[특허]Retaining and sealing ring assembly

Rolls-Royce Corporation

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Retaining and sealing ring assembly

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F03B-003/12
미국특허분류(USC)	416/220R;
출원번호	US-0491276 (2009-06-25)
등록번호	US-8419370 (2013-04-16)
발명자 / 주소	Ruba, Daniel Scott, Matthew Bowman, Thomas
출원인 / 주소	Rolls-Royce Corporation
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 0 인용 특허 : 49

초록

A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly is disclosed herein. The ring assembly includes an inner ring operable to prevent aft movement of a fan blade positioned in a slot formed in the blade disk. The ring assembly also includes an outer ring operable to seal against a platform of the fan blade. The inner ring and the outer ring are formed from different materials.

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1. A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly comprising: an inner ring operable to prevent aft movement of a fan blade, said fan blade including a portion positioned in a slot formed in the blade disk, said inner ring including a load bearing surface engaged in abutment against an aft-most end surface of said portion of said fan blade positioned in said slot in said blade disk to prevent said aft movement; andan outer ring operable to seal against a platform of the fan blade, wherein said inner ring and said outer ring are formed from different materials. 2. The ring assembly of claim 1 wherein said inner ring is formed from a first material defining a first strength and said outer ring is formed from a second material defining a second strength less than the first strength. 3. The ring assembly of claim 1 wherein said inner ring and said outer ring are centered on a common axis and abut one another along said axis. 4. The ring assembly of claim 3 wherein said inner ring and said outer ring radially overlap one another relative to said axis. 5. The ring assembly of claim 1 wherein said inner ring is formed from titanium and said outer ring is formed from aluminum. 6. The ring assembly of claim 1 wherein said inner ring and said outer ring are concentric and wherein said outer ring further comprises an annular slot in which said inner ring is received, and wherein said outer ring includes a radial inner surface adjacent said annular slot, said radial inner surface engaged in abutment against said aft-most end surface of said portion of said fan blade. 7. The ring assembly of claim 1 wherein: said outer ring further comprises a first set of apertures for receiving fasteners; andsaid inner ring further comprises a second set of apertures, wherein said first and second set of apertures are aligned for jointly receiving the fasteners. 8. The ring assembly of claim 1 wherein said inner ring is formed from a first material and said outer ring is formed from a second material that is more machinable than said first material, and wherein said outer ring comprises greater machining than said inner ring. 9. The ring assembly of claim 8 wherein material removed from said inner ring by the machining is less than material removed from said outer ring. 10. The ring assembly of claim 1 wherein said inner ring contacts said fan blade at a single surface abutment interface defined by the abutment of the load bearing surface against the aft-most end surface of said portion of said fan blade. 11. A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly comprising: an inner ring operable to prevent aft movement of a fan blade, said fan blade including a portion positioned in a slot formed in the blade disk; andan outer ring operable to seal against a platform of the fan blade, wherein said inner ring and said outer ring are formed from different materials;wherein said inner ring includes a single bearing surface abutting said fan blade at a single surface abutment interface to prevent said aft movement, and wherein said single bearing surface abuts an aft-most end surface of said portion of said fan blade positioned in said slot in said blade disk to define said single surface abutment interface. 12. A method comprising the steps: retaining a fan blade including a portion positioned in a slot formed in a blade disk to prevent aft movement with a fan blade retaining and sealing ring assembly;sealing against a platform of the fan blade with the fan blade retaining and sealing ring assembly; andbifurcating structures of the fan blade retaining and sealing ring assembly applied for said retaining step and for said sealing step by forming the fan blade retaining and sealing ring assembly with an inner ring and an outer ring of different materials, said inner ring including a load bearing surface engaged in abutment against an aft-most end surface of said portion of said fan blade positioned in said slot in said blade disk to prevent said aft movement. 13. The method of claim 12 further comprising the steps of: locating the inner ring on the blade disk with at least two structures defined by the inner ring. 14. The method of claim 13 wherein said locating step is further defined as: locating the inner ring on the blade disk with an annular hook and a first set of apertures. 