Gas turbine engine bleed flow control

Abstract

An engine includes a compressor including an inner shell and an outer shell, where the inner shell defines a primary flow path for a primary airflow through the compressor. The inner shell and the outer shell define an air bleed cavity therebetween. The inner shell at least partially defines a bleed channel extending circumferentially about the inner shell to direct a bleed flow from the primary flow into the bleed cavity. One or more flow control devices are positioned circumferentially about the compressor to actively or passively circumferentially balance the flow of the bleed airflow into or within the bleed cavity, where the one or more flow control devices are at least partially disposed within the bleed channel, forming at least a portion of the bleed channel, or extending axially rearward from the bleed channel.

Description

Technical Field

[0001] This disclosure relates to gas turbine engines, and more specifically, to bleed air flow control. Background Technology

[0002] Gas turbine engines (such as turbofan engines) are used for aircraft propulsion. A turbofan engine typically consists of a fan and a gas turbine engine or core engine that drives the fan. A gas turbine engine comprises a compressor section, a combustor, and a turbine section arranged in a series flow configuration. Some gas turbine engines extract high-pressure air from the compressor section, called "bleed air." This bleed air can be used to pressurize the aircraft's cabin, provide cooling for one or more parts of the engine, and / or power one or more systems of the aircraft. Attached Figure Description

[0003] The complete and feasible disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0004] Figure 1 This is a perspective view of an exemplary aircraft based on exemplary aspects of this disclosure.

[0005] Figure 2 This is a cross-sectional view of an exemplary gas turbine engine according to an exemplary aspect of this disclosure.

[0006] Figure 3 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0007] Figure 4 This is a plan view of an exemplary flow control device according to an exemplary aspect of this disclosure.

[0008] Figure 5 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0009] Figure 6 This is a plan view of an exemplary flow control device according to an exemplary aspect of this disclosure.

[0010] Figure 7 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0011] Figure 8 This is a plan view of an exemplary flow control device according to an exemplary aspect of this disclosure.

[0012] Figure 9 This is a plan view of an exemplary flow control device according to an exemplary aspect of this disclosure.

[0013] Figure 10 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0014] Figure 11 This is a plan view of an exemplary flow control device according to an exemplary aspect of this disclosure.

[0015] Figure 12 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0016] Figure 13 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0017] Figure 14 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0018] Figure 15 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0019] Figure 16 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0020] Figure 17 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0021] Figure 18 This is a plan view of an exemplary flow control device according to an exemplary aspect of this disclosure.

[0022] Figure 19 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0023] Figure 20It is according to the exemplary aspects of this disclosure along Figure 19 A plan view of an exemplary flow control device, taken from line 20-20.

[0024] Figure 21 Based on exemplary aspects of this disclosure, such as Figure 2 An enlarged cross-sectional view of a portion of the high-pressure compressor of the gas turbine engine shown.

[0025] Figure 22 This is a block diagram depicting an example computing system according to exemplary embodiments of the present disclosure.

[0026] Reference numerals used repeatedly in this specification and drawings are intended to indicate the same or similar features or elements of this disclosure. Detailed Implementation

[0027] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0028] The term “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as superior or better than other implementations. Furthermore, all embodiments described herein should be considered exemplary unless explicitly stated otherwise. Unless the context clearly specifies otherwise, the singular forms “a,” “an,” and “the” include plural references. The term “at least one” in the context of, for example, “at least one of A, B, and C” means only A, only B, only C, or any combination of A, B, and C.

[0029] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of individual components. Furthermore, the terms “upstream” and “downstream” refer to the relative direction of fluid flow in a fluid path. For example, “upstream” refers to the direction from which fluid flows, and “downstream” refers to the direction towards which fluid flows. The terms “forward” and “rear” refer to relative positions within the gas turbine engine or vehicle and are based on the normal operating attitude of the gas turbine engine or vehicle. More specifically, “forward” and “rear” are used herein with reference to the direction of travel of the vehicle and the propulsion thrust direction of the gas turbine engine.

[0030] The term "turbine" refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines that together generate torque output. The term "gas turbine engine" refers to an engine that has a turbine as all or part of its power source. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid electric versions of one or more of these engines.

[0031] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term combustion section can refer to a section that includes one or more of a knock combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assembly. In some example embodiments, the combustion section may include an annular burner, a can burner, a tubular burner, a vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0032] When used with compressors, turbines, shafts, or spools, unless otherwise specified, the terms “low” and “high,” or their respective comparatives (e.g., “lower” and “higher,” where applicable), refer to relative speeds within the engine. For example, “low-speed turbine” or “low-turbine” defines a component constructed to operate at a rotational speed (e.g., the maximum permissible rotational speed) lower than that of the engine’s “high-speed turbine” or “high-speed turbine.”

[0033] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the gas turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the gas turbine engine.

[0034] As used herein throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “approximately,” “approximately,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 10%, 15%, or 20%. These approximate margins may be applied to a single value, defining any one or both endpoints of a numerical range, and / or the margin of the range between the endpoints.

[0035] Unless otherwise stated herein, the terms “connection,” “fixed,” “attached to,” etc., refer to both direct connection, fixation, or attachment, and indirect connection, fixation, or attachment via one or more intermediate components or features.

[0036] The term "closer" refers to being closer to one end than to the other end. For example, when used in conjunction with the first end and the second end; the high-pressure side and the low-pressure side; etc., the phrase "closer to the first end" or "closer to the high-pressure side" respectively refers to a position closer to the first end than the second end, or a position closer to the high-pressure side than the low-pressure side.

[0037] As used herein, the term "cruise speed" refers to the operation of a turbine engine that powers an aircraft to operate at a cruise speed after the aircraft has climbed to a specified altitude and is level. The turbine engine can operate at a cruise speed of 50% to 90% of its rated speed (e.g., 70% to 80% of its rated speed). In some embodiments, the cruise speed can be achieved at about 80% of full throttle (e.g., about 50% to about 90% of full throttle, or about 70% to about 80% of full throttle). As used herein, the term "cruise phase" refers to a flight phase in which the aircraft is at a level altitude following the climb phase and preceding the descent to the approach phase. In various examples, cruise flight can be conducted at a cruise altitude of up to about 65,000 ft. In some examples, the cruise altitude is between about 28,000 ft and about 45,000 ft. In other examples, the cruise altitude is expressed in flight altitude (FL) based on sea-level standard atmospheric pressure, where cruise flight is between FL280 and FL650. In another example, cruise flight occurs between FL280 and FL450. In still other examples, cruise altitude is defined at least based on atmospheric pressure, with cruise altitudes ranging from approximately 4.85 psia to approximately 0.82 psia based on a sea-level pressure of approximately 14.70 psia and a sea-level temperature of approximately 59 degrees Fahrenheit. In yet another example, cruise altitudes range from approximately 4.85 psia to approximately 2.14 psia. It should be understood that in some examples, the range of pressure-defined cruise altitudes may be adjusted based on different reference sea-level pressures and / or sea-level temperatures.

[0038] This disclosure generally relates to bleed air extraction flow control for a high-pressure compressor in a gas turbine engine. A gas turbine engine typically includes a compressor section, a combustion section, and a turbine section arranged in a sequential flow order. The compressor section includes a low-pressure compressor and a high-pressure compressor. The compressor section includes a compressor housing that surrounds a sequential arrangement of stator and rotor blades of the low-pressure and high-pressure compressors. During operation, bleed air is extracted from the compressor at one or more locations and directed via corresponding bleed air channels into one or more corresponding bleed air chambers or cavities. The bleed air is then distributed from the bleed air chambers via various pipes or tubes to cool turbine components and / or servic / support various aircraft systems, including but not limited to cabin air pressurization systems, air conditioning, fuel tank pressurization, thrust reversing systems, fuel heating, anti-icing systems, etc.

[0039] The air discharged from the compressor flow path to the offtake cavity is circumferentially balanced to ensure that the bleed does not circumferentially deform around the main air flow path through the compressor. Circumferentially unbalanced bleed (caused by a low number of ducts, asymmetrical port locations, or unbalanced port sizes) circumferentially distorts the airflow in the compressor flow path, adversely affecting compressor operability. The need to keep compressor deformation within limits drives mechanical decisions such as the number of bleed ports and ducts, their circumferential location, housing radius, and flow dimensions (including variable areas such as scrolls).

[0040] Embodiments of this disclosure include features, either in conjunction with or independent of external features, such as bleed channels or bleed chambers, or both, to achieve an asymmetric bleed port geometry while keeping compressor deformation within limits. In exemplary embodiments, various types of passive and / or active flow control devices (such as, as a non-limiting example, one or more baffles with circumferentially varying features) are used to manage compressor deformation using asymmetric bleed. Embodiments of this disclosure enable asymmetric bleed port geometries that prevent or reduce the need for increased bleed chamber area or exhaust vortex for managing compressor deformation. Embodiments of this disclosure include flow control devices for managing compressor deformation, which can also be adjusted and / or modified after installation, thereby allowing improvements in compressor deformation and compressor operability on a single gas turbine engine basis. Embodiments of this disclosure manage deformation by altering the limitation and / or pressure loss around the circumference of the bleed outlet, and / or by adjusting the diffusion and / or recovery pressure downstream of the compressor's circumference. Embodiments of this disclosure include using orifices connected to other cavities (such as adjacent vent chambers or lower covers) to manage pressure in the bleed air chamber. The flow control device of this disclosure can be actuated and / or actively altered, and / or can passively alter the bleed airflow using material properties (e.g., thermal expansion). Therefore, embodiments of this disclosure circumferentially balance the air discharged from the compressor flow path. In other words, the flow control device of this disclosure maintains a uniform airflow rate around the circumference of the compressor housing.

