[특허]Turbine blade damper seal

Turbine blade damper seal 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/14 F01D-005/22 F01D-005/30 F01D-011/00
출원번호	US-0362552 (2012-01-31)
등록번호	US-10113434 (2018-10-30)
발명자 / 주소	Snyder, Daniel A. Lana, Kyle Charles Sandoval, Jonathan Perry Virkler, Scott Daniel Taraskevich, Jaimie Otero, Edwin
출원인 / 주소	UNITED TECHNOLOGIES CORPORATION
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 49

초록 ▼

A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

대표청구항 ▼

1. A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf, the damper seal comprising: a central body portion having a first end region, an opposing second end region, and a width;a first portion extending from the first end region of the central body portion, wherein the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion, wherein the first portion includes a first another tab that extends substantially perpendicularly to the first outwardly extending tabs, and the first another tab extends away from the central body portion such that the first outwardly extending tabs are located between the central body portion and the first another tab; anda second portion extending from the opposing second end region of the central body portion. 2. The damper seal as recited in claim 1 wherein the second portion includes second outwardly extending tabs that define a second enlarged portion that has a second width greater than the width of the central body portion. 3. The damper seal as recited in claim 1 wherein the damper seal is formed from stamped sheet metal. 4. The damper seal as recited in claim 2 wherein the second portion includes a second another tab that extends substantially perpendicularly to the second outwardly extending tabs, and the second another tab extends away from the central body portion such that the second outwardly extending tabs are located between the central body portion and the second another tab. 5. The damper seal as recited in claim 1 wherein a portion of the damper seal engages a groove in a turbine disk lug of a turbine disk. 6. The damper seal as recited in claim 1 wherein the central body includes a projection that defines an opening, and the opening receives a lug of a turbine blade to align the damper seal relative to the turbine blade. 7. The turbine blade as recited in claim 1 wherein the first portion has a first height and the second portion has a second height, and the second height is greater than the first height. 8. The turbine blade as recited in claim 1 wherein the central body portion is curved. 9. The turbine blade as recited in claim 1 wherein the damper seal is substantially c-shaped. 10. A turbine blade comprising: a root received in a slot of a turbine disk;a blade;a platform located between the root and the blade, wherein the platform includes a retention shelf, and a cavity is defined between a lower surface of the platform and the retention shelf; anda damper seal received in the cavity of the turbine blade, the damper seal including a central body portion having a first end region, an opposing second end region, a width, a first portion extending generally downward from the first end region of the central body portion, and a second portion extending generally downward from the opposing second end region of the central body portion, wherein the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion, wherein the first portion includes a first another tab that extends substantially perpendicularly to the first outwardly extending tabs, and the first another tab extends away from the central body portion such that the first outwardly extending tabs are located between the central body portion and the first another tab. 11. The turbine blade as recited in claim 10 wherein the second portion includes second outwardly extending tabs that define a second enlarged portion that has a second width greater than the width of the central body portion. 12. The turbine blade as recited in claim 10 wherein the damper seal is formed from stamped sheet metal. 13. The turbine blade as recited in claim 10 wherein the first enlarged portion rests on the retention shelf of the turbine blade. 14. The turbine blade as recited in claim 11 wherein the second portion includes a second another tab that extends substantially perpendicularly to the second outwardly extending tabs, and the second another tab extends away from the central body portion such that the second outwardly extending tabs are located between the central body portion and the second another tab. 15. The turbine blade as recited in claim 10 wherein a portion of the damper seal engages a groove in a turbine disk lug of the turbine disk. 16. The turbine blade as recited in claim 10 wherein the central body includes a projection that defines an opening, and the opening receives a lug on the lower surface of the platform of the turbine blade to align the damper seal relative to the turbine blade. 17. The damper seal as recited in claim 10 wherein the first portion has a first height and the second portion has a second height, and the second height is greater than the first height. 18. The damper seal as recited in claim 10 wherein the central body portion is curved. 19. The damper seal as recited in claim 10 wherein the damper seal is substantially c-shaped.

이 특허에 인용된 특허 (49)

