Turbine engine hanger

Abstract

A hanger for a turbine engine can include a first surface facing a cooling airflow, a second surface facing a heating airflow, and a third surface radially outward of the first surface. The hanger can further include a cyclone separator having a dirty air inlet and a clean air outlet, and a cooling air circuit extending through the cyclone separator.

Description

[0001] This application is a continuation-in-part of the patent application No. 202010185432.X, titled "TURBINE ENGINE HANGER", filed on March 17, 2020. TECHNICAL FIELD

[0002] The present disclosure relates generally to a particle separator for a turbine engine, and more particularly to a cyclonic separator within a turbine engine component. BACKGROUND

[0003] Turbine engines, and particularly gas turbine engines or combustion turbine engines, are rotary engines that extract energy from a pressurized flow of hot gas that is produced by combustion.

[0004] Turbine engines are typically designed to operate at high temperatures to improve engine efficiency. It is beneficial to provide cooling measures for components such as airfoils in high temperature environments, where such cooling measures can reduce material wear on these components and improve structural stability during engine operation.

[0005] Cooling measures can include bleed air from a compressor that is directed to desired locations in the engine. The bleed air can be used to provide a purge air flow at the interface of particular components. Optimizing the delivery and coverage of the bleed air further helps to improve engine efficiency. SUMMARY

[0006] In one aspect, the present invention relates to a hanger for a turbine engine. The hanger comprises: a first surface facing a cooling gas flow, a second surface facing a heating gas flow, a third surface radially outward of the first surface; a cyclonic separator having a cyclonic body at least partially defined by the third surface and having a dirty air inlet, a clean air outlet, and a scavenge air outlet radially outward of the clean air outlet; and a cooling air circuit having a cooling air inlet on the first surface and a cooling air outlet on the second surface, and extending through the cyclonic separator between the dirty air inlet and the clean air outlet.

[0007] In another aspect, the present disclosure is directed to a shroud and sting assembly for a turbine engine. The shroud and sting assembly includes a sting having a first surface facing a cooling airflow, a second surface facing a hot airflow, a third surface radially outward of the first surface, a cyclone separator having a cyclone body at least partially defined by the third surface and having a dirty air inlet, a clean air outlet, and a scavenge air outlet radially outward of the clean air outlet, and a cooling air circuit having a cooling air inlet on the first surface and a cooling air outlet on the second surface and extending through the cyclone separator between the dirty air inlet and the clean air outlet. The shroud and sting assembly further includes a shroud having an inner surface facing the second surface of the sting, a hot surface facing the hot airflow, and a shroud cooling circuit fluidically connected to the cooling air circuit and extending through the shroud between a shroud inlet on the inner surface and a shroud outlet on the hot surface.

[0008] In another aspect, the present disclosure is directed to a turbine engine including an axially-flowing compressor, a combustor, and a turbine. The turbine engine includes a cooling component having an internal cooling passage and a hot surface facing a hot airflow, and a sting having a first surface facing a cooling airflow, a second surface facing the hot airflow, a third surface radially outward of the first surface, a cyclone separator having a cyclone body at least partially defined by the third surface and having a dirty air inlet, a clean air outlet, and a scavenge air outlet radially outward of the clean air outlet, and a cooling air circuit fluidically coupled to the internal cooling passage, the cooling air circuit having a cooling air inlet on the first surface and a cooling air outlet on the second surface and extending through the cyclone separator between the dirty air inlet and the clean air outlet. BRIEF DESCRIPTION OF DRAWINGS

[0009] In the drawings:

[0010] Figure 1 is a schematic cross-sectional view of a turbine engine for an aircraft.

[0011] Figure 2 is a turbine engine according to various aspects described herein Figure 1 is an enlarged view of a high pressure turbine section of the turbine engine of

[0012] Figure 3 is Figure 2 is a perspective view of a portion of the shroud and sting assembly of

[0013] Figure 4 is Figure 3 is a cross-sectional view of the shroud and sting assembly of including a cyclone separator along line IV-IV.

[0014] Figure 5 is Figure 4 a cross-sectional view of the shroud and hanger assembly showing airflow within the cyclone separator.

[0015] Figure 6 is a perspective view of another shroud and hanger assembly having a cyclone separator according to various aspects described herein. DETAILED DESCRIPTION

[0016] The described embodiments of the present disclosure are directed to shroud and hanger assemblies of a turbine engine. For purposes of illustration, the present disclosure will be described with respect to a turbine section in an aircraft turbine engine. However, it will be understood that the present disclosure is not so limited and can have general applicability within engines, including within compressor sections, and in non-aircraft applications, such as other mobile applications and non-mobile industrial, commercial, and residential applications.

[0017] Cooling airflow within a turbine engine can carry dust or other debris that can migrate into the cooled components, such as shrouds, hangers, airfoils, platforms, inner or outer bands, etc. This dust or debris can collect within the interior of the cooled components, or cause blockage within the cooling holes or passages. Removal of this debris can improve cooling performance and reduce the usage of cooling air.

