Turbine containment system

Abstract

A turbine housing system is provided. The turbine housing system includes a first housing member surrounding a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; and a second housing member communicating with the first housing member, wherein the first housing member and the second housing member together house each of the rotor disks and rotor blades therein.

Description

Technical Field

[0001] This topic generally relates to a gas turbine engine, or more specifically to a turbine housing system. Background Technology

[0002] Gas turbine engines comprise several sections, including rotating blades housed within an engine casing (e.g., a turbine housing). If a blade breaks, it must be contained within the casing. To ensure the broken blade does not puncture the casing, the casing walls are manufactured to be relatively thick and / or reinforced with metal or other suitable materials. The turbine housing relies on external ducting systems for cooling, such as Active Clearance Control (ACC) external ducting arrangements, to supply cooler air to the outer surfaces of the casing, helping to maintain the proper temperature of the casing and provide adequate turbine rotor / stator clearance during operation. The complexity of external and auxiliary ducting, supports, and valves increases manufacturing costs and engine weight. Summary of the Invention

[0003] Aspects and advantages of the invention 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 invention.

[0004] In one exemplary embodiment of this disclosure, a turbine housing system is provided. The turbine housing system includes: a first housing member surrounding a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; and a second housing member communicating with the first housing member, wherein the first housing member and the second housing member together house each of the rotor disks and rotor blades therein.

[0005] In some exemplary embodiments, the first receiving member is an active clearance control housing in communication with the turbine.

[0006] In some exemplary embodiments, the second receiving member includes a Kevlar wrapping disposed on a portion of the active clearance control housing.

[0007] In some exemplary embodiments, the turbine housing system includes a shroud with holes on its inner surface, wherein the shroud supports a portion of a second housing member.

[0008] In some exemplary embodiments, the turbine housing system includes a source of cooling air in communication with the active clearance control housing and the shroud, wherein a first flow of cooling fluid from the cooling air source is directed through orifices in the active clearance control housing and the shroud to the turbine.

[0009] In some exemplary embodiments, the openings in the shroud are positioned radially adjacent to the turbine.

[0010] In some exemplary embodiments, the turbine housing system includes a spoke mounting connector between an active clearance control housing and a second housing member to control thermal motion therebetween.

[0011] In some exemplary embodiments, a first receiving member surrounds the turbine between a first end and a second end along the longitudinal axis of the turbine receiving system, and wherein a first thickness of the first receiving member at the first end is different from a second thickness of the first receiving member at the second end.

[0012] In some exemplary embodiments, the second housing member is a soft-walled hoop member attached to the turbine housing system below the core cowling portion of the turbine engine.

[0013] In some exemplary embodiments, the soft-walled hoop member is formed of ultra-high molecular weight polyethylene material.

[0014] In some exemplary embodiments, the turbine housing system includes a high-temperature hard-walled housing disposed on a first housing member.

[0015] In some exemplary embodiments, the high-temperature hard-walled shell is formed of a titanium alloy material.

[0016] In some exemplary embodiments, a high-temperature hard-walled casing is attached to the turbine housing system below the core cowling portion of the turbine engine.

[0017] In another exemplary embodiment of this disclosure, a turbine housing system is provided. The turbine housing system includes: a first housing member surrounding a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; a second housing member communicating with the first housing member; and a shroud including a hole on an inner surface of the shroud, wherein the shroud supports a portion of the second housing member; wherein the first housing member and the second housing member together house each of the rotor disks and rotor blades therein.

[0018] In some exemplary embodiments, the turbine housing system includes a source of cooling air in communication with the first housing member and the shroud.

[0019] In some exemplary embodiments, a first cooling fluid flow from a cooling air source is guided through holes in a first receiving member and a shroud to reach the turbine.

[0020] In some exemplary embodiments, the turbine housing system includes a spoke mounting connector between a first housing member and a second housing member to control thermal motion therebetween.

[0021] In some exemplary embodiments, a first receiving member surrounds the turbine between a first end and a second end along the longitudinal axis of the turbine receiving system, and wherein a first thickness of the first receiving member at the first end is different from a second thickness of the first receiving member at the second end.

