Method and apparatus for providing cross-diffuser bleed air

Abstract

Systems, apparatuses, articles, and methods are provided for cross-diffuser bleed air. An example gas turbine engine includes a frame defining a cavity at a forward side of a diffuser of the gas turbine engine; a compressor including a diffuser defining a primary flow path to provide a flow of air to the combustor, and including at least one conduit fluidly coupled to the cavity; and a downstream sink fluidly coupled to the cavity via at least one conduit defining at least a portion of the exhaust air path.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to diffuser assemblies, and more specifically to methods and apparatus for providing cross-diffuser bleed. BACKGROUND

[0002] Typical aircraft propulsion systems include one or more gas turbine engines. For certain propulsion systems, the gas turbine engine generally includes a fan and a core arranged in flow communication with one another. Further, the core of the gas turbine engine generally includes, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air is provided from the fan to an inlet of the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. The compressed air exiting the compressor section of the gas turbine engine generally has a high velocity. However, typical combustion sections of gas turbine engines require a high pressure, low velocity airflow to reduce the likelihood of flameout, promote stable and consistent combustion, and achieve an overall improved combustion process. Accordingly, certain gas turbine engines include a diffuser designed to restore the static pressure of the compressed airflow by reducing the velocity of the compressed airflow. The diffuser includes a plurality of diffuser vanes to assist in reducing the velocity of the compressed airflow. Fuel is mixed with the compressed air and combusted within the combustion section to provide combustion gases. The combustion gases are directed from the combustion section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section, which is then directed through the exhaust section, for example, to the atmosphere.

[0003] A secondary purpose of the compressor, particularly the high pressure compressor, is to provide bleed air (e.g., bleed air) for use in other systems of the aircraft (e.g., cabin pressure, turbine cooling, air conditioning, oil sump pressurization, ice protection, etc.). The bleed air is compressed air bled from a primary flow path of the compressor section upstream of the fuel combustion section of the gas turbine engine. BRIEF DESCRIPTION OF DRAWINGS

[0004] Figure 1 is a cross-sectional view of an example engine in which examples disclosed herein can be implemented.

[0005] Figure 2 is a cross-sectional view of a portion of an example engine including an example bleed air system having an example diffuser in accordance with the teachings of the present disclosure.

[0006] Figure 3 is a perspective view of an example diffuser in accordance with the teachings of the present disclosure. Figure 2

[0007] Figure 4A is a cross-sectional view of a portion of an example engine including an example bleed air system having an example diffuser in accordance with the teachings of the present disclosure. Figure 3 Figure 2 ​​cross-sectional view of a portion of an example diffuser.

[0008] Figure 4B is a cross-sectional view of another example diffuser according to the teachings of this disclosure. Figure 3 is a cross-sectional view of another example diffuser according to the teachings of this disclosure. Figure 2 is a cross-sectional view of another example diffuser according to the teachings of this disclosure.

[0009] Figure 4C is a cross-sectional view of another example diffuser according to the teachings of this disclosure. Figure 3 is a cross-sectional view of another example diffuser according to the teachings of this disclosure. Figure 2 is a cross-sectional view of another example diffuser according to the teachings of this disclosure.

[0010] Figure 5 is a cross-sectional view of another example exhaust air system having another example diffuser according to the teachings of this disclosure.

[0011] Figure 6 is a cross-sectional view of another example exhaust air system having another example diffuser according to the teachings of this disclosure.

[0012] Figure 7 is a cross-sectional view of another example exhaust air system having another example diffuser according to the teachings of this disclosure.

[0013] Figure 8 is a cross-sectional view of another example diffuser according to the teachings of this disclosure. Figure 2 is a cross-sectional view of a portion of another example diffuser according to the teachings of this disclosure.

[0014] Figure 9 is a flowchart representing an example process for directing exhaust air within an engine using a diffuser according to the teachings of this disclosure. Figure 2

[0015] Figure 10 is a flowchart representing an example process for manufacturing an example diffuser according to the teachings of this disclosure. Figure 2

[0016] Generally, across the entire drawing figures and accompanying written description, like reference numerals will be used to refer to like or similar components. The drawing figures are not necessarily to scale. Instead, the thickness of layers or regions can be exaggerated in the drawing figures. Although these drawing figures show layers and regions as having clear lines and boundaries, some or all of these lines and / or boundaries can be idealized. In fact, the boundaries and / or lines can be unobservable, mixed, and / or irregular. DETAILED DESCRIPTION

[0017] ​​In the following detailed description, reference is made to the accompanying drawings that form a part hereof, and in which are shown, by way of illustration, specific examples in which the subject matter can be practiced. These examples are described in sufficient detail to enable those skilled in the art to practice the subject matter, and it is to be understood that other examples can be utilized. The following detailed description is, therefore, not to be taken in a limiting sense. Certain features from the various aspects of the description below can be combined to form yet further new aspects of the subject matter.

[0018] “Include” and “comprise” (and all forms of these terms) are used herein as open-ended terms. Thus, whenever a claim employs any form of “include” or “comprise” (e.g., comprises, includes, containing, having, etc.) as a preamble or in any part of a claim it is to be understood that additional elements, terms, etc. can be present in the corresponding claim or statement. As used herein, when the phrase “at least” is used as the transition term in, for example, a preamble of a claim, it is open-ended in the sense that additional elements, terms, etc. can be present in the corresponding claim or statement. For example, when used in the context of a set of items, the term “and / or” is intended to mean that at least one of the items, or any combination of one or more of the items, can be present. Similarly, as used herein in the context of describing structural, compositional, or other physical and / or functional characteristics of structures, components, items, objects, and / or things, the phrase “at least one of’ is intended to mean that at least one of the recited items, or any combination of one or more of the recited items, can be present. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or other events, the phrase “at least one of” is intended to mean that at least one of the recited processes, instructions, actions, activities, and / or other events can be performed or executed. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or other events, the phrase “at least one of” is intended to mean that at least one of the recited processes, instructions, actions, activities, and / or other events can be performed or executed.

[0019] As used herein, singular references (e.g., “a,” “an,” “one,” “first,” “second,” etc.) are not excluded from a plural interpretation unless the context clearly indicates otherwise. As used herein, the term “a” or “an” object refers to one or more of the object. The terms “a” (or “an”), “one or more,” and “at least one” are used interchangeably herein. Furthermore, although individually listed, a plurality of means, elements or actions can be implemented by, e.g., a single entity or object. Additionally, although various features can be included in different examples or claims, these features can also be combined, and the combination of features is possible even if the features are not explicitly stated in a claim.

[0020] As used herein, unless otherwise stated, the term “above” describes a relationship with respect to the earth of two portions. If a second portion has at least a portion between the earth and a first portion, the first portion is above the second portion. Likewise, as used herein, a first portion is “below” a second portion when the first portion is closer to the earth than the second portion. As described above, a first portion can be above or below a second portion with one or more of: having other portions therebetween, having no other portions therebetween, the first portion and the second portion in contact, or the first portion and the second portion not in direct contact with each other.