[0018] Turbine engines can also include components formed by additive manufacturing. As used herein, an "additively manufactured" component refers to a component formed by an additive manufacturing (AM) process, in which the component is built up layer by layer through successive material deposition. AM is an apt name for a technology that describes the construction of 3D objects by adding material, whether plastic or metal, layer by layer. AM technology can utilize computers, 3D modeling software (computer-aided design or CAD), mechanical equipment, and layered materials. Once a CAD sketch is generated, the AM equipment can read the data from the CAD file and spread or add successive layers of liquid, powder, sheet material, or other material in a layer-by-layer fashion to manufacture the 3D object. It will be appreciated that the term "additive manufacturing" encompasses a number of technologies, including subsets such as 3D printing, rapid prototyping (RP), direct digital manufacturing (DDM), layered manufacturing, and additive fabrication. Non-limiting examples of additive manufacturing that can be used to form additively manufactured components include powder bed fusion, photopolymerization, binder jetting, material extrusion, directed energy deposition, material jetting, sheet lamination. Additionally, "additively manufactured" components can also include components formed by investment casting, 3D printing, additive metal, or any combination thereof.

[0019] As used herein, the terms "forward" or "upstream" refer to movement in a direction toward an engine inlet, or a component being relatively closer to the engine inlet as compared to other components. The term "aft" or "downstream" used in connection with "forward" or "upstream" refers to a direction toward an engine aft or outlet, or a component being relatively closer to the engine outlet as compared to other components.

[0020] As used herein, a "set" can include any number of the respective described elements, including only one element. Further, as used herein, the terms "radial" or "radially" refer to a dimension extending between a central longitudinal axis of the engine and an outer engine circumference.

[0021] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are used only for identification and do not create limitations on the position, orientation, or use of the disclosure, unless specifically stated. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate members between the elements that are connected and relative movement between elements. As such, connection references do not necessarily infer that two elements are directly connected and in fixed relation to each other. The exemplary drawings are for purposes of illustration only and the dimensions, positions, order and relative sizes reflected in the drawings attached hereto can vary.

[0022] Figure 1 is a cross-sectional schematic view of a gas turbine engine 10 for an aircraft. The engine 10 has a generally longitudinally extending axis or centerline 12 extending from a forward end 14 to an aft end 16. The engine 10 includes, in downstream serial flow relationship, a fan section 18 including a fan 20, a compressor section 22 including a booster or low-pressure (LP) compressor 24 and a high-pressure (HP) compressor 26, a combustion section 28 including a combustor 30, a turbine section 32 including an HP turbine 34 and a LP turbine 36, and an exhaust section 38.

[0023] The fan section 18 includes a fan casing 40 surrounding the fan 20. The fan 20 includes a plurality of fan blades 42 disposed radially about the centerline 12. The HP compressor 26, the combustor 30, and the HP turbine 34 form a core 44 of the engine 10 that produces combustion gases. The core 44 is surrounded by a core casing 46, which can be coupled with the fan casing 40.

[0024] An HP shaft or spool 48 coaxially disposed about the centerline 12 of the engine 10 drivingly connects the HP turbine 34 to the HP compressor 26. An LP shaft or spool 50 coaxially disposed about the centerline 12 of the engine 10 within a larger diameter annular HP spool 48 drivingly connects the LP turbine 36 to the LP compressor 24 and the fan 20. The spools 48, 50 can rotate about the engine centerline and be coupled to a plurality of rotatable elements that can collectively define a rotor 51.

[0025] The LP compressor 24 and the HP compressor 26 each include a plurality of compressor stages 52, 54 having a set of blades 56, 58 and a set of vanes 60, 62. Each set of blades 56, 58 includes a set of compressor blades 56, 58 rotating relative to each set of vanes 60, 62 (also referred to as nozzles) to compress or pressurize a fluid flow through the stage. In a single compressor stage 52, 54, the plurality of compressor blades 56, 58 can be disposed in a ring and can extend radially outward from a blade platform to a blade tip relative to the centerline 12, with the corresponding set of stationary compressor vanes 60, 62 located upstream and adjacent to the rotating blades 56, 58. Note that the number of stages, vanes, and blades shown is selected for illustrative purposes only, and other numbers are possible. Figure 1 The number of stages, vanes, and blades shown is selected for illustrative purposes only, and other numbers are possible.

[0026] The blades 56, 58 of a compressor stage can be mounted to (or integrated with) a disk 61 that is mounted to a corresponding one of the HP and LP spools 48, 50. The vanes 60, 62 of a compressor stage can be circumferentially arranged mounted to the core casing 46.

[0027] The HP turbine 34 and the LP turbine 36 each include a plurality of turbine stages 64, 66 having a set of blades 68, 70 and a set of vanes 72, 74. Figure 2 ) Each set of blades 68, 70 includes a set of turbine blades 68, 70 rotating relative to each set of vanes 72, 74 (also referred to as nozzles) to extract energy from a fluid flow through the stage. In a single turbine stage 64, 66, the plurality of turbine blades 68, 70 can be disposed in a ring and can extend radially outward from a blade platform to a blade tip relative to the centerline 12, with the corresponding set of stationary turbine vanes 72, 74 located upstream and adjacent to the rotating blades 68, 70. Note that the number of stages, vanes, and blades shown is selected for illustrative purposes only, and other numbers are possible. Figure 1 The number of stages, vanes, and blades shown is selected for illustrative purposes only, and other numbers are possible.

[0028] The blades 68, 70 of a turbine stage can be mounted to (or integrated with) a disk 71 that is mounted to a corresponding one of the HP and LP spools 48, 50. The vanes 72, 74 of a turbine stage can be circumferentially arranged mounted to the core casing 46.

