Turbine engine including an air turbine starter and an induction circuit

Abstract

A turbine engine includes an engine core, an engine drive shaft, an accessory gear box (AGB), an air turbine starter (ATS), and an air induction circuit. The engine core has a fan section, a compressor section, a combustion section, and a turbine section arranged in series flow. The engine drive shaft is operably coupled to the fan section, the compressor section, and the turbine section. The AGB and the ATS are operably coupled to the engine drive shaft.

Description

[0001] This application is a divisional application of a patent application filed on October 23, 2024 (application number 2024114823173, invention title "Turbine Engine Including Air Turbine Starter and Bleed Air Circuit"). Technical Field

[0002] This disclosure generally relates to a turbine engine including an air turbine starter, and more specifically to a bleed air circuit from a turbine engine. Background Technology

[0003] Turbine engines, such as gas turbine engines, use an air turbine starter (ATS) during startup. The ATS is typically mounted near the turbine engine and may be coupled to a high-pressure fluid source, such as compressed air, which impinges on the turbine rotor within the ATS, causing it to rotate at a relatively high speed. The ATS includes an output drive shaft, typically driven by the turbine rotor via a reduction gearbox, which provides rotational energy to a rotatable element of the turbine engine (e.g., a crankshaft or rotatable shaft) to initiate rotation. The rotation caused by the ATS continues until the turbine engine reaches a self-sustaining operating speed. Attached Figure Description

[0004] This specification sets forth a complete and implementable disclosure of the subject matter for those skilled in the art, including its best mode, and references the accompanying drawings, wherein: Figure 1 This is a schematic diagram of a turbine engine with an air turbine starter, based on the various aspects described in this article.

[0005] Figure 2 Is it suitable for Figure 1 A schematic block diagram of the bleed air circuit used in a turbine engine, which supplies bleed air from the turbine engine to the air turbine starter. Detailed Implementation

[0006] This disclosure relates to a turbine engine including an ATS (Automatic Guided Vehicle) and a bleed air circuit for drawing bleed air from the turbine engine. The turbine engine includes an engine drive shaft. The ATS is coupled to an accessory gearbox (AGB). The AGB is selectively coupled to the engine drive shaft. The drive of the ATS can drive the engine drive shaft via the drive of the AGB.

[0007] The bleed air circuit is used to supply bleed air from the turbine engine to the ATS. The bleed air drives the AGB, which in turn drives the engine drive shaft. A portion of the bleed air within the bleed air circuit can be supplied to systems external to the turbine engine. The bleed air circuit, including the ATS, can be used to extract work from the bleed air to enhance the drive of the engine drive shaft. For ease of illustration, this disclosure will be described with respect to a turbine engine. However, it will be understood that the aspects of the disclosure described herein are not limited thereto and can be generally applied to other engines or other turbine engines. For example, this disclosure can be applied to engine starter assemblies used with any suitable engine or within any suitable vehicle and can provide benefits in industrial, commercial, and residential applications.

[0008] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous relative to other implementations. Furthermore, unless explicitly indicated otherwise, all embodiments described herein should be considered exemplary.

[0009] As used herein, terms such as “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of the individual components.

[0010] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and are used in the context of the normal operating posture of the gas turbine engine or vehicle. For example, for a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0011] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "front" or "forward" indicate being in front of something, while "back" or "rear" indicates being behind something. For example, when used in relation to fluid flow, front / forward can indicate upstream, while back / rear can indicate downstream.

[0012] Furthermore, as used herein, the term "radial" or "radially" refers to a direction extending toward or away from a common center. For example, in the general context of a turbine engine, radial refers to the direction of a ray extending between the central longitudinal axis of the turbine engine and the outer circumference of the engine. Additionally, as used herein, the term "group" or "united" elements can be any number of elements, including only one.

[0013] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, front, rear, etc.) are for illustrative purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly regarding the location, orientation, or use of the aspects of the disclosure described herein. Connection references (e.g., attachment, coupling, fastening, joining, and linking) should be interpreted broadly and, unless otherwise indicated, may include intermediate structural elements between sets of elements and relative movement between elements. Therefore, a connection reference does not necessarily mean that two elements are directly connected and fixed to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, orders, and relative sizes reflected in the figures accompanying this document may vary.

[0014] As used herein, a “controller” may include at least one processor and memory. Non-limiting examples of memory may include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic storage, such as optical discs, DVDs, CD-ROMs, etc., or any suitable combination of these types of storage. The processor may be configured to run any suitable program or executable instructions designed to perform various methods, functions, processing tasks, calculations, etc., to enable or implement the technical operations or activities described herein. The program may include a computer program product, which may include a machine-readable medium for carrying or storing machine-executable instructions or data structures thereon. Such a machine-readable medium may be any available medium that can be accessed by a general-purpose or special-purpose computer or other machine having a processor. Generally, such a computer program may include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a particular task or implementing a particular abstract data type.

[0015] The exemplary drawings are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying drawings may vary.

[0016] Figure 1 This is a schematic perspective view of a turbine engine 14. The turbine engine 14 may include an air turbine starter (ATS) 10. The ATS 10 is coupled to an accessory gearbox (AGB) 12, also known as a transmission housing. The AGB 12 includes a housing (not shown) containing at least a plurality of gears (not shown).

[0017] The turbine engine 14 may include a fan section 16, a compressor section 18, a combustion section 20, a turbine section 22, and an exhaust section 26 arranged in series. The fan section 16 may be at least partially enclosed by a fan casing 28, or otherwise enclosed by the nacelle or casing of the turbine engine 14. The turbine engine 14 may include other components not shown.