[0022] In some exemplary embodiments, the second housing member is a soft-walled hoop member attached to the turbine housing system below the core cowling portion of the turbine engine.

[0023] In some exemplary embodiments, the turbine housing system includes a high-temperature hard-walled housing disposed on a first housing member.

[0024] These and other features, aspects, and advantages of this disclosure will become better understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and form a part of this specification, illustrate various aspects of this disclosure and, together with the description, serve to explain the principles of this disclosure. Attached Figure Description

[0025] The specification sets forth a complete and practical disclosure for those skilled in the art, including its best mode, which is referenced in the accompanying drawings, wherein:

[0026] Figure 1 This is a schematic cross-sectional view of an exemplary gas turbine engine according to an exemplary embodiment of the present disclosure.

[0027] Figure 2A This is a cross-sectional view of a turbine housing system according to an exemplary embodiment of the present disclosure.

[0028] Figure 2B This is an exploded cross-sectional view of the connection system of a turbine housing system according to an exemplary embodiment of the present disclosure.

[0029] Figure 3 This is a cross-sectional view of a turbine housing system according to another exemplary embodiment of the present disclosure.

[0030] Figure 4 This is a cross-sectional view of a turbine housing system according to another exemplary embodiment of the present disclosure.

[0031] Figure 5 This is a cross-sectional view of a first housing member of a turbine housing system having various thickness configurations according to exemplary embodiments of the present disclosure.

[0032] The corresponding reference symbols indicate the respective portions throughout the multiple views. The exemplary embodiments set forth herein illustrate exemplary embodiments of this disclosure, and such exemplary embodiments should not be construed as limiting the scope of this disclosure in any way. Detailed Implementation

[0033] 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 description uses numerals and letter names to refer to features in the drawings. The same or similar reference numerals in the drawings and description are used to refer to the same or similar parts of the invention.

[0034] The following description is provided to enable those skilled in the art to make and use the described embodiments contemplated for carrying out the invention. However, various modifications, equivalents, variations, and options will still be apparent to those skilled in the art. Any and all such modifications, variations, equivalents, and options are intended to fall within the spirit and scope of the invention.

[0035] For the purposes of the description below, the terms “upper,” “lower,” “right,” “left,” “vertical,” “horizontal,” “top,” “bottom,” “lateral,” “longitudinal,” and their derivatives shall be used in connection with the invention as they are oriented in the accompanying drawings. However, it should be understood that various alternative variations are presupposed in the invention unless explicitly stated otherwise. It should also be understood that the specific devices shown in the drawings and described in the following specification are merely exemplary embodiments of the invention. Therefore, the specific dimensions and other physical characteristics associated with the embodiments disclosed herein are not to be considered limiting.

[0036] 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.

[0037] The terms "front" and "rear" refer to the relative positions within a gas turbine engine. "Front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0038] As used herein, the terms “upstream” and “downstream” refer to the relative directions of fluid flow within a fluid flow path. For example, “upstream” refers to the direction from which fluid flows, and “downstream” refers to the direction from which fluid flows.

[0039] Unless the context clearly specifies otherwise, the singular forms “a,” “an,” and “the” include plural references.

[0040] Furthermore, unless otherwise stated, the terms "low," "high," or their respective degrees of comparison (e.g., lower, higher, where applicable) refer to relative speeds within the engine. For example, a "low-pressure turbine" operates at pressures typically lower than a "high-pressure turbine." Alternatively, unless otherwise stated, the above terms may be understood at their superlative level. For example, a "low-pressure turbine" may refer to the turbine with the lowest maximum pressure within the turbine section, while a "high-pressure turbine" may refer to the turbine with the highest maximum pressure within the turbine section.

[0041] The approximate language used in this specification and claims is intended to modify any quantitative representation that may allow for variation without altering the underlying functionality. Therefore, values ​​modified by one or more terms, such as “approximately,” “about,” and “substantially,” 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 part and / or system. For example, approximate language may refer to a margin of 10%. Scope limitations are combined and interchanged herein and throughout this specification and claims, and these scopes are identified and include all subscopes contained herein, unless the context or language otherwise indicates.