[0021] As used in this patent, to state that any portion (e.g., a layer, film, zone, region, or plate) is on (e.g., positioned on, located on, disposed on, or formed on another portion, etc.) another portion in any manner indicates that the referenced portion is in contact with the other portion, or that the referenced portion is above the other portion with one or more intervening portions therebetween.

[0022] As used herein, unless otherwise stated, a connection reference (e.g., attached, coupled, connected, and joined) can include intermediate members between the elements being connected reference and / or relative movement between these elements. Thus, a connection reference does not necessarily infer that two elements are directly connected and / or in fixed relation to one another. As used herein, to state that any portion is “in contact” with another portion means that there are no intervening portions between the two portions.

[0023] Unless specifically stated otherwise, descriptors used herein, such as “first,” “second,” “third,” etc., do not in any way connote or otherwise imply any priority, physical order, arrangement, and / or ordering of elements, but are merely used as labels and / or arbitrary names to facilitate understanding of the disclosed examples. In some examples, a descriptor “first” can be used to refer to an element in the detailed description, while the same element can be referred to with a different descriptor (e.g., “second” or “third”) in the claims. In such instances, it should be understood that the descriptors are used only to clearly identify the elements in the context of the discussion (e.g., within the claims).

[0024] As used herein, “approximately” and “about” modify a value or a subject by accounting for variations that can exist in real-world applications. For example, “approximately” and “about” can modify a dimension to account for manufacturing tolerances and / or other real-world defects that can not be precise, as will be understood by those of ordinary skill in the art. For example, “approximately” and “about” can mean that the dimensions can be within a tolerance range of + / - 10%, unless otherwise specified herein.

[0025] Bleed air is extracted from a compressor section of a gas turbine engine for use in other systems of an aircraft via a bleed air system. The bleed air system uses a network of tubing (e.g., tubes, pipes, etc.) and valves to direct bleed air from the compressor section to various locations within the aircraft to achieve a plurality of bleed air functions. Such bleed air functions include, but are not limited to, providing cabin pressure, turbine cooling, air conditioning, oil sump pressurization, anti-icing, and powering engine starters.

[0026] Some known bleed air systems utilize external piping, fittings, and check valves to direct bleed air to its destinations. The external path of the bleed air needs to be reduced to prevent potential damage to the external components of the bleed air system that can occur during installation, maintenance, and use caused by, for example, foreign objects. For example, such reductions include check valves and redundant flow paths, which increase the number of parts of the system, the required maintenance, and installation steps. In addition to the existing bleed air systems requiring a large amount of maintenance, the external tubing and valve network also contribute to the overall weight of the engine. As gas turbine engines become smaller and smaller, the weight of the external components of the existing bleed air systems becomes a larger and larger percentage of the total weight of the engine, limiting the range of the engine and increasing the fuel consumption of the engine. Therefore, the performance of existing aircraft engines is poor due to the increased weight of the external bleed air system, the limited functionality of using bleed air, or the need for alternative mechanisms to achieve these functions, which also increases the overall weight of the aircraft.

[0027] The methods, systems, and devices disclosed herein direct bleed air within a gas turbine engine. The bleed air systems disclosed herein include a radial diffuser having at least one bleed air conduit (e.g., conduit) to direct bleed air from a forward side of the diffuser to an aft side of the diffuser. As used herein, the “forward” and “aft” sides of the diffuser are defined with respect to a main flow path that is radially diverted through the diffuser. The forward side of the diffuser is along the main flow path in the direction of the upstream compressor. The aft side of the diffuser is along the main flow path in the direction of the downstream turbine.

[0028] The methods, systems, and devices disclosed herein include a frame that defines a bleed air cavity (e.g., cavity) on the forward side of the diffuser, a combustor, and a downstream water trough. In examples disclosed herein, the compressor includes a diffuser having a plurality of surfaces that define a plurality of discrete passageways to provide airflow to a downstream combustor. In some examples, the plurality of surfaces are a plurality of diffuser vanes, a plurality of ducts, a plurality of holes, etc. At least one bleed air conduit is included between respective ones of the plurality of surfaces to enable bleed air to flow from the forward side of the diffuser to the aft side of the diffuser. In some examples, the number of gaps between the discrete passageways that include the at least one bleed air conduit, the number of bleed air conduits included in the gaps, the size of the at least one bleed air conduit, and the shape of the at least one bleed air conduit can be determined based on a plurality of design considerations, including but not limited to: the amount of bleed air required for bleed air functionality, the size of the gaps, the shape of the gaps, the number of gaps in the diffuser, the distance between the gaps, etc. For example, the at least one bleed air conduit can have an elliptical cross-sectional shape to enable sufficient bleed air to be supplied through the diffuser.

[0029] In some examples, the surfaces are additively manufactured using the at least one bleed air conduit. In other examples, the diffuser is machined, brazed, or welded. For example, the at least one bleed air conduit can be drilled into the diffuser in the gaps. In some examples, the diffuser is a unitary piece. In other examples, the diffuser is composed of multiple pieces that are assembled together.

[0030] In some examples, at least one channel is fluidly coupled to an air duct at the rear of the diffuser, and this at least one channel receives exhaust air from the bleed chamber via the air duct. In some examples, the gas turbine engine includes a pipe coupled to the diffuser, which is fluidly coupled to the bleed chamber via at least one air duct. The number of channels, the size of the channels, and the shape of the channels depend on, for example, the amount of exhaust air required for the exhaust air function, the number of aircraft and / or engine systems requiring exhaust air, the number of gaps including at least one air duct, the number of air ducts, and the amount of available space in the engine for the channels. In some examples, the exhaust air system is a passive exhaust air system, meaning that exhaust air is supplied to downstream tanks without intervention from the control system. In other examples, at least one channel includes at least one fluid control valve and at least one controller to control the amount of exhaust air directed to at least one downstream tank. For example, at least one controller may determine that the aircraft and / or engine system no longer requires an exhaust air supply and activate at least one fluid control valve to limit the exhaust air flow to the first of at least one downstream tank.

[0031] The exhaust air system disclosed herein supplies exhaust air to the downstream tank via an internal exhaust air path within the gas turbine engine. This results in a shortened exhaust air path length, fewer parts, reduced weight, lower cost, increased durability, and improved maintainability. By removing external exhaust air system components, the exhaust air system also reduces nacelle drag by decreasing the engine's frontal area. In some examples, the exhaust air system is entirely integrated within the gas turbine engine. By incorporating the entire exhaust air system within the gas turbine engine, potential damage to external components of the exhaust air system that could occur during installation, maintenance, and use is avoided. In some examples, the exhaust air system does not include any check valves or redundant flow paths.

[0032] Now refer to the attached diagram, Figure 1 This is a cross-sectional view of example engine 10 (e.g., a turbofan gas turbine engine). Figure 1 As shown, engine 10 has a longitudinal or axial centerline axis 12 through which for reference. Engine 10 also defines an upstream end 99 and a downstream end 98 for reference. Typically, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14. For reference, engine 10 defines an axial direction A, a radial direction R, and a circumferential direction C. Typically, the axial direction A extends parallel to the axial centerline axis 12, the radial direction R extends outward and inward from the axial centerline axis 12 in a direction orthogonal to the axial direction A, and the circumferential direction extends 360° around the axial centerline axis 12.

