Embedded motor cooling

Abstract

In one exemplary embodiment, a gas turbine engine is provided. The gas turbine engine defines a radial direction, an axial direction, and an axis extending in the axial direction of the gas. A gas turbine engine includes: a shaft configured to rotate about an axis; a motor including a rotor and a stator coupled to and rotatable with the shaft, the rotor defining an end portion in an axial direction; and a cooling manifold rotatable with the rotor and positioned at an end of the rotor, the cooling manifold configured to receive a flow of cooling fluid and provide the cooling fluid to the stator during operation of the gas turbine engine.

Description

[0001] This application is a divisional application of the invention patent application filed on December 22, 2021, with application number 202111582427.3 and invention title "Embedded Motor Cooling".

[0002] Related Applications

[0003] This application claims priority to Polish patent application number P.437703, filed on April 26, 2021. Technical Field

[0004] This application generally relates to a cooling assembly for an embedded motor in a gas turbine engine. Background Technology

[0005] The motor generates heat during operation. Therefore, even when installed in the cold section of an aircraft engine, cooling may be necessary. A system and method for cooling the motor would be useful. Summary of the Invention

[0006] The aspects and advantages of this disclosure will be set forth in part in the description which follows, or may be apparent from the description, or may be learned by practice of the practices disclosed herein.

[0007] In one exemplary embodiment, a gas turbine engine is provided. The gas turbine engine defines an axis extending radially, axially, and along the axial direction of a gas. The gas turbine engine includes: a shaft configured to rotate about the axis; an electric motor including a rotor and a stator, the rotor being coupled to and rotatable with the shaft, the rotor defining an end along the axial direction; and a cooling manifold rotatable with the rotor and positioned at the end of the rotor, the cooling manifold being configured to receive a flow of cooling fluid and supply cooling fluid to the stator during operation of the gas turbine engine.

[0008] These and other features, aspects, and advantages of the invention will become better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate various aspects of this disclosure and, together with the description, serve to explain the principles of the invention. Attached Figure Description

[0009] The specification sets forth a complete and enabling disclosure for those skilled in the art, including its best mode, which relates to the accompanying drawings, in which:

[0010] Figure 1 This is a schematic cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure.

[0011] Figure 2This is a close-up schematic cross-sectional view of an electric motor according to an exemplary aspect of this disclosure.

[0012] Figure 3 This is a perspective view of a cooling manifold according to an exemplary aspect of this disclosure.

[0013] Figure 4 yes Figure 3 A first cross-sectional view of an exemplary cooling manifold.

[0014] Figure 5 yes Figure 3 A second cross-sectional view of an exemplary cooling manifold.

[0015] Figure 6 This is a cross-sectional view of a cooling manifold according to an exemplary aspect of this disclosure.

[0016] Figure 7 yes Figure 6 A cross-sectional view of an exemplary cooling manifold along line 7-7.

[0017] Figure 8 This is a schematic diagram of a seal according to an exemplary embodiment of the present disclosure. Detailed Implementation

[0018] Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Detailed descriptions use numerals and letter names to refer to features in the drawings. Similar or analogous reference numerals in the drawings and description are used to refer to similar or analogous portions of the invention.

[0019] The term “exemplary” as used herein means “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” need not be construed as being superior or advantageous to other implementations.

[0020] 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 a single component.

[0021] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and to the normal operating posture of the gas turbine engine or vehicle. For example, in the context of a gas turbine engine, "front" refers to the position closer to the engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust port.

[0022] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0023] The terms “connection,” “fixation,” “attachment,” etc., refer to direct connection, fixation, or attachment, as well as indirect connection, fixation, or attachment via one or more intermediate components or features, unless otherwise specified herein.

[0024] The singular forms “a,” “one,” and “the” include plural references unless the context clearly specifies otherwise.

[0025] The approximate language used in this specification and claims is intended to modify any quantitative expression that may be varied without altering the underlying function. Therefore, values ​​modified by one or more terms, such as “approximately,” “about,” and “basically,” are not limited to specified precise values. In at least some instances, 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%.

[0026] Throughout this specification and claims, scope limitations are combined and interchanged, and these scopes are identified and include all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0027] Now refer to the attached diagram, Figure 1 A front sectional view of an exemplary embodiment of a gas turbine engine is shown, which can be incorporated into one or more inventive aspects of this disclosure. In particular, Figure 1 An exemplary gas turbine engine is configured as a single pipeless rotary engine 10, which defines an axial direction A, a radial direction R, and a circumferential direction C (extending around the axial direction A). Figure 1 As can be seen, the engine 10 adopts an open rotor propulsion system and has a rotor assembly 12, which includes an array of airfoils arranged around the central longitudinal axis 14 of the engine 10, and more specifically, an array of rotor blades 16 arranged around the central longitudinal axis 14 of the engine 10. Furthermore, as will be explained in more detail below, the engine 10 also includes a non-rotating blade assembly 18 positioned behind the rotor assembly 12 (i.e., non-rotating relative to the central axis 14), which includes an array of airfoils also arranged around the central axis 14, and more specifically, an array of blades 20 arranged around the central axis 14. The rotor blades 16 may be arranged around the centerline 14 at generally equidistant intervals. The rotor assembly 12 further includes a hub 45 located in front of the plurality of rotor blades 16.

