$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색도움말
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

통합검색

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison, Kafe, Webinar 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

Circular arc multi-bore fan disk

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-005/32   
미국특허분류(USC) 416/220.R; 416/221; 416/244.A; 416/245.R
출원번호 US-0723109 (2000-11-27)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Herkamp, Nathan D.Rosen, Steven J.
인용정보 피인용 횟수 : 20  인용 특허 : 24
초록

A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart dovetail slots are disposed through the rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of the rim, and extending radially inwardly from a disk outer surface of the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of th...

대표
청구항

A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart dovetail slots are disposed through the rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of the rim, and extending radially inwardly from a disk outer surface of the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of th...

이 특허에 인용된 특허 (24)

  1. Antuna Eugene J. (Springdale OH) Keck Donald F. (Fairfield OH). Apparatus and method for the disassembly of an ultra high bypass engine. USP1994055307623.
  2. Przytulski James C. (Fairfield OH) Hemsworth Martin C. (Cincinnati OH). Apparatus for preloading an airfoil blade in a gas turbine engine. USP1992065123813.
  3. Dhuic Jean-Claude (Melun FRX). Axial and radial holding system for the rotor vane of a turbojet engine. USP1984104474535.
  4. Manharth Gary B. (Milford OH) Cornell Jay L. (Cincinnati OH). Blade assembly for a turbomachine. USP1984114483661.
  5. Luebering George W. (Cincinnati OH). Blade retainer assembly. USP1977074033705.
  6. Marlin Francois M. P. (Melun FRX). Bladed disc for a turbomachine rotor. USP1991095049035.
  7. Peterson Stephen C. (West Chester OH) Przytulski James C. (Fairfield OH). Burst resistant rotor disk assembly. USP1993055213475.
  8. Harris Daniel J. (West Chester OH) Przytulski James C. (Fairfield OH) Szpunar Stephen J. (West Chester OH). Fan assembly having lightweight platforms. USP1994015281096.
  9. Surdi Jean M. (Melun FRX). Fan blade axial and radial retention device. USP1984104478554.
  10. Kebedjis Georges (Alfortville FRX). Fan blade axial locking device. USP1985034502841.
  11. Youssef Nashed A. (Mississauga CAX). Fan blade axial retention device. USP1991115067877.
  12. Szpunar Stephen J. (West Chester OH). Fan blade retainer. USP1994025282720.
  13. Prentice Ian F. (Cincinnati OH) Juenger Jerome A. (Cincinnati OH). Gas turbine engine blade retainer sub-assembly. USP1994095350279.
  14. Pool Francis C. (Duffield GB2). Gas turbine engine having an automatic ice shedding spinner. USP1983074393650.
  15. Gilchrist Alan R. (Fairfield OH) Sullivan Thomas J. (Fairfield OH) Walker Roger C. (Middletown OH). Hybrid spinner nose configuration in a gas turbine engine having a bypass duct. USP1993025182906.
  16. Williams Sam B. (Bloomfield Hills MI) Jones John F. (Berkley MI) Dorer David K. (Milford MI). Medium bypass turbofan engine. USP1986074598544.
  17. Glynn Christopher C. (Hamilton OH) Hemsworth Martin C. (Cincinnati OH). Multiple rotor disk assembly. USP1993035197857.
  18. Corsmeier Robert J. (Cincinnati OH). Platform assembly for attaching rotor blades to a rotor disk. USP1993065222865.
  19. Salemme Charles T. (Cincinnati OH) Ravenhall Richard (Cincinnati OH) Harris David J. (Fairfield OH). Platform for a turbomachinery blade. USP1977044019832.
  20. Leone Donald J. (Tolland CT). Spinner. USP1976113990814.
  21. Lammas Andrew J. ; Dingwell William T. ; Hungler Anthony E.. Stress relieved dovetail. USP2000036033185.
  22. Juenger Jerome A. (Cincinnati OH) Peterson Stephen C. (West Chester OH) Herzner Frederick C. (Fairfield OH). Stress-relieved rotor blade attachment slot. USP1992085141401.
  23. Langley, Kenneth R.. Turbomachine rotor blade fixings. USP1984054451203.
  24. Bucy ; Jr. Raymond W. (Terrace Park OH) Gallardo ; Jr. Vicente C. (Hamilton OH) Hollett Ronald C. (Cincinnati OH) Young Eric A. (Cincinnati OH). Turbomachinery blade retaining assembly. USP1981054265595.

이 특허를 인용한 특허 피인용횟수: 20

  1. Anderson, Carney R.; Tomeo, Peter V.. Axial retention system for a bladed rotor with multiple blade types. USP2015028961141.
  2. Stone,Paul. Bladed disk fixing undercut. USP2006127153102.
  3. Luo, Jian; Hernandez, Maria; Laskowsky, John. Brushless DC motor with stepped skewed rotor. USP2005066906443.
  4. Forrester, James Michael; Stevenson, Joseph Timothy; Potter, Jeffrey Clayton; Corrigan, Sean Joel. Circular arc multi-bore fan disk assembly. USP2003106634863.
  5. McDonald, Seth Alexander; Strock, William James; Tudor, Courtney James; Hasting, William Howard; Worthoff, Frank. Composite vane mounting. USP2013108550776.
  6. Stoughton, Philip Howard; Dietsch, Benjamin Allen; Durchholz, Anthony John; Eckert, Michael Charles. Dampers for fan spinners of aircraft engines. USP2016029261112.
  7. Brown, Charles W.. Detachable fan blade platform and method of repairing same. USP20180710024177.
  8. Turner, Matthew A.; Brown, Charles W.; Bugaj, Shari L.; Quinn, Christopher M.; Hyland, David J.; Alarcon, Andrew G.. Fairing assembly. USP2016029267386.
  9. Tatton, Royce. Fan blade platform seal with leading edge winglet. USP2018069988920.
  10. Turner, Matthew A.; Tatton, Royce E.; Wood, Kristin; Satterwhite, Matthew. Fan platform with stiffening feature. USP2018059976426.
  11. Ackermann, William K.; Stripinis, Philip S.. Gas turbine engine buffer system providing zoned ventilation. USP20180710018116.
  12. Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.. Gas turbine engine front architecture. USP2018059957918.
  13. Duelm, Shelton O.; Quinn, Christopher M.; Brown, Charles W.. Low profile fan platform attachment. USP2017099759226.
  14. Kray, Nicholas Joseph; Crall, David William; Mollmann, Daniel Edward. Method and apparatus for gas turbine engines. USP2010087780410.
  15. Dix, Brian Edward; Takehara, Joann Mari; Garrison, Michael Ray. Methods and apparatus for assembling gas turbine engines. USP2005056887043.
  16. 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. USP2012058182229.
  17. 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. USP2013128602738.
  18. Robertson, Thomas J.; McPhail, James J.. Recirculation seal for use in a gas turbine engine. USP20190210215045.
  19. Delapierre, Mickael; Gignoux, Herve; Loro, Gael; Wintenberger, Sylvie. Rotating inlet cowl for a turbine engine, comprising an eccentric forward end. USP2015038984855.
  20. Delapierre, Mickael; Gignoux, Herve; Loro, Gael; Wintenberger, Sylvie. Rotating inlet cowl for a turbine engine, comprising an eccentric forward end. USP2016019243562.