[0029] In addition to the rotor portion, the stationary portion of the engine 10, such as the static vanes 60, 62, 72, 74 in the compressor and turbine sections 22, 32, are also referred to individually or collectively as the stator 63. As such, the stator 63 can refer to the combination of non-rotating elements in the entire engine 10.

[0030] In operation, the airflow exiting the fan section 18 is split such that a portion of the airflow is directed into the LP compressor 24, which then supplies pressurized air 76 to the HP compressor 26, further pressurizing the air. The pressurized air 76 from the HP compressor 26 is mixed with fuel in the combustor 30 and ignited, producing combustion gases. The HP turbine 34 extracts some work from these gases, driving the HP compressor 26. The combustion gases are discharged into the LP turbine 36, which extracts additional work to drive the LP compressor 24, and the exhaust is ultimately discharged from the engine 10 via the exhaust section 38. The drive of the LP turbine 36 drives the LP spool 50 to rotate the fan 20 and the LP compressor 24.

[0031] A portion of the pressurized airflow 76 can be extracted from the compressor section 22 as bleed air 77. The bleed air 77 can be extracted from the pressurized airflow 76 and provided to engine components that require cooling. The temperature of the pressurized airflow 76 entering the combustor 30 is significantly elevated. As such, cooling provided by the bleed air 77 is necessary to operate such engine components in an elevated temperature environment.

[0032] The remaining portion of the airflow 78 bypasses the LP compressor 24 and the engine core 44 and exits the engine assembly 10 through a stationary vane row, more specifically an exit guide vane assembly 80 (which includes a plurality of airfoil guide vanes 82) at the fan discharge side 84. More specifically, a circumferential row of radially extending airfoil guide vanes 82 are utilized proximate the fan section 18 to impart some directional control to the airflow 78.

[0033] Some of the air supplied by the fan 20 can bypass the engine core 44 and be used to cool portions of the engine 10, particularly hot portions, and / or to cool or power other aspects of the aircraft. In the case of a turbine engine, the hot portions of the engine are generally downstream of the combustor 30, particularly the turbine section 32, with the HP turbine 34 being the hottest portion as it is directly downstream of the combustion section 28. Other sources of cooling fluid can be, but are not limited to, fluid bled from the LP compressor 24 or the HP compressor 26.

[0034] Figure 2 is Figure 1FIG. 2 is a close-up view of a portion of the HP turbine 34, more clearly showing one half of the annular passage 49 at the HP turbine 34; it should be understood that the HP turbine 34 can include additional components not shown. The HP turbine 34 can include a plurality of turbine stages 64. Each turbine stage 64 can include a pair of airfoil assemblies, and is shown to include exemplary vane and bucket assemblies 65, 67. Although the HP turbine 34 is shown, aspects of the present disclosure can be applied to other areas of the engine, including the LP turbine 36 and the compressor section 22, and further including exemplary vane and bucket assemblies 55, 57 Figure 1 Additionally, it should be understood that the HP turbine 34 can include more or fewer stages 64 than shown, and that the stages 64 are for illustrative purposes only.

[0035] The vane and bucket assemblies 65, 67 are provided within the annular passage 49 in a circumferentially spaced arrangement of vanes 68 and buckets 72 through which the flow of combustion gases can move. The vane assembly 65 can include vanes 68 mounted on a vane platform 88 and extending radially outward from dovetails 90. The dovetails 90 are mounted to a disk 71, which are collectively connected to form the rotor 51.

[0036] A plurality of hangers 95 are schematically shown coupled to the core casing 46 Figure 1 and are structured to support a corresponding plurality of annular shrouds 97, with each shroud 97 surrounding a corresponding vane 68. The hangers 95 and shrouds 97 can collectively define a shroud and hanger assembly 100. For clarity, the hangers 95 and shrouds 97 are shown with a rectangular geometric profile in Figure 2 and it should be understood that any desired geometric profile can be used. Additionally, either or both of the hangers 95 and shrouds 97 can include attachment arms, seals, internal cavities, baffles, or any other desired components suitable for the environment of the shroud and hanger assembly 100.

[0037] Further details of the shroud and hanger assembly 100 are shown in Figure 3 The hangers 95 can include a first surface 101 facing a cooling gas flow 115, a second surface 102 facing a heating gas flow 117, and a third surface 103 radially outward of the first surface 101. In the example shown, the second surface 102 of the hangers 95 is spaced apart from the heating gas flow 117 by the shrouds 97. It should also be understood that the hangers 95 can form part of an annular shroud and hanger assembly. In the example shown, the hangers 95 and shrouds 97 form part of an annular shroud and hanger assembly 100 that encircles the HP turbine 34 and surrounds the corresponding vanes 68.

[0038] The cyclone separators 120 can be included within the pylon 95. It is contemplated that the pylon 95 can have a unitary body 105 in which the third surface 103 at least partially defines the cyclone separators 120. In such a case, the cyclone separators 120 can be integrally formed with the pylon 95, such as by additive manufacturing. As shown, the unitary body 105 includes a plurality of cyclone separators 120 that are arranged in a circumferentially spaced apart arrangement in the unitary body. Any number of cyclone separators 120 can be included. Additionally, diagonal load brackets 104 can be provided along the third surface 103 to increase the structural stability of the pylon 95. In such a case, as shown, a plurality of cyclone separators 120 can be included between adjacent diagonal load brackets 104.