[0018] AGB 12 and ATS 10 are schematically shown as corresponding portions mounted to the turbine engine 14. At least a portion of ATS 10 or AGB 12 may be located radially outward of the fan housing 28. That is, ATS 10, AGB 12, or a combination thereof may be located radially outward of the fan section 16. Alternatively, in different and non-limiting examples, it is contemplated that at least a portion of ATS 10, AGB 12, or a combination thereof may be located within any suitable portion of the turbine engine 14, such as near the compressor section 18, wherein ATS 10 or AGB 12 is coupled to a transmission gearbox (not shown).

[0019] The AGB 12 can be coupled to the turbine engine 14 at a portion of the turbine section 22 via a mechanical power take-off device 27. The mechanical power take-off device 27 includes multiple gears and devices for mechanically coupling the AGB 12 to the turbine engine 14.

[0020] Figure 2 Is to make Figure 1 A schematic block diagram of the bleed air circuit 30 interconnected with the turbine engine 14 and the ATS 10. The ATS 10 is drive-connected to the AGB 12 and fluidly connected to the bleed air circuit 30.

[0021] Fan section 16, compressor section 18, combustion section 20, and turbine section 22 together define engine core 15. At least a portion of engine core 15 may be disposed on connection to fan housing 28. Figure 1 The turbine engine 14 may be housed within the engine casing 17 or the engine compartment. Any suitable portion of the turbine engine 14 may be housed within the engine casing 17.

[0022] Compressor section 18 may include a low-pressure (LP) compressor 34 and a high-pressure (HP) compressor 36 arranged in series. Turbine section 22 may include a high-pressure (HP) turbine 40 and a low-pressure (LP) turbine 42 arranged in series. Combustion section 20 may include a combustor 38 disposed between the HP compressor 36 and the HP turbine 40, and fluidly connecting the HP compressor 36 to the HP turbine 40. Engine drive shaft 44 drivesly connects turbine section 22 to compressor section 18 and fan section 16. Although not shown, engine drive shaft 44 may include: a high-pressure (HP) shaft that drivesly connects the HP turbine 40 to the HP compressor 36 to jointly define an HP spool; and a low-pressure (LP) shaft that drivesly connects the LP turbine 42 to the LP compressor 34 and fan section 16 to jointly define an LP spool.

[0023] AGB 12 is indirectly operably coupled to engine drive shaft 44. AGB 12 includes AGB drive shaft 78, which defines the mechanical output of AGB 12. AGB drive shaft 78 is selectively operably coupled to engine drive shaft 44. As a non-limiting example, separator 80 may selectively operably coupled AGB drive shaft 78 and engine drive shaft 44. Alternatively, AGB drive shaft 78 may be directly coupled to engine drive shaft 44 or integrally formed with engine drive shaft 44. AGB 12 is operably coupled to any suitable portion of engine drive shaft 44.

[0024] The turbine engine 14 includes a precooler heat exchanger (PCE) 70 configured to direct bleed air from the turbine engine 14 to an external system 74 located outside the turbine engine 14. The PCE 70 is fluidly connected to the external system 74 via a bleed air outlet line 64. The external system 74 may include any suitable system that utilizes bleed air from the turbine engine 14 during operation of the external system 74, such as, but not limited to, an environmental control system (ECS). The PCE 70 is also fluidly connected to a cooling fluid source via a cooling fluid inlet 72. The cooling fluid source may be from a portion of the turbine engine 14, such as fan section 16 or compressor section 18. The PCE 70 may discharge cooling fluid from the cooling fluid source via a cooling fluid outlet 75. The cooling fluid outlet 75 may be fluidly connected to the atmosphere or a portion of the turbine engine 14, such as turbine section 22, exhaust section 26, etc. Figure 1 ) or combinations thereof.

[0025] ATS 10 includes an ATS output shaft 76, an ATS gearbox 112, an ATS drive shaft 118, and an ATS turbine 114. The ATS turbine 114 is driveably coupled to the ATS gearbox 112 via the ATS drive shaft 118 to define the mechanical input of the ATS gearbox 112. The ATS gearbox 112 is coupled to the ATS output shaft 76 to define the mechanical output of the ATS gearbox 112 and the ATS 10 as a whole. At least portions of the ATS turbine 114, ATS gearbox 112, ATS drive shaft 118, and ATS output shaft 76 can be received within an ATS housing (not shown).

[0026] Bleed air circuit 30 is fluidly coupled to turbine engine 14 and configured to draw bleed air from at least a portion of turbine engine 14. Bleed air circuit 30 may include three bleed air passages directly fluidly coupled to corresponding portions of turbine engine 14. It will be understood that the passages of bleed air circuit 30 may be formed as discrete elements (e.g., ducts) or otherwise integrally formed within, for example, the existing structure of turbine engine 14. As a non-limiting example, bleed air circuit 30 may include a first LP bleed air passage 46, a second LP bleed air passage 48, and an HP bleed air passage 50. HP bleed air passage 50 may be coupled to a portion of turbine engine 14 having a higher pressure working airflow relative to the locations where the first LP bleed air passage 46 and the second LP bleed air passage 48 are located. In other words, HP bleed air passage 50 includes bleed air at a higher pressure than the bleed air in the first LP bleed air passage 46 and the second LP bleed air passage 48. First LP bleed air passage 46 may be coupled to a portion of turbine engine 14 upstream of the second LP bleed air passage 48. As a non-limiting example, both the first LP bleed air passage 46 and the second LP bleed air passage 48 may be located upstream of the HP bleed air passage 50. Both the first LP bleed air passage 46 and the second LP bleed air passage 48 may be directly fluidly connected to the LP compressor 34, and the HP bleed air passage 50 may be directly fluidly connected to the HP compressor 36.