[0042] Throughout this specification and claims, scope limitations are combined and interchanged, and these scopes are identified and include all subscopes contained herein, unless the context or language indicates otherwise. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0043] The turbine housing system of this disclosure includes a first housing member and a second housing member communicating with the first housing member, together protectively surrounding a turbine or a portion of a turbine assembly. It is contemplated that the turbine housing system of this disclosure can be configured to protectively surround an LP turbine, an HP turbine, or other turbines. In an exemplary embodiment, the turbine assembly includes a plurality of rotor disks, each rotor disk including rotor blades coupled thereto.

[0044] The turbine housing system disclosed herein protectively surrounds a portion of a turbine or turbine assembly such that a first housing member and a second housing member together house each of the rotor disk and rotor blades therein. For example, the rotating portion of a turbine assembly (e.g., an LP turbine) may be subjected to high centrifugal forces, which could cause the rotor (e.g., rotor blades and rotor disk) to burst together due to high stress or manufacturing defects. The present invention effectively houses both the rotor blades and rotor disk by utilizing both the first housing member and the second housing member simultaneously.

[0045] Referring now to the accompanying drawings, the same numbers throughout the drawings denote the same elements. Figure 1 This is a schematic cross-sectional view of a gas turbine engine according to exemplary embodiments of the present disclosure. More specifically, for Figure 1In an embodiment, an exemplary gas turbine engine 10 has a longitudinal axis 11 defining a longitudinal direction L and a radial direction R extending radially outward from the longitudinal axis 11. The gas turbine engine 10 includes a fan assembly 12 and a core gas turbine engine 13. The core gas turbine engine 13 includes a high-pressure compressor 14, a combustor 16, and a high-pressure turbine 18. In an exemplary embodiment, the gas turbine engine 10 may also include a low-pressure turbine 20. The fan assembly 12 includes an array of fan blades 24 extending radially outward from a rotor disk 26. The engine 10 has an intake side 28 and an exhaust side 30. The gas turbine engine 10 also includes a plurality of bearing assemblies (not shown), for example, used to provide rotational and axial support to the fan assembly 12, compressor 14, high-pressure turbine 18, and low-pressure turbine 20.

[0046] In operation, the inlet airflow 48 flows through the fan assembly 12 and is divided into a first portion 50 and a second portion 52 by the airflow splitter 44. The first portion 50 of the airflow is directed through the compressor 14, where the airflow is further compressed and delivered to the combustor 16. The hot combustion products from the combustor 16 are used to drive the turbines 18 and 20, thereby generating engine thrust. The gas turbine engine 10 also includes a bypass duct 40 for allowing the second portion 52 of the airflow exiting the fan assembly 12 to bypass the core gas turbine engine 13. More specifically, the bypass duct 40 extends between the inner wall 43 of the fan housing or shroud 42 and the outer wall 45 of the splitter 44.

[0047] Figure 2A-5 Exemplary embodiments of this disclosure are shown. References Figure 2A-2B In an exemplary embodiment, the turbine housing system 100 can be coupled with... Figure 1 The exemplary gas turbine engine 10 shown is used in conjunction with this. The turbine housing system 100 includes a first housing member 102 and a second housing member 104. (Reference) Figure 2A The first receiving member 102 and the second receiving member 104 surround the turbine assembly 120 along the longitudinal axis 150 of the turbine receiving system 100.

[0048] like Figure 2A As shown, a first receiving member 102 and a second receiving member 104 communicating with the first receiving member 102 protectively surround a portion of the turbine or turbine assembly 120. It is envisioned that the turbine receiving system 100 of this disclosure can protectively surround the LP turbine 20 ( Figure 1 Furthermore, it is envisioned that the turbine housing system 100 of this disclosure can protectively surround the HP turbine 18 ( Figure 1 Alternatively, a turbine configuration may be used. In an exemplary embodiment, the turbine assembly 120 includes a plurality of rotor disks 122, each rotor disk 122 including rotor blades 124 coupled thereto.

