[특허]Bladed disk fixing undercut

[미국특허] Bladed disk fixing undercut 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/30 F01D-005/00 F01D-005/32
출원번호	US-0845189 (2004-05-14)
발명자 / 주소	Stone,Paul
출원인 / 주소	Pratt & Whitney Canada Corp.
대리인 / 주소	Ogilvy Renault LLP
인용정보	피인용 횟수 : 11 인용 특허 : 17

초록

An undercut is provided in a gas turbine engine disk to smooth out an uneven axial distribution of radial stress in the disk. The undercut is defined radially inwardly of the blade attachment slots provided at the periphery of the disk.

대표청구항 ▼

The invention claimed is: 1. A gas turbine engine rotor disk comprising a disk body having a plurality of blade attachment slots circumferentially distributed about a periphery thereof, and wherein an undercut is provided radially inwardly of said blade attachment slots, wherein said undercut is bounded by radially inner and outer walls which converge towards a rotational axis of the disk in a depthwise direction of the undercut. 2. A gas turbine engine rotor disk as defined in claim 1, wherein said undercut has an annular configuration. 3. A gas turbine engine rotor disk as defined in claim 1, wherein said undercut curves in an axial direction from the front of the disk towards the rotational axis thereof. 4. A gas turbine engine rotor disk as defined in claim 3, wherein said undercut has a generally rounded shape. 5. A gas turbine engine rotor comprising a plurality of blades, each of said blades having a root received in a corresponding blade attachment slot defined in a disk adapted to be mounted for rotation about an axis, and wherein an axial distribution of radial stress in the disk is smoothed by providing an undercut in the disk radially inwardly of the blade attachment slots, the undercut and the blade attachment slots defining therebetween a rim, and wherein each of said blades has an overhang abutted against the rim, the overhang limiting axial rearward insertion of the blades in the blade attachment slots. 6. A gas turbine engine rotor as defined in claim 5, wherein said undercut is annular. 7. A gas turbine engine rotor as defined in claim 5, wherein said undercut curves in an axial direction from the front of the disk towards a rotational axis thereof. 8. A gas turbine engine rotor as defined in claim 6, wherein said undercut has a generally rounded shape. 9. A gas turbine engine rotor as defined in claim 5, wherein said rotor is a swept fan, and wherein said undercut is defined in a front side of the disk. 10. A gas turbine engine rotor as defined in claim 5, wherein said blades are asymmetric with respect to respective radial axes thereof so that a significant portion of the weight of said blades is cantillevered over a front portion of the disk, thereby causing an uneven axial distribution of the radial load along the roots and corresponding blade attachment slots, and wherein said undercut is defined in the front portion of the disk. 11. A method to smooth out an uneven axial distribution of radial stress in a gas turbine engine rotor disk having a plurality of blade attachment slots in which are retained a corresponding number of blades, the method comprising: determining an axial location of the disk which is subject to high radial stress and defining the undercut at said axial location, and providing an undercut radially inwardly of said plurality of blade attachment slots, said undercut being bounded by radially inner and outer walls which converge towards a rotational axis of the disk in a depthwise direction of the undercut. 12. A method as defined in claim 11, wherein the undercut is annular. 13. A method as defined in claim 12, wherein the annular undercut curves radially inwardly from the front of the disk. 14. A method as defined in claim 11, wherein said blades are asymmetric with respect to respective radial axes thereof so that a significant portion of the weight of said blades is cantilevered over a front portion of the disk, thereby causing an uneven axial distribution of the radial load along the blade attachment slots.

이 특허에 인용된 특허 (17) 인용/피인용 타임라인 분석

Bourcier Pierre (Paris FRX), Arrangement for clipping stress peaks in a turbine blade root.
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Suciu, Gabriel L.; Babu, Michael; Murdock, James R., Blade for turbine engine.
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Luebering George W. (Cincinnati OH), Blade retainer assembly.
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Forrester, James Michael; Bolt, Janine Elizabeth; Rhoda, James Edwin; Stevenson, Joseph Timothy, Circular arc multi-bore fan disk.
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Hayner Denis R. (Newburyport MA) Rock Peter J. (Byfield MA), Double rabbet rotor blade retention assembly.
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Greer John (Burlington CAX) Chijiiwa Haruhisa (Mississauga CAX) Dowhan Michael J. (Milton CAX), Fan blade axial retention device.
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Youssef Nashed A. (Mississauga CAX), Fan blade axial retention device.
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Wadia Aspi R. ; Prentice Ian F. ; Crall David W. ; Koch Carl C., Forward swept fan blade.
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Smith M. Lawrence (Orlando FL), Freestanding mixed tuned blade.
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Brown Wilmott G. (Winter Park FL), Freestanding mixed tuned steam turbine blade.
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Eduardo Enrique Paz, Gas turbine blade with platform undercut.
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King Michael J. (Derby GB2) Throssell Jonathan P. (Derby GB2) Knott David S. (Leicestershire GB2) Richards Martyn (Derbyshire GB2), Gas turbine engine rotary disc.
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Mori Masahiko,JPX ; Hashimoto Yukihiro,JPX ; Tada Hiroji,JPX ; Fukue Ichiro,JPX ; Tsukagoshi Keizo,JPX ; Masada Jyunichiro,JPX, Gas turbine moving blade.
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Yasuoki Tomita JP; Yukihiro Hashimoto JP; Kiyoshi Suenaga JP; Hisato Arimura JP; Shunsuke Torii JP; Jun Kubota JP; Akihiko Shirota JP; Sunao Aoki JP; Tatsuo Ishiguro JP, Gas turbine moving blade.
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Balsdon Julian G,GBX, Seal plate.
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Lammas Andrew J. ; Dingwell William T. ; Hungler Anthony E., Stress relieved dovetail.
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Barr Lawrence D. ; Borns Frederick G. ; Johnson Mark C., Turbine blade attachment stress reduction rings.
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이 특허를 인용한 특허 (11) 인용/피인용 타임라인 분석

El-Wardany, Tahany Ibrahim; Smith, Peter G.; Reynolds, Warren; Ng, Eugene; Adams, Kay V., Abrasive waterjet machining and method to manufacture a curved rotor blade retention slot.
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Alvanos, Ioannis; OConnor, John J., Asymmetrical rotor blade fir-tree attachment.
상세보기
Lattanzio, Santiago; Amoo, Olaleye M., Fan blades for gas turbine engines with reduced stress concentration at leading edge.
상세보기
Bois, Stephane; Accary, Arnaud; Dejaune, Claude; Kiener-Calvet, Benjamin; Foll, Julien; Tan-Kim, Alexandre; Petard, Benjamin, Fan disk for a jet engine and jet engine.
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Barnett, Barry, Fan hub design.
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Barnett, Barry, Fan hub design.
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Anderson, Carney R.; Tomeo, Peter V., Gas turbine engine fan blade lock assembly.
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Rajarajan, Rathina; Sharadchandra, Desai Tushar; Babu, Santhanagopalakrishnan; Satish, Akkur Marigowda; Neikirk, Michael Byron, Methods and apparatus to repair a rotor disk for a gas turbine.
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Spangler, Brandon W., Reduced weight blade for a gas turbine engine.
상세보기
McCaffrey, Michael G., Rotatable component with controlled load interface.
상세보기
Jablonski, Laurent, Turbine engine fan disk.
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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

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[미국특허] Bladed disk fixing undercut 원문보기

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[미국특허] Bladed disk fixing undercut 원문보기

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