[0028] Still refer to Figure 1The blade assembly 18 extends from the fairing 48 and is positioned behind the rotor assembly 12. The blades 20 of the blade assembly 18 can be mounted to a stationary frame or other mounting structure and do not rotate relative to the central axis 14. For illustrative purposes, Figure 1 The arrow F also depicts the forward direction, which in turn defines the front and rear parts of the system. For example... Figure 1 As shown, the rotor assembly 12 is located at the front end of the engine 10 and is in a "traction" configuration.

[0029] Additionally, the engine 10 includes a turbine 30, which has a core 32 (or a high-speed system) and a low-speed system. The core 32 generally includes a high-speed compressor 34, a high-speed turbine 36, and a high-speed shaft 38, which extends between and connects the high-speed compressor 34 and the high-speed turbine 36. The high-speed compressor 34, the high-speed turbine 36, and the high-speed shaft 38 can be collectively referred to as the engine's high-speed spool. Furthermore, a combustion section 40 is located between the high-speed compressor 34 and the high-speed turbine 36. The combustion section 40 may include one or more configurations for receiving a fuel-gas mixture and providing a flow of combustion gases through the high-speed turbine 36 to drive the high-speed spool.

[0030] The low-speed system similarly includes a low-speed turbine 42, a low-speed compressor or supercharger 44, and a low-speed shaft 46, which extends between and connects the low-speed compressor 44 and the low-speed turbine 42. The low-speed compressor 44, the low-speed turbine 42, and the low-speed shaft 46 can be collectively referred to as the low-speed spool of the engine.

[0031] Although engine 10 is depicted as having a low-speed compressor 44 positioned in front of high-speed compressor 34, in some embodiments, compressors 34 and 44 may be arranged in an interleaved manner. Additionally or alternatively, although engine 10 is depicted as having a high-speed turbine 36 positioned in front of low-speed turbine 42, in some embodiments, turbines 36 and 42 may similarly be arranged in an interleaved manner.

[0032] Still refer to Figure 1 The turbine 30 is typically enclosed within a cowling 48. Furthermore, it should be understood that the cowling 48 at least partially defines the inlet 50 and the exhaust port 52, and includes a turbine flow path 54 extending between the inlet 50 and the exhaust port 52. For the illustrated embodiment, the inlet 50 is an annular or axisymmetric 360-degree inlet located between the rotor blade assembly 12 and the stationary or stationary blade assembly 18, and provides a path for atmospheric air to enter the turbine flow path 54 (and the compressors 44, 34, combustion section 40, and turbines 36, 42) along the radially inward side of the guide vane 20.

[0033] However, in other embodiments, the inlet 50 may be located in any other suitable location, such as behind the blade assembly 18, or arranged in a non-axisymmetric manner.

[0034] As shown in the figure, rotor assembly 12 is driven by turbine 30, and more specifically, by low-speed shaft 46. More specifically, still targeting... Figure 1 An exemplary embodiment of the engine 10 shown includes a power gearbox 56 and a rotor assembly 12 driven by a low-speed shaft 46 of a turbine 30 passing through the power gearbox 56. In this way, the rotating rotor blades 16 of the rotor assembly 12 can rotate about an axis 14 and generate thrust to propel the engine 10, and thus propel the associated aircraft in a forward direction F.

[0035] The power gearbox 56 may include a gear set for reducing the rotational speed of the low-speed shaft 46 relative to the low-speed turbine 42, so that the rotor assembly 12 can rotate at a slower speed than the low-speed shaft 46.

[0036] Furthermore, in the illustrated embodiment, the engine 10 includes a motor 62 coupled to a shaft of the engine rotatable about a longitudinal axis 14 of the engine 10, and located radially R inside the engine flow path 54 and radially R inside the airflow passing through the rotor blades 16 of the rotor assembly 12. More specifically, in the illustrated embodiment, it should be understood that the engine 10 includes a rotor shaft 64 extending from the gearbox 56 to the plurality of rotor blades 16 of the rotor assembly 12 for driving the plurality of rotor blades 16 of the rotor assembly 12. In the illustrated embodiment, the motor 62 is coupled to the rotor shaft 64 and is rotatable with the rotor shaft 64.

[0037] As will be described in more detail below, engine 10 includes a cooling system for maintaining the temperature of motor 62 within specified temperature limits. The cooling system generally includes a liquid cooling system 66 in thermal communication with motor 62 to cool it, and a cooling air system 68. Cooling air system 68 may receive airflow from engine flow path 54 at a location downstream of inlet 50 via one or more ducts 70 and valves 72. The inlet of duct 70 may include features (e.g., one or more louvers, scoops, slots, etc.) that guide the flow through duct 70 based on, for example, the required amount of cooling flow, the desired amount of steering pressure recovery (e.g., to ensure cooling air system 68 is properly pressurized), etc. Duct 70 may also extend through engine flow path 54 at a location downstream of inlet guide vanes 74 of engine 10 and upstream of low-speed compressor 44 to motor 62. However, in other embodiments, duct 70 of cooling air system 68 may extend through engine flow path 54 at any other suitable location, or may provide any other suitable form of cooling airflow to motor 62.

