[특허]Replacement part for a gas turbine blade of a gas turbine, gas turbine blade and method for repairing a gas turbine blade

Replacement part for a gas turbine blade of a gas turbine, gas turbine blade and method for repairing a gas turbine blade 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/20 F01D-005/00 B23P-006/00
출원번호	US-0062939 (2009-09-09)
등록번호	US-8944772 (2015-02-03)
우선권정보	DE-10 2008 047 043 (2008-09-13)
국제출원번호	PCT/DE2009/001280 (2009-09-09)
§371/§102 date	20110701 (20110701)
국제공개번호	WO2010/028641 (2010-03-18)
발명자 / 주소	Eberlein, Armin Schneider, Albert-Valentin
출원인 / 주소	MTU Aero Engines GmbH
대리인 / 주소	Crowell & Moring LLP
인용정보	피인용 횟수 : 0 인용 특허 : 48

초록 ▼

A replacement part for a gas turbine blade is disclosed. The replacement part is designed to replace a removed portion of the blade, the portion including a section of the blade tip and a section of the leading edge and/or the trailing edge, and the replacement part having at least one joining side with which it can be brought to contact with the blade that is reduced by the removed portion and joined therewith. The joining side has at least one section, the cross-section of which is U-shaped.

대표청구항 ▼

1. A replacement part for a gas turbine blade, comprising: a section of a blade tip;a section of at least one of a leading edge and a trailing edge of a blade; anda joining side for welding to the gas turbine blade, wherein the joining side is on a side of the replacement part that is opposite from the section of at least one of the leading edge and the trailing edge of the blade and wherein the joining side has a section that is U-shaped in cross section; wherein the U-shaped cross-section is formed by a base which is flanked on two sides by flanges, wherein at least one of the flanges has a gradual thickening of a wall thickness in at least one region running in a longitudinal direction of the joining side as compared to at least one other region of the flange located in the longitudinal direction. 2. The replacement part according to claim 1, wherein the gas turbine blade is a blade of an aircraft engine. 3. The replacement part according to claim 1, wherein the joining side has a second section that is L-shaped in cross-section. 4. The replacement part according to claim 3, wherein the section that is U-shaped in cross section is essentially directly adjacent to the second section that is L-shaped in cross-section. 5. The replacement part according to claim 1, wherein at least one of the flanges in at least one region running in the longitudinal direction of the joining side as compared to at least one other region of the flange located in the longitudinal direction is longer in a direction extending transverse to the longitudinal direction and transverse to the base than in the at least one other region. 6. The replacement part according to claim 1, wherein the joining side runs straight along a longitudinal direction of extension. 7. A gas turbine blade, comprising: a remnant portion; anda replacement part according to claim 1 formed onto the remnant portion via a welded connection. 8. The gas turbine blade according to claim 7, wherein the joining side has a second section that is L-shaped in cross-section and wherein the second section is adjacent to a leading edge or a trailing edge of the gas turbine blade. 9. The gas turbine blade according to claim 7, wherein the at least one region of the flange forming the gradual thickening is adjacent to a leading edge or a trailing edge of the gas turbine blade. 10. A method for repairing a gas turbine blade, comprising the steps of: removing a portion of the gas turbine blade so that a blade remnant portion remains that is reduced by the removed portion, wherein the removed portion includes a section of a blade tip and a section of at least one of a leading edge and a trailing edge of the gas turbine blade;welding a replacement part to the blade remnant portion, wherein the replacement part includes: a section of a blade tip;a section of at least one of a leading edge and a trailing edge of a blade; anda joining side, wherein the joining side is on a side of the replacement part that is opposite from the section of at least one of the leading edge and the trailing edge of the blade and wherein the joining side has a section that is U-shaped in cross section, wherein the U-shaped cross-section is formed by a base which is flanked on two sides by flanges, wherein at least one of the flanges has a gradual thickening of a wall thickness in at least one region running in a longitudinal direction of the joining side as compared to at least one other region of the flange located in the longitudinal direction;wherein a welding direction when welding on the replacement part is such that welding is performed from a direction of the at least one of the leading edge and the trailing edge in a direction of the blade tip.

이 특허에 인용된 특허 (48)