[0033] The core engine 16 can generally include a substantially tubular outer casing 18 defining an annular inlet 20. The outer casing 18 encloses or at least partially forms, in serial flow relationship, a compressor section having a booster or low pressure (LP) compressor 22, a high pressure (HP) compressor 24; a combustor 26; an expansion section or turbine section including a high pressure (HP) turbine 28, a low pressure (LP) turbine 30; and an ejection exhaust nozzle section 32. The HP compressor 24 includes a high pressure multi-stage axial compressor 50 and a single-stage centrifugal compressor 52 as a final compressor stage. The single-stage centrifugal compressor 52 includes a diffuser 54. In some examples, the diffuser 54 can be implemented with the novel structures disclosed herein in connection with Figures 2-7 An outlet guide vane (OGV) is disposed between the multi-stage axial compressor 50 and the single-stage centrifugal compressor 52. The HP compressor 24 includes a forward casing and an aft casing. The forward casing generally surrounds the axial compressor 50 and the aft casing generally surrounds the centrifugal compressor 52.

[0034] A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 can also be connected to a fan shaft 38 of the fan assembly 14. In certain examples, as Figure 1 shown, the LP rotor shaft 36 is connected to the fan shaft 38 via a reduction gear 40, for example, in an indirect drive or geared drive configuration.

[0035] As Figure 1 shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan casing or nacelle 44 can circumferentially surround at least a portion of the fan assembly 14 and / or the core engine 16. It will be appreciated by those skilled in the art that the nacelle 44 can be configured to be supported relative to the core engine 16 by a plurality of circumferentially spaced OGVs or struts 46. Further, at least a portion of the nacelle 44 can extend over an outer portion of the core engine 16 so as to define a fan flow passage 48 therebetween. It will be appreciated, however, that various configurations of the engine 10 can omit the nacelle 44 or omit the nacelle 44 extending around the fan blades 42.

[0036] It should be appreciated that the combination of shafts 34, 36, compressors 22, 24, and turbines 28, 30 define a rotor assembly 90 of engine 10. For example, the HP rotor shaft 34, HP compressor 24, and HP turbine 28 can define a high speed or HP rotor assembly of engine 10. Similarly, the combination of LP rotor shaft 36, LP compressor 22, and LP turbine 30 can define a low speed or LP rotor assembly of engine 10. Various examples of engine 10 can also include a fan shaft 38 and fan blades 42 as a LP rotor assembly. In certain examples, engine 10 can also define a fan rotor assembly that is mechanically decoupled from the LP spool at least in part via fan shaft 38 and reduction gear 40. Further examples can further define one or more intermediate rotor assemblies (not shown) defined by an intermediate pressure compressor, an intermediate pressure shaft, and an intermediate pressure turbine disposed between the LP rotor assembly and the HP rotor assembly (relative to a serial aerodynamic flow arrangement).

[0037] During operation of engine 10, a flow of air, schematically illustrated by arrow 74, enters an inlet 76 of engine 10 defined by a fan case or nacelle 44. A portion of the air, schematically illustrated by arrow 80, enters the core engine 16 through an annular inlet 20 defined at least in part via outer case 18. The flow of air is provided through compressors 22, 24, combustor 26, and expansion section in a serial flow manner via core flow path 70. As the flow of air 80 flows through successive stages of compressors 22, 24, the flow of air 80 is compressed more and more, as schematically illustrated by arrow 82. As the flow of air 80 flows through successive stages of multi-stage axial compressor 50, the flow of air 80 is compressed more and more. The compressed air is discharged from the impeller of centrifugal compressor 52, directly into diffuser 54, then through a deswirler and into combustor 26.

[0038] The compressed air 82 enters combustor 26 and is mixed with liquid and / or gaseous fuel and ignited to produce a combustion gas 86. It should be appreciated that combustor 26 can form a suitable system for producing a combustion gas, including but not limited to a deflagration or detonation combustion system, or combinations thereof. Combustor 26 can include an annular, can, barrel, trapped vortex, involute or scroll, rich, lean, rotary detonation, or pulse detonation configuration, or combinations thereof.

[0039] Combustion gas 86 releases energy to drive rotation of the HP and LP rotor assemblies before being discharged from the injection exhaust nozzle section 32. The release of energy from combustion gas 86 further drives rotation of the fan assembly 14, including fan blades 42. A portion of air 74 bypasses core engine 16 and flows through fan flow passage 48, as schematically illustrated by arrow 78.

[0040] It should be appreciated that Figure 1 A dual-flow engine having a fan flow passage 48 and a core flowpath 70 is depicted and described. Figure 1 The depicted example has a nacelle 44 surrounding the fan blades 42 in order to provide noise attenuation, blade-off protection, and other known benefits for the nacelle, and it can be referred to herein as a "ducted fan," or the entire engine 10 can be referred to as a "ducted engine."

[0041] Figure 2 An example gas turbine engine 200 including an example bleed air system 202 is shown. The example gas turbine engine 200 includes the example bleed air system 202, an example impeller 204, an example diffuser 206, an example de-swirler 208, and an example combustor 210. In Figure 2 In the shown example, the diffuser 206 and de-swirler are joined using an outer frame member 212 and an inner frame member 214. In addition, a plurality of fasteners 216 are used to join these various components together and secure the diffuser 206 and de-swirler 208 in the gas turbine engine 200. An impeller shroud 218 surrounds the impeller 204 and defines an outer flowpath surface that closely surrounds the impeller blades of the impeller 204. In some examples, the diffuser 206 can be integrally formed with the de-swirler 208, the outer frame member 212, the impeller shroud 218, and / or an example frame 220 that defines a bleed air cavity 222.

[0042] The example bleed air system 202 includes an example frame 220 that defines a bleed air cavity 222, an example diffuser 206, an example passage 224, and an example port 226. The example bleed air system 202 is a passive bleed air system. In other examples, the bleed air system 202 can be an active bleed air system. The example bleed air cavity 222 receives bleed air 228 from a main flowpath 250. The diffuser 206 directs the bleed air 228 from a forward side of the diffuser 206 to an aft side of the diffuser 206 via an example bleed air conduit 230. The passage 224 receives the bleed air 228 at the aft side of the diffuser 206 and directs the bleed air 228 to at least one downstream sink 232 for use by at least one aircraft or engine system. In some examples, the bleed air 228 travels from a forward side of the diffuser 206 to the aft side of the diffuser 206 entirely inside the gas turbine engine 200. In some examples, the example passage 224 includes at least one fluid control valve and at least one controller to control an amount of bleed air 228 directed to the at least one downstream sink 232. For example, the at least one controller can determine that the aircraft and / or engine system no longer requires a supply of bleed air 228 and activate the at least one valve to restrict the flow of bleed air 228 to a first of the at least one downstream sinks.