[0038] However, it should be understood that, Figure 1 The exemplary single-rotor pipeless engine 10 depicted is merely an example, and in other exemplary embodiments, engine 10 may have any other suitable configuration, including, for example, any other suitable number of shafts or spools, turbines, compressors, etc. Furthermore, although engine 10 is depicted as a single pipeless rotor engine 10, in other embodiments, engine 10 may further include a nacelle or duct surrounding at least a portion of the rotor assembly 12, turbine, or both. In this configuration, outlet guide vanes may be connected to the nacelle, and the nacelle and turbine may together define a bypass passage. Additionally or alternatively, although engine 10 is depicted as a geared engine 10 (i.e., including a gearbox between the low-speed shaft 46 and rotor assembly 12), in other embodiments, aspects of this disclosure may be additionally or alternatively applied to direct-drive engines, wherein the low-speed shaft 46 and the rotor shaft 64 of the rotor assembly are connected or coordinated such that the low-speed shaft rotates at the same speed as the rotor assembly 12.

[0039] Furthermore, although engine 10 is described as having a rotor assembly with single-stage rotor blades, in other embodiments, engine 10 may include a multi-stage rotor configuration (open or closed by the nacelle), and the disclosed aspects described below may be incorporated therein.

[0040] Furthermore, in other exemplary embodiments, any other suitable gas turbine engine 10 may be provided. For example, in other exemplary embodiments, the gas turbine engine 10 may be a ducted turbofan engine 10, a turboshaft engine, a turboprop engine, a turbojet engine, etc.

[0041] Now refer to Figure 2 It depicts a close-up schematic diagram of a motor 62, which is coupled to and rotates with the engine shaft 80 of the engine 10, the engine shaft 80 being rotatable about the axis 14 of the engine 10. In some exemplary embodiments, Figure 2 The motor 62 and engine 10 depicted in the above description can be compared with those described above. Figure 1 The exemplary motor 62 in the described engine 10 is configured in a similar manner, so the same or similar reference numerals may refer to the same or similar parts. In this way, it should be understood that, in at least some exemplary embodiments, Figure 2 The engine shaft 80 depicted in the image can be Figure 1 An exemplary rotor shaft 64 of the engine 10 is configured to rotate a plurality of rotor blades 16 of the rotor assembly 12 about an axis 14.

[0042] However, in other embodiments, aspects of this disclosure may be applied to other motor 62 mounting locations and / or engine configurations, such that the engine shaft 80 may be any other suitable engine shaft (e.g., low-pressure shaft, high-pressure shaft, etc.).

[0043] In the illustrated embodiment, the motor 62 generally includes a rotor 82 and a stator 84, with the rotor 82 coupled to and rotating with the engine shaft 80. More specifically, in the illustrated embodiment, the rotor 82 is coupled to and rotates with the engine shaft 80 via a rotor mounting portion 86. In the illustrated embodiment, the rotor mounting portion 86 extends from the engine shaft 80 to the rotor 82 to couple the rotor 82 of the motor 62 to the engine shaft 80.

[0044] Motor 62 is typically configured as a radial flux motor, defining an air gap 88 between rotor 82 and stator 84, the air gap 88 extending generally along the axial direction A of engine 10. Furthermore, in the illustrated embodiment, motor 62 is configured as an "in-runner" motor 62, such that rotor 82 is located inside stator 84 along the radial direction R of engine 10. However, it is worth noting that in other embodiments, motor 62 may have other suitable configurations. For example, in other embodiments, motor 62 may optionally be oriented such that air gap 88 defines an angle relative to the axial direction A of engine 10.

[0045] As shown in the figures, for the depicted embodiment, the rotor 82 generally extends along axial direction A, defining a first end 90 and a second end 92 along axial direction A. Similarly, the stator 84 generally extends along axial direction A, defining a first end 94 and a second end 96 along axial direction A. More specifically, the stator 84 includes a core 98 and a plurality of windings 100, and for the illustrated embodiment, the plurality of windings 100 include portions at the first end 94 and the second end 96 of the stator 84. However, it should be understood that in other exemplary aspects, any other suitable stator configuration may be provided such that the first end and the second end 96 of the stator include any other suitable features.

[0046] Compared with the above reference Figure 1 The embodiments described are the same. Figure 2 The exemplary engine 10 depicted includes a cooling system for maintaining the temperature of the motor 62 within specified limits. The cooling system includes a liquid cooling system 64 and a cooling air system 68, the liquid cooling system 64 being thermally coupled to the motor 62. More specifically, the liquid cooling system 64 may operate in conjunction with a stator 84 to reduce the temperature of certain aspects of the stator 84.

[0047] However, the liquid cooling system 64 may have difficulty effectively reducing the temperature of other aspects of the stator 84 of the motor 62, such as the first end 94 and the second end 96 of the stator 84, such as the portions of the winding 100 located at the first end 94 and the second end 96 of the stator 84. Therefore, for the depicted embodiment, the provided cooling air system 68 can help cool one or more of these portions of the motor 62.

[0048] Similar to the embodiments described above, Figure 2 An exemplary cooling air system 68 of the engine 10 depicted includes one or more cooling ducts 70 for providing a flow of cooling fluid toward the motor 62 during operation of the engine 10. More specifically, the one or more ducts 70 may provide a flow of cooling air 102 toward the motor 62 during operation of the engine 10. For example, in some exemplary aspects, the one or more cooling ducts 70 may receive the flow of cooling air 102 as an exhaust gas stream from the compressor section of the engine 10. For example, the exhaust gas stream may be provided from a low-pressure compressor, from a high-pressure compressor, and / or from a location between the low-pressure compressor and the high-pressure compressor. Alternatively, the cooling air flow 102 in the ducts 70 may be provided from, for example, an ambient location or a location on the cowling 48 of the engine 10.

