[특허]Cabin air compressor diffuser vane drive ring

Hamilton Sundstrand Corporation

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Cabin air compressor diffuser vane drive ring

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-017/12 F04D-029/46 F16C-035/00
출원번호	US-0856504 (2013-04-04)
등록번호	US-9341193 (2016-05-17)
발명자 / 주소	Beers, Craig M. Rosen, Seth E.
출원인 / 주소	Hamilton Sundstrand Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 7

초록

A cabin air compressor drive ring includes an outer ring defining an axis, an inner ring co-axial with the outer ring, a plurality of webbings connecting the inner ring to the outer ring, and a plurality of vane engagement pins axially protruding from the outer ring. The vane engagement pins are spaced circumferentially about the outer ring, and the inner ring includes a drive ring bearing interface.

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1. A cabin air compressor drive ring comprising: an outer ring defining an axis;an inner ring co-axial with the outer ring said inner ring defining a bearing interface track operable to mount said drive ring to a cabin air compressor bearing, said bearing interface track comprising a first and second facing wall, each of said first and second facing walls are perpendicular to the axis, and a bearing interface base surface, said bearing interface base surface is parallel to the axis;a plurality of webbings connecting the inner ring to the outer ring;a plurality of vane engagement pins axially protruding from the outer ring, wherein said vane engagement pins are spaced circumferentially about the outer ring;said inner ring comprises a drive ring bearing interface; anda first clearance cut protruding radially into said bearing interface base surface and axially into a first of said facing walls at a joint between said first of said facing walls and said bearing interface base surface. 2. The cabin air compressor drive ring of claim 1, wherein an axial length of each of the first and second facing walls is within the range of 0.115-0.125 inches (0.2921-0.3175 cm). 3. The cabin air compressor drive ring of claim 1, wherein an axial length of the bearing interface is in the range of 1.120-1.130 inches (2.8448-2.8702 cm). 4. The cabin air compressor drive ring of claim l, wherein an axial length of the bearing interface base surface is in the range of 1.002-1.004 inches (2.545-2.550 cm). 5. The cabin air compressor drive ring of claim 1, wherein a ratio of an axial length of the bearing interface to an axial length of the bearing interface base surface is in the range of 1.120:1.004-1.130:1.002. 6. A cabin air compressor drive ring comprising: an outer ring defining an axis;an inner ring co-axial with the outer ring, the inner ring defines a bearing interface track operable to mount said drive ring to a cabin air compressor bearing, said bearing interface track comprises a first and second facing wall wherein each of said first and second facing walls are perpendicular to the axis, and a bearing interface base surface wherein said bearing interface base surface is parallel to the axis;a plurality of webbings connecting the inner ring to the outer ring;a plurality of vane engagement pins axially protruding from the outer ring, wherein said vane engagement pins are spaced circumferentially about the outer ring;said inner ring comprises a drive ring bearing interface;a first clearance cut protruding radially into said bearing interface base surface and axially into a first of said facing walls at a joint between said first of said facing walls and said bearing interface base surface;a second clearance cut protruding radially into said bearing interface base surface and axially into a second of said facing walls at a joint between said second of said facing walls and said bearing interface base surface; andwherein a ratio of said axial protrusion of each of said clearance cuts to said radial protrusion of each of said clearance cuts is in the range of 0.005:0.035-0.015:0.025. 7. The cabin air compressor drive ring of claim 1, wherein said outer ring defines an outer ring diameter measured from a radially innermost edge of the outer ring and said outer ring diameter is in the range of 14.280-14.400 inches (36.271-36.576 cm). 8. The cabin air compressor drive ring of claim 1, wherein said inner ring defines an inner ring diameter measured from a radially innermost edge of the inner ring and the inner ring diameter is in the range of 10.395-10.405 inches (26.403-26.429 cm). 9. The cabin air compressor drive ring of claim 1, wherein said outer ring defines an outer ring diameter measured from a radially innermost edge of the outer ring, said inner ring defines an inner ring diameter measure from a radially innermost edge of the inner ring and a ratio of said inner ring diameter to said outer ring diameter is in the range of 10.395:14.400-10.405:14.280. 10. The cabin air compressor drive ring of claim 1, wherein each of said plurality of vane engagement pins defines an engagement pin center point, a diametral circle connecting each of said engagement pin center point defines a diametral circle diameter of the outer diameter ring, and said diametral circle diameter is in the range of 15.435-15.465 inches (39.205-39.281 cm). 11. The cabin air compressor drive ring of claim 10, wherein said outer ring defines an outer ring diameter measured from a radially innermost edge of the outer ring and wherein a ratio of said diametral circle diameter to said outer ring diameter is in the range of 14.280:15.435-14.400:15.465. 12. A cabin air compressor comprising: a compressor inlet;a compressor outlet fluidly connected to the compressor inlet via a passage;a plurality of rotatable diffuser vanes positioned in said passage;a drive ring connected to each of said rotatable diffuse vanes via a plurality of engagement pins, wherein said drive ring is controllably coupled to an actuator such that said actuator can rotate said drive ring thereby adjusting a cross sectional area of said rotatable diffuser vanes relative to gas flowing through said passage;wherein said drive ring further comprises a cabin air compressor drive ring comprising:an outer ring defining an axis;an inner ring co-axial with the outer ring said inner ring defining a bearing interface track operable to mount said drive ring to a cabin air compressor bearing, said bearing interface track comprising a first and second facing wall, each of said first and second facing walls are perpendicular to the axis, and a bearing interface base surface, said bearing interface base surface is parallel to the axis;a plurality of webbings connecting the inner ring to the outer ring;said plurality of vane engagement pins axially protruding from the outer ring, wherein said vane engagement pins are spaced circumferentially about the outer ring;said inner ring comprises a drive ring bearing interface; anda first clearance cut protruding radially into said bearing interface base surface and axially into a first of said facing walls at a joint between said first of said facing walls and said bearing interface base surface. 13. The cabin air compressor of claim 12, wherein said cabin air compressor further includes a bearing track, and wherein said drive ring is mounted to said bearing track via a bearing track interface on a radially interior surface of said inner ring. 14. The cabin air compressor of claim 13, wherein said bearing track interface comprises a pair of facing side walls approximately perpendicular to said axis and base surface parallel to said axis, and said base surface defines an inner ring base diameter in the range of 10.801-10.805 inches (27.434-27.445 cm). 15. The cabin air compressor of claim 14, wherein a ratio of said inner ring base diameter to an inner ring diameter measured from an innermost surface of the pair of facing side walls is in the range of 10.801:10.405-10.805:10.395. 16. The cabin air compressor of claim 14, wherein a ratio of said inner ring base diameter to a diameter of a circle connecting an axial centerpoint of each of said engagement pins is in the range of 10.801:15.465-10.805:15.435. 17. The cabin air compressor of claim 12, wherein each of said engagement pins includes an axial center point, wherein a circle connecting each of said axial center points defines a diametral circle of said engagement pins, and a diameter of said diametral circle is in the range of 15.435-15.465 inches (39.205-39.281 cm). 18. The cabin air compressor of claim 1, further comprising a second clearance cut protruding radially into said bearing interface base surface and axially into a second of said facing walls at a joint between said second of said facing walls and said bearing interface base surface. 19. The cabin air compressor of claim 18, wherein a ratio of said axial protrusion of each of said clearance cuts to said radial protrusion of each of said clearance cuts is in the range of 0.005:0.035-0.015:0.025.

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Cabin air compressor diffuser vane drive ring

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