[0039] The cyclone separators 120 can also form a portion of the internal ducting within the pylon 95 for cooling the airflow 115. For example, a set of cooling air inlets 108 can be formed in the first surface 101 of the pylon 95 such that the cooling airflow 115 can enter the body of the pylon 95. Any number, size, or shape of cooling air inlets 108 can be used.

[0040] Figure 4 A cross-sectional view of the shroud and pylon assembly 100 is shown. A reference line 13 is shown that generally represents and is parallel to the engine centerline 12. The cyclone separators 120 can include a cyclone body 122 having a conical portion 124 and a cylindrical portion 126 shown, as well as a centerline 132. In the example shown, the conical portion 124 and the cylindrical portion 126 of the cyclone separators 120 are aligned with the centerline 132 as shown. In other non-limiting examples (not shown), the conical portion 124 and the cylindrical portion 126 can not be aligned with the centerline 132, or each can be parallel to and offset from the centerline 132.

[0041] It is also contemplated that the centerline 132 of the cyclone separators 120 can not be aligned with the centerline 12 of the turbine engine 10. For example, the cyclone separators 120 can be oriented at an angle such that the centerline 132 is parallel to the diagonal load brackets 104 Figure 2 ) of the pylon 95.

[0042] The cyclone separators 120 can further include a tangential dirty air inlet 134, a scavenge outlet 136, and a clean air outlet 138. As shown, the dirty air inlet 134 and the clean air outlet 138 are located in the cylindrical portion 126, and the scavenge outlet 136 is located in the conical portion 124. Additionally, the scavenge outlet 136 can be located radially outward of the clean air outlet 138. The dirty air inlet 134 can also be located radially outward of the clean air outlet 138, such as between the clean air outlet 138 and the scavenge outlet 136.

[0043] A clean air conduit 135 can be located within the cyclonic separator 120 proximate the dirty air inlet 134 and the clean air outlet 138, and fluidly coupled to the scavenge outlet 136. The clean air conduit 135 can have an annular geometric profile about the centerline 132. In the illustrated example, the clean air conduit 135 can extend at least partially over and spaced apart from the dirty air inlet 134 to prevent air from flowing directly from the dirty air inlet 134 to the clean air outlet 138.

[0044] The inlet conduit 140 can extend into the monolithic body 105 and fluidly couple the cooling air inlets 108 and the dirty air inlet 134. In alternative examples (not shown), the dirty air inlet can be positioned on the first surface 101 to define a cooling air inlet without the use of an inlet conduit. In yet another example (not shown), a single cooling air inlet can be fluidly coupled to multiple cyclonic separators. It will also be appreciated that although two cooling air inlets 108 are shown fluidly coupled to the inlet conduit 140, any number of cooling air inlets 108 can be utilized, including a single cooling air inlet 108 coupled to a single inlet conduit 140.

[0045] The cooling air outlet 144 can be formed on the second surface 102 of the monolithic body 105, and the outlet conduit 142 can extend into the cyclonic body 122 and fluidly couple the clean air outlet 138 and the cooling air outlet 144. In this manner, the monolithic body 105 can define a cooling air circuit 155 between the cooling air inlets 108 on the first surface 101 and the cooling air outlet 144 on the second surface 102. As shown, the cooling air circuit 155 can pass through the cyclonic separator 120 between the dirty air inlet 134 and the clean air outlet 138. It is further contemplated that the clean air outlet 138 can have an outlet centerline 139 that is aligned with the centerline 132.

[0046] It will be appreciated that air exiting the clean air outlet 138 can still carry some dirt or debris, with the majority of the dirt or debris entering the cyclonic separator 120 being exhausted through the scavenge outlet 136. Where "clean air" is described herein, it will be appreciated that "clean" can refer to the removal of less than all of the contaminants that can be present in the air stream. It will also be appreciated that in examples where the monolithic body 105 defines multiple cyclonic separators 120 Figure 3 ) the multiple cooling air circuits 155 can extend through each of the respective multiple cyclonic separators 120.

[0047] Additionally, the conical portion 124 can define a first length 128, while the cylindrical portion 126 can define a second length 130. In the example shown, the first length 128 is greater than the second length 130. However, it is also contemplated that the first length 128 can also be equal to or less than the second length 130. The first length 128, the second length 130, and the ratio of the lengths 128, 130 can be adjusted to adjust any or all of the airflow rate within the cyclone separator 120, the rate at which contaminants are removed from the airflow within the cyclone separator 120, or the dust / debris particle size limit removed from the airflow within the cyclone separator 120. In one example, a faster airflow through the separator 120 can result in an increased rate of particle removal via the scavenger outlet 136. In another example, a slower airflow can provide for the removal of larger particle sizes from the airflow.