[0049] Still refer to Figure 2One or more cooling ducts 70 of the cooling air system 68 generally provide cooling airflow 102 to cool various parts of the motor 62. Specifically, for the exemplary embodiment shown, one or more cooling ducts 70 of the cooling air system 68 define a first cooling airflow path 104 extending to a first end (e.g., end 90, 94) of the motor 62 and a second cooling airflow path 106 extending to a second end (e.g., end 92, 96) of the motor 62. The first cooling airflow path 104 and the second cooling airflow path 106 are separated at a junction 108 within one or more ducts 70. It should be understood that the one or more ducts 70 may include a single duct 70 or a plurality of ducts 70 positioned circumferentially. In this way, the junction 108 may be a single junction or a plurality of junctions 108 at different locations circumferentially.

[0050] A first cooling airflow path 104 extends through a first opening 110 defined within one or more ducts 70 to an air chamber 112, which is at least partially defined by a rotating rotor mounting portion 86 extending between an engine shaft 80 in the rotor 82 and a static structure including the ducts 70. The first cooling airflow path 104 further extends through one or more openings 114 within the rotor mounting portion 86 to a cooling manifold 116, which is rotatable with the rotor 82 and positioned at a first end 90 of the rotor 82. The cooling manifold 116 is configured to receive a cooling fluid flow, and more specifically, to provide such cooling fluid to the stator 84 during operation of the engine 10. More specifically, still, for the illustrated embodiment, the cooling fluid flow is a cooling airflow 102 provided along the first cooling airflow path 104.

[0051] In short, it should be further understood that the second cooling airflow path 106 travels from the junction 108 to the static manifold 117, which is located at the second end 92 of the rotor 82, inside the second end 96 of the stator 84. The static manifold 117 may extend circumferentially and has a generally annular chamber 119. A flow control feature 176 may be included, for example, upstream of the static manifold 117, to control the amount of airflow 102 to the annular chamber 119. The flow control feature 176 may be, for example, a baffle or groove, to drive the flow into the annular chamber 119, increasing the heat transfer coefficient in the chamber 119, thereby providing additional cooling to the fluid seal 144 (described below). The dimensions of the flow control feature 176 may be designed to provide deterministic heat transfer cooling to the fluid seal before the flow is delivered through the static manifold 117 to the upper cavity. The static manifold 117 defines one or more second openings 118 oriented toward the second end 96 of the stator 84 of the motor 62. In this way, a cooling airflow 102 via the second cooling airflow path 106 can be provided to the second end 96 of the stator 84, or more specifically to a portion of the winding 100 of the stator 84 located at the second end 96 of the stator 84. The second airflow path 106 further extends through an air gap 88 of the motor 62 defined between the rotor 82 and the stator 84, such that the cooling airflow 102 via the second airflow path 106 can further provide cooling to the motor 62 along the air gap 88.

[0052] Still refer to Figure 2 Returning to the cooling manifold 116, it should be noted that, in the illustrated embodiment, the cooling manifold 116 is connected to the first end 90 of the rotor 82 of the motor 62, to the rotor mounting portion 86 (which connects the rotor 82 of the motor 62 to the engine shaft 80), or both. In the illustrated embodiment, the cooling manifold 116 is connected to both the rotor 82 and the rotor mounting portion 86. However, in other embodiments, the cooling manifold 116 may be connected only to the rotor 82 or only to the rotor mounting portion 86.

[0053] More specifically, now refer to Figure 3 Cooling manifold 116 and Figure 2 A perspective cross-sectional view of a portion of motor 62. Figure 3As can be understood from the views, for any of the embodiments shown, the cooling manifold 116 is connected to the rotor mount 86 and the rotor 82 using a plurality of fasteners 120 spaced apart circumferentially C along the engine 10. More specifically, again, for the embodiment shown, the cooling manifold 116 is connected to the rotor mount 86 using a plurality of fasteners 120 at a first position 122 and a second position 124 radially R, the plurality of fasteners 120 being circumferentially spaced apart at each of the first position 122 and the second position 124 radially R. Although for the embodiment shown, the cooling manifold 116 is not directly connected to the rotor 82 of the motor 62, it should be understood that the cooling manifold 116 is positioned radially R adjacent to the first end 90 of the rotor 82 of the motor 62, and in the embodiment shown, directly contacts the rotor 82 of the motor 62. Additionally, as will be further discussed below, the cooling manifold 116 is located radially R inside the second end 94 of the stator 84 (at the same or overlapping position axially A).

[0054] from Figure 3 As can also be understood from the view, the cooling manifold 116 is configured as a generally annular manifold that defines a generally annular airflow chamber 126, which is configured to receive a cooling airflow 102 from a first airflow path 104 of the cooling air system 68. (Refer to...) Figure 4 and Figure 5 From the simplified cross-sectional view, it should be understood that the cooling manifold 116 defines a plurality of protrusions 128 extending inwardly along the axial direction A to allow the cooling manifold 116 to be coupled to the rotor 82 at a second position 124 along the radial direction R using a plurality of fasteners 120. More specifically, Figure 4 A cross-sectional view of the cooling manifold 116 at one of these protrusions 128 is shown, and Figure 5 Cross-sectional views of the cooling manifold 116 at different circumferential positions between protrusions 128 are provided. (See figure) Figure 5 As shown, the cooling manifold 116 defines a clear flow path between the opening 114 in the rotor mounting portion 86 and the generally annular airflow chamber 126 of the cooling manifold 116 (although there is a protrusion 128).