[0041] Now refer to the attached diagram, Figure 1 This is a perspective view of an exemplary aircraft 10 that can be incorporated into at least one exemplary embodiment of this disclosure. (See also...) Figure 1 As shown, the aircraft 10 has a fuselage 12, wings 14 attached to the fuselage 12, and a tail 16. The aircraft 10 also includes a propulsion system 18 that generates thrust to propel the aircraft 10 during flight, taxiing operations, etc. Although the propulsion system 18 is shown attached to the wing 14, in other embodiments, it may additionally or alternatively include one or more aspects coupled to other components of the aircraft 10 (e.g., tail 16, fuselage 12, or both). The propulsion system 18 includes at least one engine. In the exemplary embodiment shown, the aircraft 10 includes a pair of engines 20. Each engine 20 is mounted to the aircraft 10 in an underwing configuration. Each engine 20 is capable of selectively generating thrust for the aircraft 10. The engines 20 may be configured to burn various forms of fuel, including but not limited to jet fuel / aviation turbine fuel and hydrogen fuel, unless otherwise specified.

[0042] Figure 2This is a cross-sectional side view of an engine 20 according to an exemplary embodiment of the present disclosure. In the exemplary embodiment, the engine 20 may be a gas turbine engine. More specifically, for Figure 2 In one embodiment, engine 20 is a multi-axis high-bypass turbofan jet engine, sometimes also referred to as a "turbofan engine." For example... Figure 2 As shown, engine 20 defines an axial direction A (extending parallel to the longitudinal centerline 22 provided for reference), a radial direction R, and a circumferential direction C extending about the longitudinal centerline 22. Generally, engine 20 includes a fan section 24 and a turbine 26 disposed downstream of the fan section 24.

[0043] The depicted exemplary turbine 26 generally includes a casing 28 defining an annular core inlet 30. The casing 28 at least partially surrounds, in a series flow relationship: an axial compressor section including a turbocharger or low-pressure (LP) compressor 32 and a high-pressure (HP) compressor 34; a combustion section 36; a turbine section including a high-pressure (HP) turbine 38 and a low-pressure (LP) turbine 40; and an exhaust nozzle 42.

[0044] The high-pressure (HP) shaft 44 drives the HP turbine 38 to the HP compressor 34. The low-pressure (LP) shaft 46 drives the LP turbine 40 to the LP compressor 32. The LP compressor 32, HP compressor 34, combustion section 36, HP turbine 38, LP turbine 40 and exhaust nozzle 42 together define the core airflow path 48 through the engine 20.

[0045] In the described embodiment, fan section 24 includes a fan 50 having a plurality of fan blades 52 spaced apart and coupled to disk 54. As depicted, the fan blades 52 extend generally outward from disk 54 in a radial direction R. Each fan blade 52 is operably coupled to a suitable pitch mechanism 56 by means of the fan blades 52, which is rotatable together with disk 54 about pitch axis P, the pitch mechanism 56 being configured to, for example, uniformly and collectively change the pitch of the fan blades 52.

[0046] Engine 20 also includes a power gearbox 58. Fan blades 52, disk 54, and pitch mechanism 56 can rotate together about longitudinal centerline 22 across the power gearbox 58 via LP shaft 46. The power gearbox 58 includes multiple gears for adjusting the rotational speed of fan 50 relative to LP shaft 46, so that fan 50 and LP shaft 46 can rotate at a more efficient relative speed.

[0047] Still referencing Figure 2In an exemplary embodiment, the disk 54 is covered by a rotatable front hub 60 (sometimes referred to as a "rotor") of the fan section 24. The front hub 60 is aerodynamically shaped to facilitate airflow through a plurality of fan blades 52. Additionally, the exemplary fan section 24 includes an annular fan housing or outer nacelle 62 circumferentially surrounding at least a portion of the fan 50 and / or turbine 26. In the depicted embodiment, the outer nacelle 62 is supported relative to the turbine 26 by a plurality of circumferentially spaced struts or outlet guide vanes 64. Furthermore, a downstream section 66 of the outer nacelle 62 extends over the outer portion of the turbine 26 to define a bypass airflow passage 68 between them.

[0048] However, it should be understood that Figure 2 The exemplary engine 20 depicted is provided by way of example only, and in other exemplary embodiments, engine 20 may have other configurations. Additionally or alternatively, although the depicted engine 20 is configured as a geared gas turbine engine (e.g., including a power gearbox 58) and a variable-pitch gas turbine engine (e.g., including a fan 50 configured as a variable-pitch fan), in other embodiments, engine 20 may be configured as a direct-drive gas turbine engine (such that the LP shaft 46 rotates at the same speed as the fan 50), a fixed-pitch gas turbine engine (such that the fan 50 includes fan blades 52 that are not rotatable about the pitch axis P), or both. It should also be understood that in other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of this disclosure may (as appropriate) be incorporated into, for example, a turboprop gas turbine engine, a turboshaft gas turbine engine, or a turbojet gas turbine engine.

[0049] During engine 20 operation, a certain amount of air 70 enters engine 20 through the external nacelle 62 and the corresponding inlet 72 of the fan section 24. As the air 70 passes through the fan blades 52, a first portion of the air 74 is directed or directed into the bypass airflow passage 68, and a second portion of the air 76 is directed or directed into the core airflow path 48, or more specifically, into the LP compressor 32. The ratio between the first portion of air 74 and the second portion of air 76 is commonly referred to as the bypass ratio.

[0050] As the second portion of air 76 enters the LP compressor 32, one or more sequential stages of the low-pressure (LP) compressor rotor blades 80 and low-pressure (LP) compressor stator blades 78, coupled to the LP shaft 46, progressively compress the second portion of air 76 flowing through the LP compressor 32 toward the HP compressor 34. Next, one or more sequential stages of the high-pressure (HP) compressor rotor blades 84 and high-pressure (HP) compressor stator blades 82, coupled to the HP shaft 44, further compress the second portion of air 76 flowing through the HP compressor 34. This supplies compressed air to the combustion section 36, where it is mixed with fuel and combusted to provide combustion gases 86.

[0051] Combustion gas 86 is directed through HP turbine 38, where a portion of the thermal and / or kinetic energy from the combustion gas 86 is extracted via a sequential stage of high-pressure (HP) turbine stator blades 88 connected to the turbine housing and high-pressure (HP) turbine rotor blades 90 connected to the HP shaft 44, thus rotating the HP shaft 44 to support the operation of HP compressor 34. Combustion gas 86 is then directed through LP turbine 40, where a second portion of the thermal and kinetic energy is extracted from the combustion gas 86 via a sequential stage of low-pressure (LP) turbine stator blades 92 connected to the turbine housing and low-pressure (LP) turbine rotor blades 94 connected to the LP shaft 46, thus rotating the LP shaft 46 to support the operation of LP compressor 32 and / or the rotation of fan 50.

[0052] Combustion gas 86 is then directed through the exhaust nozzle 42 of turbine 26 to provide propulsive thrust. The pressure of the first portion of air 74 is also significantly increased as it is directed through bypass airflow passage 68 before exiting from the fan nozzle exhaust section 96 of engine 20, also providing propulsive thrust. HP turbine 38, LP turbine 40, and exhaust nozzle 42 at least partially define a hot gas path 98 for directing combustion gas 86 through turbine 26.

[0053] Figure 3 Is it like this? Figure 2 An enlarged cross-sectional view of a portion of the HP compressor 34 of the engine 20 shown. Figure 3 As shown, the HP compressor 34 includes a housing 100. The housing 100 may correspond to the outer casing 28. Figure 2 This may be a portion of the housing 28. In a particular example, housing 100 may include multiple housings. In an exemplary embodiment, as shown... Figure 3 As shown, housing 100 includes an inner shell 102 that is radially spaced inward from outer shell 104 relative to the radial direction R. Inner shell 102 and outer shell 104 can be connected together by fasteners (such as bolts).

[0054] The inner casing 102 defines, forms, and / or otherwise surrounds the primary flow path 106 for allowing airflow to flow rearward or downstream over the HP compressor 34 to reach the combustion zone 36. Figure 2 As shown). Figure 3 As shown, the HP compressor stator blades 82 are connected to the inner housing 102 and extend radially inward from the inner housing 102. The HP compressor rotor blades 84 are connected to the HP shaft 44. Figure 2 ) and extends radially outward from the HP shaft 44, and is disposed between successive rows of stator blades 82 of the HP compressor. The HP compressor 34 may include multiple stages that gradually increase toward the combustion section 36 ( Figure 2 The pressure of the air flowing through the HP compressor 34.

[0055] In an exemplary embodiment, the inner housing 102 and the outer housing 104 define one or more openings or slots to extract high-pressure air from the primary flow path 106 of the HP compressor 34. This high-pressure air is referred to as "bleed air" because it is "exhausted" from the HP compressor 34. Bleed air is used for various purposes in the engine 20 and / or the aircraft 10. For example, bleed air can be used to cool or reduce the temperature of the HP and LP turbines. Additionally or alternatively, bleed air can be used to pressurize certain seals in the engine 20, which helps maintain tighter fittings and tolerances. Furthermore, if the engine 20 is used on an aircraft, bleed air can be used to power and / or provide a constant air supply to one or more systems, such as an environmental control system (ECS) (which provides pressurized and temperature-controlled air to the cabin), a wing anti-icing system, and / or an engine anti-icing system.

[0056] In various embodiments, such as Figure 3 As shown, engine 20 includes a bleed air chamber 108 (e.g., air chamber, collection chamber) defined between inner housing 102 and outer housing 104. In an exemplary embodiment, bleed air chamber 108 may also be referred to as a high-pressure (HP) bleed air chamber. During operation, bleed air is drawn from primary flow path 106 and fills bleed air chamber 108. One or more conduits 110 in the form of hoses or fluid lines are fluidly coupled to housing 104 for guiding (e.g., distributing) bleed air from bleed air chamber 108 through offtake 111 of conduit 110 to one or more downstream locations and / or systems 112. For example, downstream locations and / or systems 112 may include HP and / or LP turbines 38, 40 ( Figure 2 (For example, for cooling), one or more systems of the Environmental Control System (ECS) 113 (such as, but not limited to, cabin pressurization system, wing anti-icing system, engine anti-icing system), and / or engine 20 or aircraft 10 ( Figure 1 Any other location and / or system (as shown).

[0057] To supply bleed air to the bleed chamber 108, the inner shell 102 includes an opening 114. The opening 114 may be defined by a slot or hole extending through the inner shell 102 and extending circumferentially around the inner shell 102 relative to the circumferential direction C. In various embodiments, such as Figure 3 As shown, opening 114 defines air intake channel 116, which provides fluid communication between primary flow path 106 and air intake chamber 108. Air intake channel 116 is at least partially defined by upstream wall 120, which is axially spaced from downstream wall 122 relative to axial direction A.