[0049] A first receiving member 102 and a second receiving member 104 communicating with the first receiving member 102 protectively surround a portion of the turbine or turbine assembly 120 such that the first receiving member 102 and the second receiving member 104 together house each of the rotor disk 122 and the rotor blade 124 therein.

[0050] In an exemplary embodiment, the first receiving member 102 is an active clearance control housing (ACC) 103, which is in communication with the turbine assembly 120 to supply cooler air to the surface of the engine housing.

[0051] Furthermore, in one exemplary embodiment, the second receiving member 104 of the turbine receiving system 100 may also include a Kevlar wrap 105 disposed on a portion of the active clearance control housing 103. It is contemplated that the Kevlar wrap 105 may include various numbers of Kevlar wraps 105 disposed on a portion of the active clearance control housing 103 for a particular application.

[0052] Reference Figure 2A and 2B In an exemplary embodiment, a first receiving member 102 and a second receiving member 104 communicating with the first receiving member 102 protectively surround a portion of the turbine or turbine assembly 120 such that the first receiving member 102 and the second receiving member 104 together house each of the rotor disk 122 and the rotor blades 124 therein. For example, the second receiving member 104 may cover and surround the first receiving member 102. In other exemplary embodiments, the second receiving member 104 may communicate with the first receiving member 102 in other configurations, such as in a series or parallel configuration where each of the rotor disk 122 and the rotor blades 124 is housed together therein.

[0053] refer to Figure 2B In an exemplary embodiment, the turbine housing system 100 further includes a connection system 130 between the first housing member 102 and the second housing member 104 to secure the second housing member 104 to the first housing member 102 and control thermal movement therebetween. (Refer to...) Figure 2BThe connection system 130 includes a first connecting member 132 and a second connecting member 134. In this way, the connection system 130 provides a mechanism for securing the second receiving member 104 to the first receiving member 102, protectively surrounding a portion of the turbine or turbine assembly 120, such that the first receiving member 102 and the second receiving member 104 together house each of the rotor disk 122 and rotor blades 124. It is envisioned that the connection system 130 may include a spoke-mounted connection system between the active clearance control housing 103 and the second receiving member 104 to control thermal movement therebetween and securely connect the components together.

[0054] The turbine housing system 100 of this disclosure protectively surrounds a portion of a turbine or turbine assembly 120 such that a first housing member 102 and a second housing member 104 together house each of the rotor disk 122 and rotor blades 124 therein. For example, turbine assembly 120 (e.g., LP turbine 20) Figure 1 The rotating parts of the rotor may be subjected to high centrifugal forces, which, due to high stress or manufacturing defects, may cause the rotor (e.g., rotor blades and rotor disk) to burst together. The present invention effectively accommodates both the rotor blades and rotor disk by using both the first accommodating member 102 and the second accommodating member 104 simultaneously.

[0055] refer to Figure 2A In one exemplary embodiment, the turbine housing system 100 further includes a shroud 108, which includes an aperture 110 on its inner surface 112. The shroud 108 is configured to provide the internal aperture 110 as part of a flow path for supplying air from the active clearance control housing to the engine housing and also as a support member capable of supporting a portion of the second housing member 104. In this exemplary embodiment, although other configurations are contemplated for supplying a flow of cool air to the turbine assembly 120, the aperture 110 of the shroud 108 is positioned radially adjacent to the turbine assembly 120.

[0056] refer to Figure 2A In one exemplary embodiment, the turbine housing system 100 includes a cooling air source 200 in communication with a first housing member 102 and a shroud 108. The cooling air source 200 provides a first cooling fluid flow 140 that is directed through the first housing member 102 (e.g., an active clearance control housing 103) and the orifice 110 of the shroud 108 to the turbine assembly 120.