[0055] Still largely refer to Figures 3 to 5It should be understood that the cooling manifold 116 further defines one or more impact openings 130 oriented radially outward. More specifically, the cooling manifold 116 defines one or more impact openings 130 oriented toward the stator 84 for providing a flow of cooling air 102 received by the cooling manifold 116 within a generally annular airflow chamber 126 to the stator 84. The one or more impact openings 130 may comprise a plurality of impact openings 130 spaced apart along the circumferential direction C of the engine 10. Alternatively, the one or more impact openings 130 may comprise continuous or generally continuous impact openings 130 extending along the circumferential direction C.

[0056] Especially refer to Figure 3 It should be understood that, in the illustrated embodiment, one or more impact openings 130 of the cooling manifold 116 are oriented toward the first end 94 of the stator 84 for providing a flow of cooling air 102 received by the cooling manifold 116 within a generally annular airflow chamber 126 to the first end 94 of the stator 84. More specifically, in the depicted embodiment, one or more impact openings 130 of the cooling manifold 116 are oriented toward at least a portion of the plurality of windings 100 of the stator 84 located at the first end 94 of the stator 84 for providing a flow of cooling air 102 received by the cooling manifold 116 within a generally annular airflow chamber 126 to the portion of the plurality of windings 100 located at the first end 94 of the stator 84.

[0057] However, it should be understood that in other exemplary embodiments of this disclosure, the cooling air system 68 may have any other suitable configuration. For example, the cooling air manifold 116 may have any other suitable configuration. For example, the manifold 116 may define one or more impact openings 130 oriented radially outward in any other suitable manner, such as not directly radially R.

[0058] Here is a brief reference. Figure 6 A cooling manifold 116 is provided according to another exemplary embodiment of the invention. The depicted exemplary cooling manifold 116 includes a local thickness 168 defining one or more impact openings 130. Including the local thickness 168 (the maximum thickness of which may be at least twice the thickness of the surrounding portion of the cooling manifold 116, and up to 100 times the thickness of the surrounding portion of the cooling manifold 116) allows the impact openings 130 to guide cooling air 102 in a more precise manner.

[0059] For example, now refer to Figure 7 Provided Figure 6 One or more impact openings 130 along Figure 6The schematic cross-sectional view along line 7-7 in the figure should be understood to mean that, in some exemplary aspects, the impact opening 130 may be oriented toward the stator 84 at an angle 170 relative to the radial direction R, so as to apply a circumferential velocity to the cooling air 102 through the impact opening 130. The angle 170 may be between 5 degrees and 85 degrees, such as at least 15 degrees, such as at least 30 degrees, such as at least 45 degrees, such as at least 60 degrees, such as at least 70 degrees, such as up to 80 degrees. Furthermore, it should be understood that... Figure 7 The exemplary impact opening 130 depicted defines a length 172 and a diameter 174 (or the maximum width of a non-circular opening). The ratio of length 172 to diameter 174 can be greater than 1:1 and less than 4:1, such as less than 3:1, such as less than 2:1. Although the rotor 82 rotates, this configuration can allow for more efficient cooling of the stator 84.

[0060] According to one or more of these exemplary embodiments, including the cooling manifold 116, the cooling air system 68 of the engine 10 may provide the desired amount of cooling to the portion of the plurality of windings 100 located at the first end 94 of the stator 84.

[0061] Now return to the reference. Figure 2 It should be understood that, Figure 2 The exemplary engine 10 depicted further includes a fluid seal 132 adjacent to the motor 62, and more specifically, adjacent to the second end 92 of the rotor 82 of the motor 62. The fluid seal 132 provides a static-rotational fluid seal between the first cooling air flow path 104 and the second cooling air flow path 106, and thus, the fluid seal 132 is in airflow communication with the first cooling air flow path 104 and the second cooling air flow path 106. In at least some exemplary aspects, the pressure of the cooling air flow 102 through the first cooling air flow path 104 may differ from the pressure of the cooling air flow 102 through the second cooling air flow path 106. In this way, the fluid seal 132 can prevent or minimize airflow leakage between the first cooling air flow path 104 and the second cooling air flow path 106.

[0062] Still referencing Figure 8 A close-up cross-sectional view of the fluid seal 132 is provided. As shown, the fluid seal 132 generally includes a first component 134 rotatable with the rotor 82 of the motor 62 and a second component 136 coupled to or integrally formed with a static structure, such as one or more pipes 70 including a cooling air system 68 or a circumferential manifold defining an opening 118 (see Figure 134). Figure 2The first component 134 generally includes a first group of sealing teeth 140 of 138, and the second component 136 generally includes a second group of sealing teeth 144 of 142. The sealing teeth 140 and 144 of the first group 138 and the second group 142 are alternately spaced along the length L of the fluid seal 132.