[0058] The bleed air channel 116 is formed, shaped, and / or oriented to guide a portion of the airflow as bleed airflow 118 from the primary flow path 106 into the bleed air chamber 108. During operation of the engine 20, a portion of the airflow (e.g., high-pressure air) in the primary flow path 106 flows through the opening 114 (e.g., as bleed airflow 118), flows through the bleed air channel 116, and fills the bleed air chamber 108. In an exemplary embodiment, the bleed air channel 116 is located in the downstream direction (e.g., in...). Figure 3 The air bleed airflow 118 is angled or tilted (from left to right). This allows the bleed airflow 118 to flow into the bleed air chamber 108 effectively (in a generally downstream direction). In an exemplary embodiment, the bleed air chamber 108 is filled with the bleed airflow 118 by receiving pressurized air from the primary flow path 106 in an upstream stage of the HP compressor 34 (such as, but not limited to, the fourth stage of the HP compressor 34).

[0059] During operation, the flow rate of the bleed air flow 118 entering the bleed air chamber 108 and the pressure within the bleed air chamber 108 depend on the requirements of conditions from downstream locations and / or system 112, and the temperature of the bleed air flow 118 may depend on the operating aspects of the HP compressor 34 or the aircraft 10 ( Figure 1 The flight phase of aircraft 10. For example, during the flight phase of aircraft 10. Figure 1 During the takeoff or climb phase of the compressor, the temperature of the bleed airflow 118 can be higher than that during the cruise phase. Furthermore, the air discharged from the primary flow path 106 as the bleed airflow 118 is circumferentially balanced to ensure that the airflow in the primary flow path 106 does not undergo circumferential deformation. Circumferentially unbalanced bleed (caused by a low number of ducts, asymmetrical bleed port locations, or unbalanced bleed port sizes) circumferentially distorts the airflow in the primary flow path 106, adversely affecting compressor operability. Therefore, the need to keep compressor deformation within limits drives mechanical decisions such as the number of bleed ports and ducts, the circumferential location of the bleed ports and ducts, the housing radius, and flow dimensions (including variable areas, such as vortex tubes). Exemplary embodiments of this disclosure provide passive and / or active flow control for compressor bleed, maintaining allowable compressor deformation while enabling asymmetrical bleed port locations and flow areas.

[0060] In an exemplary embodiment, the engine 20 includes one or more flow control devices 130 at least partially disposed within the bleed air channel 116 and / or bleed air chamber 108 to passively and / or actively control the bleed airflow 118 within and through the bleed air chamber 108. The one or more flow control devices 130 may be located at one or more circumferential positions relative to the inner housing 102 or relative to one or more circumferential positions of the ducts 110. Figure 3 In this embodiment, one or more flow control devices 130 include one or more baffles 132 at least partially disposed within the air intake chamber 108. The one or more baffles 132 may be axially oriented, radially oriented, or a combination of both. The one or more baffles 132 may be crescent-shaped, perforated sheet metal, mesh material, or any other suitable structure for regulating the flow of air intake gas 118 within and through the air intake chamber 108. The one or more baffles 132 may include one or more orifices 134 for allowing the air intake gas 118 to pass from the air intake channel 116 through the one or more baffles 132 to reach one or more conduits 110. The one or more orifices 134 may have different sizes and densities (e.g., the spacing between adjacently positioned orifices 134) based on the circumferential position of the one or more orifices 134, the radial and / or axial position of the one or more orifices 134, the circumferential position of the one or more orifices 134 relative to the one or more conduits 110, or any combination thereof. The air intake channel 116 includes an inlet end 140 disposed near the primary flow path 106 and an outlet end 142 disposed away from the inlet end 140 and positioned near the air intake chamber 108. In the illustrated embodiment, one or more baffles 132 are coupled to at least a portion of the wall 120 and extend radially outward and axially rearward into the medial portion of the air intake chamber 108. In an exemplary embodiment, one or more baffles 132 extend radially outward from the wall 120 and then transition axially rearward to a partition wall 144 defining the rear boundary of the air intake chamber 108. However, it should be understood that one or more baffles 132 may be otherwise constructed, positioned, or coupled to the housing 100. In the illustrated embodiment, the axial position of the outlet 111 of the conduit 110 is behind the air intake channel 116. Therefore, in an exemplary embodiment, at least a portion of one or more flow control devices 130 is located axially forward of the outlet 111 of the conduit 110. In other words, in an exemplary embodiment, at least a portion of one or more flow control devices 130 is located axially in front of the outlet 111 of the duct 110, such that when the bleed airflow 118 flows in the axial rearward and / or radial outward direction, control of the bleed airflow 118 occurs at least partially.

[0061] Figure 4A plan view of at least a portion of an exemplary baffle 132 according to this disclosure is depicted. Figure 4 In this context, baffle 132 includes one or more series or groups of first holes 134A, the size of which is designed to be larger than one or more series or groups of second holes 134B. For example... Figure 4 The depicted circumferential positions and spacing between holes 134 can be based on the circumferential positions of one or more holes 134, the radial and / or axial positions of one or more holes 134, and the positions of one or more holes 134 relative to one or more pipes 110. Figure 3 The circumferential position of the second holes 134B varies. In an exemplary embodiment, one or more second holes 134B may be circumferentially positioned to be close to one or more pipes 110. Figure 3 ), and one or more first holes 134A can be circumferentially positioned away from one or more pipes 110 ( Figure 3 ), so that the inner shell 102 ( Figure 3 The circumference of the primary flow path 106 ( Figure 3 Uniformly extract the circumferential airflow 118 ( Figure 3 In an exemplary embodiment, access is positioned to approach one or more pipes 110 ( Figure 3 The circumferential position of the air venting chamber 108 ( Figure 3 ) area or part of the exhaust airflow 118 ( Figure 3 The flow rate is equal to or substantially equal to the flow rate into one or more pipes. Figure 3 The circumferential position of the air venting chamber 108 ( Figure 3 ) area or part of the exhaust airflow 118 ( Figure 3 The flow rate of ) makes the inner shell 102 ( Figure 3 The circumference of the primary flow path 106 ( Figure 3 Uniformly extract the circumferential airflow 118 ( Figure 3 In other words, the function of the second hole 134B is to restrict the entry into the air bleed chamber 108 to a greater extent than that of the first hole 134A. Figure 3 ) area or part of the exhaust airflow 118 ( Figure 3 The flow rate is determined based on the circumferential position of the corresponding orifice 134 and one or more pipes 110 ( Figure 3 The circumferential position of ) relative to the inner shell 102 ( Figure 3 ) Circumferential balance enters the expiratory air chamber 108 ( Figure 3 ) of the induced airflow 118 ( Figure 3 The flow rate of ). Therefore, although one or more pipes 110 ( Figure 3 The positions of the first and second holes 134A and 134B are asymmetrical, but the size and / or placement of these holes serve to change or adjust the arrangement around the inner shell 102. Figure 3 From the primary flow path 106 ( Figure 3 The circumferentially extracted airflow is balanced from the primary flow path 106. Figure 3 The extracted airflow. In other words, the size and / or placement of the first and second holes 134A, 134B serve to approach and distance from one or more pipes 110 ( Figure 3 The circumferential position of the air intake channel 116 ( Figure 3 The circumferential position between ) allows the air intake channel 116 ( Figure 3 ) of the induced airflow 118 ( Figure 3 The flow rates are equal.

[0062] Figure 5 Another exemplary embodiment of one or more baffles 132 is depicted. Figure 5 In this configuration, one or more baffles 132 are attached to at least a portion of the wall 120 and extend into the inner portion of the air intake chamber 108. Figure 5 In this configuration, one or more baffles 132 are constructed without one or more holes 134. Figure 3 and Figure 4In an exemplary embodiment, one or more baffles 132 extend radially outward from wall 120 and transition axially rearward toward partition wall 144. In an exemplary embodiment, the length of baffle 132 in the rear axial direction may vary based on the circumferential position of one or more pipes 110. In an exemplary embodiment, baffle 132 may include a portion 150 extending radially outward from wall 120 and a portion 152 extending axially rearward from the radial portion 150 toward partition wall 144. The axial position of the rear end portion 154 of portion 152 may vary circumferentially to create a gap 163 of different sizes between the rear end portion 154 and partition wall 144 at different circumferential positions. The length of the axially rearwardly extending portion 152 may vary based on the circumferential position of portion 152 and the circumferential position of one or more pipes 110. Alternatively or additionally, the radial positions of portions 150 and / or 152 may vary based on the circumferential positions of the respective portions 150, 152 and the circumferential position of one or more pipes 110. In an exemplary embodiment, portion 152 may extend axially rearward from portion 150 by a greater distance at a circumferential position near one or more pipes 110 than at a circumferential position away from one or more pipes 110. In this configuration, portion 152 more significantly restricts the flow of bleed airflow 118 exiting the bleed air channel 116 to reach one or more pipes 110 at a circumferential position near one or more pipes 110, while allowing more bleed airflow 118 to flow circumferentially towards one or more pipes 110 from a circumferential position away from one or more pipes 110, exiting the bleed air channel 116. One or more baffles 132 may also circumferentially alter the diffusion of bleed airflow 118 entering the bleed air chamber 108, and correspondingly, circumferentially alter the sink pressure of the bleed airflow 118 exposed around the inner shell 102. Figure 6 Depicting as a combination Figure 5 A plan view of at least a portion of an exemplary baffle 132 according to this disclosure. Figure 6 In this design, portion 152 is depicted as having a crescent shape extending in the axial direction. However, it should be understood that portion 152 may have other geometries and its length in the axial direction may be increased or decreased at multiple circumferential locations. It should also be understood that different axial lengths of portion 152 may be associated with, for example, […]. Figure 3 and Figure 4 One or more holes 134 are depicted together.