[0057] In one exemplary embodiment, a cooling airflow 140 is drawn from a cooling air source 200 and guided along an integral cooling duct 114 within a first receiving member 102. In some embodiments, the cooling air source 200 is bypass air 52 from a bypass duct 40 of the engine 10. Figure 1 In other embodiments, the cooling air source 200 is fan air 48 from the fan assembly 12 of the engine 10. Figure 1 In other embodiments, the cooling air source 200 is fan air 50 from the fan assembly 12 of the engine 10. Figure 1 In other exemplary embodiments, the cooling air source 200 is air from the high-pressure compressor 14 or may be from other components of the engine 10. Typically, the cooling air source 200 is any air source from the external core 13 that provides cryogenic, low-pressure, or high-pressure air to the turbine housing system 100. Using such air in the turbine housing system 100 minimizes the impact of removing a portion of the air from other engine 10 systems, thus minimizing the impact on engine 10 performance. It is contemplated that the cooling air source 200 may also be derived from other systems of the engine 10.

[0058] refer to Figure 5 In one exemplary embodiment, the turbine housing system 100 of this disclosure includes a first housing member 102 that surrounds the turbine assembly 120 between a first end 152 and a second end 154 along a longitudinal axis 150 of the turbine housing system 100, and wherein a first thickness T1 of the first housing member 102 at the first end 152 is different from a second thickness T2 of the first housing member 102 at the second end 154. For example, as Figure 5 As shown, the second thickness T2 of the first receiving member 102 may be greater than the first thickness T1 of the first receiving member 102. In other exemplary embodiments, it is contemplated that the first thickness T1 of the first receiving member 102 may be greater than the second thickness T2 of the first receiving member 102. In further exemplary embodiments, it is contemplated that various other thickness configurations of the first receiving member 102 may be used, such as a reduced thickness portion of the first receiving member 102 between two larger thickness portions at the first end 152 and the second end 154, or various other thickness configurations for other applications. It is contemplated that such various thickness configurations of the first receiving member 102 along the length of the housing may be based on the kinetic energy from the rotor disk 122 and rotor blades 124 at different stages of the turbine assembly 120. It is also contemplated that the second receiving member 104 and Kevlar 105 may also include various thickness configurations as described for the first receiving member 102.

[0059] Figure 3 Another exemplary embodiment of this disclosure is shown. (Reference) Figure 3The turbine housing system 300 disclosed herein includes a second housing member 104, which is attached to the turbine engine 10. Figure 1 The soft-walled hoop member 305 is located below the core fairing portion 310 and attached to the turbine housing system 300.

[0060] In such an embodiment, the soft-walled receiving member, which serves as the hoop member 305, can be formed of Kevlar, composite materials, or ultra-high molecular weight polyethylene.

[0061] Figure 4 Another exemplary embodiment of this disclosure is shown. (Reference) Figure 4 The turbine housing system 400 of this disclosure further includes a high-temperature hard-walled housing 420 disposed on the first housing member 102. In other exemplary embodiments, it is contemplated that the high-temperature hard-walled housing 420 may be disposed on each of the first housing member 102 and the second housing member 104.

[0062] In an exemplary embodiment, a high-temperature hard-walled housing 420 disposed on the first receiving member 102 is attached to the turbine engine 10. Figure 1 The core fairing section 410 is located below and attached to the turbine housing system 400.

[0063] In such an embodiment, the high-temperature hard-walled housing 420 may be formed of a high-temperature resistant polymer-based composite (PMC) material. It is also contemplated that the high-temperature hard-walled housing 420 may be formed of other high-temperature resistant materials, such as titanium alloys, steel alloys, nickel alloys, or other similar alloys.

[0064] The turbine housing system disclosed herein protectively surrounds a portion of a turbine or turbine assembly such that a first housing member and a second housing member together house each of the rotor disk and rotor blades therein. For example, the rotating portion of a turbine assembly (e.g., an LP turbine) may be subjected to high centrifugal forces, which could cause the rotor (e.g., rotor blades and rotor disk) to burst together due to high stress or manufacturing defects. The present invention effectively houses both the rotor blades and rotor disk by utilizing both the first housing member and the second housing member simultaneously.