[0063] More specifically, in the illustrated embodiment, the sealing teeth 140 of the first group 138 includes at least three sealing teeth 140, and the sealing teeth 144 of the second group 142 also includes at least three sealing teeth 144. More specifically, in the illustrated embodiment, the sealing teeth 140 of the first group 138 includes five sealing teeth 140, and the sealing teeth 144 of the second group 142 includes four sealing teeth 144. It should be understood that each sealing tooth 140, 144 is generally positioned around the axis 14 of the engine 10 (see...). Figure 2 The sealing teeth extend 360° in the circumferential direction C. Although, for the illustrated embodiment, the sealing teeth 140 of the first group 138 includes five sealing teeth 140 and the sealing teeth 144 of the second group 142 includes four sealing teeth 140, in other embodiments, the sealing teeth 140 of the first group 138, the sealing teeth 144 of the second group 142, or both may have any other suitable number of sealing teeth 140 within their respective groups. For example, in another exemplary embodiment, the sealing teeth 140 of the first group 138, the sealing teeth 144 of the second group 142, or both may include 1 sealing tooth, 2 sealing teeth, 3 sealing teeth, 4 sealing teeth, 5 sealing teeth, 6 sealing teeth, 7 sealing teeth, 8 sealing teeth, 9 sealing teeth, 10 sealing teeth, or up to 30 sealing teeth. The sealing teeth 140 of the first group 138 may include the same number of sealing teeth 144 as the second group 142, or, optionally, the sealing teeth 140 of the first group 138 and the sealing teeth 144 of the second group 142 may have different numbers of sealing teeth 140.

[0064] Furthermore, in the illustrated embodiment, each sealing tooth 140 within the sealing teeth 140 of the first group 138 and the sealing teeth 144 of the second group 142 extends generally in a direction perpendicular to the length L of the fluid seal 132. More specifically, in the illustrated embodiment, the length L of the fluid seal 132 is generally aligned with and defined along the radial direction R of the engine 10. In this way, it should be understood that the sealing teeth 140 of the first group 138 and the sealing teeth 144 of the second group 142 extend generally in the axial direction A of the engine 10.

[0065] However, it should be understood that in other exemplary embodiments, the fluid seal 132 may be oriented in any other suitable direction (e.g., defining an angle relative to the radial direction R of the engine 10), and / or the sealing teeth 140 of the first set 138 and the plurality of sealing teeth 144 of the second set 142 may not extend directly perpendicular to the length L of the fluid seal 132.

[0066] Still refer to Figure 8 It should be understood that the first member 134 of the fluid seal 132 further defines a first plurality of valleys 148 between adjacent sealing teeth 140 of the first set 138, and similarly, the second member 136 defines a second plurality of valleys 150 between adjacent sealing teeth 144 of the second set 142. In the illustrated embodiment, the sealing teeth 140 of the first set 138 define a gap 152A with the second plurality of valleys 150 along axial direction A, and similarly, the sealing teeth 144 of the second set 142 define a gap 154 ​​with the first plurality of valleys 148 along axial direction A. This configuration allows for any natural variation along axial direction A between the rotor 82 of the motor 62 and the static structure surrounding the rotor 82 of the motor 62 during operation of the engine 10.

[0067] Furthermore, to further accommodate these natural variations, it should be understood that the first component 134 further includes a wear-resistant coating 156 on a first plurality of valleys 148 defined between adjacent sealing teeth 140 of the sealing teeth 140 of the first set 138, and similarly, the second component 136 also includes a wear-resistant coating 158 on a second plurality of valleys 150 defined between adjacent sealing teeth 144 of the sealing teeth 144 of the second set 142. The wear-resistant coatings 156, 158 are positioned on the surfaces of the valleys 148, 150 to interfere with the opposing sealing teeth 140, 144. In this way, when the relative movement between the rotor 82 of the motor 62 and the static structure surrounding the rotor 82 of the motor 62 exceeds the length of the gaps 152, 154, the corresponding sealing teeth 140 can avoid causing unnecessary damage to the first component 134, the second component 136, or both, and furthermore, can substantially not interrupt, for example, the operation of the motor 62.

[0068] It is worth noting that, although not depicted, it should be understood that, in at least some exemplary aspects, the sides of teeth 140, 144 may also include a wear-resistant coating to accommodate relative movement, for example, along radial R.

[0069] Refer again Figure 2It should be understood that, in some exemplary embodiments, the cooling airflow 102 from the cooling air system 68 may additionally provide further benefits and serve additional functions to the engine 10. For example, in the illustrated embodiment, the cooling air system 68 further defines a third cooling airflow path 160 branching from the first cooling airflow path 104 to provide the cooling airflow 102 / pressurized airflow to the reservoir. More specifically, the engine 10 defines a bearing reservoir 162 surrounding a bearing 164 that supports rotation of the engine shaft 80. Furthermore, the engine 10 includes a seal 166 (which is schematically represented and may be, for example, a labyrinth seal) that at least partially defines the bearing reservoir 162 surrounding the bearing 164. The cooling airflow 102 through the second cooling airflow path 160 can pressurize the bearing reservoir 162 by providing pressurized air to the seal 166, and can also provide cooling by providing any cooling 102 to the bearing reservoir 162.

