[특허]Bearing compartment seal

United Technologies Corporation

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특허 상세정보

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Bearing compartment seal

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/06 F02C-007/28 F01D-011/00 F01D-025/16 F16J-015/06 F01D-025/12 F02C-003/14
출원번호	US-0603088 (2015-01-22)
등록번호	US-10215098 (2019-02-26)
발명자 / 주소	Cherolis, Anthony P. Farah, Jorge I. Max, Seth A. Mosley, John H. Porter, Steven D. Reinhardt, Gregory E. Zacchera, Kevin
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Kinney & Lange, P.A.
인용정보	피인용 횟수 : 0 인용 특허 : 14

초록

A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.

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1. A sealing arrangement comprising: a turbine static structure having a seal ring with a groove, the groove having a first contact surface;a bearing compartment that is surrounded by the turbine static structure, the bearing compartment comprising: a bearing;a bearing casing connected to the bearing;a heat shield; anda seal support disposed between the heat shield and the bearing casing, wherein the heat shield has a second contact surface, and wherein the heat shield and the seal support are connected to the bearing casing; anda piston seal positioned between the turbine static structure and the heat shield, the piston seal comprising: a first side configured to contact the first contact surface; anda second side configured to contact the second contact surface; anda joint formed by circumferentially opposed ends of the piston seal;wherein the piston seal is positioned in the groove such that the groove substantially surrounds the first side, a third side, and a fourth side of the piston seal;wherein the joint permits the second side of the piston seal to have an uninstalled inner diameter that is smaller than an outer diameter of the second contact surface. 2. The sealing arrangement of claim 1, wherein the first contact surface is positioned on a first groove side, the sealing arrangement further comprising: a third contact surface on a second groove side of the groove;wherein the third side of the piston seal is configured to contact the third contact surface for reverse flow sealing. 3. The sealing arrangement of claim 1, wherein the first contact surface is an annular surface. 4. The sealing arrangement of claim 1, wherein the seal ring is fastened to the turbine static structure. 5. The sealing arrangement of claim 1, wherein the first contact surface is substantially perpendicular to the second contact surface. 6. The sealing arrangement of claim 1, wherein the second contact surface is a cylindrical surface. 7. The sealing arrangement of claim 1, wherein the seal ring includes a passage extending radially outward through the seal ring from the groove. 8. A gas turbine engine arranged along an axis, the gas turbine engine comprising: a fan;a first compressor downstream of the fan;a second compressor downstream of the first compressor;a combustor downstream of the second compressor;a first turbine downstream of the combustor;a second turbine downstream of the first turbine;a turbine static structure proximate at least one of the first turbine and the second turbine, the turbine static structure having a seal ring with a groove having a first contact surface;a bearing compartment connected to the turbine static structure and surrounded by the turbine static structure, the bearing compartment comprising: a bearing;a bearing casing connected to the bearing;a heat shield; anda seal support disposed between the heat shield and the bearing casing, wherein the heat shield has a second contact surface, and wherein the heat shield and the seal support are connected to the bearing casing; anda piston seal positioned in the groove of the turbine static structure such that a first side of the piston seal is configured to contact the first contact surface of the turbine static structure during operation of the gas turbine engine, a second side of the piston seal is configured to contact the second contact surface of the heat shield during operation of the gas turbine engine, wherein the groove substantially surrounds the first side, a third side, and a fourth side of the piston seal, and wherein the piston seal includes a joint formed by circumferentially opposed ends of the piston seal that permits the second side of the piston seal to have an uninstalled inner diameter that is smaller than an outer diameter of the second contact surface. 9. The gas turbine engine of claim 8, wherein the piston seal is constrained axially by the groove and constrained radially by the groove and the bearing compartment. 10. The gas turbine engine of claim 8, wherein the turbine static structure is positioned downstream of the first turbine and upstream of the second turbine. 11. The gas turbine engine of claim 8, wherein the gas turbine engine includes a first bearing, a second bearing, a third bearing, and a fourth bearing arranged in sequential order from a front of the gas turbine engine, and wherein the bearing compartment includes the fourth bearing of the gas turbine engine. 12. The gas turbine engine of claim 8, wherein the turbine static structure further comprises: a gas tube;a fairing surrounding the gas tube; andan inner case connected to the gas tube and the seal ring. 13. The gas turbine engine of claim 8, wherein the piston seal is configured to contact an annular portion of the groove and a cylindrical portion of the bearing compartment for sealing during operation of the gas turbine engine. 14. A method of assembling a gas turbine engine, the method comprising: connecting a bearing compartment to an inner case;inserting a piston seal into a groove in a seal ring of a turbine static structure such that a first side of the piston seal contacts a first contact surface on a first side of the groove and the groove substantially surrounds the first side, a third side, and a fourth side of the piston seal;expanding the piston seal from an uninstalled configuration into an expanded configuration at a joint formed by circumferentially opposed ends of the piston seal;fixing the piston seal in the expanded configuration;positioning an inner diameter of a second side of the piston seal around an outer diameter of a second contact surface of a heat shield connected to a bearing case of the bearing compartment to allow the second side of the piston seal to contact the second contact surface of the bearing compartment, wherein the inner diameter of the second side of the piston seal is smaller than the outer diameter of the second contact surface in the uninstalled configuration, and wherein a seal support is disposed between the heat shield and the bearing case and is connected to the bearing case. 15. The method of claim 14, and further comprising: fastening the seal ring to the inner case. 16. The method of claim 14, wherein positioning the piston seal comprises: moving the seal ring along an engine axis until the piston seal is positioned around the second contact surface of the bearing compartment. 17. The method of claim 14, wherein fixing the piston seal in the expanded configuration comprises: applying adhesive to a joint in the piston seal.

이 특허에 인용된 특허 (14)

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특허 상세정보

Bearing compartment seal

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특허 상세정보

Bearing compartment seal

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이 특허에 인용된 특허 (14)

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IPC 상세정보(version : 201201)

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