[0048] The hanger 95 can further include a back wall 109 having at least one drain hole 110. For clarity, the at least one drain hole 110 is shown as a single hole extending through the back wall 109. It will be understood that the at least one drain hole 110 can include multiple holes, any or all of which can be straight or curved, and can have any suitable centerline angle relative to the back wall 109. The drain hole 110 can be fluidly coupled to the scavenger outlet 136 and to a benign region 145 of the turbine engine 10. As used herein, a "benign region" will refer to a region of the turbine engine 10 that is not adversely affected by dust or debris, or that has sufficient tolerance for the presence of dust or debris such that the performance or efficiency of the turbine engine 10 is not reduced by an undesirable amount. For example, certain regions within the engine 10 can be cooled by the use of cooling air (e.g., upstream or downstream purge cavities) or prevented from ingesting hot combustion airflow even though debris can be present in the cooling air. A "benign region" can also refer to a region of the turbine engine 10 that is easily accessible or cleanable, such that any accumulated dust or debris can be easily removed.

[0049] The shroud 97 can be coupled to the hanger 95 to form a shroud and hanger assembly 100. The shroud 97 can include a shroud body 160 having an inner surface 161 facing the second surface 102 of the hanger 95 and a heating surface 162 facing the heated airflow 117. A shroud cooling circuit 166 can extend through the shroud body 160 between a shroud inlet 164 on the inner surface 161 and a shroud outlet 168 on the heating surface 162. For clarity, the shroud cooling circuit 166 is shown schematically as a single passage extending through the shroud body 160. It will be understood that the shroud cooling circuit 166 can further include multiple passages, cavities, or other internal features (not shown), and can be formed within the shroud body 160 to have any desired size, geometry, or shape. In one non-limiting example, the shroud cooling circuit 166 can be in the form of a plurality of film holes extending between the inner surface 161 and the heating surface 162. In another non-limiting example, the shroud cooling circuit 166 can include a plurality of fluidly coupled internal passages within the interior of the shroud body 160.

[0050] It is contemplated that the shroud cooling circuit 166 can be fluidly coupled to the cooling air circuit 155 in the hanger 95. More specifically, the shroud inlet 164 can be fluidly coupled to the clean air outlet 138 at the cylindrical portion 126 of the cyclone body 122.

[0051] Figure 5 Air flowing through the shroud and hanger assembly 100 during operation of the engine 10 Figure 1 ) is shown. The debris-laden cooling air 116 (shown by arrows) can enter the unitary body 105 through the cooling air inlet 108 and flow into the cyclone body 122 through the dirty air inlet 134. A portion of the debris-laden cooling air 116 can move through the purge outlet 136 to define the purge airflow 118. The remaining portion of the debris-laden cooling air 116 can define a clean cooling airflow 119 that moves through the clean air outlet 138.

[0052] The dirty air inlet 134 can form a tangential inlet such that the debris-laden cooling air 116 can spin within the cyclone body 122 around the clean air conduit 135 and move toward the conical portion 124. The converging, angled walls of the conical portion 124 can cause the spinning cooling airflow 116 to increase in velocity as it moves toward the scavenge outlet 136. Dust, dirt, or other debris 135 within the spinning cooling air 116 can have sufficient momentum within the scavenge airflow 118 to exit the scavenge outlet 136. The cleaned cooling airflow 119 can be redirected back into the cylindrical portion 126. The cleaned cooling airflow 119 can then flow through the outlet conduit 142 and exit the hanger 95 through the clean air outlet 138. In this manner, the cooling air circuit 155 can extend through the conical portion 124 and the cylindrical portion 126 of the cyclone separator 120.

[0053] It is also contemplated that the scavenge outlet 136 of the cyclone separator 120 can be fluidly separated from the shroud cooling circuit 166, thereby preventing debris 135 from entering the shroud cooling circuit 166. Additionally, the scavenge airflow 118 can exit the hanger 95 through the at least one drain hole 110 and into the benign zone 145. For example, the scavenge airflow 118 can flow through the drain hole 110 and into a main combustion airflow (not shown) downstream of the hanger 95. It is contemplated that the flow rate of the scavenge airflow 118 through the at least one drain hole 110 can be less than the flow rate of the cleaned cooling air through the clean air outlet 138. In another example, the flow rate of the scavenge airflow 118 through the at least one drain hole 110 can be less than the flow rate of the debris-laden cooling air 116 entering the dirty air inlet 134.

[0054] After exiting the hanger 95, the cleaned cooling airflow 119 can enter the shroud 97 through the shroud inlet 164. Additionally, the cleaned cooling airflow 119 from multiple cyclone separators 120 of the monolithic body 105 Figure 3 ) can enter the at least one shroud inlet 164. In one example, each shroud inlet 164 can be coupled to a corresponding single clean air outlet 138 of the hanger 95. In another non-limiting example, multiple clean air outlets of the hanger can be fluidly coupled to a single shroud inlet; in yet another example, a single clean air outlet of the hanger can be fluidly coupled to multiple shroud inlets. After entering the shroud 97, the cooling air 116 can then flow through the shroud cooling circuit 166 and exit the shroud 97 via the shroud outlet 168. In a non-limiting example, the exiting cooling air 116 can be used to cool the heated surfaces 162 of the shroud 97 or used as purge air for the region of the engine 10 proximate to the shroud and hanger assembly 100.

[0055] While the cooled component is shown as the shroud 97, this is merely an example and is not intended to limit the various aspects of the disclosure described herein. It is contemplated that the cooling air circuit 155 of the pylon 95 can be fluidly coupled to any cooled component within the turbine engine 10 having any suitable cooling passage and a heated surface facing a heated fluid flow. Such a cooling passage of a cooled component can be fluidly coupled to at least one of the plurality of cooling air circuits 155 of the pylon 95. It will be understood that any cooled component within the engine 10, including a cooled airfoil such as a rotating blade or a stationary vane, can be fluidly coupled to the pylon 95 and the cyclone separator 120.