[0043] In some examples, the exhaust air system 202 is fully integrated within the gas turbine engine 200. By integrating the entire exhaust air system 202 within the gas turbine engine 200, potential damage to external components of the exhaust air system 202 that could occur during installation, maintenance, and use is prevented. For example, the exhaust air system 202 can eliminate check valves or redundant flow paths that would otherwise be necessary in a conventional external design.

[0044] Diffuser 206 includes multiple diffuser blades ( Figure 2 Not shown in the image, see [link / reference]. Figure 3 These diffuser blades define multiple discrete pathways. Figure 2 Not shown in the image, see [link / reference]. Figure 3 This provides a primary flow path for supplying air to the burner 210. In other examples, the diffuser 206 includes multiple ducts, multiple orifices, etc., to define the primary flow path. Example bleed air duct 230 is included in one of multiple diffuser blades. In some examples, the diffuser 206 includes more than one bleed air duct 230 (e.g., two diffuser blades, three diffuser blades, etc.) in more than one diffuser blade (e.g., two bleed air ducts, three bleed air ducts, four bleed air ducts, etc.). For example, the diffuser 206 may include a first bleed air duct 230 located in a first diffuser blade and a second bleed air duct 230 located in a second diffuser blade. In some examples, the number of bleed air ducts 230 and the number of diffuser blades including at least one bleed air duct 230 are determined based on at least one of several factors, including but not limited to: the amount of exhaust air 228 required for the exhaust air function, the size of the diffuser blades, the shape of the diffuser blades, the number of diffuser blades in the diffuser 206, and the distance between the diffuser blades.

[0045] The cross-sectional shape of the air intake conduit 230 can be circular, elliptical, square, triangular, rectangular, or other two-dimensional geometric shapes. In some examples, the cross-sectional shape of the air intake conduit 230 varies along its length. For example, the air intake conduit 230 may have an elliptical cross-sectional shape at its first end and a circular cross-sectional shape at its second end. In some examples, the cross-sectional shape of the air intake conduit 230 is rounded to reduce stress concentration caused by localized stress concentrations (e.g., sharp corners, grooves, notches, etc.).

[0046] In some examples, the shape of the bleed air duct 230 can be determined based on several factors, including but not limited to: the amount of exhaust air required for the exhaust air function, the size of the diffuser blades, the shape of the diffuser blades, the number of diffuser blades in the diffuser, and the distance between the diffuser blades. For example, the shape of the bleed air duct 230 can have an elliptical cross-section to accommodate the amount of exhaust air 228 required to pass through the diffuser 206. In this example, due to the ratio of the length to the width of the diffuser blades, the elliptical cross-section can allow the cross-sectional area of ​​the bleed air duct 230 to be larger than other shapes. In some examples, the first bleed air duct 230 has a first cross-sectional shape, and the second bleed air duct 230 has a second cross-sectional shape. For example, the first bleed air duct 230 can have a first cross-sectional shape of a rounded (e.g., rounded) rectangle in a first portion of the diffuser blades and a second cross-sectional shape of a circle in a second portion of the diffuser blades near the tip of the diffuser blades. The cross-sectional shape of the bleed air duct 230 can be any shape inside the diffuser blades, providing sufficient flow area for the downstream tank 232.

[0047] In some examples, the diffuser blades of diffuser 206 are cast or additively manufactured using at least one bleed air duct 230. In other examples, diffuser 206 is machined, brazed, or welded. For example, after the diffuser blades are brazed to the remainder of diffuser 206, at least one bleed air duct 230 may be drilled into the diffuser blades. In some examples, diffuser 206 is a single piece. In other examples, diffuser 206 consists of multiple parts assembled together.

[0048] Example channel (e.g., pipe, tube, etc.) 224 is connected to diffuser 206 at first end 234. Figure 2 In the example shown, channel 224 extends through inlet 236 provided by port 226, and at the second end ( Figure 2 (Not shown) is connected to at least one downstream tank 232. In some examples, the number of channels 224, the size of channels 224, and the shape of channels 224 depend on, for example, the amount of exhaust air 228 required for exhaust air function, the number of aircraft and / or engine systems that require exhaust air 228, the number of diffuser blades including at least one bleed air duct 230, the number of bleed air ducts 230, and the amount of available space in the gas turbine engine 200 for channels 224.

[0049] Figure 3is a perspective view of an example diffuser 206. As shown, the diffuser 206 includes an annular inner shell 302, an outer shell 304, and a plurality of diffuser vanes 306. The inner shell 302 and the outer shell 304 extend along a circumferential direction C and are spaced apart from one another in a radial direction R to define a flow passage. The diffuser vanes 306 are positioned within the flow passage such that the inner shell 302, the outer shell 304, and the diffuser vanes 306 define a plurality of fluid passages 308. In Figure 3 examples, the plurality of surfaces are the diffuser vanes 306. More specifically, the diffuser vanes 306 extend between the inner shell 302 and the outer shell 304 to divide the flow passage into the plurality of fluid passages 308 and split the flow of compressed air. In Figure 3 the illustrated example, the diffuser 206 includes thirty-six diffuser vanes 306 (not all shown) that define thirty-six fluid passages 308 (not all shown) that are evenly spaced about the circumferential direction C. However, it should be appreciated that a suitable number of diffuser vanes 306 can be used in accordance with alternative embodiments, e.g., more than twenty diffuser vanes 306, more than thirty diffuser vanes 306, etc. In some examples, the diffuser vanes 306 are unevenly spaced about the circumferential direction C. At least one of the plurality of diffuser vanes 306 includes at least one bleed air conduit 310 (shown in Figure 4A to direct bleed air from a front side of the diffuser 206 to a rear side of the diffuser 206. In some examples, the at least one bleed air conduit 310 receives bleed air from a bleed air cavity of the front side of the diffuser 206 and directs the bleed air to at least one passage of the rear side of the diffuser 206.

[0050] Figure 4A is a cross-sectional view of a portion of the example diffuser 206 taken along line 9-9 of Figure 3 is a cross-sectional view of a portion of the example diffuser 206 taken along line 9-9 of Figure 4A the illustrated example, the diffuser 206 includes a plurality of diffuser vanes 306. For clarity, two diffuser vanes 306 are labeled, but Figure 4A more diffuser vanes 306 are shown in FIG. 4. The plurality of diffuser vanes 306 includes a first diffuser vane 402 and a second diffuser vane 404. The first diffuser vane 402 has a length 406 and a width 408 at its widest point. In some examples, the length 406 of the first diffuser vane 402 is different than the length 406 of the second diffuser vane 404. In some examples, the width 408 of the first diffuser vane 402 is different than the width 408 of the second diffuser vane 404. The first diffuser vane 402 includes a bleed air conduit 412. In some examples, the first diffuser vane 402 includes more than one bleed air conduit 412 (e.g., two bleed air conduits, three bleed air conduits). The bleed air conduit 412 receives bleed air from a bleed air cavity 222 (shown in Figure 4Aexhaust air 228 travels through the diffuser 206 via the bleed air conduit 412. The exhaust air 228 then travels to at least one downstream water trough 232 (not shown in FIG. 2) positioned at a rear side of the diffuser 206. Figure 4A

