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특허 상세정보

Non-integral fan platform

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-005/22   
미국특허분류(USC) 416/193A; 416/2190R; 416/2450R; 416/248
출원번호 US-0723108 (2000-11-27)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Nathan D. Herkamp
인용정보 피인용 횟수 : 28  인용 특허 : 19
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 circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to ...

대표
청구항

1. A non-integral gas turbine engine fan blade platform for circumferential disposition between fan blades, said platform comprising:a platform wall with a radially outer surface which faces radially outwardly and a radially inner surface which faces radially inwardly, said platform wall is sloped with respect to a centerline with an increasing radius of the outer surface in the axially aft direction, forward, mid, and aft mounting lugs depend radially inwardly from said platform wall, and a wedge shaped platform bumper depends radially inwardly from the...

이 특허에 인용된 특허 (19)

  1. Przytulski James C. (Fairfield OH) Hemsworth Martin C. (Cincinnati OH). Apparatus for preloading an airfoil blade in a gas turbine engine. USP1992065123813.
  2. Manharth Gary B. (Milford OH) Cornell Jay L. (Cincinnati OH). Blade assembly for a turbomachine. USP1984114483661.
  3. Marlin Francois M. P. (Melun FRX). Bladed disc for a turbomachine rotor. USP1991095049035.
  4. Peterson Stephen C. (West Chester OH) Przytulski James C. (Fairfield OH). Burst resistant rotor disk assembly. USP1993055213475.
  5. Harris Daniel J. (West Chester OH) Przytulski James C. (Fairfield OH) Szpunar Stephen J. (West Chester OH). Fan assembly having lightweight platforms. USP1994015281096.
  6. Youssef Nashed A. (Mississauga CAX). Fan blade axial retention device. USP1991115067877.
  7. Szpunar Stephen J. (West Chester OH). Fan blade retainer. USP1994025282720.
  8. Prentice Ian F. (Cincinnati OH) Juenger Jerome A. (Cincinnati OH). Gas turbine engine blade retainer sub-assembly. USP1994095350279.
  9. Pool Francis C. (Duffield GB2). Gas turbine engine having an automatic ice shedding spinner. USP1983074393650.
  10. 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.
  11. Glynn Christopher C. (Hamilton OH) Hemsworth Martin C. (Cincinnati OH). Multiple rotor disk assembly. USP1993035197857.
  12. Corsmeier Robert J. (Cincinnati OH). Platform assembly for attaching rotor blades to a rotor disk. USP1993065222865.
  13. Salemme Charles T. (Cincinnati OH) Ravenhall Richard (Cincinnati OH) Harris David J. (Fairfield OH). Platform for a turbomachinery blade. USP1977044019832.
  14. Brioude Michel A. (Melun FRX) Chereau Philippe (Savigny Le Temple FRX) Naudet Jacky (Bondoufle FRX). Rotor fitted with spacer blocks between the blades. USP1992115161949.
  15. Knott David S. (Derby GB2). Rotors for gas turbine engines. USP1995115466125.
  16. Inizan Grard F. (Paris) Jourdain Grard E. A. (Saintry sur Seine) Pabion Philippe (Dammarie les Lys) Payen Jean-Michel (Le Mee sur Seine) Ruffier Christine J. G. (Vitry sur Seine FRX). Separate inter-blade platform for a bladed rotor disk. USP1993035193982.
  17. Lammas Andrew J. ; Dingwell William T. ; Hungler Anthony E.. Stress relieved dovetail. USP2000036033185.
  18. Juenger Jerome A. (Cincinnati OH) Peterson Stephen C. (West Chester OH) Herzner Frederick C. (Fairfield OH). Stress-relieved rotor blade attachment slot. USP1992085141401.
  19. 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: 28