[0027] Bleed air circuit 30 includes a first bleed air passage 54, a second bleed air passage 56, and a third bleed air passage 58. The first bleed air passage 54 is fluidly connected to the turbine engine 14 via a first LP bleed air passage 46, a second LP bleed air passage 48, and an HP bleed air passage 50. The second bleed air passage 56 fluidly connects the first bleed air passage 54 to the ATS 10 and defines the fluid input to the ATS 10. The third bleed air passage 58 fluidly connects the ATS 10 to a bleed air inlet 62 that leads directly to the PCE 70.

[0028] The bleed air circuit 30 includes a bypass passage 60 that fluidly connects the first bleed air passage 54 to the third bleed air passage 58, while bypassing either the ATS 10 or the second bleed air passage 56. The bypass passage 60 and the third bleed air passage 58 meet at a junction 84. The junction 84 may be located upstream of the PCE 70. Alternatively, the bypass passage 60 and the third bleed air passage 58 may be connected to the PCE 70 separately, such that the bypass passage 60 bypasses the ATS 10, and together the bypass passage 60 and the third bleed air passage 58 define a bleed air inlet line 62 leading to the PCE 70. When the bypass passage 60 and the third bleed air passage 58 are independently connected to the PCE 70, the PCE 70 defines the junction 84. When PCE 70 is output to external system 74 via bleed outlet line 64, the third bleed passage 58 can be said to fluidly connect ATS 10 to external system 74, and the bypass passage 60 can be said to fluidly connect the first bleed passage 54 to external system 74.

[0029] The bleed air circuit 30 may include an auxiliary bleed air passage 66 fluidly coupled to an auxiliary system 93 of the turbine engine 14. The auxiliary system 93 is defined as any suitable system of the turbine engine 14 capable of utilizing bleed air from at least one of the first LP bleed air passage 46, the second LP bleed air passage 48, or the HP bleed air passage 50. As a non-limiting example, the auxiliary system 93 may be an oil cooling system, a wing anti-icing system, a blade anti-icing system, a nacelle anti-icing system, or a combination thereof.

[0030] At least a portion of the bleed air circuit 30, ATS 10, and AGB 12 are disposed outside the engine housing 17. As a non-limiting example, the bleed air circuit 30 (except for the first LP bleed air passage 46, the second LP bleed air passage 48, and the HP bleed air passage 50), ATS 10, and AGB 12 are all disposed outside the engine housing 17.

[0031] The bleed air circuit 30 is selectively fluidly connected to the first LP bleed air passage 46 and the second LP bleed air passage 48 via a first valve 86. The first valve 86 may include any suitable valve. As a non-limiting example, the first valve 86 may be a switching valve or a shut-off valve that selectively opens and closes to supply or stop bleed air from the first LP bleed air passage 46 and the second LP bleed air passage 48 accordingly. The first LP bleed air passage 46 and the second LP bleed air passage 48 mix at point 52 upstream of the first valve 86 or within the first valve 86, such that the first valve 86 may be a mixing valve. It will be understood that by placing corresponding valves upstream of the mixing point of the first LP bleed air passage 46 and the second LP bleed air passage 48, the first LP bleed air passage 46 and the second LP bleed air passage 48 can supply bleed air to the bleed air circuit 30 independently of each other.

[0032] The bleed air circuit 30 is selectively fluidly connected to the HP bleed air passage 50 via a second valve 88. The second valve 88 may include any suitable valve. As a non-limiting example, the second valve 88 may be a switching valve or a shut-off valve that selectively opens and closes to supply bleed air from the HP bleed air passage 50 to the bleed air circuit 30 or to stop bleed air from the HP bleed air passage 50 from flowing into the bleed air circuit 30.

[0033] The bleed air circuit 30 includes a third valve 96 disposed along the first bleed air passage 54. The third valve 96 may include any suitable valve. As a non-limiting example, the third valve 96 may include a check valve disposed along the junction between the first bleed air passage 54 and the second bleed air passage 56, preventing backflow from the second bleed air passage 56 or the bypass passage 60 to the first bleed air passage 54. As a non-limiting example, the third valve 96 may include a diverter valve that diverts all fluid below a certain volumetric flow rate to the second bleed air passage 56 and diverts all fluid above a certain volumetric flow rate to the bypass passage 60. The diverter valve may be used in cases where the ATS 10 has a specific maximum acceptable volumetric flow rate. In this case, the diverter valve may be sized to ensure that the volumetric flow rate of the fluid within the second bleed air passage 56 and supplied to the ATS 10 does not exceed the maximum volumetric flow rate of the ATS 10. As a non-limiting example, the ATS 10 may have a maximum volumetric flow rate of approximately 5 cubic meters per second. In such an example, during operation, if approximately 6 cubic meters per second of bleed air is supplied through the first bleed air passage 54, the third valve 96 transfers approximately 5 cubic meters per second of bleed air to the ATS 10 through the second bleed air passage 56, and the third valve 96 supplies the remaining approximately 1 cubic meter per second of bleed air through the bypass passage 60. The third valve 96 may be located at the junction of the first bleed air passage 54, the second bleed air passage 56, and the bypass passage 60.

[0034] The bleed air circuit 30 includes a fourth valve 90 disposed along the second bleed air passage 56. The fourth valve 90 fluidly connects the second bleed air passage 56 to the ATS 10. The fourth valve 90 may include any suitable valve. As a non-limiting example, the fourth valve 90 may include one or more of a check valve or a needle valve for controlling the volumetric flow rate of fluid supplied to the ATS 10 within the second bleed air passage 56.