15. The method of claim 13 further comprising the steps of: locating the outer ring on the blade disk with the inner ring and with a plurality of structures defined by the outer ring. 16. The method of claim 12 wherein the inner ring is formed from a first material and the outer ring is formed from a second material that is more machinable than the first material, and wherein the outer ring is subjected to greater machining than the inner ring. 17. The method of claim 16 wherein material removed from the inner ring by the machining is less than material removed from the outer ring. 18. The method of claim 12 wherein the inner ring contacts the fan blade at a single surface abutment interface defined by the abutment of the load bearing surface against the aft-most end surface of said portion of said fan blade. 19. A method comprising the steps: retaining a fan blade including a portion positioned in a slot formed in the blade disk to prevent aft movement with a fan blade retaining and sealing ring assembly;sealing against a platform of the fan blade with the fan blade retaining and sealing ring assembly; andbifurcating structures of the fan blade retaining and sealing ring assembly applied for said retaining step and for said sealing step by forming the fan blade retaining and sealing ring assembly with an inner ring and an outer ring of different materials, wherein the inner ring includes a single bearing surface to prevent the aft movement, and wherein the single bearing surface abuts an aft-most end surface of the portion of the fan blade positioned in the slot in the blade disk to prevent said aft movement. 20. A turbine engine comprising: a blade disk centered on a centerline axis and defining at least one slot extending along said centerline axis;a fan blade including a portion positioned in said at least one slot; anda retaining and sealing ring assembly positioned on an aft side of said fan blade and having an inner ring operable to prevent aft movement of said fan blade and an outer ring operable to seal against a platform of said fan blade to direct air flow into the engine core, said inner ring including a load bearing surface engaged in abutment against an aft-most end surface of said portion of said fan blade positioned in said slot in said blade disk to prevent said aft movement, wherein said inner ring and said outer ring are adjacent to one another and formed from different materials. 21. The turbine engine of claim 20 wherein said inner ring further comprises an annular hook and said blade disk further comprises an annular projection received in said annular hook, wherein cooperation between said annular hook and said annular projection locates said inner ring radially relative to said blade disk. 22. The turbine engine of claim 20 wherein said inner ring further comprises a first set of apertures and said blade disk further comprises a second set of apertures, wherein said first set of apertures and said second set of apertures are aligned to locate said inner ring circumferentially relative to said blade disk. 23. The turbine engine of claim 22 wherein said outer ring further comprises a third set of apertures, wherein said third set of apertures and said second set of apertures are aligned to locate said outer ring circumferentially relative to said blade disk. 24. The turbine engine of claim 20 wherein said outer ring further comprises an annular notch and said inner ring is further defined as being received in said annular notch, wherein cooperation between said annular notch and said inner ring locates said outer ring radially relative to said blade disk, and wherein said outer ring includes a radial inner surface adjacent said annular notch, said radial inner surface engaged in abutment against said aft-most end surface of said portion of said fan blade. 25. The turbine engine of claim 20 wherein said inner ring and said outer ring are centered on a common axis and abut one another along said axis. 26. The turbine engine of claim 20 wherein said inner ring and said outer ring overlap one another axially and radially relative to a center axis of said blade disk. 27. The turbine engine of claim 20 wherein said inner ring is formed from a first material and said outer ring is formed from a second material, wherein said second material is more machinable. 28. The turbine engine of claim 20 wherein said inner ring is formed from a first material and said outer ring is formed from a second material that is more machinable than said first material, and wherein said outer ring comprises greater machining than said inner ring. 29. The turbine engine of claim 28 wherein material removed from said inner ring by the machining is less than material removed from said outer ring. 30. The turbine engine of claim 20 wherein said inner ring contacts said fan blade at a single surface abutment interface defined by the abutment of the load bearing surface against the aft-most end surface of said portion of said fan blade. 31. The turbine engine of claim 20 wherein a radial inner surface of said outer ring contacts said aft-most end surface of said portion of said fan blade, and wherein a sealing surface of said outer ring contacts said platform, wherein said outer ring is spaced from said fan blade along at least part of a radial distance between said radial inner surface and said sealing surface.

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