Benoit Roland (Lake Park FL) Beverly Eugene M. (Palm Beach Gardens FL) Love Charles M. (Jupiter FL) Mack Gregory J. (Palm Beach Gardens FL), Abrasive blade tip.
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Sherlock, Graham D.; Nowak, Daniel A.; Balsone, Stephen J.; Mohr, Patrick J., Bi-layer tip cap.
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Ellis ; Delmar H., Composite reinforcement of metallic airfoils.
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Horvath Richard L. (Hamilton OH) Harris Robert W. (Fairfield OH), Cooled turbine blade tip closure.
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Richard J. Grylls ; Joseph D. Rigney ; Warren D. Grossklaus, Jr. ; Melvin R. Jackson, Environmentally resistant squealer tips and method for making.
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Schell Jerry D. (Evendale OH) Farr Howard J. (Blue Ash OH) Kelley Thomas J. (Cincinnati OH) Monson Paul J. E. (Wilmington NC) Ferrigno Stephen J. (Cincinnati OH), Environmentally-resistant turbine blade tip.
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Marshall Darwin (Tonawanda NY), Erosion resistant propellers.
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Ingistov, Steve; Pistor, Robert, Extended tip turbine blade for heavy duty industrial gas turbine.
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Gely Jean-Marie L. (Le Havre FRX) Goutines Marius J. (Melun FRX) Meauz Geordes (Paris FRX), Fairing for turbo-jet engine fan leading edge.
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Trewiler,Gary Edward, Fusion welding method and welded article.
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Stalker Kenneth W. (Cincinnati OH) Zelahy John W. (West Chester OH) Fairbanks Norman P. (Cincinnati OH), Gas seal for turbine blade tip.
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Wang,John Z.; Bailey,Mark J.; Berry,Robert R.; Fernandez,Emilio, Gas turbine bucket tip cap.
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Wilkins, Melvin H.; Corrigan, Sean J.; Dingwell, William T., Gas turbine engine compressor blade restoration method.
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Ferrigno Stephen J. ; Cowie William D. ; Mannava Seetharamaiah, Laser shock peening for gas turbine engine weld repair.
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Freling Melvin (West Hartford CT) Gruver Gary A. (South Windsor CT) Parkos ; Jr. Joseph J. (East Haddam CT) Welch Douglas A. (Portland CT), Method and apparatus for reducing stress on the tips of turbine or compressor blades.
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Keith, Sean Robert; DeMarche, Thomas Edward; Staker, John Robert; Tressler, Judd Dodge, Method and apparatus for reducing turbine blade tip region temperatures.
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Ryznic, John E, Method and leading edge replacement insert for repairing a turbine engine blade.
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Stalker Kenneth W. (Cincinnati OH) Zelahy John W. (West Chester OH) Fairbanks Norman P. (Cincinnati OH), Method for making an improved gas seal.
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Bowden ; Jr. Joseph H. ; Roedl Lawrence J., Method for repairing a turbine engine member damaged tip.
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Murphy Guy C. (Fairfield OH) Jones Jackie D. (Fairfield OH) Salemme Charles T. (Madeira OH), Method of fabricating hollow composite airfoils.
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Mons, Claude Marcel; Vigneau, Joël Olivier Alfred Abel, Method of making a rim situated at the free end of a blade, a blade obtained by the method, and a turbomachine fitted with the blade.
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Beyer James R. ; Fisher ; Jr. Richard K., Method of making a turbine blade.
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Fraser Michael J. (Broughton Hackett GB2), Method of manufacture and repair of turbine blades.
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Bouet, Bernard; Derrien, Gerard; Kerneis, Stephane Michel; Pagnon, Claude Andre Charles; Pinto, Eric Christian Jean, Method of repairing a blisk and test pieces by welding.
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Hiskes, David J., Method repair of turbine blade tip.
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Dulaney Jeff L. ; Clauer Allan H. ; Clarady Joseph F. ; Baumgarten Robert ; Weinstein Jerry G. ; Hack Benjamin R., Method using laser shock peening to process airfoil weld repairs pertaining to blade cut and weld techniques.
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Imano, Shinya; Doi, Hiroyuki; Ichikawa, Kunihiro; Tanaka, Katsumi, Ni-based alloy member, method of producing the alloy member, turbine engine part, welding material, and method of producing the welding material.
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Horvath, Richard L., One-piece HPTR blade squealer tip.
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Coulon Andr (Bessoncourt FRX), Protective tip for a titanium blade and a method of brazing such a tip.
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Smith Blair A. ; Cook James ; Mattavi Joseph L. ; Eaton Harry E., Replaceable ceramic blade insert.
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Kozlin Joseph R. (Jupiter FL), Rotor blade having a tip cap end closure.
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Eiswerth James E. (West Chester OH), Tip cap for a rotor blade and method of replacement.
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Bergander, Katharina; Bostanjoglo, Georg; Buchal, Tobias; Eβer, Winfried; Goldschmidt, Dirk; Koch, Torsten; Küperkoch, Rudolf; Mattheis, Thorsten; Münzer, Jan; Müsgen, Ralf; Oechsner, Matthias; Pickert, Ursula; Vosberg, Volker, Turbine blade.
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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
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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

Replacement part for a gas turbine blade of a gas turbine, gas turbine blade and method for repairing a gas turbine blade 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

이 특허에 인용된 특허 (48)

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Replacement part for a gas turbine blade of a gas turbine, gas turbine blade and method for repairing a gas turbine blade 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

전체(0) 논문(0) 특허(0) 보고서(0)

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이 특허에 인용된 특허 (48)

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