[0051] In the illustrated example, the bleed air conduit 412 has an elliptical cross-sectional shape. In other examples, the bleed air conduit 412 has a circular, rectangular, square, triangular, or other two-dimensional geometric cross-sectional shape. In some examples, the size and shape of the bleed air conduit 412 can be determined based on a number of factors including, but not limited to: the amount of exhaust air 228 required for the exhaust air function, the size of the first diffuser vane 402, the shape of the first diffuser vane 402, the number of diffuser vanes 306 in the diffuser 206, and the distance between the first diffuser vane 402 and the second diffuser vane 404. For example, the size of the bleed air conduit 412 is limited by the length 406 and width 408 of the first diffuser vane 402. Figure 4B and Figure 4C is a cross-sectional view of an alternative embodiment of the example diffuser 206. In Figure 4B In the illustrated example, the diffuser vanes 306 each include three bleed air conduits 420. For example, the first diffuser vane 422 includes a first bleed air conduit 420A, a second bleed air conduit 420B, and a third bleed air conduit 420C. In Figure 4B In the illustrated example, the first, second, and third bleed air conduits 420A-C each have a cross-sectional area with a rounded rectangular shape. In other examples, the shape of the cross-sectional area of one or more of the first, second, and / or third bleed air conduits 420A-C is different than the shape of the cross-sectional area of another one of the first, second, and / or third bleed air conduits 420A-C. The example second bleed air conduit 420B is positioned at a center of the first diffuser vane 422 and has a larger cross-sectional area than the first bleed air conduit 420A, which in turn has a larger cross-sectional area than the third bleed air conduit 420C. In some examples, any of the cross-sectional areas of the first, second, and third bleed air conduits 420A-C can be larger and / or smaller than illustrated. For example, in some examples, the third bleed air conduit 420C can have the largest cross-sectional area of the first, second, and third bleed air conduits 420A-C. Figure 4B In the illustrated example, the diffuser vanes 306 each include three bleed air conduits 420. For example, the first diffuser vane 422 includes a first bleed air conduit 420A, a second bleed air conduit 420B, and a third bleed air conduit 420C. In

[0052] In Figure 4C ​In the illustrated example, the diffuser vanes 306 include a first diffuser vane 430A, a second diffuser vane 430B, a third diffuser vane 430C, a fourth diffuser vane 430D, and a fifth diffuser vane 430E. The first diffuser vane 430A does not include a bleed conduit, the second diffuser vane 430B and the fifth diffuser vane 430E include one bleed conduit 432, and the third diffuser vane 430C and the fourth diffuser vane 430D include three bleed conduits 432. In some examples, the cross-sectional shape of the bleed conduits 432 varies within an individual diffuser vane 430A, 430B, 430C, 430D, 430E. For example, the third diffuser vane 430C includes a first bleed conduit 432A having a rounded rectangular cross-sectional shape and a second bleed conduit 432B having a circular cross-sectional shape. In some examples, the cross-sectional shape of the bleed conduits varies across the diffuser vanes 430A, 430B, 430C, 430D, 430E. For example, the bleed conduit 432C of the second diffuser vane 430B has a rounded rectangular cross-sectional shape and the bleed conduit 432D has an elongated crescent-shaped cross-sectional shape.

[0053] In other examples, at least one of the first, second, third, fourth, and / or fifth diffuser vanes 430A-E includes more or fewer bleed conduits 432 than included in the first, second, third, fourth, and / or fifth diffuser vanes 430A-E included in FIG. 4. Figure 4C In other examples, at least one of the first, second, third, fourth, and / or fifth diffuser vanes 430A-E includes more or fewer bleed conduits 432 than included in the first, second, third, fourth, and / or fifth diffuser vanes 430A-E included in FIG. 4.

[0054] In some examples, the structural design of the diffuser vanes 430A-E and the arrangement of the bleed conduits 432 in the diffuser vanes 430A-E depend on a number of design parameters including, but not limited to, bleed air flow requirements, weight of the diffuser 206, local loads experienced by the diffuser vanes 430A-E (e.g., loads caused by pressure differentials), and engine airframe loads. For example, the inclusion of bleed conduits 432 in the diffuser vanes 430A-E can impede the ability of the diffuser vanes 430A-E to withstand the forces they are subjected to in the compressor. In some examples, the metal surface of the diffuser vanes 430A-E around the bleed conduits 432 provides structural support to the diffuser vanes 430A-E.

[0055] Figure 5A portion of another example engine 500 is shown. Engine 500 includes an example exhaust air system 502. The example exhaust air system 502 includes an example impeller shroud 504 defining an air bleed chamber 506, an example diffuser 508, and an example plurality of channels 510. The example air bleed chamber 506 receives exhaust air 512 from the primary flow path of the compressor of engine 500. The diffuser 508 includes an air bleed duct 514. The diffuser 508 guides the exhaust air 512 from the front side of the diffuser 508 to the rear side of the diffuser 508 via the air bleed duct 514. The plurality of channels 510 receive the exhaust air 512 at the rear side of the diffuser 508 and guide the exhaust air 512 to at least one downstream tank. Figure 5 (Not shown) for use by at least one aircraft and / or engine system. In some examples, exhaust air 512 travels from the front side of diffuser 508 to the rear side of diffuser 508, entirely within the interior of engine 500 (e.g., within engine 500). In some examples, the plurality of channels 510 include at least one fluid control valve and at least one controller to control the amount of exhaust air 512 directed to at least one downstream tank. For example, at least one controller may determine that the aircraft and / or engine system no longer requires a supply of exhaust air 512 and activate at least one valve to restrict the flow of exhaust air 512 to the first of at least one downstream tank.

[0056] In some examples, the exhaust air system 502 is entirely integrated within the engine 500 (e.g., inside the engine 500). By including the entire exhaust air system 502 inside the engine 500, potential damage to external components of the exhaust air system 502 that may occur during installation, maintenance, and use is reduced or eliminated. For example, the exhaust air system 502 may not include any check valves or redundant flow paths required in external implementations.

[0057] In some examples, the multiple channels 510 are additively formed. In some examples, the multiple channels 510 are separate from each other. In other examples, the multiple channels 510 are connected together. In some examples, the multiple channels 510 include a first set of channels connected together and a second set of channels connected together, the first set of channels and the second set of channels being separate from each other. The number of multiple channels 510, the size of the multiple channels 510, and the shape of the multiple channels 510 can be determined by a number of factors, including, for example, the amount of exhaust air 512 used for exhaust air function, the number of aircraft and / or engine systems using exhaust air 512, the number of surfaces including at least one bleed air duct 514, the number of bleed air ducts 514, and the amount of space in the engine 500 available for the multiple channels 510.

