发明授权
- 专利标题: Aircraft gas turbine engine blade tip clearance control
- 专利标题(中): 飞机燃气涡轮发动机叶片顶端间隙控制
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申请号: US11833596申请日: 2007-08-03
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公开(公告)号: US08126628B2公开(公告)日: 2012-02-28
- 发明人: John Erik Hershey , Brock Estel Osborn , Donald Lee Gardner , Rafael Jose Ruiz , William Lee Herron
- 申请人: John Erik Hershey , Brock Estel Osborn , Donald Lee Gardner , Rafael Jose Ruiz , William Lee Herron
- 申请人地址: US NY Schenectady
- 专利权人: General Electric Company
- 当前专利权人: General Electric Company
- 当前专利权人地址: US NY Schenectady
- 代理商 William Scott Andes; Steven J. Rosen
- 主分类号: G06F19/00
- IPC分类号: G06F19/00 ; G06G7/70
摘要:
A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.
公开/授权文献
- US20090037035A1 AIRCRAFT GAS TURBINE ENGINE BLADE TIP CLEARANCE CONTROL 公开/授权日:2009-02-05