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특허 상세정보

Aircraft gas turbine engine backbone deflection control

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/20   
미국특허분류(USC) 060/039.31; 060/039.32; 244/054
출원번호 US-0985776 (1992-12-04)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Squillaro, Jerome C.Rafter, John R.
인용정보 피인용 횟수 : 13  인용 특허 : 5
초록

A gas turbine engine backbone deflection control apparatus to counter the effects of backbone bending due to gust, thrust. and maneuver loads by introducing a controlled backbone counter-bending moment by applying controlled tensioning forces only between axially spaced apart frames connected by the backbone. One embodiment of the invention, for a high bypass ratio turbofan engine, provides a hydraulically powered actuator to produce tensioning forces in cables connected between a fan frame and a turbine frame and the actuator is controlled by the engine...

대표
청구항

1. A backbone counter-bending control apparatus for an aircraft gas turbine engine, said apparatus comprising: a backbone counter-bending moment means for applying tensioning forces only throughout the operating range of the aircraft gas turbine engine between axially spaced apart forward and aft frames that are connected by a backbone structure and a control means for controlling the amount of tensioning forces produced by aid backbone counter-bending moment means. 2. An apparatus as claimed in claim 1 wherein said backbone counter-bending moment m...

이 특허를 인용한 특허 피인용횟수: 13

  1. Journade, Frédéric; Jalbert, Delphine. Aircraft engine assembly comprising a turbojet engine with reinforcing structures connecting the fan casing to the central casing. USP2014118881536.
  2. Haaser, Frederic Gardner; Kamentser, Boris; Zul, Francisco; Kamentser, Eugenia. Apparatus for measuring bearing thrust load. USP2010057707902.
  3. Haaser,Frederic Gardner; Kamentser,Boris; Zul,Francisco; Kamentser,Eugenia. Apparatus for measuring bearing thrust load. USP2008107430926.
  4. Balk, Wouter. Attachment of a multiflow turbojet engine to an aircraft. USP2012078215580.
  5. Peters, Donald W.. Liner hanger cable. USP2016049309834.
  6. Willett, Jr., Fred Thomas. Method and apparatus for measuring turbine shell clearance. USP2014118876460.
  7. Marche,Herve. Mounting system inserted between an aircraft engine and a rigid structure of an attachment strut fixed under a wing of this aircraft. USP2007067232091.
  8. Marche,Herv챕. Mounting system inserted between an aircraft engine and a rigid structure of an attachment strut fixed under a wing of this aircraft. USP2006067063290.
  9. McArthur, John. Strain gauge and accelerometer measurement for thrust estimation. USP2017119829401.
  10. Stuart, Alan Roy; Fehrmann, John Robert. System and method for mounting an aircraft engine. USP2014058727269.
  11. Howarth,Nicholas; Freeman,Christopher. Turbine engine arrangements. USP2007017165744.
  12. Somanath, Nagendra; Dye, Christopher M.; Kumar, Keshava B.. Turbine engine frame having an actuated equilibrating case. USP2011088001791.
  13. Willett, Jr., Fred Thomas; Koza, Kenneth Michael. Turbomachine cold clearance adjustment. USP2017039587511.