[0035] The bleed air circuit 30 may include a fifth valve 92 disposed along the third bleed air passage 58. The fifth valve 92 fluidly connects the third bleed air passage 58 to the bleed air inlet line 62. The fifth valve 92 may include any suitable valve. As a non-limiting example, the fifth valve 92 may include a check valve to prevent backflow into the ATS 10.

[0036] The bleed air circuit 30 may include a sixth valve 98 disposed along the bleed air inlet line 62. The sixth valve 98 fluidly connects the bleed air inlet line 62 to the PCE 70 or additionally to an external system 74. The sixth valve 98 may include any suitable valve. As a non-limiting example, the sixth valve 98 may include a switch valve or a shut-off valve.

[0037] The bleed air circuit 30 may include a seventh valve 99 disposed along the auxiliary bleed air passage 66. The seventh valve 99 fluidly connects the first bleed air passage 54 to the auxiliary bleed air passage 66. The seventh valve 99 may include any suitable valve. As a non-limiting example, the seventh valve 99 may include a needle valve for controlling the volumetric flow rate of fluid supplied to the auxiliary system 93 within the auxiliary bleed air passage 66.

[0038] It will be understood that valves in the bleed air circuit 30 may be altered, moved, or removed as needed, and one or more of the valves may include valve combinations. The turbine engine 14 may include any other suitable valves, such as, but not limited to, an eighth valve 101 disposed along the cooling fluid inlet 72. The eighth valve 101 fluidly connects the cooling fluid within the cooling fluid inlet 72 to the PCE 70. As a non-limiting example, the bleed air circuit 30 may include an orifice plate 100 along a bypass passage 60. The orifice plate 100 may be used to create a pressure drop along the bypass passage 60 to ensure that the fluid within the bypass passage 60 is at a desired pressure before being supplied to the PCE 70, the external system 74, the manifold 84, or combinations thereof. Although shown as an orifice plate 100, it will be understood that the bypass passage 60 or any other passage of the bleed air circuit 30 may include any suitable component configured to create a pressure drop along the respective passage, such as, but not limited to, the orifice plate 100, a valve, an injector, an orifice, or a combination thereof.

[0039] The ATS 10 can be selectively fluidly connected to an external starting system 102, which is configured to supply airflow to the ATS 10 independently of the bleed air circuit 30. The external starting system 102 may include, for example, a ground cart 104. The external starting system 102 can be selectively fluidly connected to the ATS 10 via a starter inlet line 68. The starter inlet line 68 may include a starter air valve 97, which may include any suitable valve, such as, but not limited to, a switching valve. Although described with respect to the ground cart 104, it will be understood that the external starting system 102 may include an air source.

[0040] It will be understood that, relative to the illustrated configuration, components of the bleed air circuit 30 or the turbine engine 14 may be moved, replaced, or removed. For example, the PCE 70 may be excluded from the turbine engine 14 or otherwise moved to different locations along the bleed air circuit 30. As a non-limiting example, the bleed air circuit 30 may include additional or different locations of bleed air passages configured to draw bleed air from the turbine engine 14, including but not limited to fan section 16, compressor section 18, turbine section 22, exhaust section 26, or combinations thereof.

[0041] Controller 106 (e.g., an electronic controller) can be used to selectively and operably control certain parts of the turbine engine 14. As a non-limiting example, controller 106 can be used to selectively and operably control a first valve 86, a second valve 88, a third valve 96, a fourth valve 90, a fifth valve 92, a sixth valve 98, a seventh valve 99, an eighth valve 101, a separator 80, a starter air valve 97, any other valve, or any combination thereof. Controller 106 may include a processor 108 and a memory 110, and is communicatively coupled to a corresponding part of the bleed air circuit 30 or the turbine engine 14. Memory 110 may be defined as memory for controlling or monitoring various aspects of the bleed air circuit 30 or the turbine engine 14. For example, memory 110 may store codes, executable instructions, commands, commands, authorization keys, private data keys, passwords, etc. Memory 110 may be RAM, ROM, flash memory, or one or more different types of portable electronic memory, such as optical discs, DVDs, CD-ROMs, etc., or any suitable combination of these types of memory. Processor 108 may be defined as part of controller 106, which can receive inputs, perform calculations, and output executable data. Processor 108 may include a microprocessor. Although described with respect to controller 106, it will be understood that controller 106 may be a control system comprising multiple separate controllers coupled to corresponding parts of turbine engine 14. The control system may collectively define a system for automatically controlling the operation of turbine engine 14 and bleed air circuit 30.

[0042] During operation of the turbine engine 14, a free-flowing airflow flows against the front of the turbine engine 14. A portion of the free-flowing airflow enters the fan section 16 to define the inlet airflow. A portion of the inlet airflow enters the engine core 15 to define the working airflow, which is used for combustion within the engine core 15.

[0043] More specifically, the working airflow flows into the LP compressor 34, which then pressurizes the working airflow, thus defining a pressurized airflow. This pressurized airflow is supplied to the HP compressor 36, which further pressurizes the air. The working airflow or pressurized airflow from the HP compressor 36 mixes with fuel in the combustor 38 and is ignited, producing combustion gases. The high-pressure turbine 40 extracts some work from these gases and drives the HP compressor 36 via the engine drive shaft 44. The combustion gases are discharged into the LP turbine 42, which extracts additional work to drive the LP compressor 34, and the working airflow or exhaust gas is finally discharged from the turbine engine 14 via the exhaust section 26. The drive of the LP turbine 42 drives the engine drive shaft 44 to rotate the fan section 16 and the LP compressor 34.