[0065] Other aspects of the invention are provided by the subject matter of the following provisions:

[0066] 1. A turbine housing system comprising: a first housing member surrounding a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; and a second housing member communicating with the first housing member, wherein the first housing member and the second housing member together house each of the rotor disks and rotor blades therein.

[0067] 2. The turbine clearance control system according to any one of the preceding clauses, wherein the first receiving member is an active clearance control housing in communication with the turbine.

[0068] 3. The turbine clearance control system according to any one of the preceding clauses, wherein the second receiving member comprises a Kevlar wrapping disposed on a portion of the active clearance control housing.

[0069] 4. The turbine clearance control system according to any of the preceding clauses further includes a shroud, the shroud including a hole on the inner surface of the shroud, wherein the shroud supports a portion of the second receiving member.

[0070] 5. The turbine clearance control system according to any one of the preceding clauses further includes a cooling air source in communication with the active clearance control housing and the shroud, wherein a first cooling fluid flow from the cooling air source is directed through orifices in the active clearance control housing and the shroud to the turbine.

[0071] 6. The turbine clearance control system according to any one of the preceding clauses, wherein the aperture of the shroud is positioned radially adjacent to the turbine.

[0072] 7. The turbine clearance control system according to any one of the preceding clauses further includes a spoke mounting connector between the active clearance control housing and the second receiving member to control thermal motion therebetween.

[0073] 8. The turbine clearance control system according to any one of the preceding clauses, wherein a first receiving member surrounds the turbine between a first end and a second end along the longitudinal axis of the turbine receiving system, and wherein a first thickness of the first receiving member at the first end is different from a second thickness of the first receiving member at the second end.

[0074] 9. The turbine clearance control system according to any one of the preceding clauses, wherein the second housing member is a soft-walled hoop member of the turbine housing system attached below the core cowling portion of the turbine engine.

[0075] 10. The turbine clearance control system according to any one of the preceding clauses, wherein the soft-wall hoop member is formed of ultra-high molecular weight polyethylene material.

[0076] 11. The turbine clearance control system according to any one of the preceding clauses further includes a high-temperature hard-walled housing disposed on the first receiving member.

[0077] 12. The turbine clearance control system according to any one of the preceding clauses, wherein the high-temperature hard-walled housing is formed of titanium alloy material.

[0078] 13. The turbine clearance control system according to any one of the preceding clauses, wherein the high-temperature hard-walled housing is attached to the turbine housing system below the core cowling portion of the turbine engine.

[0079] 14. A turbine housing system comprising: a first housing member surrounding a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; a second housing member communicating with the first housing member; and a shroud including a hole on an inner surface of the shroud, wherein the shroud supports a portion of the second housing member; wherein the first housing member and the second housing member together house each of the rotor disks and rotor blades therein.

[0080] 15. The turbine clearance control system according to any one of the preceding clauses further includes a cooling air source in communication with the first housing member and the shroud.

[0081] 16. The turbine clearance control system according to any one of the preceding clauses, wherein a first cooling fluid flow from a cooling air source is directed through a hole in a first receiving member and a shroud to reach the turbine.

[0082] 17. The turbine clearance control system according to any one of the preceding clauses further includes a spoke mounting connector between the first receiving member and the second receiving member to control thermal motion therebetween.

[0083] 18. The turbine clearance control system according to any one of the preceding clauses, wherein a first receiving member surrounds the turbine between a first end and a second end along the longitudinal axis of the turbine receiving system, and wherein a first thickness of the first receiving member at the first end is different from a second thickness of the first receiving member at the second end.

[0084] 19. The turbine clearance control system according to any one of the preceding clauses, wherein the second housing member is a soft-walled hoop member of the turbine housing system attached below the core cowling portion of the turbine engine.

[0085] 20. The turbine clearance control system according to any one of the preceding clauses further includes a high-temperature hard-walled housing disposed on the first receiving member.

[0086] This written description uses examples to disclose aspects of this disclosure, including best practices, and also enables those skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and performing any combination of methods. The patentable scope of this 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 have structural elements that do not differ from the wording of the claims, or if they include equivalent structural elements that do not differ significantly from the wording of the claims.