Mueller Peter W. (Morrow OH) Stevenson Joseph T. (Amelia OH) Panovsky Josef (Hamilton OH) Glynn Christopher C. (Hamilton OH) Park Sang Y. (W. Chester OH) Wines Daniel E. (Cincinnati OH), Blade damper.
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Surace, Raymond; Colon, Dennis I., Blade damper.
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Garth Kneeland Grover ; Gary Charles Liotta, Blade damper and method for making same.
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Schwarzmann Russell A. (Marlborough CT) Lillibridge Herbert J. (Plainville CT), Blade to blade vibration damper.
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Jones Carmen B. (West Chester OH), Broad spectrum vibration damper assembly fixed stator vanes of axial flow compressor.
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Lagrange, Benjamin Arnette; Good, Randall Richard; Liotta, Gary Charles; DeLong, Jon Robert; Collier, Matthew Durham; Vehr, James William; Chiurato, Anthony Aaron, Bucket vibration damper system.
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Eveker Kevin M. ; Gysling Daniel L. ; Nett Carl N. ; Wang Hua O., Compressor stall and surge control using airflow asymmetry measurement.
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Mercadante Anthony J. (9 Lake St. South Windsor CT 06074) Boursy Andrews P. (22 Riverview Cir. Marlborough CT 06447), Coolable rotor assembly.
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Sheridan William G. (Southington CT) Pagluica Gino J. (Manchester CT), Coupling system for a planetary gear train.
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Smith Dale E. (Windsor CT) Chase ; III Edward W. (West Suffield CT), Damper and seal for propeller quill shaft.
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Lee,Ching Pang; Brassfield,Steven Robert; Schilling,Jan Christopher, Damper cooled turbine blade.
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Teets J. Michael ; Teets Jon W., Electricity generating system having an annular combustor.
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Sheridan, William G., Epicyclic gear train for turbo fan engine.
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Duong, Loc; McCune, Michael E.; Dobek, Jr., Louis J., Epicyclic gear train integral sun gear coupling design.
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Stickler David B. ; Kerrebrock Jack L., Evaporatively cooled rotor for a gas turbine engine.
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Sheridan, William G.; McCune, Michael E.; Pescosolido, Alessio, Flexible shaft for gas turbine engine.
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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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Chlus Wieslaw A. (Wethersfield CT), Gas turbine blade seal.
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Schilling, Jan Christopher, Gas turbine engine assembly and method of assembling same.
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Law,Chi, Geartrain coupling for a turbofan engine.
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Lindemuth James E. ; Anderson William G., Heat pipe cooling for turbine stators.
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Duong, Loc; McCune, Michael E.; Dobek, Jr., Louis J., Integral sun gear coupling.
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Kalogeros Robert R. (Glastonbury CT), Interblade seal for turbomachine rotor.
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Evans, Charles R.; Ward, Douglas D., Jet aircraft fan case containment design.
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Curley Robert C. (White Marsh MD) Fisher Mark T. (Bel Air MD) Dileonardi James V. (Baltimore MD) DePinho ; Jr. A. Norton (Baldwin MD), Light weight fan blade containment system.
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Haloff ; Gary J., Method and system of controlling a jet engine for avoiding engine surge.
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Singh Anant P. (Cincinnati OH), Oil film damper seal ring.
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Brauer John C. ; Di Salle David A. ; Brill Edward P. ; Albers Robert J. ; Lenahan Dean T., Shielded turbine rotor.
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Stallone Michael J. (Cincinnati OH) Mollmann Daniel E. (Cincinnati OH), Squeeze film bearing damper with annular end plenums.
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Monzel Fred J. (Loveland OH), Squeeze film damper seal.
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Monzel Fred J. (Loveland OH), Squeeze film damper seal.
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Stec Philip F. (Medford MA), Stable blade vibration damper for gas turbine engine.
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Sheridan William G., Star gear system with lubrication circuit and lubrication method therefor.
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Benjamin Robert B. (Windsor CT) Adams Betsy B. (Cambridge MA), Turbine blade damper and seal.
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Gonsor Michael ; Kelley ; III Sanford E. ; Houston David P., Turbine blade damper and seal.
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Houston David P. ; Pelland Natalie A. ; Gonsor Michael ; Airey David, Turbine blade damper and seal.
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Charbonneau,Robert A.; Botticello,Kenneth P.; Gregg,Shawn J.; Hlavaty,Kirk David; Levine,Jeffrey R.; Lonczak,Kenneth A.; McGarrah,Craig R.; Mongillo,Dominic J.; O'Neill,Lisa P.; Pietraszkiewicz,Edward; Salzillo,Richard M.; Terry,Heather Ann, Turbine blade including revised platform.
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Ramlogan, Amarnath; Agrawal, Rajendra K.; Doll, Stephen D., Turbine blade nested seal and damper assembly.
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Beattie,Jeffrey, Turbine blade nested seal damper assembly.
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Airey David ; Pelland Natalie A. ; Houston David P., Turbine blade platform seal.
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Barcza William K. (Palm City FL), Turbine engine rotor blade platform seal.
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Barcza William K. (Palm City FL), Turbine engine rotor blade platform sealing and vibration damping device.
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Dietrich Douglas J. ; Stoner Alan W. ; Wiebe David J., Turbine engine rotor blade platform sealing and vibration damping device.
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Brown Wesley D. (Jupiter FL) Hill Edward C. (Tequesta FL) Vercellone Peter T. (Lake Worth FL), Turbine rotor retention system.
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Lieser, Dirk; Reichert, Arnd; Strassberger, Micheal; Tiemann, Peter, Turbo-machine comprising a sealing system for a rotor.
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Duesler Paul W. ; Loffredo Constantino V. ; Prosser ; Jr. Harold T. ; Jones Christopher W., Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation 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

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Turbine blade damper seal 원문보기

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Turbine blade damper seal 원문보기

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이 특허에 인용된 특허 (49)

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