[0070] Furthermore, such as Figure 2 Schematably depicted, after cooling measures are taken, cooling airflow 102 (or at least a portion of cooling airflow 102 from the first cooling airflow path 104, the second cooling airflow path 106, and / or the third cooling airflow path 160) can be provided to the engine flow path 54 of the engine 10. For example, cooling airflow 102 via the first cooling airflow path 104 and the second cooling airflow path 106 can be provided to the engine flow path 54 after being provided to / impacting the stator 84 of the motor 62. For example, in the illustrated embodiment, cooling airflow 102 in the engine 10 (see also, for example, Figure 1 The fluid path 54 is provided upstream of the compressor of the engine 10, and more specifically, upstream of the inlet guide vane 74 of the engine 10. In particular, for the illustrated embodiment, the cooling airflow 102 is provided to the engine flow path 54 at the location of the arrow representing the cooling airflow (labeled 102) reaching the flow path 54.

[0071] In this way, the cooling airflow 102 provided by the cooling air system 68 can be used to reduce the temperature of one or more exemplary aspects of the motor 62 and / or other components of the engine 10, and can subsequently provide energy to the engine flow path 54, increasing the amount of energy and airflow through the engine flow path 54.

[0072] Finally, still refer to Figure 2It should be understood that at least certain components that can operate with and / or are adjacent to the motor 62 may be formed of a material configured to reduce the risk of electrical losses due to these components. For example, in at least some exemplary embodiments, the cooling manifold 116, the first member 134 of the fluid seal 132, the second member 136 of the fluid seal 132, and / or the circumferential manifold defining the opening 118 may be formed of a material configured to reduce the risk of electrical losses. More specifically, in some exemplary embodiments, the material may be a material with relatively low electrical conductivity, such as a plastic material, a composite material, etc.

[0073] Further aspects of the invention are provided by the subject matter of the following clauses:

[0074] A gas turbine engine defining an axis extending radially, axially, and along the axial direction of a gas, the gas turbine engine comprising: a shaft configured to rotate about the axis; an electric motor including a rotor and a stator, the rotor being coupled to and rotatable with the shaft, the rotor defining an end along the axial direction; and a cooling manifold rotatable with the rotor and positioned at the end of the rotor, the cooling manifold being configured to receive a flow of cooling fluid and supply cooling fluid to the stator during operation of the gas turbine engine.

[0075] An engine according to one or more of these clauses, wherein the gas turbine engine includes a rotor assembly, and wherein the shaft is a rotor shaft for driving the pipeless rotor assembly.

[0076] An engine according to one or more of these terms, wherein the gas turbine engine includes a compressor, and wherein the cooling fluid is an exhaust gas flow from the compressor.

[0077] An engine according to one or more of these terms, wherein a cooling manifold is connected to the end of the rotor of the motor, and wherein the end of the rotor is optionally located radially at least partially inside the stator.

[0078] An engine according to one or more of these terms, wherein a cooling manifold is connected to the end of the motor rotor, to a rotor mounting portion that connects the rotor to the engine shaft, or both.

[0079] An engine according to one or more of these terms, wherein the rotor mounting portion defines one or more openings for supplying cooling fluid flow to the cooling manifold.

[0080] An engine according to one or more of these terms further includes a rotor mounting portion extending between the shaft and the rotor, wherein a cooling manifold is connected to the rotor mounting portion.

[0081] An engine according to one or more of these terms, wherein the cooling manifold defines one or more impingement openings oriented toward the stator for supplying cooling fluid as an impingement airflow to the stator.

[0082] An engine according to one or more of these terms, wherein the stator includes a plurality of windings, and wherein one or more impact openings are oriented toward at least a portion of the plurality of windings of the stator for supplying cooling fluid as an impact airflow to the plurality of windings of the stator.

[0083] An engine according to one or more of these terms, wherein the manifold is generally annular.

[0084] An engine according to one or more of these terms further includes a liquid cooling system, wherein the liquid cooling system is in thermal communication with the motor to cool the motor.

[0085] An engine according to one or more of these terms further includes: a bearing, a bearing supporting the rotation of a shaft; a seal, the seal at least partially defining a bearing reservoir surrounding the bearing; and a cooling airflow supply device, wherein the cooling airflow supply device is in airflow communication with a cooling manifold to provide a cooling fluid flow to the cooling manifold and in airflow communication with the seal to pressurize the seal.

[0086] An engine according to one or more of these terms, wherein the engine is a single pipeless rotary engine.

[0087] An engine according to one or more of these terms, wherein the engine is any one of the following: a ducted turbofan engine, a ductless turbofan engine, a turboprop engine, a turboshaft engine, or a turbojet engine.

[0088] An engine according to one or more of these terms, wherein a gas turbine engine defines an engine flow path, and wherein cooling fluid is provided to the engine flow path after being provided to the stator of an electric motor.

[0089] An engine according to one or more of these terms, wherein the gas turbine engine includes a compressor, and wherein cooling fluid is provided to the engine flow path at a location upstream of the compressor after being provided to the stator of the electric motor.

[0090] An engine according to one or more of these terms, wherein the gas turbine engine includes an inlet guide vane, and wherein cooling fluid is provided to the engine flow path at a location upstream of the inlet guide vane after being provided to the stator of the motor.