[0063] Figure 7 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 7In this embodiment, one or more flow control devices 130 include one or more baffles 160 disposed within or near the outlet end 142 of the air intake channel 116. In an exemplary embodiment, at least a portion of the one or more baffles 160 restricts or alters the flow of bleed airflow 118 exiting the air intake channel 116 at different circumferential positions relative to the housing 100. In the illustrated embodiment, one or more baffles 160 are disposed within the air intake channel 116 such that at least a portion of the one or more baffles 160 extends from wall 120 to wall 122. However, it should be understood that the one or more baffles 160 may also be located at the outlet end 142 of the air intake channel 116 or at other locations relative to the air intake channel 116. In an exemplary embodiment, the one or more baffles 160 may include one or more orifices 162 such that the flow of bleed airflow 118 can pass from the air intake channel 116 through the one or more baffles 160 to the air intake chamber 108. In an exemplary embodiment, similar to the combination Figure 3 and Figure 4 The size and / or density of the depicted one or more orifices 134 and one or more orifices 162 may vary based on the circumferential position of the one or more orifices 162, the circumferential position of the one or more conduits 110, or both. In an exemplary embodiment, the size and / or density of the one or more orifices 162 at a circumferential position away from the one or more conduits 110 may be greater than the size and / or density of the one or more orifices 162 at a circumferential position close to the one or more conduits 110. In this configuration, the orifices 162 restrict the flow of bleed airflow 118 exiting the bleed air channel 116 at a circumferential position close to the one or more conduits 110, while allowing more bleed airflow 118 to flow circumferentially from a circumferential position away from the one or more conduits 110 toward the one or more conduits 110, exiting the bleed air channel 116.

[0064] Figure 8 A plan view of at least a portion of an exemplary baffle 160 according to this disclosure is depicted. Figure 8 In this context, baffle 160 includes one or more series or groups of first holes 162A, the size of which is designed to be larger than one or more series or groups of second holes 162B. For example... Figure 8 The depicted circumferential positions and spacing between holes 162 may be based on the circumferential positions of one or more holes 162 and / or the positions of one or more holes 162 relative to one or more pipes 110. Figure 7 The circumferential position of the holes 162B varies. In an exemplary embodiment, one or more holes 162B may be circumferentially positioned to be close to one or more pipes 110. Figure 7 ), and one or more first holes 162A can be circumferentially positioned away from one or more pipes 110 ( Figure 7 ), so that the inner shell 102 ( Figure 7 The circumference of the primary flow path 106 ( Figure 7 Uniformly extract the circumferential airflow 118 ( Figure 7 In an exemplary embodiment, access is positioned to approach one or more pipes 110 ( Figure 7 The circumferential position of the air venting chamber 108 ( Figure 7 ) area or part of the exhaust airflow 118 ( Figure 7 The flow rate is equal to or substantially equal to the flow rate into one or more pipes. Figure 7 The circumferential position of the air venting chamber 108 ( Figure 7 ) area or part of the exhaust airflow 118 ( Figure 7 The flow rate of the second orifice 162B. In other words, the function of the second orifice 162B is to restrict the flow into the air chamber 108 to a greater extent than the first orifice 162A. Figure 7 ) area or part of the exhaust airflow 118 ( Figure 7 The flow rate is determined based on the circumferential position of the corresponding orifice 162 and one or more pipes 110 ( Figure 7 The circumferential position of ) is used to balance the circumferential flow from the primary flow path 106 ( Figure 7 Extracted and introduced into the air extraction chamber 108 ( Figure 7 ) of the induced airflow 118 ( Figure 7 The flow rate of ). Therefore, although one or more pipes 110 ( Figure 7 The positions of the first and second holes 162A and 162B are asymmetrical, but the size and / or placement of these holes serve to change or adjust the arrangement around the inner shell 102. Figure 7 From the primary flow path 106 ( Figure 7 The circumferentially extracted airflow is balanced from the primary flow path 106. Figure 7 The extracted airflow. In other words, the size and / or placement of the first and second holes 162A, 162B serve to extract airflow relative to one or more pipes 110. Figure 7 The circumferentially balanced airflow between the near and far positions of the circumferential position 118 ( Figure 7 The flow rate of ).

[0065] Figure 9 A plan view of at least a portion of an exemplary baffle 160 according to this disclosure is depicted. Figure 9 In this configuration, baffle 160 includes a portion 164 extending radially from one or both of the walls 120, 122 relative to the inner shell 102 along a varying circumferential distance into the air intake channel 116. Figure 9 In this configuration, baffle 160 may include a centrally located aperture 166 defined by the outer portion 164, such that the size of aperture 166 varies circumferentially based on the distance by which portion 164 extends radially inward. Therefore, baffle 160 is configured to circumferentially balance the flow through air intake channel 116. Figure 7 ) of the induced airflow 118 ( Figure 7 The flow of ) . In an exemplary embodiment, the baffle 160 may be configured to interact with the flow of one or more pipes 110 ( Figure 7 The airflow 118 ( ) flows through the air intake channel 116 at the circumferential position of the circumferential position of the air intake channel 116. Figure 7 Compared to the flow rate of ), the flow rate near one or more pipes 110 is reduced. Figure 7 The airflow 118 ( ) flows through the air intake channel 116 at the circumferential position of the circumferential position of the air intake channel 116. Figure 7 The flow of the primary flow path 106 is altered or regulated circumferentially. In other words, the baffle 160 functions to change or regulate the flow from the primary flow path 106. Figure 7 The extracted airflow was 118 ( Figure 7 ), so that although one or more pipes 110 ( Figure 7 The circumferential position of ) is unbalanced or asymmetrical, but around the inner shell 102 ( Figure 7 ) circumferential airflow 118 ( Figure 7 The flow is uniform.

[0066] Figure 10 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 10 In this embodiment, one or more flow control devices 130 include one or more baffles 170 disposed within or near the outlet end 142 of the air intake channel 116. In an exemplary embodiment, the one or more baffles 170 include one or more stationary baffles 170A and one or more movable or translational baffles 170B. Baffles 170B may be movable or translational relative to baffles 170A to circumferentially alter the flow of the air intake gas stream 118 flowing through the air intake channel 116 and into the air intake chamber 108. Figure 10 In this configuration, one or more actuators 172 may be coupled to one or more baffles 170B, such that actuation of the one or more actuators 172 causes translational movement of the one or more baffles 170B relative to one or more baffles 170A. The one or more actuators 172 may be communicatively coupled to one or more controllers 174 to automatically control the actuation of the one or more actuators 172 and the corresponding movement of the one or more baffles 170B. The controller 174 may be a standalone controller dedicated to downstream position and / or system 112, or alternatively, may be integrated into the aircraft 10 (… Figure 1 Controller 174 is one or more of the main system controllers (such as a full authority digital engine control system, also known as FADEC). Controller 174 can be configured similarly to the following reference. Figure 22 An exemplary computing device of the computing system 400 described.

[0067] In an exemplary embodiment, one or more sensors 176 may be at least partially located within the air intake chamber 108 to detect at least one of the pressure within the air intake chamber 108 or the flow rate of the bleed air flow 118 relative to one or more circumferential positions of the air intake chamber 108. The one or more sensors 176 may also be communicatively coupled to one or more controllers 174 to receive feedback or data detected by the one or more sensors 176. In an exemplary embodiment, based on the pressure within the air intake chamber 108 and / or the flow rate data received by the controller 174 from the one or more sensors 176, the controller 174 may be configured to automatically and independently control the flow rate of the bleed air flow 118 relative to one or more circumferential positions of the air intake chamber 108 via one or more baffles 170A, 170B.

[0068] Figure 11 Depicting according to this disclosure Figure 10 A plan view of at least a portion of exemplary baffles 170A, 170B. In the illustrated embodiment, one or more baffles 170A include one or more holes 180, and one or more baffles 170B include one or more holes 182. In the illustrated embodiment, the one or more holes 180 have a constant or identical size, while the size of the one or more holes 182 is based on the size of the one or more holes relative to the inner shell 102 ( Figure 10 The circumferential position of the holes 180 and 182 varies. However, it should be understood that the dimensions of the holes 180 and 182 may be opposite to those of the baffles 170A and 170B, or the dimensions of the holes 180 and 182 may be the same on both baffles 170A and 170B. In the illustrated embodiment, the movement control of the baffle 170B relative to the baffle 170A, such as in the circumferential direction, can be achieved through the airflow 118 of the baffles 170A and 170B. Figure 10 The flow of or change in its amount (e.g., based on the alignment or misalignment of holes 180 and 182, via holes 180, 182). In an exemplary embodiment, baffle 170B may be configured with gear teeth 184, the gear teeth 184 being configured to interact with actuator 172 ( Figure 10 The gear teeth (not shown) engage correspondingly. Alternatively or additionally, one or more lever arms 186 may be coupled to the baffle 170B and the actuator 172. Figure 10 This facilitates the movement of baffle 170B relative to baffle 170A. It should also be understood that other types of actuation mechanisms can be used to facilitate the movement of baffle 170B relative to baffle 170A.

[0069] Figure 12 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 12In this embodiment, one or more flow control devices 130 are formed as part of or can be coupled to the wall 120. In an exemplary embodiment, the geometric parameters of the air intake channel 116 can vary circumferentially relative to the inner shell 102, causing the cross-sectional area of ​​the air intake channel 116 to vary circumferentially. Figure 12 As depicted, wall 120 may be spaced apart from wall 122 at different circumferential positions relative to inner shell 102 by different radial distances, axial distances, or both, to provide circumferentially varied flow of expedited airflow 118 through expedited air channels 116 at different circumferential positions. In an exemplary embodiment, wall 120 may be... Figure 12 The dashed lines in the diagram depict various circumferential positions closer to or further away from wall 122, causing circumferential variations in the geometry of the air intake channel 116. In an exemplary embodiment, a nominal position 190 of at least a portion of wall 120 may extend circumferentially around at least a portion of inner shell 102, and in various circumferential regions, at least a portion of wall 120 may be positioned inward toward wall 122 at a narrowing position 192, or outward away from wall 122 at an enlarged position 194. Therefore, compared to nominal position 190, at the narrowing position 192, the cross-sectional area or geometry of air intake channel 116 is at least partially reduced at or near outlet end 142 to reduce the flow of air intake gas 118 at these circumferential positions. Correspondingly, compared to nominal position 190, at the enlarged position 194, the cross-sectional area or geometry of air intake channel 116 is at least partially increased at or near outlet end 142 to increase the flow of air intake gas 118 at these circumferential positions. In an exemplary embodiment, the nominal position 190, the narrowing position 192, and the widening position 194 may be circumferentially positioned based on the circumferential positions of one or more pipes 110. In an exemplary embodiment, the wall 120 may be constructed at or near the circumferential positions of one or more pipes 110 at the narrowing position 192, and the wall 120 may be constructed at the widening position 194 at a circumferential position remote from the circumferential positions of one or more pipes 110. It should be understood that the wall 120 may gradually transition between the nominal position 190, the narrowing position 192, and the widening position 194 in different circumferential regions relative to the inner shell 102.