[0058] Figure 6A portion of another example engine 600 is shown. Engine 600 includes an example exhaust air system 602. The example exhaust air system 602 includes an example frame 604 defining an air bleed chamber 606, an example diffuser 608, an example pipe 610, and an example port 612. The example air bleed chamber 606 receives exhaust air 614 from the primary flow path of the compressor of engine 600. The diffuser 608 includes an air bleed duct 616. The diffuser 608 guides exhaust air 614 from the front side of the diffuser 608 to the rear side of the diffuser 608 via the air bleed duct 616. The pipe 610 receives exhaust air 614 at the rear side of the diffuser 608 and guides exhaust air 614 to at least one downstream tank. Figure 6 (Not shown) for use by at least one aircraft and / or engine system. In some examples, exhaust air 614 travels from the front of diffuser 608 to the rear of diffuser 608, entirely within the engine 600. In some examples, pipe 610 includes at least one fluid control valve and at least one controller to control the amount of exhaust air 614 directed to at least one downstream tank. For example, at least one controller may determine that the aircraft and / or engine system no longer requires a supply of exhaust air 614 and activate at least one valve to restrict the flow of exhaust air 614 to the first of at least one downstream tank.

[0059] In some examples, the exhaust air system 602 is fully integrated within the engine 600. By including the entire exhaust air system 602 inside the engine 600, potential damage to external components of the exhaust air system 602 that may occur during installation, maintenance, and use is reduced and / or avoided. In some examples, the exhaust air system 602 does not include any check valves or redundant flow paths.

[0060] In some examples, the tube 610 is brazed or welded into place. In other examples, the tube 610 is additively formed. In some examples, the tube 610 and the port 612 are integrally formed. In some examples, the tube 610 includes at least one bend 618. In the illustrated example, the centerline bend radius of the at least one bend 618 is equal to the diameter of the tube 610. In other examples, the centerline bend radius of the at least one bend 618 is different from the diameter of the tube 610. Figure 6The tube 610 has a uniform diameter throughout the length of the tube 610. In other examples, the diameter of the tube 610 is not constant throughout the tube 610. For example, the tube 610 can have a first diameter at a first location and a second diameter at a second location, the second diameter being different than the first diameter. In some examples, the bleed air system 602 includes a plurality of tubes 610. The number of tubes 610, the size of the tubes 610, and the shape of the tubes 610 can be determined by a number of factors including, for example, the amount of bleed air 614 used for the bleed air function, the number of aircraft and / or engine systems using the bleed air 614, the number of surfaces including the at least one bleed air duct 616, the number of bleed air ducts 616, and the amount of space available in the engine 600 for the tubes 610.

[0061] Figure 7 A portion of another example engine 700 is shown. The engine 700 includes an example bleed air system 702. The example bleed air system 702 includes an example frame 704 defining a bleed air cavity 706, an example diffuser 708, and an example tube section 710. The example bleed air cavity 706 receives bleed air 712 from a primary flow path of a compressor of the engine 700. The diffuser 708 includes a bleed air duct 714. The diffuser 708 directs the bleed air 712 from a front side of the diffuser 708 to a back side of the diffuser 708 via the bleed air duct 714. The tube section 710 receives the bleed air 712 at the back side of the diffuser 708 and directs the bleed air 712 to at least one downstream sink (not shown) for use by at least one aircraft and / or engine system. In some examples, the bleed air 712 travels from the front side of the diffuser 708 to the back side of the diffuser 708 entirely inside the engine 700. In some examples, the tube section 710 includes at least one fluid control valve and at least one controller to control the amount of bleed air 712 directed to the at least one downstream sink. For example, the at least one controller can determine that the aircraft and / or engine system no longer requires a supply of bleed air 712 and activate the at least one valve to restrict the flow of bleed air 712 to a first of the at least one downstream sinks. Figure 7

[0062] ​In some examples, the exhaust air system 702 is completely integrated within the engine 700. By including the entire exhaust air system 702 inside the engine 700, potential damage to external components of the exhaust air system 702 that may occur during installation, maintenance, and use is reduced or eliminated. For example, the exhaust air system 702 may not include any check valves or redundant flow paths. A first portion 716 of the piping section 710 forms the internal contour of the housing 718 of the engine 700. A second portion 720 of the piping section 710 is coupled to the rear side of the diffuser 708 at a first end 722 and connected to the first portion 716 of the piping section 710 at a second end 724. The piping section is fluidly coupled to the bleed air duct 714 and at least one downstream water tank. Figure 7 (Not shown in the image). In some examples, the size and shape of the duct section 710 can be determined by a number of factors, including, for example, the amount of exhaust air 712 used for exhaust air functions, the number of aircraft and / or engine systems using the exhaust air 712 via the duct section 710, the number of surfaces including at least one bleed air duct 714, the number of bleed air ducts 714, and the amount of space in the engine 700 available for the duct section 710.

[0063] Figure 8 This is a cross-sectional view as part of another embodiment of a diffuser 800 for providing cross-diffuser bleed air according to the teachings of this disclosure. The diffuser 800 includes a plurality of conduits 802, a respective conduit 802 extending from an inner radius 840 of the diffuser 800 to an outer radius 842 of the diffuser 800. The plurality of conduits 802 define a plurality of discrete fluid paths to divert compressed air flows to be supplied to downstream combustors. In other examples, the discrete fluid paths for the primary flow path to the downstream combustor are defined (e.g., formed) by impellers, conduits, orifices, etc.

[0064] Multiple conduits 802 are connected to each other via multiple connecting surfaces 804. At least one of the connecting surfaces 804 includes at least one air duct 806 to guide exhaust air from the front side of the diffuser 800 to the rear side of the diffuser 800. Figure 8 In the example shown, each of the plurality of connecting surfaces 804 includes a bleed air conduit 806. In other examples, one or more of the plurality of connecting surfaces 804 include fewer bleed air conduits 806 (e.g., no bleed air conduit 806) or more bleed air conduits 806 (e.g., two bleed air conduits 806, three bleed air conduits 806, etc.).

[0065] In some examples, the number of bleed air conduits 806 and the number of connection surfaces 804 that include at least one bleed air conduit 806 are determined based on at least one of a plurality of factors including, but not limited to: the amount of bleed air required, the size of the connection surface 804, the shape of the connection surface 804, the number of connection surfaces 804 in the diffuser 800, and the distance between connection surfaces 804.

[0066] The cross-sectional shape of the bleed air conduit 806 can be circular, oval, square, triangular, rectangular, or other two-dimensional geometric shape. In some examples, the shape of the bleed air conduit 806 can be determined based on a plurality of factors including, but not limited to: the amount of bleed air required, the size of the connection surface 804, the shape of the connection surface 804, the number of connection surfaces 804 in the diffuser 800, and the distance between connection surfaces 804.

[0067] Figure 9 is a flowchart representing an example process 900 for directing bleed air within an engine using one of the example diffusers 206, 800. The process 900 begins at block 902 when bleed air is directed from a main flow path to a bleed air cavity. The bleed air is directed from the main flow path prior to the main flow path entering the diffuser 206, 800. For example, the bleed air can be directed from the main flow path prior to the main flow path entering an impeller, or at a front side of the diffuser 206, 800 between a compressor’s impeller and a diffuser 206, 800 stage.

