[특허]Fan

Fan 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/00
출원번호	US-0570612 (2009-09-30)
등록번호	US-8435006 (2013-05-07)
발명자 / 주소	Fulayter, Roy David Ong, James
출원인 / 주소	Rolls-Royce Corporation
대리인 / 주소	Krieg DeVault, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 55

초록 ▼

A fan is disclosed herein. The fan includes a hub portion operable to rotate about an axis. The hub portion extends along the axis between forward and aft ends. The fan also includes at least one platform operably fixed with the hub portion. The at least one platform at least partially encircles the axis. The fan also includes at least one airfoil extending from the at least one platform radially outward relative to the axis between a base and a tip. The at least one platform terminates at forward and aft circumferential edges spaced from one another along the axis. At least one of the forward and aft circumferential edges extends about the axis and along the axis.

대표청구항 ▼

1. A fan comprising: a hub portion operable to rotate about an axis and extending along said axis between forward and aft ends;at least one platform operably fixed with said hub portion and at least partially encircling said axis;at least one airfoil extending from said at least one platform radially outward relative to said axis between a base and a tip; andwherein said at least one platform terminates at forward and aft circumferential edges spaced from one another along said axis and wherein at least one of said forward and aft circumferential edges extends about said axis and along said axis; andwherein the at least one platform is configured to mesh and interlock with a spinner of the fan assembly and/or a seal plate of the fan assembly. 2. The fan of claim 1 wherein said at least one of said forward and aft circumferential edges is further defined as forming at least one groove centered on a groove axis extending at least substantially perpendicular to said axis. 3. The fan of claim 2 wherein said at least one groove includes a plurality of grooves circumferentially spaced from one another about said axis. 4. The fan of claim 2 wherein said at least one groove is circumferentially spaced from said at least one airfoil about said axis. 5. The fan of claim 2 wherein said at least one groove is square in circumferential cross-section. 6. The fan of claim 2 wherein said at least one groove is triangular in circumferential cross-section. 7. The fan of claim 2 wherein said platform defines a radially outward surface and said at least one groove communicates with said radially outward surface. 8. The fan of claim 1 wherein at least part of said at least one of said forward and aft circumferential edges is further defined as extending along a sinusoidal path about said axis. 9. The fan of claim 1 wherein both of said forward and aft circumferential edges extend about said axis and along said axis. 10. The fan of claim 1 wherein said hub portion and said at least one platform are integrally formed and unitary and wherein said at least one platform extends fully about said axis. 11. The fan of claim 1 wherein said at least one platform includes a plurality of platforms positioned adjacent to one another about said axis. 12. A fan assembly comprising: a fan having: a hub portion operable to rotate about an axis and extending along said axis between forward and aft ends;at least one platform operably fixed with said hub portion and at least partially encircling said axis;at least one airfoil extending from said at least one platform radially outward relative to said axis between a base and a tip; andwherein said at least one platform terminates at forward and aft circumferential edges spaced from one another along said axis and wherein at least one of said forward and aft circumferential edge extends about said axis and along said axis; andat least one structure positioned adjacent to said fan along said axis and defining a circumferential edge that extends about said axis and along said axis and meshes and interlocks with said at least one of said forward and aft circumferential edges. 13. The fan assembly of claim 12 wherein said at least one structure is further defined as a spinner body positioned on a forward side of said fan. 14. The fan assembly of claim 12 wherein said at least one structure is further defined as a seal plate positioned on an aft side of said fan. 15. The fan assembly of claim 12 wherein both of said forward and aft circumferential edges extend about said axis and along said axis and wherein said at least one structure is further defined as first and second structures positioned on opposite sides of said hub along said axis each having a circumferential edge that extends about said axis and along said axis and meshes with said at least one of said forward and aft circumferential edges. 16. The fan assembly of claim 15 where said first structure is further defined as a spinner body positioned on a forward side of said fan and said second structure is further defined as a seal plate positioned on an aft side of said fan opposite said spinner body. 17. The fan assembly of claim 12 wherein said at least one of said forward and aft circumferential edges of said fan defines a plurality of grooves and said circumferential edge of said at least one structure defines a plurality of projections operable to mate with said grooves. 18. The fan assembly of claim 12 wherein at least some of said plurality of grooves communicate with said at least one platform. 19. The fan assembly of claim 12 wherein said at least one structure and said fan are fixed together at a second location spaced radially inward of said meshed circumferential edges. 20. A method for stiffening the blades of a fan comprising the steps of: positioning a fan having a hub portion and a plurality of blades for rotation about an axis;positioning a first structure adjacent to the fan along the axis; andmeshing and interlocking platforms of the blades of the fan and the first structure substantially at a flow path boundary defined at respective bases of the plurality of blades and extending circumferentially about the axis.