[0091] A gas turbine engine defining an axis extending radially, axially, and along the axial direction of a gas, the gas turbine engine comprising: a static structure; a shaft configured to rotate about the axis; an electric motor including a rotor and a stator, the rotor being coupled to and rotatable with the shaft, the stator being coupled to the static structure; and a fluid seal comprising: a first member including a first set of sealing teeth, the first member being rotatable with the rotor of the electric motor; and a second member including a second set of sealing teeth, the second member being coupled to or integrally formed with the static structure, wherein the first set of sealing teeth and the second set of sealing teeth are alternately spaced along the length of the fluid seal.

[0092] An engine according to one or more of these terms, wherein the length of the fluid seal is defined along the radial direction of the engine, and wherein the first set of sealing teeth and the second set of sealing teeth extend substantially along the axial direction of the engine.

[0093] An engine according to one or more of these terms, wherein a first member is defined in a first plurality of valleys between adjacent sealing teeth of a first set of sealing teeth, wherein a second member is defined in a second plurality of valleys between adjacent sealing teeth of a second set of sealing teeth, wherein the first set of sealing teeth defines a gap with the second plurality of valleys in an axial direction, and wherein the second set of sealing teeth defines a gap with the first plurality of valleys in an axial direction.

[0094] An engine according to one or more of these terms, wherein a first member defines a plurality of valleys between adjacent sealing teeth of a first set of sealing teeth, and wherein the plurality of valleys are coated with a wear-resistant material.

[0095] According to one or more of these clauses, in an engine, the second member also defines a plurality of valleys between adjacent sealing teeth of the second set of sealing teeth, and wherein the plurality of valleys of the second member are also coated with a wear-resistant material.

[0096] According to one or more of these clauses, the sealing teeth of the first set of sealing teeth, the sealing teeth of the second set of sealing teeth, or both are coated with wear-resistant material.

[0097] According to one or more of these clauses, the first set of sealing teeth includes at least one sealing tooth, and the second set of sealing teeth also includes at least one sealing tooth.

[0098] According to one or more of these clauses, the first set of sealing teeth includes at least three rows of sealing teeth, and the second set of sealing teeth also includes at least three rows of sealing teeth.

[0099] An engine according to one or more of these clauses, wherein the motor defines a first end and a second end along the axial direction, wherein the engine includes a cooling air assembly defining a first cooling air flow path extending to the first end of the motor and a second cooling air flow path extending to the second end of the motor, and wherein a fluid seal is in airflow communication with the first cooling air flow path and the second cooling air flow path.

[0100] According to one or more of these clauses, the fluid seal is configured to prevent cooling airflow from passing between a first cooling airflow path and a second cooling airflow path.

[0101] An engine according to one or more of these terms, wherein one of the first or second components is formed of a non-metallic material.

[0102] An engine according to one or more of these clauses, wherein the second component is formed of a non-metallic material.

[0103] An engine according to one or more of these clauses, wherein the engine further includes a static manifold at a second end of the rotor of the electric motor, wherein the cooling manifold is formed of a non-metallic material, the static manifold is made of a non-metallic material, or both.

[0104] This written description uses examples to disclose the invention, including the best mode, and also enables those skilled in the art to practice the invention, including making and using any device or system and performing any combined methods. The patentable scope of the invention is defined by the claims, but may include other examples that would occur to those skilled in the art. Such other examples are intended to be 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.

Claims

1. A gas turbine engine, characterized in that, The gas turbine engine defines radial, axial, and axis extending along the axial direction of the gas flow, and the gas turbine engine includes: Static structure; A shaft, configured to rotate about an axis; An electric motor, comprising a rotor and a stator, the rotor being coupled to and rotatable with the shaft, the stator being coupled to the static structure, and the rotor defining an end along the axial direction; and Fluid seal, the fluid seal comprising A first component, comprising a first set of sealing teeth, the first component being rotatable with the rotor of the motor; and The second component includes a second set of sealing teeth, and the second component is coupled to or integrally formed with the static structure, wherein the first set of sealing teeth and the second set of sealing teeth are alternately spaced along the length of the fluid seal.

2. The gas turbine engine according to claim 1, characterized in that, The length of the fluid seal is defined along the radial direction of the gas turbine engine.

3. The gas turbine engine according to claim 2, characterized in that, The first set of sealing teeth and the second set of sealing teeth extend substantially along the axial direction of the gas turbine engine.

4. The gas turbine engine according to claim 1, characterized in that, The first component is defined in a first plurality of valleys between adjacent sealing teeth of the first set of sealing teeth.

5. The gas turbine engine according to claim 4, characterized in that, The second member is defined in a second plurality of valleys between adjacent sealing teeth of the second set of sealing teeth.

6. The gas turbine engine according to claim 5, characterized in that, The first set of sealing teeth defines a gap with the second plurality of valleys along the axial direction.

7. The gas turbine engine according to claim 5, characterized in that, The second set of sealing teeth defines a gap with the first plurality of valleys along the axial direction.

8. The gas turbine engine according to claim 1, characterized in that, The system further includes a cooling manifold that rotates with the rotor and is positioned at the ends of the rotor, the cooling manifold being configured to receive a flow of cooling fluid during operation of the gas turbine engine and to supply the cooling fluid to the stator.

9. The gas turbine engine according to claim 8, characterized in that, The gas turbine engine includes a compressor, and the cooling fluid is the exhaust gas flow from the compressor.

10. The gas turbine engine according to claim 8, characterized in that, The cooling manifold is connected to the end of the rotor of the motor, and the end of the rotor is optionally located at least partially inside the stator along the radial direction.

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