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1.发明申请GAS TURBINE ENGINE TURBINE BLADE TIP ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD 有权气体涡轮发动机涡轮叶片提升主动间隙控制系统及方法公开(公告)号：US20150142216A1
公开(公告)日：2015-05-21
申请号：US14082755
申请日：2013-11-18
Applicant: Honeywell International Inc.
Inventor： Don Tillman , Raymond Gage , Rich Barrett
CPC classification number: B64D31/06 , F01D11/20 , F01D11/24 , F02C7/18 , F02C9/16 , F05D2260/20 , F05D2260/201 , F05D2260/57 , F05D2270/07 , F05D2270/44 , Y02T50/676
Abstract: A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.
Abstract translation: 在燃气涡轮发动机中控制涡轮机叶片至静止结构间隙的系统和方法包括处理飞行器数据以确定飞机何时在高度巡航条件下飞行。 当飞机在高空巡航条件下不飞行时，压缩机排放空气被引导冲击至涡轮机罩的至少一部分。 在确定飞机在高度巡航条件下飞行时，压缩机排放空气被引导流过涡轮壳体的至少一部分并且撞击到涡轮机外罩的至少一部分。
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2.发明授权Gas turbine engine turbine blade tip active clearance control system and method 有权燃气轮机发动机叶片叶片主动间隙控制系统及方法公开(公告)号：US09266618B2
公开(公告)日：2016-02-23
申请号：US14082755
申请日：2013-11-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Tillman , Raymond Gage , Rich Barrett
CPC classification number: B64D31/06 , F01D11/20 , F01D11/24 , F02C7/18 , F02C9/16 , F05D2260/20 , F05D2260/201 , F05D2260/57 , F05D2270/07 , F05D2270/44 , Y02T50/676
Abstract: A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.
Abstract translation: 在燃气涡轮发动机中控制涡轮机叶片至静止结构间隙的系统和方法包括处理飞行器数据以确定飞机何时在高度巡航条件下飞行。 当飞机在高空巡航条件下不飞行时，压缩机排放空气被引导冲击至涡轮机罩的至少一部分。 在确定飞机在高度巡航条件下飞行时，压缩机排放空气被引导流过涡轮壳体的至少一部分并且撞击到涡轮机外罩的至少一部分。
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