이 특허에 인용된 특허 (55)

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Acton Elizabeth (Cambridge GB2) Cargill Alexander M. (Derby GB2) Ross Colin F. (Cambridge GB2) Eatwell Graham P. (Cambridge GB2), Active control of unsteady motion phenomena in turbomachinery.
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Clauer Allan H., Altering vibration frequencies of workpieces, such as gas turbine engine blades.
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Gysling Daniel L. ; Feulner Matthew R. ; Eveker Kevin M., Apparatus and method of active flutter control.
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Busbey Bruce C. ; Crall David W. ; Toye Michael D., Blade assembly with splitter shroud.
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Libertini Zoltan L. (Stamford CT) Ivanko Theodore (Fairfield CT), Boltless blade retainer for a turbine wheel.
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Day Ivor J. (Cambridge GB2), Control of flow instabilities in turbomachines.
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Forestier Alexandre (Vaux le Penil FRX), Damping device for turbojet engine fan blades.
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Girgis,Sami; Marini,Remo, Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine.
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Brafford Perry W. ; Gebre-Giorgis Yoseph ; Murthy Durbha V., Detuned fan blade apparatus and method.
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Rigo Marcel L. A. (Paray Vieille Poste FRX) Sourdeval Gilbert (Vert Saint Denis FRX), Device for axial securing of blade feet of a gas turbine disk.
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Surdi Jean M. (Melun FRX), Device to lock the blades of a turboblower and to fasten the front cowl of a turbojet engine.
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Harris Daniel J. (West Chester OH) Przytulski James C. (Fairfield OH) Szpunar Stephen J. (West Chester OH), Fan assembly having lightweight platforms.
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Eldredge David A. (Port St. Lucie FL) Ress ; Jr. Robert A. (Carmel IN), Fan blade attachment for gas turbine engine.
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James Michael Forrester, Fan blade retainer.
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Wallace Allen K. (Hindmarsh AUX), Fan closure flap.
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Yaeger Karl J. (Coventry CT) Duke Douglas E. (Ellington CT) Sunamoto James A. (Glastonbury CT) Greene ; Jr. William Henry (South Windsor CT), Flutter resistant blades, vanes and arrays thereof for a turbomachine.
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Smith M. Lawrence (Orlando FL), Freestanding mixed tuned blade.
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Matthew Montgomery ; Marc Samit ; John A. Orosa, Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability.
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Griffin,Jerry H.; Feiner,Drew M., Fundamental mistuning model for determining system properties and predicting vibratory response of bladed disks.
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Chlus Wieslaw A. (Wethersfield CT) Gonsor Michael (Hebron CT) Houston David P. (Glastonbury CT) Kudra Paul D. (Glastonbury CT), Gas turbine blade damper.
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Farrar, Peter G G; Freeman, Christopher, Gas turbine engine blade.
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Prentice Ian F. (Cincinnati OH) Juenger Jerome A. (Cincinnati OH), Gas turbine engine blade retainer sub-assembly.
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Barb, Kevin Joseph; Mujezinovic, Amir; Martin, Nicholas Francis; Hofer, Douglas Carl, Method and apparatus for bucket natural frequency tuning.
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Heinig Roger W. (Cocoa Beach FL), Method and apparatus for reducing vibration in a turbo-machine blade.
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Eveker, Kevin M.; Gysling, Daniel L.; Nett, Carl N., Method and system of flutter control for rotary compression systems.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
구성항목	기본정보 상세정보 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	총 건의 자료가 검색되었습니다. 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오. ~ Text(ASCII format) Excel format

연합인증

Fan 원문보기

초록 ▼

대표청구항 ▼

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연합인증

Fan 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

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이 특허에 인용된 특허 (55)

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