[0044] Imagine drawing a portion of the working gas flow as bleed air (e.g., from compressor section 18). Bleed air provides airflow for engine components that require cooling or heating. The temperature of the working gas flow leaving combustion section 20 is significantly higher than that of the working gas flow within compressor section 18. Therefore, the cooling provided by the bleed air is necessary for operating such engine components in high-temperature environments or in the hot sections of the non-bypass turbine engine 14.

[0045] During operation, bleed air from the cold section (e.g., compressor section 18 or fan section 16) may be selectively drawn into the bleed air circuit 30 via, for example, a first LP bleed air passage 46, a second LP bleed air passage 48, and an HP bleed air passage 50. Since the bleed air circuit 30 may include at least three bleed air passages (e.g., a first LP bleed air passage 46, a second LP bleed air passage 48, and an HP bleed air passage 50), bleed air from at least one location within the turbine engine 14 may be supplied to the bleed air circuit 30. As a non-limiting example, bleed air from only a first portion of the LP compressor 34 (e.g., from the first LP bleed air passage 46), only a second portion of the LP compressor 34 (e.g., from the second LP bleed air passage 48), only the HP compressor 36, or combinations thereof, may be supplied to the bleed air circuit 30. Fluid supplied to the bleed air circuit 30 via at least one of the first LP bleed air passage 46, the second LP bleed air passage 48, the HP bleed air passage 50, or any other bleed air passage directly fluidly connected to the turbine engine 14 will hereinafter be referred to as circuit bleed air.

[0046] Recirculated bleed air from at least one of the first LP bleed air passage 46, the second LP bleed air passage 48, the HP bleed air passage 50, or any other bleed air passage directly fluidly connected to the turbine engine 14 is then supplied to the first bleed air passage 54. Depending on the operation of the third valve 96, the fourth valve 90, and the seventh valve 99, the recirculated bleed air in the first bleed air passage 54 can then be supplied to at least one of the second bleed air passage 56, the bypass passage 60, or the auxiliary bleed air passage 66. As a non-limiting example, if it is determined that the operation of the auxiliary system 93 is desirable for the operation of the turbine engine 14 or for other reasons (e.g., wing anti-icing of the aircraft to which the turbine engine is coupled), the seventh valve 99 can be selectively opened by the controller 106 such that at least a portion of the recirculated bleed air is supplied to the auxiliary system 93.

[0047] Bleed air can be selectively supplied to ATS 10 via a second bleed air passage 56. The bleed air supplied to ATS 10 drives ATS turbine 114, which in turn drives ATS output shaft 76. ATS output shaft 76 can be coupled to, or selectively coupled to (e.g., via a clutch, not shown) AGB 12, such that ATS output shaft 76 can drive AGB 12. Driven AGB 12, in turn, drives AGB drive shaft 78, which ultimately drives engine drive shaft 44. Therefore, it will be understood that supplying bleed air to ATS 10 can be used to drive engine drive shaft 44.

[0048] By supplying bleed air to the ATS 10 to drive the engine drive shaft 44, it can be used to enhance at least one of the rotational speed or torque of the engine drive shaft 44. In other words, during normal operation of the turbine engine 14, the engine drive shaft 44 can be driven by the turbine section 22. The ATS 10 can be used to recover energy from the bleed air to enhance the drive of the engine drive shaft 44, such that during operation of the turbine engine 14, the engine drive shaft 44 is partially driven by the turbine section 22 and the ATS 10. It is contemplated that bleed air can be supplied or selectively supplied to the ATS 10 to enhance the drive of the engine drive shaft 44. As a non-limiting example, if at least one of the sensed torque or rotational speed of the engine drive shaft 44 is lower than the desired torque or rotational speed of the engine drive shaft 44, bleed air can be selectively supplied to the ATS 10 to ultimately increase at least one of the torque or rotational speed of the engine drive shaft 44, for example, to the desired torque or rotational speed. It is contemplated that the ATS 10 can also be used as a brake for the engine drive shaft 44. As a non-limiting example, ATS 10 can rotate ATS output shaft 76 or otherwise rotate AGB drive shaft 78 in a manner opposite to the rotation of engine drive shaft 44. Therefore, ATS 10 can be used to counteract or otherwise slow down the rotation of engine drive shaft 44.

[0049] The drive of the engine drive shaft 44 via the ATS 10 can also be used during one or both of the start-up and restart of the turbine engine 14. During start-up, air can be supplied to the ATS 10 via the bleed air circuit 30 or the external start system 102 to drive the engine drive shaft 44 to begin drawing in air through the fan section 16 to initiate the process of compressing and burning the working airflow. During restart (e.g., when the turbine engine 14 has previously started but has stopped operating), the engine drive shaft 44 may begin to decelerate, reducing its rotational speed, but still drawing in air to define the working airflow and bleed air. Bleed air can be supplied to the ATS 10 via the bleed air circuit 30. The ATS 10 can then increase the rotational speed of the engine drive shaft 44 so that the turbine engine 14 can continue to draw in the working airflow and subsequently attempt to restart the turbine engine 14 by burning the compressed airflow.

[0050] The bleed air supplied to ATS 10 can then expand as it flows through ATS turbine 114. This expansion of the bleed air results in a decrease in the pressure and temperature of the bleed air. The third bleed air passage 58 defines the fluid outlet of ATS 10. Therefore, the pressure and temperature of the bleed air supplied to ATS 10 (through the second bleed air passage 56) are higher than the pressure and temperature of the bleed air supplied from ATS 10 (through the third bleed air passage 58).