[0070] In an exemplary embodiment, one or more flow control devices 130 may be formed as part of or coupled to wall 122. In an exemplary embodiment, wall 122 is defined by an inlet end 196 positioned close to the primary airflow path 106. The inlet end 196 of wall 122 is defined by a leading edge 198. In an exemplary embodiment, one or more flow control devices 130, based on the circumferential position of the leading edge 198, present different radii of curvature of the leading edge 198 to circumferentially balance the bleed airflow 118 entering the bleed air channel 116. A reduced radius of curvature of the leading edge 198 compared to a higher radius of curvature may cause the leading edge 198 to capture additional high-pressure air from the primary flow path 106 to supply the bleed airflow 118 into the bleed air chamber 108. In an exemplary embodiment, the radius of curvature of the leading edge 198 may vary at different circumferential positions of the inner shell 102 to circumferentially balance the bleed airflow 118 entering the bleed air channel 116. In an exemplary embodiment, the radius of curvature of the leading edge 198 at a circumferential position close to one or more pipes 110 may be greater than the radius of curvature of the leading edge 198 at a circumferential position away from one or more pipes 110.

[0071] Figure 13 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 13 In this embodiment, one or more flow control devices 130 include one or more actuators 172, which are coupled to or configured to apply force to at least a portion of the wall 120. In an exemplary embodiment, the one or more actuators 172 may be linear actuators configured to apply force to at least a portion of the wall 120 to circumferentially change the geometry of the air intake channel 116. In an exemplary embodiment, the one or more actuators 172 may be actuated to move at least a portion of the wall 120 toward and / or away from the wall 122 to respectively decrease or increase the geometric parameters of the air intake channel 116, such as, as a non-limiting example, the cross-sectional area near the outlet end 142 of the air intake channel 116. In an exemplary embodiment, the one or more actuators 172 may include one or more members 195, which are extendable and / or retractable, and coupled to or configured to apply force to the wall 120. One or more components 195 may be axially movable in direction 197 to move wall 120 in direction 199, thereby reducing or increasing the geometric parameters of air intake channel 116, such as, by way of a non-limiting example, the cross-sectional area of ​​air intake channel 116. In an exemplary embodiment, one or more actuators 172 are communicatively coupled to one or more controllers 174 to enable automatic control or actuation of the one or more actuators 172. Figure 13In this configuration, one or more sensors 176 may also be positioned to sense or detect one or more of the pressure within the air chamber 108 or the flow rate of the airflow 118 within the air chamber 108, and to communicate the sensed or detected parameters of the airflow 118 to one or more controllers 174. Therefore, based on the detected pressure within the air chamber 108 and / or the flow rate of the airflow 118, one or more controllers 174 may automatically control the actuation of one or more actuators 172 to change the geometry of the air channel 116 at various circumferential positions.

[0072] Figure 14 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 14 In this embodiment, one or more flow control devices 130 include one or more segmented portions 200 of a wall 122, which are radially and / or axially movable or translated relative to the primary flow path 106. In an exemplary embodiment, the wall 122 defining at least a portion of the bleed channel 116 includes one or more segmented portions 200, and the one or more segmented portions 200 are positioned proximate to the inlet end 140 of the bleed channel 116. The one or more segmented portions 200 are coupled to one or more actuators 202. The one or more actuators 202 are actuated to translate or move the one or more segmented portions 200 in direction 204, such that the one or more segmented portions 200 can be moved into or withdrawn from at least a portion of the primary flow path 106. In an exemplary embodiment, the one or more segmented portions 200 can be moved into at least a portion of the primary flow path 106 to capture additional high-pressure air from the primary flow path 106, thereby supplying a bleed airflow 118 to the bleed chamber 108. In an exemplary embodiment, one or more segmented portions 200 may be moved to at least a portion of the primary flow path 106 at circumferentially varying positions around the inner shell 102, or withdrawn from at least a portion of the primary flow path 106, to circumferentially balance the bleed airflow 118 entering the bleed air chamber 108. For example... Figure 14 Described, similar to, as in combination Figure 10 and Figure 13 As depicted and described, one or more of the sensors 176 and one or more controllers can be used to automatically control the actuation of one or more actuators 202 based on one or more of the pressure within the bleed chamber 108 or the flow rate of the bleed air flow 118.

[0073] Figure 15 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 15In this embodiment, one or more flow control devices 130 include one or more orifices 210 extending into one or more secondary chambers 212. In an exemplary embodiment, the one or more secondary chambers 212 can be pressurized at a higher pressure than the bleed chamber 108. Figure 15 In the illustrated embodiment, one or more orifices 210 extend through partition wall 144 into secondary chamber 212. In this embodiment, secondary chamber 212 may also be a bleed chamber located downstream of bleed channel 116, such that in the subsequent stage of compressor 34, a portion of the air from primary flow path 106 is captured and directed into secondary chamber 212. In an exemplary embodiment, one or more orifices 210 may be circumferentially positioned relative to inner housing 102 such that an increase in local pressure in bleed chamber 108 near where secondary airflow 214 enters bleed chamber 108 from secondary chamber 210 reduces the flow of bleed airflow 118 at that location. In an exemplary embodiment, when secondary chamber 212 is pressurized at a higher pressure than bleed chamber 108, one or more orifices 210 may be positioned circumferentially near one or more ducts 110. It should also be understood that the size and / or density of one or more orifices 210 may vary based on the circumferential position of these orifices 210. In an exemplary embodiment, one or more orifices 210 may be in a fixed position and may be used as a passive flow control device. However, in other exemplary embodiments, one or more orifices 210 may, as a non-limiting example, control the valve 216 between an open position, a closed position, or a partially open position via one or more actuators. Figure 15 As depicted, one or more actuators 218 can be coupled to one or more valves 216 to automatically control the actuation of one or more valves, thereby controlling the secondary airflow 214 entering the bleed chamber 108. Although Figure 15 Not depicted, but one or more actuators 218 may be communicatively coupled to a controller (such as controller 174). Figure 10 , Figure 13 and Figure 14 This enables the controller to automatically control the actuation of one or more valves. In an exemplary embodiment, although... Figure 15 Not described in the text, but one or more sensors (such as Figure 10 , Figure 13 and Figure 14 One or more sensors 176 depicted may be positioned within the bleed chamber 108 such that actuation of one or more valves is based on one or more of the pressure within the bleed chamber 108 or the flow rate of the bleed air flow 118 within the bleed chamber 108.

[0074] Figure 16 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 16In this embodiment, one or more flow control devices 130 include one or more orifices 230 extending into one or more secondary chambers 232 (such as a lower shroud chamber). In an exemplary embodiment, the one or more secondary chambers 232 can be pressurized at a lower pressure than the bleed chamber 108. Figure 16 In this embodiment, one or more orifices 210 extend through the housing 104 into the secondary chamber 232. In an exemplary embodiment, the one or more orifices 230 may be circumferentially positioned relative to the housing 104 such that a decrease in local pressure in the bleed chamber 108 near the bleed air flow 118, where a portion 234 of the bleed air flow exits the bleed chamber 108 into the secondary chamber 232, increases the flow of the bleed air flow 118 at that location. In an exemplary embodiment, when the secondary chamber 232 is pressurized at a lower pressure than the bleed chamber 108, the one or more orifices 230 may be positioned at a circumferential location away from the circumferential location of the one or more conduits 110. It should also be understood that the size and / or density of the one or more orifices 230 may vary based on the circumferential location of the orifices 230. In an exemplary embodiment, the one or more orifices 230 may be in a fixed position and may be used as a passive flow control device. However, in other exemplary embodiments, the one or more orifices 230 may, as a non-limiting example, control a valve via one or more actuators (similar to...). Figure 15 The valve 216 depicted is actuated between an open position, a closed position, or a partially open position. Although Figure 16 Not described in the text, but controllers (such as controller 174) Figure 10 , Figure 13 and Figure 14 )) and sensors (such as Figure 10 , Figure 13 and Figure 14 The sensor 176 depicted can be used in conjunction with these holes 230 such that the flow rate of portion 234 is controlled based on one or more of the pressure within the bleed chamber 108 or the flow rate of the bleed air flow 118 within the bleed chamber 108.

[0075] Figure 17 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 17In this embodiment, one or more flow control devices 130 include one or more baffles 260 disposed within or near the outlet end 142 of the air intake channel 116. In an exemplary embodiment, at least a portion of the one or more baffles 260 restricts or alters the flow of bleed airflow 118 exiting the air intake channel 116 at different circumferential locations relative to the housing 100. In the illustrated embodiment, one or more baffles 260 are disposed within the air intake channel 116 such that at least a portion of the one or more baffles 260 extends from wall 120 to wall 122. However, it should be understood that the one or more baffles 260 may also be located at the outlet end 142 of the air intake channel 116 or at other locations relative to the air intake channel 116. In an exemplary embodiment, the one or more baffles 260 may include one or more orifices 262 that allow the flow of bleed airflow 118 from the air intake channel 116 through the one or more baffles 260 to reach the air intake chamber 108.

[0076] In an exemplary embodiment, one or more baffles 260 may be formed of at least two different materials with different material properties, such that under different operating conditions of the engine 20, the response of one or more portions of one or more baffles 260 differs from the response of one or more other portions of one or more baffles 260. In an exemplary embodiment, one or more baffles 260 may be formed of at least two different materials with different coefficients of thermal expansion. In an exemplary embodiment, the geometric parameters of one or more portions of one or more baffles 260 may be varied based on the temperature of the bleed airflow 118. In an exemplary embodiment, portions of one or more baffles 260 formed of a material having a larger coefficient of thermal expansion than another portion of baffle 260 may deflect or expand to change the flow rate of the bleed airflow 118 through the baffle 260. Therefore, the baffles 260 may be formed with different materials positioned at different circumferential locations on the baffles 260 to circumferentially balance the flow rate of the bleed airflow 118.

