic starter. For example, in certain circumstances, the air starter will not start the engine and the operator will try to start the air starter again while parts of the air starter are still turning. Interaction with the fixed pinion and the restarted conventional diameter drive shaft causes the shaft to rupture, making the pneumatic starter unnecessary. The larger diameter considered here will result in more robust equipment.
    Still further, aspects of the present invention include a method for making a pneumatic turbine starter, comprising enclosing a turbine element in a peripheral wall between an inlet and a set of outlets to define a fluid passage and the creation of a winding passage between the turbine element and an exterior of the peripheral wall by the installation of a retention grid between the turbine element and the outlet assembly. The winding passage is designed to delay the expulsion of a fragment via the set of exits. This may include stopping or slowing down such a fragment. Furthermore, aspects also reveal that the grid disposed inside can be designed to attenuate the expulsion of flaming particles from inside the casing. During use, the grid and the outlets can also constitute a sinuous passage to be followed by a spark between the turbine element and an exterior of the peripheral wall.
    LIST OF REFERENCES
    Pneumatic turbine starter
    Accessory drive box
    Turbine engine
    wind tunnel
    High pressure compression zone
    Combustion chamber
    Turbine area
    Mechanical power take-off
    0 Carter
    Entrance
    Set of outputs
    6 Flow passage
    8 Entry system
    Turbine section
    Transmission box
    Training section
    Inlet fitting
    Entrance plenum
    Entrance opening
    Rotation axis
    Inlet valve
    Valve operating port
    Cavity
    8 Valve seat
    Solicitation element
    Flow channel
    Axial flow part
    Crown system
    Central hole
    Set of injectors
    First turbine element
    Second turbine element
    injectors
    injectors
    Intermediate crown
    injectors
    Output shaft
    Hub part
    Pair of bearings
    Gear train
    inside
    Retainer
    Plate
    Orifice
    First end
    Drive shaft
    Orifice
    Second housing
    Second end
    Bearing device
    End housing
    End
    Sprocket (124)
    Clutch system
    Piston
    Indexing system
    Groove
    Threaded part
    Serrated clutch groove
    Helical internal thread
    140 Second clutch element 142 Link to serrations 144 serrations 146 serrations 5,148 Air supply port 150 Toothed motor pinion 152 Solenoid 154 Orifice 156 Closed end 10,160 Peripheral wall 162 inside
    164 Exterior
    166 Retention grid
    168 Hub
    170 Winding passage
    172 Arrow to the end block 120
    174 Arrow illustrating the force acting on the piston 128 and the indexing system 130
    176 Arrow illustrating an internal mechanism in the indexing system 130 rotnt inside the serration clutch 136
    178 Arrow illustrating that the piston 128, the indexing system 130, the clutch system 126 and the pinion 124 are spaced from the end casing 120
    180 spring
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Pneumatic turbine starter (10), comprising:
    a casing (30) having an inlet © (32) designed to receive a pressurized gas, an outlet (34) and a flow passage extending between the inlet (32) and the outlet (34) for circulating therein a stream of compressed gas; and a secondary supply orifice (148) in fluid communication with the flow of compressed gas in the casing (30) and capable of providing a secondary supply of the compressed gas coming from the casing (30).
    [2" id="c-fr-0002]
    2. A pneumatic turbine starter (10) according to claim 1, in which the casing (30) comprises multiple sections cooperating with each other, including an inlet section and a turbine section (40).
    [3" id="c-fr-0003]
    3. A pneumatic turbine starter (10) according to claim 2, wherein the inlet section further comprises an inlet system (38) mounted on the turbine section and constitutes at least part of the inlet (32) .
    [4" id="c-fr-0004]
    4. A pneumatic turbine starter (10) according to claim 3, in which the inlet system (38) comprises an inlet fitting (46) designed to be connected to a duct and to receive a pressurized gas from it. .
    [5" id="c-fr-0005]
    5. A pneumatic turbine starter (10) according to claim 4, in which the secondary supply orifice (148) is included in the inlet system (38) and is in fluid communication downstream of the inlet fitting. (46).
    [6" id="c-fr-0006]
    6. A pneumatic turbine starter (10) according to claim 4, in which the inlet system (38) further comprises an inlet plenum (48) in fluid communication with the inlet fitting (46),
    [7" id="c-fr-0007]
    7, A pneumatic turbine starter (10) according to claim 6, wherein the secondary supply orifice (148) is included in the inlet system (38) and establishes fluid communication with the inlet plenum (48 ).
    5
    [8" id="c-fr-0008]
    8. A pneumatic turbine starter (10) according to claim 7, in which the inlet system (38) further comprises an inlet valve (52) movable between a closed position and an open position and capable of establish fluid communication between the inlet plenum (48) and the turbine section (40) when it is in the open position.
    [9" id="c-fr-0009]
    9. A pneumatic turbine starter (10) according to claim 8, in which the secondary supply orifice (148) is designed to ensure the secondary supply of pressurized gas when the inlet valve (52) is in the closed position.
    15
    [0010]
    10. A pneumatic turbine starter (10) according to claim 1, further comprising a plug designed to selectively close the secondary supply orifice (148).
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    同族专利:
    公开号 | 公开日
    US10443506B2|2019-10-15|
    CN109306900A|2019-02-05|
    GB201811756D0|2018-08-29|
    GB2566592A|2019-03-20|
    US20190032568A1|2019-01-31|
    GB2566592B|2021-05-19|
    CN109306900B|2020-12-04|
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    GB1201767A|1966-11-02|1970-08-12|Plessey Co Ltd|Improvements in or relating to engine-starting gas turbine systems|
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    CA972971A|1972-11-10|1975-08-19|Bendix Corporation |Gas turbine intake manifold having an integral overpressure cut-off valve|
    US3878677A|1974-04-10|1975-04-22|United Aircraft Corp|Auxiliary turbine/compressor system for turbine engine|
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    US4916893A|1987-09-02|1990-04-17|Sundstrand Corporation|Multipurpose auxiliary power unit|
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    US5143329A|1990-06-01|1992-09-01|General Electric Company|Gas turbine engine powered aircraft environmental control system and boundary layer bleed|
    DE10355917A1|2003-11-29|2005-06-30|Mtu Aero Engines Gmbh|Gas turbine, in particular aircraft engine, and method for generating electrical energy in a gas turbine|
    RU110414U1|2011-07-07|2011-11-20|ОАО "Омское машиностроительное конструкторское бюро"|AIR STARTER CONTROL DEVICE|US20190032566A1|2017-07-26|2019-01-31|Unison Industries, Llc|Air turbine starter|
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    法律状态:
    2019-06-20| PLFP| Fee payment|Year of fee payment: 2 |
    2020-11-06| PLSC| Search report ready|Effective date: 20201106 |
    2021-04-09| ST| Notification of lapse|Effective date: 20210305 |
    优先权:
    申请号 | 申请日 | 专利标题
    US15660235|2017-07-26|
    US15/660,235|US10443506B2|2017-07-26|2017-07-26|Air turbine starter|
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