[0051] Subsequently, the bleed gas in the third bleed passage 58 can be selectively supplied to the PCE 70 to at least partially define the bleed gas inlet line 62 of the PCE 70. At least a portion of the bleed gas can bypass the ATS 10 by being supplied to the PCE 70 via the bypass passage 60. The amount of bleed gas supplied via the bypass passage 60 can depend on at least one of the volumetric flow rate of the bleed gas in the first bleed passage 54 or the required pressure of the bleed gas supplied to the PCE 70 or the external system 74. As a non-limiting example, if the bleed gas in the third bleed passage 58 is at a lower pressure than the desired pressure of the bleed gas supplied to the external system 74, the bypass passage 60 can supply bleed gas from the first bleed passage 54 (at a higher pressure and temperature than the bleed gas in the third bleed passage 58) and mix it with the bleed gas from the third bleed passage 58 at the confluence 84. This, in turn, increases the temperature and pressure of the bleed gas supplied to the PCE 70 or the external system 74 relative to the bleed gas in the third bleed passage 58.

[0052] Cooling of the bleed air by the PCE 70 can be reduced or eliminated when the bleed air is cooled by flowing through the ATS 10. In other words, the PCE 70 does not need to cool the bleed air as much as if it were not first cooled by flowing through the ATS 10. Pre-cooling the bleed air before supplying it to the PCE 70 reduces the required size of the PCE 70 and the amount of cooling fluid supplied to the PCE 70 via the cooling fluid inlet 72. The amount of bleed air supplied through the ATS 10 can be cooled sufficiently so that the bleed air in the third bleed air passage 58 is at a sufficiently low temperature that it does not need further cooling by the PCE 70 before being supplied to the external system 74. This, in turn, means that the PCE 70 can be eliminated or otherwise bypassed entirely. The amount of cooling fluid supplied to the PCE 70 can be reduced, which means that less air needs to be vented from the turbine engine 14 or otherwise drawn from other locations of the turbine engine 14 (e.g., via RAM air configuration) to form the cooling fluid. This, in turn, means more air is available for compression and combustion, thereby increasing the speed and torque of the engine drive shaft 44. The bleed air in the bleed air circuit 30 can ultimately be supplied to the external system 74, where it is used to operate the external system 74.

[0053] The operation of ATS 10 can be automated by using controller 106. As a non-limiting example, controller 106 can operate ATS 10 by supplying bleed air to the ATS 10 circuit to enhance the power of engine drive shaft 44 based on measured torque or speed of engine drive shaft 44 and the desired output of turbine engine 14. As a non-limiting example, controller 106 may include, in memory 110 or otherwise within memory accessible to controller 106, the functionality of using ATS 10 to enhance the power of engine drive shaft 44 during normal operation of turbine engine 14. In other words, turbine engine 14 can be operated in such a way that ATS 10 is expected to be used during normal operation of turbine engine 14. Therefore, ATS 10 can be used to enhance the power of engine drive shaft 44 even if turbine engine 14 is capable of producing the desired output without using ATS 10. This, in turn, allows the turbine engine 14 to operate more efficiently, as it can extract additional work from the bleed air to enhance the power of the engine drive shaft 44, thereby reducing the amount of gaseous fuel required to produce the combustion gases needed to drive the engine drive shaft 44.

[0054] Benefits associated with this disclosure include higher efficiency of the turbine engine compared to conventional turbine engines. For example, a conventional turbine engine may include a bleed air circuit that supplies bleed air to an external system. However, no work is extracted from this bleed air to drive the engine drive shaft. However, the turbine engine described herein includes a bleed air circuit with an automatic power supply (ATS) that extracts work from the bleed air before it is supplied to the external system. This extracted work is then used to enhance the drive of the engine drive shaft. In other words, extracting work from the bleed air improves the efficiency of the turbine engine compared to a conventional turbine engine.

[0055] Other advantages of this disclosure include reduced footprint or elimination of the PCE. For example, conventional turbine engines, including bleed air circuits for supplying bleed air to external systems, require a PCE to cool the bleed air to the temperature required by the external systems. However, bleed air circuits as described herein can pre-cool the bleed air using an ATS. Compared to conventional bleed air circuits, pre-cooling the bleed air can instead reduce the size of the PCE or otherwise eliminate the need for a PCE entirely.

[0056] An additional advantage of this disclosure compared to conventional turbine engines includes an increased amount of bleed air extracted from the turbine engine. For example, in a conventional turbine engine, the extracted bleed air is not used to enhance the power of the engine drive shaft. If too much bleed air is extracted from the turbine engine, insufficient combustion gases will be produced, or the combustion gases will not reach the required pressure. This, in turn, can lead to stall in a conventional turbine engine. However, as described herein, the turbine engine uses bleed air to enhance the power of the engine drive shaft (e.g., via an ATS), which in turn means that more bleed air can be extracted from the turbine engine without the risk of turbine engine stall. Because more bleed air can be extracted from the turbine engine compared to a conventional turbine engine, more bleed air can be supplied to auxiliary or external systems, thereby improving the efficiency of the systems to which the bleed air is supplied.

[0057] To the extent not yet described, different features and structures of the various aspects can be combined or substituted for each other as desired. The absence of a feature in all examples does not imply that it cannot be shown in this way, but rather that it is done for the sake of brevity. Therefore, various features of different aspects can be mixed and matched to form new aspects as desired, whether or not the new aspects are explicitly described. All combinations or permutations of the features described herein are encompassed within this disclosure.