[0056] It will be understood that the shroud cooling circuit 166 can include any desired or suitable form of cooling circuit, including cooling circuits not explicitly shown. In one embodiment, the shroud cooling circuit can be in the form of at least one film hole (not shown) extending between the shroud inlet and the shroud outlet. In another example, the shroud cooling circuit can include a plurality of internal cooling passages (not shown) fluidly coupled to the shroud inlet and the shroud outlet through which clean cooling air from the cyclone separator can flow and provide cooling to the shroud body. In yet another example (not shown), the shroud cooling circuit can include a combination of film holes, cooling passages, and other fluidly connected conduits extending through and within the shroud to provide cooling air to the shroud.

[0057] Turning to Figure 6 , another shroud and pylon assembly 200 is shown that can be used in the turbine engine 10 of Figure 1 . The shroud and pylon assembly 200 is similar to the shroud and pylon assembly 100; therefore, like components will be identified with like numbers increased by 100, and it will be understood that the description of like parts of the shroud and pylon assembly 100 apply to the shroud and pylon assembly 200 unless otherwise noted.

[0058] The shroud and pylon assembly 200 includes a pylon 195 having a first surface 201 facing a cooling airflow 215, a second surface 202 facing a heated airflow 217, and a third surface 203 radially outward of the first surface 201. The pylon 195 also includes a cyclone separator 220 having a cyclone body 222 with a dirty air inlet 234, a scavenger outlet 236, and a clean air outlet 238. As shown, the cyclone body 222 can also have a conical portion 224, a cylindrical portion 226, and a centerline 232. It is also contemplated that the pylon 195 can include a unitary body 205 having the first surface 201, the second surface 202, the third surface 203, and the cyclone separator 220.

[0059] The cooling air circuit 255 can extend through the gantry 195. The cooling air circuit 255 can include a cooling air inlet 244 on the first surface 201 and a cooling air outlet 244 on the second surface 202. The cooling air circuit 255 can also extend through the cyclone 220 between the dirty air inlet 234 and the clean air outlet 238.

[0060] The shroud and gantry assembly 200 can also include a shroud 197 having an inner surface 261 facing the second surface 202 of the gantry 195 and a heating surface 262 facing the heated air stream 217. The shroud 197 can also include a shroud cooling circuit 266 fluidly coupled to the cooling air circuit 244 between a shroud inlet 264 on the inner surface 261 and a shroud outlet 268 on the heating surface 262.

[0061] One difference is that a baffle 270 can be included in the shroud and gantry assembly 200. The baffle 270 can include a set of perforations 272 as shown. The baffle 270 can be positioned between the first surface 201 of the gantry 195 and the inner surface 261 of the shroud 197. In the example shown, a front impingement cavity 274 is defined between the baffle 270 and the first surface 201 of the gantry 195 and a rear impingement cavity 276 is defined between the baffle 270 and the inner surface 261 of the shroud 197.

[0062] During operation, the debris-laden cooling air 216 can flow through the cooling air circuit 255 and into the cyclone 220. The clean cooling air 219 can exit the cyclone 220 through the clean air outlet 238, into the front impingement cavity 274, and impinge upon and flow through the perforated baffle 270. The clean cooling air 219 can then enter the rear impingement cavity 276 and impinge upon the inner surface 261 of the shroud 197 to cool the shroud 197. The clean cooling air 219 can also enter the shroud inlet 264, flow through the shroud cooling circuit 266, and flow through the shroud outlet 268. In one example, the shroud cooling circuit 266 can include at least one internal cooling channel in which the clean cooling air 219 can reduce heat within the shroud 197. In another example, the shroud outlet 268 can be in the form of at least one film hole in which the clean cooling air 219 can provide cooling to the heating surface 262 of the shroud 197. In yet another example, the shroud outlet 268 can be in the form of at least one jet hole to reduce possible stagnation proximate to the heating surface 262.

[0063] Aspects of the present disclosure provide a variety of benefits, including increasing the component life of an engine operating in a high dust environment. It can be appreciated that a hanger with a cyclone separator can provide clean cooling air without the need for additional upstream separators or other debris removal components, and the removal of debris can improve the cooling performance of the cooling air. Improved cooling performance can reduce the cooling air supplied to cool engine components, thereby improving engine efficiency during operation.

[0064] Additionally, an additively manufactured hanger with an integrated cyclone separator can provide a custom geometry of the shape of the internal cooling passages, ducts, inlets, outlets, or walls, such that the dust removal rate or dust removal type or size can be optimized. For example, a portion of the annular shroud and hanger assembly can be customized to remove dust particles larger than a predetermined size, while another portion of the annular shroud and hanger assembly can be customized to remove as much dust as possible, regardless of particle size.

[0065] It should be appreciated that the application of the disclosed design is not limited to turbine engines having fan and booster sections, but can also be applied to turbojet and turboshaft engines.

[0066] In unrecited ranges, different features and structures of various embodiments can be used in combination or substituted for one another as desired. The failure to show one feature in all embodiments does not imply that it cannot be so shown, but rather for brevity of description. Thus, the various features of different embodiments can be mixed and matched as desired, regardless of whether a new embodiment is explicitly described. All combinations or permutations of features described herein are covered by the present disclosure.

