Casing for an aircraft turbofan bypass engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/24
F01D-009/06
출원번호
US-0344057
(2012-01-05)
등록번호
US-8979484
(2015-03-17)
발명자
/ 주소
Eleftheriou, Andreas
Menheere, David
Denis, David
출원인 / 주소
Pratt & Whitney Canada Corp.
대리인 / 주소
Norton Rose Fulbright Canada LLP
인용정보
피인용 횟수 :
1인용 특허 :
36
초록▼
A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular spl
A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.
대표청구항▼
1. A casing for an aircraft turbofan bypass engine comprising: an outer ring and an inner hub defining an annular space therebetween, the inner hub configured for connection to at least one spool bearing, the outer ring configured for connection to at least one engine mount;a plurality of hollow rad
1. A casing for an aircraft turbofan bypass engine comprising: an outer ring and an inner hub defining an annular space therebetween, the inner hub configured for connection to at least one spool bearing, the outer ring configured for connection to at least one engine mount;a plurality of hollow radial struts arranged in a circumferential array mounting the inner hub to the outer ring; andan annular splitter box disposed between the inner hub and outer ring and configured to be connected with an upstream annular splitter tip structure to divide an air flow through the annular space into a core air flow and a bypass air flow, the splitter box defined by an inner wall and an outer wall, the outer ring and the outer wall of the splitter box in combination forming a bypass duct for the bypass air flow, the inner wall of the splitter box and the inner hub in combination forming a core fluid path for the core air flow, the splitter box further having an intermediate wall positioned radially between the inner and outer walls and extending downstream conically inward from said outer wall, the splitter box having openings in each of said inner, outer and intermediate walls for receiving said struts passing therethrough, each of said splitter box walls terminating at a downstream end configured for connection to a downstream engine case, the struts being mounted to said splitter box with a respective peripheral weld or braze between the intermediate wall and the struts at the openings of the intermediate wall. 2. The casing as defined in claim 1 wherein the annular intermediate wall is thicker than the respective annular outer and inner walls. 3. The casing as defined in claim 1 wherein the downstream end of the annular intermediate wall is radially spaced apart from both annular outer and inner walls to provide access to the annular space between the annular outer and inner walls. 4. The casing as defined in claim 1 wherein an upstream end of the annular intermediate wall is welded or brazed to the annular outer wall at an axial location adjacent leading edges of the struts. 5. The casing as defined in claim 1 wherein the annular splitter box comprises a plurality of circumferentially spaced brackets, each connecting the annular intermediate wall to a corresponding one of the respective struts. 6. The casing as defined in claim 5 wherein each of the brackets comprises a plate having a substantially U-shaped slot to receive a trailing edge portion of the corresponding strut, and the bracket being affixed to the corresponding strut by welding or brazing along an edge of the slot. 7. The casing as defined in claim 1 wherein the splitter box comprises a plurality of circumferentially spaced brackets, each bracket connecting a corresponding one of the respective struts to an annular flange extending radially inwardly from a downstream end of the annular intermediate wall. 8. An aircraft turbofan bypass engine comprising: a fan assembly, a compressor assembly, a combustion gas generator assembly and a turbine assembly; anda fabricated case having an annular splitter box supporting an upstream annular splitter tip structure, the annular splitter tip structure dividing a fan driven inlet air flow into a bypass air flow and a core air flow, the fabricated case including: an outer ring and an inner hub defining an annular space therebetween, the inner hub configured for connection with at least one spool bearing, the outer ring configured for connection with at least one engine mount;a plurality of load-bearing hollow radial struts arranged in a circumferential array to mount the inner hub to the outer ring,an annular splitter box disposed within the annular space and including an annular outer wall and an annular inner wall, the annular inner wall being disposed within the annular outer wall, the annular splitter box being connected to the upstream annular splitter tip structure and a downstream engine case, the annular outer wall in combination with the outer ring defining a section of a bypass air duct for directing said bypass air flow, the annular inner wall in combination with the inner hub defining a section of a core fluid path of the engine for directing said core air flow, the annular outer and annular inner walls defining a plurality of respective circumferentially spaced openings for allowing the individual struts to radially extend therethrough, andan annular intermediate wall extending downstream conically inward from the outer wall and connected to the downstream engine case, the intermediate wall having a plurality of circumferentially spaced openings receiving the individual struts to radially extend therethrough, the annular intermediate wall being affixed to the struts by welding or brazing along a periphery of a respective one of said openings in the annular immediate wall, an upstream end of the annular intermediate wall being welded or brazed to the annular outer wall and a downstream end of the annular intermediate wall being welded or brazed to a plurality of circumferentially spaced brackets, each bracket being welded or brazed to a corresponding one of the respective struts. 9. The aircraft turbofan bypass engine as defined in claim 8 wherein each of the brackets comprises a plate having a substantially U-shaped slot to receive a trailing edge portion of the corresponding strut. 10. The aircraft turbofan bypass engine as defined in claim 8 wherein an upstream end of the annular intermediate wall is welded or brazed to the annular outer wall at an axial location adjacent leading edges of the struts. 11. The aircraft turbofan bypass engine as defined in claim 8 wherein the downstream end of the annular intermediate wall is radially spaced apart from the annular outer and inner walls, to provide access to the annular space between the annular outer and inner walls. 12. The aircraft turbofan bypass engine as defined in claim 8 wherein the annular intermediate wall is thicker than the respective annular outer and inner walls. 13. The aircraft turbofan bypass engine as defined in claim 8 wherein the downstream end of the intermediate wall comprises a radially inwardly extending flange for connection with the downstream engine case.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (36)
Somanath, Nagendra; Kumar, Keshava B.; Dye, Christopher M., Actuated variable geometry mid-turbine frame design.
Lenhart Kenneth J. (Cincinnati OH) Barron Michael L. (Loveland OH) Wakeman Thomas G. (Lawrenceburg IN) Bellia Donald L. (West Chester OH), Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing.
Krützfeldt, Joachim; Kunze, Markus; Martin, Silvio-Ulrich; Mutke, Stefan; Qian, Kang; Richter, Christoph; Schneider, Oliver; Schröder, Peter; Schwarz, Michael; Waltke, Ulrich, Locking sub-assembly for closing the remaining gap between the first and the last of a blade ring which are inserted in a circumferential groove of a turbomachine, and corresponding turbomachine.
Demouzon Francis Michel,FRX ; Fer Rene Pierre,FRX ; Huet Patrick Jean Alibert,FRX ; Marnas Laurent Pierre Elysee Gaston,FRX, Redundant front suspension system for a turboshaft engine.
Larrabee John R. (Portland CT) Lucas Arthur W. (West Hartford CT) Faucher Peter A. (Brooklyn CT), Stiffening ring for a stator assembly of an axial flow rotary machine.
Subramaniyan, Moorthi; Chengappa, Manjunath Bangalore; Patel, Pradeep, Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.