[0058] This written description uses examples to illustrate the disclosed aspects described herein, including best practices, and also enables those skilled in the art to practice the disclosed aspects, including making and using any apparatus or system and performing any combined methods. The patentable scope of the disclosed aspects is defined by the claims and may include other examples that would occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0059] Other aspects are provided by the subject of the following clauses: A turbocharged engine includes: an engine core comprising a fan section, a compressor section, a combustion section, and a turbine section arranged in series; an engine drive shaft operatively connected to the fan section, compressor section, and turbine section; an accessory gearbox (AGB) operatively connected to the engine drive shaft; an air turbine starter (ATS) having an ATS turbine, an ATS gearbox, an ATS drive shaft operatively connected to the ATS turbine and the ATS gearbox, and an ATS output shaft operatively connected to the ATS gearbox and the AGB; and a bleed air circuit including a first bleed air passage fluidly connected to the compressor section, a second bleed air passage fluidly connected to the ATS, a third bleed air passage fluidly connected to the output of the ATS, and a bypass passage fluidly connected to the third bleed air passage while bypassing the ATS.

[0060] An assembly for a turbine engine includes an accessory gearbox (AGB); an air turbine starter (ATS) having an ATS turbine, an ATS gearbox, an ATS drive shaft operatively connecting the ATS turbine and the ATS gearbox, and an ATS output shaft operatively connecting the ATS gearbox to the AGB; and a bleed air circuit including a first bleed air passage, a second bleed air passage fluidly connected to the first bleed air passage to the ATS, a third bleed air passage fluidly connected to the output of the ATS, and a bypass passage fluidly connected to the third bleed air passage while bypassing the ATS.

[0061] The turbine engine according to any of the foregoing provisions also includes a precooler heat exchanger (PCE) fluidly connected to a system that connects the fan section and the exterior of the turbine engine.

[0062] According to any of the preceding clauses, the third bleed air passage and the bypass passage meet at the confluence upstream of the PCE.

[0063] According to any of the foregoing provisions, the PCE is selectively fluidly connected to at least one of a third bleed air passage or a bypass passage to define the input of the PCE, and fluidly connected to a system external to the turbine engine to define the output of the PCE.

[0064] The turbine engine according to any of the foregoing clauses, wherein the PCE includes a cooling fluid inlet and a cooling fluid outlet, wherein the cooling fluid inlet is fluidly connected to at least one of the fan section or the compressor section.

[0065] The turbine engine according to any of the foregoing clauses, wherein the external systems of the turbine engine include an environmental control system.

[0066] According to any of the foregoing provisions, the turbine engine includes a second bleed air passage and a third bleed air passage, each containing a corresponding working fluid with a corresponding temperature and a corresponding pressure, and the temperature and pressure of the working fluid in the third bleed air passage are lower than those of the working fluid in the second bleed air passage.

[0067] According to any of the preceding clauses, the turbine engine, which drives the ATS by working fluid supplied to the ATS via a second bleed air passage, drives the AGB via the ATS drive shaft.

[0068] The turbine engine according to any of the foregoing clauses, wherein the AGB is driven via the ATS drive shaft during operation of the turbine engine.

[0069] The turbine engine according to any of the foregoing clauses, wherein the ATS is configured to start the turbine engine by driving the ATS output shaft.

[0070] According to any of the foregoing provisions, the turbine engine is wherein the ATS is configured to restart the turbine engine during deceleration and by driving the ATS output shaft.

[0071] According to any of the foregoing provisions, the turbine engine wherein, during the restart of the turbine engine, working fluid in the second bleed air passage is supplied to the ATS.

[0072] The turbine engine according to any of the foregoing provisions, wherein the bleed air circuit includes a low-pressure (LP) bleed air passage and a high-pressure (HP) bleed air passage, wherein the LP bleed air passage is fluidly connected to a portion of the turbine engine upstream of the HP bleed air passage.

[0073] According to any of the foregoing provisions, the turbine engine wherein the LP bleed air passage and the HP bleed air passage are each independently and selectively fluidly connected to the first bleed air passage.

[0074] The turbine engine according to any of the foregoing provisions, wherein the LP bleed air passage includes a first LP bleed air passage and a second LP bleed air passage, wherein the first LP bleed air passage is fluidly connected to a portion of the turbine engine upstream of the second LP bleed air passage.

[0075] According to any of the foregoing provisions, the turbine engine includes a high-pressure (HP) compressor and a low-pressure (LP) compressor, wherein the LP bleed air passage is fluidly connected to the LP compressor and the HP bleed air passage is fluidly connected to the HP compressor.

[0076] The turbine engine according to any of the foregoing provisions further includes a diverter valve defining a junction between a second bleed air passage and a bypass passage. The diverter valve is configured to divert the working fluid in the first bleed air passage between ATS fluid supplied to the ATS through the second bleed air passage and bypass fluid supplied to the bypass passage, such that all working fluid is directed to the ATS until the ATS fluid meets a threshold volumetric flow rate, and any excess working fluid exceeding the threshold volumetric flow rate is then directed to the bypass passage.

[0077] The turbine engine according to any of the foregoing clauses, wherein the bleed air circuit further includes an auxiliary system bleed air passage that fluidly connects at least one of the LP bleed air passage or HP bleed air passage to the auxiliary system.

[0078] The turbine engine according to any of the foregoing provisions further includes a controller configured to automatically and selectively supply working fluid in the first bleed air passage to at least one of the ATS or bypass passage based on at least one of the rotational speed or torque of the engine drive shaft or the requirements of external systems of the turbine engine.

[0079] The turbine engine according to any of the foregoing provisions also includes an engine housing that houses the engine core, wherein the ATS is disposed outside the engine housing.

[0080] The turbine engine according to any of the foregoing provisions also includes a first valve disposed along the low-pressure bleed air passage.

[0081] According to any of the foregoing provisions, the turbine engine wherein the first valve selectively fluidly connects bleed air from the turbine engine to the first bleed air passage via the LP bleed air passage.

[0082] According to any of the foregoing provisions, in the turbine engine, the first valve is located downstream of the junction of the first LP bleed air passage and the second LP bleed air passage.