  1. Tatton, Royce E.. Airfoil platform having dual pin apertures and a vertical stiffener. USP20190210215046.
  2. Bottome, Kristofer J.. Annulus filler. USP2015049017031.
  3. De Gaillard, Thomas Alain; Boisson, Alexandre Bernard Marie; Laguerre, Audrey. Aviation turbine engine fan assembly including a fitted platform. USP20190310233939.
  4. Forrester, James Michael; Stevenson, Joseph Timothy; Potter, Jeffrey Clayton; Corrigan, Sean Joel. Circular arc multi-bore fan disk assembly. USP2003106634863.
  5. Garcia-Crespo, Andres Jose. Composite airfoil assembly. USP2015038967974.
  6. Brown, Charles W.. Detachable fan blade platform and method of repairing same. USP20180710024177.
  7. Turner, Matthew A.; Brown, Charles W.; Bugaj, Shari L.; Quinn, Christopher M.; Hyland, David J.; Alarcon, Andrew G.. Fairing assembly. USP2016029267386.
  8. Blanchard, Stephane Pierre Guillaume; Dakowski, Mathieu; Garin, Fabrice Marcel Noel; Judet, Maurice Guy. Fixed vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such fixed vane assembly. USP2014108864458.
  9. Kling, Colin J.; Brown, Charles W.; Quinn, Christopher M.; Duelm, Shelton O.; Tomeo, Peter V.; Hubbert, Corey L.. Gas turbine engine fan spacer platform attachments. USP20181110119423.
  10. Alvanos, Ioannis; Suciu, Gabriel L.; Dye, Christopher M.; Levasseur, Glenn. Hybrid rotor disk assembly for a gas turbine engine. USP2014108851853.
  11. Alvanos, Ioannis; Suciu, Gabriel L.; Dye, Christopher M.; Levasseur, Glenn. Hybrid rotor disk assembly with a ceramic matrix composite airfoil for a gas turbine engine. USP2014098834125.
  12. Alvanos, Ioannis; Suciu, Gabriel L.; Dye, Christopher M.; Levasseur, Glenn. Hybrid rotor disk assembly with ceramic matrix composites platform for a gas turbine engine. USP2015018936440.
  13. Murdock, James R.. Injection molded composite fan platform. USP20181210145268.
  14. Queriault,Michele Jacqueline; Lejars,Claude Robert Louis. Lightened interblade platform for a turbojet blade support disc. USP2007017163375.
  15. Ravier, Anne-Laure. Linear gasket for an inter-blade platform. USP2018019869323.
  16. Duelm, Shelton O.; Quinn, Christopher M.; Brown, Charles W.. Low profile fan platform attachment. USP2017099759226.
  17. Kray, Nicholas Joseph; Platz, Jr., Gregory Allen; Hastings, Matthew Robert; Bryant, Jr., Gary Willard; Kral, Justin Jeffrey. Metallic fan blade platform. USP2014078777576.
  18. Kray, Nicholas Joseph; Crall, David William; Mollmann, Daniel Edward. Method and apparatus for gas turbine engines. USP2010087780410.
  19. Audic, Stephane; Lefebvre, Eric Jacques; Nitre, Thierry. Method of calibrating the mass of components intended to be mounted at the periphery of a rotor. USP2009067553125.
  20. Gignoux, Herve; Gvozdenovic, Eric; Loro, Gael; Bassot, Alain Jacques Michel. Method of repairing or reworking a turbomachine disk and repaired or reworked turbomachine disk. USP2014108864472.
  21. Dix, Brian Edward; Takehara, Joann Mari; Garrison, Michael Ray. Methods and apparatus for assembling gas turbine engines. USP2005056887043.
  22. Lamboy, Jorge Orlando; Gann, Matthew Glen; Kray, Nicholas Joseph; Pauley, Gerald Alexander; Wilkin, II, Daniel Allen; Xie, Ming. Non-integral fan blade platform. USP2016079399922.
  23. Robertson, Thomas J.; McPhail, James J.. Recirculation seal for use in a gas turbine engine. USP20190210215045.
  24. Boisson, Alexandre Bernard Marie; Berdou, Caroline Jacqueline Denise; De Gaillard, Thomas Alain; Gimat, Matthieu Arnaud. Rotary assembly for an aviation turbine engine, the assembly comprising a separate fan blade platform mounted on a fan disk. USP20181010094390.
  25. Delapierre, Mickael; Gignoux, Herve; Loro, Gael; Wintenberger, Sylvie. Rotating inlet cowl for a turbine engine, comprising an eccentric forward end. USP2015038984855.
  26. Delapierre, Mickael; Gignoux, Herve; Loro, Gael; Wintenberger, Sylvie. Rotating inlet cowl for a turbine engine, comprising an eccentric forward end. USP2016019243562.
  27. Liang, George. Turbine airfoil cooling system with platform edge cooling channels. USP2010077762773.
  28. Brown, Wesley D.. Turbine blade with detached platform. USP2011017874804.