[0087] While this disclosure has been described as having an exemplary design, further modifications can be made to this disclosure within its spirit and scope. Therefore, this application is intended to cover any variations, uses, or adaptations of this disclosure using its general principles. Furthermore, this application is intended to cover such deviations from this disclosure that are known or customary practices in the field to which this disclosure pertains and that fall within the limitations of the appended claims.

Claims

1. A turbine housing system, characterized in that, include: A first housing member surrounds a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; and A second receiving member, which is connected to the first receiving member; The first and second accommodating members together house each of the rotor disk and the rotor blades therein; The first housing component is an active clearance control housing that communicates with the turbine; The second receiving member includes a Kevlar wrapping disposed on a portion of the active clearance control housing; and a spoke mounting connector between the active clearance control housing and the second receiving member to control thermal movement therebetween.

2. The turbine housing system according to claim 1, characterized in that, Further includes: A protective cover, the protective cover including a hole on the inner surface of the protective cover, wherein the protective cover supports a portion of the second receiving member.

3. The turbine housing system according to claim 2, characterized in that, It further includes a cooling air source in communication with the active clearance control housing and the shroud, wherein a first cooling fluid flow from the cooling air source is directed through the holes in the active clearance control housing and the shroud to reach the turbine.

4. The turbine housing system according to claim 2, characterized in that, The opening in the shield is positioned radially adjacent to the turbine.

5. The turbine housing system according to claim 1, characterized in that, The first receiving member surrounds the turbine between a first end and a second end along the longitudinal axis of the turbine receiving system, and wherein the first thickness of the first receiving member at the first end is different from the second thickness of the first receiving member at the second end.

6. The turbine housing system according to claim 1, characterized in that, The second housing member is a soft-walled hoop member attached to the turbine housing system below the core cowling portion of the turbine engine.

7. The turbine housing system according to claim 6, characterized in that, The soft-walled hoop component is made of ultra-high molecular weight polyethylene material.

8. The turbine housing system according to claim 1, characterized in that, It further includes a high-temperature hard-walled housing disposed on the first receiving member.

9. The turbine housing system according to claim 8, characterized in that, The high-temperature hard-walled shell is made of titanium alloy.

10. The turbine housing system according to claim 8, characterized in that, The high-temperature hard-walled shell is attached to the turbine housing system below the core cowling portion of the turbine engine.

11. A turbine housing system, characterized in that, include: A first housing member surrounds a portion of a turbine, the turbine including a plurality of rotor disks and rotor blades; A second receiving member, which is connected to the first receiving member; and A protective cover, the protective cover including a hole on the inner surface of the protective cover, wherein the protective cover supports a portion of the second receiving member; The first and second accommodating members together house each of the rotor disk and the rotor blades therein; The first housing component is an active clearance control housing that communicates with the turbine; The second receiving member includes a Kevlar wrapping disposed on a portion of the active clearance control housing; A spoke mounting connector is provided between the active clearance control housing and the second receiving member to control thermal movement therebetween.

12. The turbine housing system according to claim 11, characterized in that, It further includes a cooling air source in communication with the first housing member and the shield.

13. The turbine housing system according to claim 12, characterized in that, A first flow of cooling fluid from the cooling air source is guided through the holes in the first housing member and the shroud to reach the turbine.

14. The turbine housing system according to claim 11, characterized in that, The device further includes a spoke mounting connector between the first receiving member and the second receiving member to control thermal movement therebetween.

15. The turbine housing system according to claim 11, characterized in that, The first receiving member surrounds the turbine between a first end and a second end along the longitudinal axis of the turbine receiving system, and wherein the first thickness of the first receiving member at the first end is different from the second thickness of the first receiving member at the second end.

16. The turbine housing system according to claim 11, characterized in that, The second housing member is a soft-walled hoop member attached to the turbine housing system below the core cowling portion of the turbine engine.

17. The turbine housing system according to claim 11, characterized in that, It further includes a high-temperature hard-walled housing disposed on the first receiving member.

Images