[0067] This written description uses examples to disclose the application, including the best mode, and also to enable any person skilled in the art to practice the application, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the application is defined by the claims, and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent

[0068] Other aspects of the application are provided by the subject matter of the following clauses:

[0069] 1. A hanger for a turbine engine, comprising: a first surface facing a cooling airflow; a second surface facing a heating airflow; a third surface radially outside the first surface; a cyclone separator having a cyclone body at least partially defined by the third surface and having a dirty air inlet, a clean air outlet and a scavenging outlet radially outside the clean air outlet; and a cooling air circuit having a cooling air inlet on the first surface and a cooling air outlet on the second surface, and extending through the cyclone separator between the dirty air inlet and the clean air outlet.

[0070] 2. According to any hanger in the preceding clause, wherein the dirty air inlet is located radially outside the clean air outlet.

[0071] 3. According to any hanger in the preceding paragraph, it further includes multiple cyclone separators and multiple cooling air circuits, each extending through the corresponding multiple cyclone separators.

[0072] 4. According to any of the hangers in the preceding paragraph, the cyclone body also includes a conical section, a cylindrical section and a centerline.

[0073] 5. According to any hanger in the preceding clause, both the tapered and cylindrical portions are aligned with the centerline.

[0074] 6. According to any hanger in the preceding clause, the clean air outlet is aligned with the centerline.

[0075] 7. According to any hanger in the preceding paragraph, at least one of the dirty air inlet or clean air outlet is located in the cylindrical portion.

[0076] 8. According to any hanger in the preceding clause, wherein the scavenging outlet is located in the conical section.

[0077] 9. According to any of the hangers in the preceding paragraph, it further includes a diagonal load support, wherein the centerline of the cyclone separator is parallel to the diagonal load support.

[0078] 10. According to any hanger in the preceding paragraph, it further includes an inlet duct that extends through the first surface and fluidly connects the cooling air inlet to the dirty air inlet.

[0079] 11. According to any hanger in the preceding paragraph, it further includes an outlet conduit extending through the second surface and fluidly connecting the clean air outlet and the cooling air outlet.

[0080] 12. Any hanger according to the preceding clause further includes an integral body having a first surface, a second surface, a third surface and a cyclone separator.

[0081] 13. A shroud and pylon assembly for a turbine engine, comprising a pylon and a shroud, the pylon comprising: a first surface facing a cooling airflow; a second surface facing a heating airflow; a third surface radially outward of the first surface; a cyclone separator having a cyclone body at least partially defined by the third surface and having a dirty air inlet, a clean air outlet, and a sweep air outlet radially outward of the clean air outlet; and a cooling air circuit having a cooling air inlet on the first surface and a cooling air outlet on the second surface and extending through the cyclone separator between the dirty air inlet and the clean air outlet; the shroud comprising: an inner surface facing the second surface of the pylon; a heating surface facing the heating airflow; and a shroud cooling circuit fluidly coupled to the cooling air circuit and extending through the shroud between a shroud inlet on the inner surface and a shroud outlet on the heating surface.

[0082] 14. The shroud and pylon assembly of any preceding clause, wherein the dirty air inlet is radially outward of the clean air outlet.

[0083] 15. The shroud and pylon assembly of any preceding clause, wherein the cyclone body further comprises a conical portion and a cylindrical portion.

[0084] 16. The shroud and pylon assembly of any preceding clause, wherein the shroud inlet is fluidly coupled to the clean air outlet at the cylindrical portion.

[0085] 17. The shroud and pylon assembly of any preceding clause, wherein the sweep air outlet is at the conical portion and fluidly separated from the shroud cooling circuit.

[0086] 18. The shroud and pylon assembly of any preceding clause, further comprising a baffle between the first surface of the pylon and the inner surface of the shroud and defining at least one of a forward impingement cavity or an aft impingement cavity.

[0087] 19. A turbine engine comprising a compressor, a combustor, and a turbine in axial flow arrangement, comprising: a cooling component having an internal cooling passage and a heating surface facing a heating airflow; and a pylon comprising: a first surface facing a cooling airflow; a second surface facing a heating airflow; a third surface radially outward of the first surface; a cyclone separator having a cyclone body at least partially defined by the third surface and having a dirty air inlet, a clean air outlet, and a sweep air outlet radially outward of the clean air outlet; and a cooling air circuit having a cooling air inlet on the first surface and a cooling air outlet on the second surface and extending through the cyclone separator between the dirty air inlet and the clean air outlet.

[0088] 20. The turbine engine of any preceding clause, wherein the cooling component comprises a portion of a casing surrounding at least one of the compressor, the combustor, or the turbine.

Claims

1. A hanger for a turbine engine having an engine centerline, characterized in that, include: A first surface, the first surface facing the cooling airflow; The second surface faces the heated airflow; A third surface, which is radially outside the second surface relative to the engine centerline; Cyclone separator, the cyclone separator comprising: A cyclone body, the cyclone body being at least partially defined by the third surface and having a conical portion, a cylindrical portion, and a separator centerline extending through the conical portion and the cylindrical portion, wherein the separator centerline is not aligned with the engine centerline; A dirty air inlet, wherein the dirty air inlet is located in one of the cylindrical portion or the conical portion; Clean air outlet, the clean air outlet being located within the cylindrical portion; and A scavenging outlet, wherein the scavenging outlet is located in the conical portion; Adjacent to the outer wall of the cyclone body and an exhaust port extending through the outer wall, wherein the exhaust port is located radially inside the scavenging outlet; and A cooling air circuit having a cooling air inlet on a first surface and a cooling air outlet on a second surface, and extending through the cyclone separator between the dirty air inlet and the clean air outlet.