[0077] Figure 18 A plan view of an exemplary baffle 260 according to the present disclosure is depicted. In the illustrated embodiment, the baffle 260 may include an outer boundary 264 that abuts against or closely approaches the wall 120. Figure 17The baffle 260 also includes an inner boundary 266 defining the aperture 262. In the illustrated embodiment, the baffle 260 is formed having portions 268 and 270. Portion 268 may be formed of a material having different material properties than the material used to form portion 270. Portions 268 and 270 may have any circumferential span and may be located at different circumferential positions around the baffle 260. In an exemplary embodiment, portion 268 is formed of a material with a coefficient of thermal expansion less than that of the material used to form portion 270. Therefore, at elevated temperatures, portion 270 will experience greater deflection or expansion than portion 268. The baffle 260 may be configured such that portions 268 and 270 surround the inner shell 102 ( Figure 17 Circumferential positioning, relative to the inner shell 102 ( Figure 17 Circumferential balanced airflow 118 ( Figure 17 The flow rate of the baffle 260. Therefore, in the illustrated embodiment, the inner boundary 266 of the region of the baffle 260 corresponding to the portion 270 will be deflected or expanded in the direction 272 to reduce the size or geometry of the orifice 262. In an exemplary embodiment, the portion 270 may be circumferentially positioned to approach one or more pipes 110. Figure 17 The circumferential position of ). In this embodiment, in the direction that causes the bleed airflow 118 ( Figure 17 The higher temperature of the aircraft 10 ( Figure 1 During the climb phase of flight, due to the expansion of part of 270, the bleed airflow 118 ( Figure 17 The flow rate will be in one or more pipes 110 ( Figure 17 The circumferential position decreases. This leads to an airflow of 118 ( Figure 17 The temperature of the aircraft during the climb phase is 10 ( Figure 1 During the cruise phase of flight, as part of the 270 retracts from its expanded state during the climb phase, the bleed airflow 118 ( Figure 17 The flow rate will be in one or more pipes 110 ( Figure 17 The flow rate increases near the circumferential position of the airflow. Therefore, exemplary embodiments of this disclosure utilize different materials with different material properties to form one or more flow control devices to circumferentially balance the bleed airflow 118. Figure 17 To manage compressor 34 ( Figure 17 ) Deformation.

[0078] Figure 19 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 19 In this process, one or more flow control devices 130 include one or more baffles 280 disposed within the air intake chamber 108. Figure 19In the inner shell 108, one or more baffles 280 are coupled to at least a portion of the wall 120 and extend into the inner portion of the air intake chamber 108. In an exemplary embodiment, the one or more baffles 280 extend at least partially radially outward from the wall 120 and transition axially rearward to the partition wall 144. In an exemplary embodiment, the one or more baffles include one or more baffle elements 281, each including portions 282 and 284, wherein portion 282 is coupled to and / or extends radially outward from the wall 120, and portion 284 extends axially rearward from portion 282 to the partition wall 144. In an exemplary embodiment, the one or more baffle elements 281 include one or more holes 286 to allow the air intake flow 118 to pass through the one or more baffle elements 281. The size and placement of the one or more holes 286 may vary radially, axially, and / or circumferentially relative to the inner shell 102.

[0079] In an exemplary embodiment, one or more baffles 280 further include one or more baffle elements 287 positioned to alter the size of one or more orifices 286 or control the amount of bleed airflow 118 passing through one or more orifices 286. In an exemplary embodiment, one or more baffle elements 287 include one or more shields 288 configured to extend over at least a portion of one or more orifices 286 to alter the flow rate of bleed airflow 118 passing through one or more orifices 286. Similar to the combination... Figure 17 and Figure 18 The depicted and described baffle 260, and one or more shields 288, are formed of a material having different material properties than the material used to form the one or more baffle elements 281. In the illustrated embodiment, one or more shields 288 are coupled to portion 284. One or more shields 288 are depicted on the radially outer side of portion 284; however, it should be understood that the position of one or more shields 288 may be otherwise positioned relative to portion 284. One or more shields 288 may also be positioned in other locations, such as on portion 282.

[0080] In an exemplary embodiment, one or more baffles 288 are formed of a material with a coefficient of thermal expansion greater than that of the material used to form at least portion 284. In an exemplary embodiment, the difference in the coefficients of thermal expansion between one or more baffles 288 and portion 284 allows one or more baffles 288 to expand or deflect by a greater amount than portion 284 to change the size of one or more orifices 286 in response to temperature changes in the bleed airflow 118. Figure 20 Depicting from Figure 19A plan view of the baffle 280 taken by line 20-20. In an exemplary embodiment, at least a portion 290 of the baffle 288 is fixedly connected to a portion 284 of the side 292 near the hole 286. At least a portion 294 of the baffle 288 away from the portion 290 is not connected to the portion 284 and can move freely relative to the portion 284. In an exemplary embodiment, with the airflow 118 ( Figure 19 As the temperature rises, the baffle 288 expands, causing portion 294 to move in direction 296 to reduce the geometry or size of the orifice 286. This is in response to the bleed airflow 118 ( Figure 19 As the temperature decreases, the baffle 288 retracts from its expanded state, causing portion 294 to move in a direction opposite to direction 296, thereby increasing the geometry or size of the aperture 286. The number and circumferential position of one or more baffles 288 can be based on one or more pipes 110 ( Figure 19 The circumferential position of the airflow 118 varies. In this embodiment, the airflow 118 is caused by the change in the circumferential position of the airflow 118. Figure 19 The higher temperature of the aircraft 10 ( Figure 1 During the climb phase of flight, due to the expansion of the baffle 288, the bleed airflow 118 ( Figure 19 The flow rate will be at the baffle 288 located in one or more pipes 110 ( Figure 19 The flow rate decreases near the circumferential position of the airflow. This results in an airflow rate of 118 ( Figure 19 The temperature of the aircraft during the climb phase is 10 ( Figure 1 During the cruise phase of flight, as the shield 288 retracts from its expanded state during the climb phase, the bleed airflow 118 ( Figure 19 The flow rate will be at the baffle 288 located in one or more pipes 110 ( Figure 17 The area near the circumferential position of ) increases.

[0081] Figure 21 Another exemplary embodiment of one or more flow control devices 130 is depicted. Figure 21 In this embodiment, one or more flow control devices 130 are formed as at least a portion of the wall 120. In an exemplary embodiment, this is similar to the combination... Figure 17-20 In one or more embodiments of the flow control device 130 described and depicted, at least a portion of the wall 120 may be formed of different materials with different material properties. In the illustrated embodiment, the wall 120 includes an inlet end 300 disposed near the primary flow path 106 and an outlet end 302 disposed away from the inlet end 300 near the outlet end 142 of the air intake channel 116. The outlet end 302 of the wall 120 includes a portion 304 connected to or disposed in contact with the portion 306. Similar to a combination... Figure 17 and Figure 18The depiction and description of the baffle 260 and its combination Figure 19 and Figure 20 The baffle 280 depicted and described, portions 304 and 306 are formed of materials with different material properties. In the illustrated embodiment, portion 304 is formed of a material with a coefficient of thermal expansion greater than that of the material used to form portion 306. In an exemplary embodiment, the difference in the coefficients of thermal expansion between portions 304 and 306 allows portion 304 to expand or deflect by a greater amount than portion 306 to change the size of the bleed air channel 116 at the outlet end 140 in response to temperature changes in the bleed air flow 118.

[0082] In an exemplary embodiment, in response to an increase in temperature of the bleed airflow 118, portion 304 expands by a greater amount in direction 308 than portion 306, causing the outlet end 302 of wall 120 to deflect toward wall 122 to position 310, thereby reducing the geometry or size of the outlet end 140 of the bleed air channel 116. In response to a decrease in temperature of the bleed airflow 118, portion 304 retracts by a greater amount in the direction opposite to direction 308 than portion 306, causing the outlet end 302 of wall 120 to deflect away from wall 122 to position 312, thereby increasing the geometry or size of the outlet end 140 of the bleed air channel 116. The circumferential positions of portions 304 and 306 can vary circumferentially around the inner shell 102 to circumferentially balance or control the flow rate of the bleed airflow 118. In an exemplary embodiment, portions 304 and 306 may be circumferentially positioned based on the circumferential position of one or more pipes 110 to increase or decrease the flow rate of the bleed airflow 118 at locations near or far from the circumferential position of one or more pipes 110, similar to combining Figure 17-20 Described.

[0083] It should be understood that, in combination Figure 3-21 One or more of the flow control devices 130 depicted and described can be used in combination. For example, but not limited to, one or more baffles 132 ( Figure 1-6 ) can be used with movable part 200 ( Figure 14 Used in combination. Additionally or alternatively, but not limited to, one or more baffles 160 ( Figure 7-9 It can be used with one or more holes 210 or 230. Figure 15 and Figure 16 (Used in combination.) It should also be understood that, if combined... Figure 3-21 The different types of flow control devices 130 depicted and described may be located at different circumferential positions relative to the inner housing 102. For example, but not limited to, one or more baffles 132 ( Figure 1-6 It can extend in a semi-circular shape or for a specific circumferential span, and one or more baffles 160 ( Figure 7-9 It can extend over different semi-circular distances or different circumferential spans.

[0084] Figure 22 An example computing system 400 according to an exemplary embodiment of the present disclosure is provided. For example, the computing device or element described herein (such as controller 174) may include various components and perform the various functions of the computing system 400 described below.

[0085] like Figure 22 As shown, computing system 400 may include one or more computing devices 402. Computing device 402 may include one or more processors 402A and one or more memory devices 402B. The one or more processors 402A may include any suitable processing device, such as a microprocessor, microcontroller, integrated circuit, logic device, and / or other suitable processing device. The one or more memory devices 402B may include one or more computer-executable or computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard disk drives, flash drives, and / or other memory devices.