[0068] At block 904, the bleed air is directed through a bleed air conduit 230, 806 of the diffuser 206, 800 from the bleed air cavity at a front side of the diffuser 206, 800 to a back side of the diffuser 206, 800. In some examples, the bleed air is directed through a plurality of bleed air conduits 230, 806. In some examples, respective bleed air conduits of the plurality of bleed air conduits 230, 806 are distributed between respective surfaces of a plurality of surfaces of the diffuser 206, 800.

[0069] At block 906, after directing the bleed air through the bleed air conduit 230, 806, the bleed air is directed to at least one downstream water trough via at least one passage positioned at a back side of the diffuser 206, 800. In some examples, the at least one passage is implemented by the plurality of passages 510, the tube 610, and / or the pipe section 710. For example, the tube 610 directs the bleed air to the at least one downstream water trough through the port 612.

[0070] At block 908, a condition of providing bleed air to a first aircraft or engine system of the at least one aircraft and / or engine system is evaluated. When bleed air is to continue to be supplied to the first aircraft or engine system (e.g., a block 908 returns a “no” result), then the example process 900 returns to block 906. When bleed air is to stop being supplied to the first aircraft or engine system (e.g., a block 908 returns a “yes” result), then control moves to block 910 where bleed air flow to the first aircraft or engine system is limited by moving the valve from the open position to the closed position. For example, during takeoff, the supply of bleed air can be limited to maximize the amount of air in the main flow path to maximize the thrust generated by the combustor. At block 912, a condition of resuming bleed air to the first aircraft or engine system is evaluated. When bleed air flow to the first aircraft or engine system is to continue to be limited (e.g., a block 912 returns a “no” result), then at block 914 the valve remains in the closed position. When bleed air flow to the first aircraft or engine system is to be resumed (e.g., a block 912 returns a “yes” result), then at block 916 the valve is moved from the closed position to the open position to provide bleed air flow to the first aircraft or engine system. For example, when the desired thrust generated by the engine does not require the maximum amount of air in the main flow path, bleed air can be provided to support the aircraft and / or engine system utilizing bleed air.

[0071] Figure 10 is a flowchart representative of an example process 1000 of manufacturing an example diffuser 206, 800. The example process 1000 begins at block 1002 when an inner shell is formed, the inner shell extending along the circumferential direction C. At block 1004, an outer shell is formed, the outer shell extending along the circumferential direction C and spaced apart from the inner shell in the radial direction R such that the inner shell and the outer shell define a passageway. At block 1006, a plurality of surfaces defining a plurality of discrete passageways are formed. In some examples, the plurality of surfaces are a plurality of diffuser vanes 306, a plurality of ducts 802, a plurality of holes, etc. In some examples, forming the inner shell, the outer shell, and / or the plurality of surfaces includes depositing and fusing additive material. In some examples, blocks 1002, 1004, and 1006 are performed together. In some examples, the inner shell, the outer shell, and / or the plurality of surfaces are integrally formed. In other examples, the inner shell, the outer shell, and / or the plurality of surfaces are distinct. In some examples, the inner shell, the outer shell, and / or the plurality of surfaces are connected by brazing, welding, fastening, and / or other methods of connecting distinct mechanical components. At block 1008, at least one bleed air conduit 230, 806 is formed in the outer shell and in at least one gap between the plurality of discrete passageways. The bleed air conduit 230, 806 has a first end at a first side of the diffuser and a second end at a second side of the diffuser 206, 800 to pass bleed air from the first side through the diffuser 206, 800 to the second side.

[0072] In some examples, any combination of blocks 1002, 1004, 1006, and 1008 of example process 1000 can be performed collectively. For example, if diffuser 206, 800 is manufactured by additive manufacturing, casting, injection molding, etc., each of blocks 1002-1008 can be performed in a single action.

[0073] From the foregoing, it will be appreciated that example systems, apparatus, articles, and methods have been disclosed that provide bleed air to a downstream water sump via a bleed air path internal to a gas turbine engine, where the bleed air path length is shortened, the number of parts is reduced, the weight is reduced, the cost is reduced, the durability is increased, and the maintainability is increased. The bleed air systems disclosed herein direct bleed air from a forward side of a diffuser to an aft side of the diffuser via a plenum conduit. The example systems, apparatus, articles, and methods disclosed herein also reduce the forward area of the engine by eliminating the need for external bleed air system components, thereby reducing nacelle drag.

[0074] Further examples are provided by the subject matter of the following clauses:

[0075] A gas turbine engine comprising: a frame defining a cavity at a forward side of a diffuser of the gas turbine engine; a compressor including the diffuser, the diffuser defining a primary flow path to provide an air flow to a combustor and including at least one conduit fluidly coupled to the cavity; and a downstream water sump fluidly coupled to the cavity via the at least one conduit, the at least one conduit defining at least a portion of a bleed air path.

[0076] The gas turbine engine according to any preceding clause, further comprising at least one passage fluidly coupled to one or more of the at least one conduit and the downstream water sump.

[0077] The gas turbine engine according to any preceding clause, further comprising a tube coupled to the diffuser, the tube fluidly coupled to the cavity via one or more of the at least one conduit.

[0078] The gas turbine engine according to any preceding clause, further comprising a port, wherein the tube fluidly extends through an inlet of the port.

[0079] The gas turbine engine according to any preceding clause, wherein a cross-sectional shape of one or more of the at least one conduit is one of circular, elliptical, and rectangular.

[0080] The gas turbine engine of any preceding paragraph, wherein the compressor is a centrifugal compressor, and wherein the exhaust air path is internal to the gas turbine engine.

[0081] The gas turbine engine of any preceding paragraph, wherein the diffuser includes a plurality of diffuser vanes defining the primary flow path and the at least one conduit is positioned in at least one of the plurality of diffuser vanes.

[0082] The gas turbine engine of any preceding paragraph, wherein the diffuser includes a plurality of ducts defining the primary flow path, the at least one conduit is positioned between respective ones of the plurality of ducts.

[0083] The gas turbine engine of any preceding paragraph, wherein the downstream water trough is a first downstream water trough and the exhaust air path is a first exhaust air path, the gas turbine engine further comprising a second downstream water trough fluidly coupled to one or more of the at least one conduit and a second exhaust air path, wherein a first portion of exhaust air is to travel from the cavity to the first downstream water trough via the first exhaust air path and a second portion of exhaust air is to travel from the cavity to the second downstream water trough via the second exhaust air path.

[0084] The gas turbine engine of any preceding paragraph, wherein the cavity receives the exhaust air from a flow path that supplies air to the primary flow path.

[0085] The gas turbine engine of any preceding paragraph, wherein exhaust air is passively provided to the downstream water trough.

[0086] The gas turbine engine of any preceding paragraph, further comprising a fluid control valve fluidly coupled between one or more of the at least one conduit and the downstream water trough.

[0087] The gas turbine engine of any preceding paragraph, wherein the fluid control valve is operable between an open position and a closed position, exhaust air is provided to the downstream water trough when the valve is in the open position, and exhaust air flow to the downstream water trough is limited when the valve is in the closed position.