[0083] The turbine engine according to any of the foregoing clauses, wherein the first valve is a mixing valve for the first LP bleed air passage and the second LP bleed air passage.

[0084] The turbine engine according to any of the foregoing provisions also includes a second valve disposed along the HP bleed air passage.

[0085] According to any of the foregoing provisions, the turbine engine wherein the second valve selectively fluidly connects bleed air from the turbine engine to the first bleed air passage via the HP bleed air passage.

[0086] The turbine engine according to any of the foregoing provisions further includes a third valve disposed along the first bleed air passage.

[0087] According to any of the preceding clauses, in a turbine engine, a third valve selectively fluidly connects bleed air from a first bleed air passage to at least one of a second bleed air passage or a bypass passage.

[0088] In any of the preceding clauses of the turbine engine, the third valve is located at the junction between the second bleed air passage and the bypass passage.

[0089] The turbine engine according to any of the foregoing provisions also includes a fourth valve disposed along the second bleed air passage.

[0090] According to any of the preceding clauses, the turbine engine wherein the fourth valve selectively fluidly connects the bleed air from the first bleed air passage to the ATS.

[0091] The turbine engine according to any of the foregoing provisions also includes a fifth valve disposed along the third bleed air passage.

[0092] According to any of the foregoing provisions, the fifth valve selectively connects the circuit bleed air from the ATS to the PCE or an external system.

[0093] The turbine engine according to any of the foregoing provisions also includes a sixth valve that selectively fluidly connects at least one of the bypass passage or the third bleed air passage to the PCE or an external system.

[0094] The turbine engine according to any of the foregoing provisions also includes a seventh valve disposed along the auxiliary bleed air passage.

[0095] According to any of the preceding clauses, in a turbine engine, a seventh valve selectively fluidly connects bleed air from a first bleed air passage to an auxiliary system.

[0096] The turbine engine according to any of the foregoing provisions also includes an orifice plate disposed along the bypass passage.

[0097] A method of operating a turbine engine according to any of the foregoing provisions, the method comprising supplying bleed air from the turbine engine to an ATS.

[0098] The method according to any of the foregoing clauses further includes driving the ATS output shaft by bleed air supplied to the ATS.

[0099] The method according to any of the foregoing clauses further includes driving the engine drive shaft at least in part via the ATS output shaft.

[0100] The method according to any of the foregoing clauses further includes driving the engine drive shaft at least partially via the ATS output shaft during operation of the turbine engine.

[0101] The method according to any of the foregoing provisions further includes supplying bleed air from the turbine engine from a first position and a second position other than the first position and supplying the bleed air to the ATS.

[0102] The method according to any of the foregoing provisions further includes supplying bleed air from the turbine engine from a first position, a second position different from the first position, and a third position different from the first and second positions, and supplying the bleed air to the ATS.

Claims

1. A turbine engine, comprising: The engine core comprises a fan section, a compressor section, a combustion section, and a turbine section arranged in series. An engine drive shaft operatively connects the fan section, the compressor section, and the turbine section; Accessory gearbox (AGB) operatively coupled to the engine drive shaft; An air turbine starter (ATS) having an ATS turbine, an ATS gearbox, an ATS drive shaft operably connecting the ATS turbine and the ATS gearbox, and an ATS output shaft operably connecting the ATS gearbox to the AGB, the ATS being configured to be used during the start-up of the turbine engine to drive the engine drive shaft. as well as The bleed air circuit includes: A first bleed air passage is fluidly connected to the compressor section; A second bleed air passage fluidly connects the first bleed air passage to the ATS turbine; A third air intake channel, fluidly connected to the output of the ATS; and A bypass channel, which is fluidly connected to the third bleed channel, while bypassing the ATS.

2. The turbine engine according to claim 1, wherein, The ATS is rotatably coupled to the engine drive shaft and configured to supply torque to the engine drive shaft.

3. The turbine engine of claim 1 further includes a precooler heat exchanger (PCE) fluidly connected to a system external to the fan section and the turbine engine.

4. The turbine engine according to claim 3, wherein, The third bleed air channel and the bypass channel meet at the confluence upstream of the PCE.

5. The turbine engine according to claim 4, wherein, The PCE includes a cooling fluid input and a cooling fluid output, wherein the cooling fluid input is fluidly connected to at least one of the fan section or the compressor section.

6. The turbine engine according to claim 3, wherein, The external systems of the turbine engine include an environmental control system.

7. The turbine engine according to claim 1, wherein: The second and third air intake channels each include a corresponding working fluid with a corresponding temperature and pressure; and The temperature and pressure of the working fluid in the third air intake channel are lower than those of the working fluid in the second air intake channel.

8. The turbine engine according to claim 1, wherein, The ATS is driven by the working fluid supplied to the ATS via the second bleed air channel, which in turn drives the AGB via the ATS drive shaft.

9. The turbine engine according to claim 8, wherein, The AGB is driven via the ATS drive shaft during operation of the turbine engine.

10. An assembly for a turbine engine having an engine drive shaft, the assembly comprising: Accessory gearbox (AGB) operatively coupled to the engine drive shaft; An air turbine starter (ATS) having an ATS turbine, an ATS gearbox, an ATS drive shaft operably connecting the ATS turbine and the ATS gearbox, and an ATS output shaft operably connecting the ATS gearbox to the AGB, the ATS being configured to be used during the start-up of the turbine engine to drive the engine drive shaft. as well as The bleed air circuit includes: A first bleed air passage, which is fluidly connected to the turbine engine; A second bleed air passage fluidly connects the first bleed air passage to the ATS turbine; A third air intake channel, fluidly connected to the output of the ATS; and A bypass channel, which is fluidly connected to the third bleed channel, while bypassing the ATS.

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