[0086] One or more memory devices 402B may store information accessible by one or more processors 402A, including computer-readable instructions 402C executable by one or more processors 402A. The computer-readable instructions 402C may be any set of instructions that, when executed by one or more processors 402A, cause one or more processors 402A to perform operations. In some embodiments, the computer-readable instructions 402C may be executed by one or more processors 402A to cause one or more processors 402A to perform operations such as any operations and functions configured for the computing system 400 and / or computing device 402, such as actuator 172 controlling the flow of bleed air 118. Figure 10 and Figure 13 ), Actuator 202 ( Figure 14 ), and / or valve 216 and / or actuator 218 ( Figure 15 The computer-readable instructions 402C can be software written in any suitable programming language or implemented in hardware. Additionally and / or alternatively, the computer-readable instructions 402C can be executed in logically and / or virtually separate threads on the processor 402A. The memory device 402B can also store data 402D accessible by the processor 402A. For example, data 402D may include models, lookup tables, databases, etc.

[0087] The computing device 402 may also include a network interface 402E for communicating, for example, with other components of the computing system 400 (e.g., via a communication network). The network interface 402E may include any suitable components for interfacing with one or more networks, including, for example, a transmitter, receiver, port, controller, antenna, and / or other suitable components. One or more devices may be configured to receive one or more commands from or to provide one or more commands to the computing device 402.

[0088] Therefore, embodiments of this disclosure include features, either in conjunction with or independent of external features, such as bleed channels or bleed chambers, to achieve an asymmetric bleed port geometry while maintaining a balanced or uniform airflow rate around the compressor circumference and keeping compressor deformation within limits. In exemplary embodiments, various types of passive and / or active flow control devices with circumferential variations are used to manage compressor deformation using asymmetric bleed. Embodiments of this disclosure enable asymmetric bleed port geometries that prevent or reduce the need for increased bleed chamber area or exhaust vortexes to manage compressor deformation. Embodiments of this disclosure circumferentially balance the flow rate around the compressor housing circumferentially by changing the confinement and / or pressure loss around the bleed outlet circumference, and / or by adjusting the diffusion and / or recovery pressure downstream of the compressor circumference. The flow control devices of this disclosure can be actuated and / or actively changed, and / or passively changed using material properties (e.g., thermal expansion). Therefore, embodiments of this disclosure circumferentially balance the air discharged from the compressor flow path to maintain a uniform airflow rate around the circumference of the compressor housing.

[0089] The techniques discussed herein refer to computer-based systems, actions taken by computer-based systems, information sent to computer-based systems, and information sent from computer-based systems. Those skilled in the art will recognize that the inherent flexibility of computer-based systems allows for a wide variety of possible configurations, combinations, and divisions of tasks and functions between and within components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memories, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0090] This written description uses examples to disclose this disclosure, including best practices, and to enable any person skilled in the art to practice this disclosure, including making and using any device or system and methods of making any combination. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include 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.

[0091] Further details are provided by the following topics:

[0092] An engine includes: a compressor including an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining a bleed chamber therebetween, the inner housing at least partially defining a bleed channel between the primary flow path and the bleed chamber to guide a portion of the primary airflow as a bleed airflow into the bleed chamber; and one or more flow control devices at least partially located within the bleed channel, forming at least a portion of the bleed channel, or extending axially rearward from the bleed channel, the one or more flow control devices being configured to circumferentially balance the flow of the bleed airflow entering or within the bleed chamber.

[0093] According to the engine described in the foregoing clause, the one or more flow control devices include one or more baffles, the one or more baffles including one or more holes, wherein the size of the one or more holes varies based on the circumferential position of the respective one or more holes.

[0094] The engine according to any of the foregoing clauses further includes one or more pipes coupled to the housing and fluidly connected to the bleed chamber, wherein the size of the one or more orifices circumferentially positioned close to the one or more pipes is smaller than the size of the one or more orifices circumferentially positioned away from the one or more pipes.

[0095] An engine according to any of the foregoing clauses, wherein the one or more flow control devices include one or more baffles, wherein at least a portion of the one or more baffles extends axially in a rearward direction relative to the bleed air chamber, and wherein the axial length of the portion varies based on the circumferential position of the portion.

[0096] The engine according to any of the foregoing clauses further includes one or more pipes coupled to the housing and fluidly connected to the bleed chamber, and at least one of the axial lengths or radial positions of said portion varies circumferentially based on the circumferential position of said one or more pipes.

[0097] The engine according to any of the foregoing clauses further includes one or more pipes coupled to the housing and fluidly connected to the bleed chamber, wherein the axial length of the portion of the one or more pipes located circumferentially closer to the circumferential position of the one or more pipes is greater than the axial length of the portion of the one or more pipes positioned circumferentially away from the one or more pipes.

[0098] An engine according to any of the foregoing clauses, wherein the inner housing includes a first wall and a second wall defining the bleed air passage, and wherein the one or more flow control devices include one or more baffles extending at least partially from at least one of the first wall or the second wall into the bleed air passage.

[0099] The engine according to any of the foregoing clauses further includes one or more ducts coupled to the housing and fluidly connected to the bleed air chamber, wherein the one or more baffles are configured such that the bleed air flow through the bleed air channel at a circumferential position near the one or more ducts is equal to the bleed air flow through the bleed air channel at a circumferential position away from the one or more ducts.

[0100] An engine according to any of the foregoing clauses, wherein the one or more flow control devices include: one or more first baffles; and one or more second baffles; and wherein at least one of the one or more first baffles or the one or more second baffles includes one or more orifices, and wherein the one or more first baffles or at least one of the one or more second baffles is movable to control the flow of the bleed airflow through the one or more orifices.

[0101] The engine according to any of the foregoing clauses further includes one or more actuators capable of being actuated to move at least one of the one or more first baffles or the one or more second baffles.

[0102] The engine according to any of the foregoing clauses further includes: one or more sensors disposed within the bleed air chamber, the one or more sensors being configured to detect at least one of pressure within the bleed air chamber or flow rate of the bleed air flow within the bleed air chamber; and a controller configured to control the one or more flow control devices to change at least one of the pressure or the flow rate.

[0103] An engine according to any of the foregoing clauses, wherein the one or more flow control devices are configured to change the size of the bleed air channel.

[0104] The engine according to any of the foregoing clauses, wherein the geometric parameters of the bleed air channel vary based on the circumferential position of the geometric parameters.

[0105] The engine according to the foregoing clause, wherein the inner housing includes a first wall and a second wall defining the air intake channel, and wherein the one or more flow control devices include at least a portion of at least one of the first wall or the second wall.

[0106] The engine according to any of the foregoing clauses further includes one or more actuators capable of being actuated to move at least a portion of the first wall, thereby changing the size of the bleed air channel.

[0107] The engine according to any of the foregoing clauses further includes one or more actuators capable of being actuated to move at least a portion of the second wall into the primary airflow.

[0108] An engine according to any of the foregoing clauses, wherein the second wall is disposed axially rearward of the first wall and includes a leading edge defining an inlet end of the second wall adjacent to the primary airflow, and wherein the radius of curvature of the leading edge varies based on the circumferential position of the leading edge.

[0109] An engine according to any of the foregoing clauses, wherein the one or more flow control devices include one or more orifices extending from the bleed chamber into at least one secondary chamber, wherein the secondary chamber is pressurized at a higher or lower pressure than the bleed chamber.

[0110] The engine according to any of the foregoing clauses further includes one or more conduits coupled to the housing and fluidly connected to the bleed chamber, wherein the secondary chamber is pressurized at a higher pressure, and wherein the one or more orifices are located at or near the circumferential position of the one or more conduits.

[0111] The engine according to any of the foregoing clauses further includes one or more conduits coupled to the housing and fluidly connected to the bleed chamber, wherein the secondary chamber is pressurized at a lower pressure, and wherein the one or more orifices are located at or near a circumferential position relative to the circumferential position of the one or more conduits.

[0112] An engine according to any of the foregoing clauses, wherein the one or more flow control devices include one or more baffles, and wherein the one or more baffles include a first material and a second material, wherein the coefficient of thermal expansion of the first material is greater than the coefficient of thermal expansion of the second material.

[0113] An engine according to any of the foregoing clauses, wherein the one or more baffles include one or more holes, and wherein the coefficient of thermal expansion of the first material causes the size of the one or more holes to vary based on the circumferential position of the one or more holes.

[0114] The engine according to any of the foregoing clauses further includes one or more conduits coupled to the housing and fluidly connected to the bleed chamber, wherein at least a portion of the first material is positioned in a circumferential position adjacent to the one or more conduits.

[0115] An engine according to any of the foregoing clauses, wherein the coefficient of thermal expansion of the first material causes a change in the size of the bleed air channel in response to a change in the temperature of the bleed air flow.

[0116] According to any of the preceding clauses of the engine, wherein the one or more baffles comprise: one or more first baffle elements, the one or more first baffle elements comprising one or more orifices, the one or more first baffle elements comprising the second material; and one or more second baffle elements fixedly coupled to the one or more first baffle elements, the one or more second baffle elements comprising the first material, the one or more second baffle elements being positioned to change the size of the one or more orifices in response to a temperature change in the bleed air flow.

[0117] An engine according to any of the foregoing clauses, wherein the one or more baffles comprise: one or more first baffle elements comprising the second material; and one or more second baffle elements fixedly coupled to the one or more first baffle elements, the one or more first baffle elements and the one or more second baffle elements defining at least a portion of the bleed air channel, and wherein the one or more second baffle elements are positioned to change the size of the bleed air channel in response to a temperature change in the bleed air flow.

[0118] The engine according to any of the foregoing clauses further includes: one or more conduits connected to the housing and fluidly connected to the bleed air chamber; one or more sensors disposed within the bleed air chamber, the one or more sensors being configured to detect at least one of pressure within the bleed air chamber or flow rate of the bleed air flow within the bleed air chamber; and a controller configured to control the one or more flow control devices to change at least one of the pressure or the flow rate based on the circumferential position of the pressure or the flow rate.

[0119] An engine according to any of the foregoing clauses, wherein at least a portion of the one or more flow control devices is located axially forward of the discharge port of the one or more pipes.

[0120] An engine according to any of the foregoing clauses, wherein the one or more flow control devices are configured to at least partially control the flow of the bleed air flow when the bleed air flow is flowing in an axial rearward direction or a radial outward direction.

[0121] An engine according to any of the foregoing clauses, wherein the engine includes a gas turbine engine.