[0088] The gas turbine engine of any preceding paragraph, wherein the diffuser includes an inner shell and an outer shell, the plurality of diffuser vanes being between the inner shell and the outer shell.

[0089] The gas turbine engine of any preceding paragraph, wherein the diffuser is additively manufactured.

[0090] A diffuser for directing exhaust air within a gas turbine engine, the diffuser comprising: an inner shell; an outer shell; and a plurality of surfaces between the inner shell and the outer shell, the plurality of surfaces defining a plurality of discrete passages, at least one conduit positioned between respective ones of the plurality of discrete passages, the at least one conduit fluidly connected to a plenum positioned at a first side of the diffuser and the at least one conduit fluidly connected to a downstream sump positioned at a second side of the diffuser, the at least one conduit defining at least a portion of an exhaust air path.

[0091] The diffuser of any preceding clause, wherein one or more of the at least one conduit is fluidly coupled to the downstream sump via at least one passage.

[0092] The diffuser of any preceding clause, wherein the diffuser is coupled to a tube at the second side of the diffuser.

[0093] The diffuser of any preceding clause, wherein a cross-sectional shape of one or more of the at least one conduit is one of circular, elliptical, and rectangular.

[0094] The diffuser of any preceding clause, wherein the diffuser is additively manufactured.

[0095] The diffuser of any preceding clause, wherein the downstream sump is a first downstream sump, the at least one conduit includes a first conduit between first ones of the plurality of discrete passages and a second conduit between second ones of the plurality of discrete passages, a first portion of the exhaust air flowing from the plenum to the first downstream sump via the first conduit and a second portion of the exhaust air flowing from the plenum to a second downstream sump via the second conduit.

[0096] The diffuser of any preceding clause, wherein the plurality of discrete passages provide a primary flow path to supply air to a combustor.

[0097] The diffuser of any preceding clause, wherein the plurality of surfaces are a plurality of diffuser vanes, the at least one conduit positioned in at least one of the plurality of diffuser vanes.

[0098] The diffuser of any preceding clause, wherein the plurality of surfaces are a plurality of ducts, the at least one conduit positioned between respective ones of the plurality of ducts.

[0099] An exhaust air system for an aircraft, the exhaust air system comprising: a frame defining a cavity; a diffuser to provide air to a combustor via a primary flow path, the diffuser comprising: at least one diffuser vane in the primary flow path; and at least one conduit in one or more of the at least one diffuser vane, the at least one conduit fluidly coupled to the cavity, the at least one conduit defining at least a portion of an exhaust air path through the at least one diffuser vane; a channel coupled to the at least one conduit at a first end of the channel; and a downstream sink coupled to the channel at a second end of the channel, the downstream sink fluidly coupled to the cavity via the at least one conduit and the channel.

[0100] A method for manufacturing a diffuser to direct exhaust air to an interior of a gas turbine engine, comprising forming an inner shell extending in a circumferential direction; forming an outer shell extending in the circumferential direction, the outer shell spaced apart from the inner shell in a radial direction, the inner shell and the outer shell defining a passageway; forming a plurality of surfaces to define a plurality of discrete passageways in the passageway; and creating at least one conduit in the outer shell and at least one of the plurality of surfaces.

[0101] The method of any preceding clause, wherein forming the inner shell, forming the outer shell, and forming the plurality of surfaces to define a plurality of discrete passageways comprises depositing and fusing additive material.

[0102] The method of any preceding clause, wherein creating the at least one conduit comprises drilling into the outer shell and the at least one surface.

[0103] The method of any preceding clause, wherein a cross-sectional shape of one or more of the at least one conduit is one of circular, elliptical, or rectangular.

[0104] A method comprising directing exhaust air from a primary flow path of a compressor to a bleed air cavity, and directing the exhaust air through an internal bleed air conduit of a diffuser.

[0105] The method of any preceding clause, further comprising directing the exhaust air to at least one downstream sink for use in at least one aircraft system or engine system.

[0106] The method of any preceding clause, further comprising determining whether to stop providing the exhaust air to a first of the at least one aircraft system or engine system.

[0107] The method of any preceding paragraph, further comprising restricting the flow of the bleed air to the first one of the at least one aircraft system or engine system by moving a valve.

[0108] The method of any preceding paragraph, further comprising determining whether to resume providing the bleed air to the first one of the at least one aircraft system or engine system.

[0109] The method of any preceding paragraph, further comprising maintaining a position of the valve.

[0110] The method of any preceding paragraph, further comprising providing the bleed air to the first one of the at least one aircraft system or engine system by moving the valve.

[0111] The following references are hereby incorporated by reference into the detailed description of this specification. Although certain example systems, devices, articles, and methods have been disclosed herein, the scope of coverage of this patent can not be limited to what is disclosed. Rather, this patent covers all systems, devices, articles, and methods falling within the scope of the claims.

Claims

1. A gas turbine engine characterized by, Comprising: a frame defining a cavity forward of a diffuser of the gas turbine engine; a compressor including the diffuser, the diffuser defining a primary flow path to provide a flow of air to a combustor, and including at least one conduit fluidly coupled to the cavity; and a downstream sump fluidly coupled to the cavity via the at least one conduit, the at least one conduit defining at least a portion of a bleed air path.

2. The gas turbine engine of claim 1, wherein, Further comprising at least one passage fluidly coupled to one or more of the at least one conduit and the downstream sump.

3. The gas turbine engine of claim 1, wherein, Further comprising a tube coupled to the diffuser, the tube fluidly coupled to the cavity via one or more of the at least one conduit.

4. The gas turbine engine of claim 3, wherein, Further comprising a port, wherein the tube fluidly extends through an inlet of the port.

5. The gas turbine engine of claim 1, wherein, Wherein a cross-sectional shape of one or more of the at least one conduit is one of circular, oval, and rectangular.

6. The gas turbine engine of claim 1, wherein, Wherein the compressor is a centrifugal compressor, and wherein the bleed air path is internal to the gas turbine engine.

7. The gas turbine engine of claim 1, wherein, Wherein the diffuser includes a plurality of diffuser vanes defining the primary flow path, and the at least one conduit is positioned in at least one of the plurality of diffuser vanes.

8. The gas turbine engine of claim 1, wherein, Wherein the diffuser includes a plurality of ducts defining the primary flow path, the at least one conduit is positioned between respective ones of the plurality of ducts.

9. The gas turbine engine of claim 1, wherein, Wherein the downstream sump is a first downstream sump, and the bleed air path is a first bleed air path, the gas turbine engine further comprising a second downstream sump fluidly coupled to one or more of the at least one conduit and a second bleed air path, wherein a first portion of bleed air is to travel from the cavity to the first downstream sump via the first bleed air path, and a second portion of bleed air is to travel from the cavity to the second downstream sump via the second bleed air path.

10. The gas turbine engine of claim 1, wherein, Wherein the cavity receives bleed air from a flow path that supplies air to the primary flow path.

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