2. The hanger according to claim 1, characterized in that, The dirty air inlet is located radially outside the clean air outlet relative to the engine centerline.

3. The hanger according to claim 1, characterized in that, The clean air outlet is aligned with the center line of the separator.

4. The hanger according to claim 1, characterized in that, The scavenging outlet fluidly connects the scavenging outlet to a benign area located outside the hanger.

5. The hanger according to claim 4, characterized in that, The scavenging outlet is located radially outside the exhaust port relative to the engine centerline.

6. The hanger according to claim 1, characterized in that, The cyclone body includes opposite ends, wherein the scavenging air outlet is located at one end of the opposite ends, and the clean air outlet is located at the other end of the opposite ends of the cyclone body.

7. The hanger according to claim 1, characterized in that, The centerline of the separator forms an acute angle with the centerline of the engine.

8. The hanger according to claim 1, characterized in that, The centerline of the separator extends at least radially.

9. The hanger according to claim 1, characterized in that, The first surface, the second surface, the third surface, and the cyclone separator are integrated into a single, monolithic body.

10. A shield and hanger assembly for defining the centerline of a turbine engine, characterized in that, include: Hanger, the hanger comprising: A first surface, the first surface facing the cooling airflow; The second surface faces the heated airflow; A third surface, which is radially outside the second surface; Cyclone separator, the cyclone separator comprising: A cyclone body, the cyclone body being at least partially defined by the third surface and having a conical portion, a cylindrical portion, and a separator centerline extending through the conical portion and the cylindrical portion, wherein the centerline is not aligned with the engine centerline; A dirty air inlet, wherein the dirty air inlet is located in one of the cylindrical portion or the conical portion; Clean air outlet, the clean air outlet being located within the cylindrical portion; and A scavenging outlet, wherein the scavenging outlet is located in the conical portion; Adjacent to the outer wall of the cyclone body and an exhaust port extending through the outer wall, wherein the exhaust port is located radially inside the scavenging outlet; and A hanger cooling air circuit having a cooling air inlet on a first surface and a cooling air outlet on a second surface, and extending between the dirty air inlet and the clean air outlet through the cyclone separator; and The protective cover includes: The inner surface faces the second surface of the hanger; A heating surface, the heating surface facing the heating airflow; and A shroud cooling circuit is fluidly connected to the hanger cooling air circuit and extends through the shroud between a shroud inlet on the inner surface and a shroud outlet on the heated surface.

11. The protective cover and hanger assembly according to claim 10, characterized in that, The dirty air inlet is located radially outside the clean air outlet relative to the engine centerline.

12. The protective cover and hanger assembly according to claim 10, characterized in that, The centerline of the separator extends at least radially.

13. The protective cover and hanger assembly according to claim 10, characterized in that, The shroud inlet is fluidly connected to the clean air outlet, thereby fluidly connecting the shroud cooling circuit to the hanger cooling air circuit.

14. The protective cover and hanger assembly according to claim 13, characterized in that, The cyclone body further includes a scavenging outlet in the conical portion.

15. The protective cover and hanger assembly according to claim 13, characterized in that, It further includes an outer wall adjacent to the cyclone body and has at least one discharge port fluidly connected to a benign area located outside the hanger.

16. The protective cover and hanger assembly according to claim 10, characterized in that, It further includes a baffle positioned between the first surface of the hanger and the inner surface of the shield, and forming at least one of a front impact cavity or a rear impact cavity.

17. A turbine engine comprising an axially flowing compressor, a combustor, and a turbine defining an engine centerline, the turbine engine generating a heated airflow and providing a cooling airflow, characterized in that, The turbine engine includes: A cooling component having an internal cooling channel and a heating surface facing the heating airflow; and Hanger, the hanger comprising: A first surface, the first surface facing the cooling airflow; A second surface, the second surface facing the heated airflow; A third surface, which is radially outside the second surface; Cyclone separator, the cyclone separator comprising: A cyclone body, the cyclone body being at least partially defined by the third surface and having a conical portion, a cylindrical portion, and a centerline extending through the conical portion and the cylindrical portion, wherein the centerline is not aligned with the engine centerline; A dirty air inlet, wherein the dirty air inlet is located in one of the cylindrical portion or the conical portion; Clean air outlet, the clean air outlet being located within the cylindrical portion; and A scavenging outlet, wherein the scavenging outlet is located in the conical portion; Adjacent to the outer wall of the cyclone body and an exhaust port extending through the outer wall, wherein the exhaust port is located radially inside the scavenging outlet; and A cooling air circuit having a cooling air inlet on a first surface and a cooling air outlet on a second surface, and extending through the cyclone separator between the dirty air inlet and the clean air outlet.

18. The turbine engine according to claim 17, characterized in that, The cooling component includes a portion of a housing surrounding at least one of the compressor, the burner, or the turbine.

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