[0122] An engine includes: a compressor including an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining a bleed chamber therebetween, the inner housing at least partially defining a bleed channel extending circumferentially around the inner housing between the primary flow path and the bleed chamber to guide a bleed airflow from the primary airflow into the bleed chamber; and one or more flow control devices circumferentially positioned around the compressor and at least partially disposed within at least one of the bleed chamber or the bleed channel, the one or more flow control devices including one or more actuators capable of actuating to circumferentially balance the flow of the bleed airflow entering or within the bleed chamber.

[0123] An engine according to any of the foregoing clauses, wherein the inner housing includes at least one wall defining the bleed air passage, and wherein the one or more actuators are actuated to move at least a portion of the at least one wall, thereby changing the size of the bleed air passage.

[0124] According to any of the preceding clauses of the engine, wherein the inner casing includes at least one wall defining the bleed air channel, and wherein the one or more actuators are actuated to move at least a portion of the at least one wall into the primary airflow.

[0125] An aircraft includes: a fuselage; a wing attached to the fuselage; and an engine including: a compressor including an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining an air bleed chamber therebetween, the inner housing at least partially defining an air bleed channel extending circumferentially around the inner housing between the primary flow path and the air bleed chamber to guide an air bleed flow from the primary airflow into the air bleed chamber; and one or more flow control devices at least partially located within at least one of the air bleed chamber or the air bleed channel, the one or more flow control devices being configured to circumferentially balance the flow of the air bleed flow entering or within the air bleed chamber.

[0126] A method for operating an engine, the engine including a compressor, the compressor including an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining a bleed chamber therebetween, the inner housing at least partially defining a bleed channel extending circumferentially around the inner housing between the primary flow path and the bleed chamber to guide a bleed airflow from the primary airflow into the bleed chamber, the method comprising: detecting at least one of a pressure within the bleed chamber or a flow rate of the bleed airflow within the bleed chamber; and controlling one or more flow control devices to circumferentially balance the flow rate of the bleed airflow entering or within the bleed chamber based on the pressure or the flow rate.

[0127] According to any of the foregoing clauses, controlling the one or more flow control devices includes actuating one or more actuators to change the size of the air intake channel.

[0128] According to any of the foregoing clauses, the one or more flow control devices include one or more baffles, the one or more baffles including one or more orifices, and wherein controlling the one or more flow control devices includes actuating one or more actuators to change the flow of the bleed airflow through the one or more orifices based on the circumferential position of the one or more orifices.

[0129] According to any of the foregoing provisions, the inner shell includes a first wall and a second wall defining the air intake channel, and the one or more flow control devices include actuating one or more actuators to move at least a portion of the first wall into the primary airflow.

[0130] According to any of the foregoing clauses of the method, wherein the engine further includes one or more conduits coupled to the housing and fluidly connected to the bleed chamber, and wherein the method further includes: controlling the one or more flow control devices to increase or decrease the flow rate at a circumferential location near the one or more conduits based on the pressure or the flow rate.

[0131] According to any of the foregoing provisions, the inner shell includes a first wall and a second wall defining the air intake channel, and the one or more flow control devices include actuating one or more actuators to move at least a portion of the first wall into the air intake channel.

[0132] A method for operating an aircraft, the aircraft including a fuselage, a wing attached to the fuselage, and an engine, the engine including a compressor, the compressor including an inner shell and an outer shell, the inner shell defining a primary flow path for a primary airflow through the compressor, the inner shell and the outer shell defining an air bleed chamber therebetween, the inner shell at least partially defining an air bleed channel extending circumferentially around the inner shell between the primary flow path and the air bleed chamber to guide an air bleed flow from the primary airflow into the air bleed chamber, the method comprising: detecting at least one of a pressure within the air bleed chamber or a flow rate of the air bleed flow within the air bleed chamber; and controlling one or more flow control devices to circumferentially balance the flow of the air bleed entering or within the air bleed chamber based on the pressure or the flow rate.

[0133] A method for operating an aircraft, the aircraft including a fuselage, wings attached to the fuselage, and an engine, the engine including: a compressor including an inner shell and an outer shell, the inner shell defining a primary flow path for a primary airflow through the compressor, the inner shell and the outer shell defining an bleed chamber therebetween, the inner shell at least partially defining an bleed channel extending circumferentially around the inner shell between the primary flow path and the bleed chamber to guide bleed airflow from the primary airflow into the bleed chamber; and one or more ducts coupled to the outer shell and fluidly connected to the bleed chamber, the method comprising: operating the engine during a takeoff flight phase of the aircraft; and, while operating the engine during the takeoff flight phase of the aircraft, controlling one or more flow control devices to reduce the flow rate of the bleed airflow at circumferential locations near the one or more ducts.

[0134] The method according to any of the foregoing clauses further includes: operating the engine during the cruise phase of the aircraft; and, while operating the engine during the cruise phase of the aircraft, controlling the one or more flow control devices to increase the flow rate of the bleed airflow at the circumferential position near the one or more ducts.

[0135] An engine includes: a compressor including an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining a bleed chamber therebetween, the inner housing at least partially defining a bleed channel extending circumferentially around the inner housing between the primary flow path and the bleed chamber to guide a bleed airflow from the primary airflow into the bleed chamber, and wherein the bleed channel includes an inlet end positioned proximate to the primary flow path and an outlet end positioned proximate to the bleed chamber and away from the inlet end; and one or more flow control devices circumferentially positioned around the compressor to actively or passively circumferentially balance the flow of the bleed airflow entering or within the bleed chamber, wherein the one or more flow control devices are at least partially disposed between the inlet end, the outlet end, or the inlet end and the outlet end.

[0136] An engine according to any of the foregoing clauses, wherein the one or more flow control devices include one or more baffles having one or more orifices, wherein the size of the one or more orifices varies based on the circumferential position of the respective one or more orifices.

[0137] According to any of the preceding clauses, the one or more flow control devices include: one or more first baffles; and one or more second baffles; and at least one of the one or more first baffles or the one or more second baffles includes one or more holes, and at least one of the one or more first baffles or the one or more second baffles is movable.

[0138] An engine according to any of the foregoing clauses, wherein the one or more flow control devices include one or more baffles having a first material and a second material, wherein the coefficient of thermal expansion of the first material is greater than the coefficient of thermal expansion of the second material.

[0139] An engine includes: a compressor including an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining a bleed chamber therebetween, the inner housing at least partially defining a bleed channel extending circumferentially around the inner housing between the primary flow path and the bleed chamber to guide a bleed airflow from the primary airflow into the bleed chamber, and wherein the bleed channel includes an inlet end positioned proximate to the primary flow path and an outlet end positioned proximate to the bleed chamber and away from the inlet end; and one or more flow control devices circumferentially positioned around the compressor to actively or passively circumferentially balance the flow of the bleed airflow entering or within the bleed chamber, wherein at least a portion of the one or more flow control devices extends axially rearward from the outlet end into the bleed chamber.

[0140] An engine according to any of the foregoing clauses, wherein at least another portion of the one or more flow control devices extends radially outward relative to the outlet end.

[0141] The engine according to any of the foregoing clauses further includes at least one conduit fluidly connected to the housing in a circumferential position to direct the bleed air flow from the bleed air chamber to one or more downstream positions, and wherein the one or more flow control devices have a length in a rear axial direction, the length varying based on the circumferential position of the at least one conduit.

[0142] According to any of the foregoing provisions, the one or more flow control devices include one or more baffles having a first material and a second material, wherein the coefficient of thermal expansion of the first material is greater than the coefficient of thermal expansion of the second material.

Claims

1. An engine, characterized in that, include: A compressor includes an inner housing and an outer housing, the inner housing defining a primary flow path for a primary airflow through the compressor, the inner housing and the outer housing defining a bleed chamber therebetween, the inner housing at least partially defining a bleed channel extending circumferentially around the inner housing between the primary flow path and the bleed chamber to guide a bleed airflow from the primary airflow into the bleed chamber; as well as One or more flow control devices are circumferentially positioned around the compressor to actively or passively balance the flow of the bleed air entering or within the bleed air chamber, wherein the one or more flow control devices are at least partially disposed within the bleed air channel, form at least a portion of the bleed air channel, or extend axially rearward from the bleed air channel.

2. The engine according to claim 1, characterized in that, in, The one or more flow control devices include one or more baffles having one or more orifices, wherein the size of the one or more orifices varies based on the circumferential position of the respective one or more orifices.

3. The engine according to claim 2, characterized in that, The device further includes one or more conduits connected to the housing and fluidly connected to the air vent, wherein the size of the one or more orifices circumferentially positioned close to the one or more conduits is smaller than the size of the one or more orifices circumferentially positioned away from the one or more conduits.

4. The engine according to claim 1, characterized in that, in, The one or more flow control devices include one or more baffles, wherein at least a portion of the one or more baffles extends axially in a rearward direction relative to the air duct, and wherein at least one of the axial length or radial position of the portion varies circumferentially based on the circumferential position of the portion.

5. The engine according to claim 1, characterized in that, in, The inner shell includes at least one wall defining the air intake channel, and the one or more flow control devices include one or more baffles that extend at least partially from the at least one wall into the air intake channel.

6. The engine according to claim 1, characterized in that, in, The one or more flow control devices include: One or more first baffles; and One or more second baffles; and The one or more first baffles or at least one of the one or more second baffles includes one or more holes, and the one or more first baffles or at least one of the one or more second baffles is movable.

7. The engine according to claim 6, characterized in that, It further includes one or more actuators capable of being actuated to move at least one of the one or more first baffles or the one or more second baffles.

8. The engine according to claim 1, characterized in that, in, The inner shell includes at least one wall defining the air intake channel, and the one or more flow control devices include at least one actuator capable of being actuated to move at least a portion of the at least one wall, thereby changing the size of the air intake channel.

9. The engine according to claim 1, characterized in that, in, The inner shell includes at least one wall defining the air intake channel, and the one or more flow control devices include at least a portion of the at least one wall.

10. The engine according to claim 1, characterized in that, in, The one or more flow control devices include one or more baffles having a first material and a second material, wherein the coefficient of thermal expansion of the first material is greater than the coefficient of thermal expansion of the second material.

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