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1.发明申请TAILORED THERMAL CONTROL SYSTEM FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL ARRAY 审中-公开用于气体涡轮发动机叶片外部空气密封阵列的定制热控制系统公开(公告)号：US20160273376A1
公开(公告)日：2016-09-22
申请号：US15023593
申请日：2014-10-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Philip R. Rioux , Neil L. Tatman
Abstract: A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends. The contoured radial outer portion defines a multiple of fins and a multiple of slots. A blade outer air seal assembly with a clearance control ring land which receives the radial inner portion. A method of controlling a radial tip clearance within a gas turbine engine includes tailoring a multiple of fins and a multiple of slots of a clearance control ring for both steady state and transient clearance operations.
Abstract translation: 用于燃气涡轮发动机的间隙控制系统的间隙控制环包括限定多个翅片和多个槽的轮廓径向外部部分。 燃气涡轮发动机的间隙控制系统包括具有径向内部部分的间隙控制环，轮廓径向外部部分从该径向内部部分延伸。 轮廓的径向外部部分限定了多个翅片和多个狭槽。 叶片外部空气密封组件，其具有容纳径向内部的间隙控制环形凸台。 控制燃气涡轮发动机内的径向顶端间隙的方法包括为稳态和瞬时间隙操作调节多个叶片和间隙控制环的多个槽。
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Patent Agency Ranking
公开(公告)号：US10247027B2
公开(公告)日：2019-04-02
申请号：US15078978
申请日：2016-03-23
Applicant: United Technologies Corporation
Inventor： Philip R. Rioux , Nicholas R Leslie , Paul M. Lutjen , Christopher W. Strock
Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.
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公开(公告)号：US10408080B2
公开(公告)日：2019-09-10
申请号：US15023593
申请日：2014-10-06
Applicant: United Technologies Corporation
Inventor： Philip R. Rioux , Neil L. Tatman
Abstract: A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends. The contoured radial outer portion defines a multiple of fins and a multiple of slots. A blade outer air seal assembly with a clearance control ring land which receives the radial inner portion. A method of controlling a radial tip clearance within a gas turbine engine includes tailoring a multiple of fins and a multiple of slots of a clearance control ring for both steady state and transient clearance operations.
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公开(公告)号：US20170276007A1
公开(公告)日：2017-09-28
申请号：US15078978
申请日：2016-03-23
Applicant: United Technologies Corporation
Inventor： Philip R. Rioux , Nicholas R Leslie , Paul M. Lutjen , Christopher W. Strock
CPC classification number: F01D11/122 , F01D5/28 , F01D25/005 , F04D29/164 , F04D29/324 , F04D29/526 , F05D2220/32 , F05D2230/31 , F05D2240/11 , F05D2240/30 , F05D2240/55 , F05D2300/175 , F05D2300/20 , F05D2300/6032 , F16J15/44 , F16J15/445 , Y02T50/672 , Y02T50/6765
Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.
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公开(公告)号：US10344769B2
公开(公告)日：2019-07-09
申请号：US15212849
申请日：2016-07-18
Applicant: United Technologies Corporation
Inventor： Louis R. Mouza , Philip R. Rioux
Abstract: Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material.
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公开(公告)号：US20180017067A1
公开(公告)日：2018-01-18
申请号：US15212849
申请日：2016-07-18
Applicant: United Technologies Corporation
Inventor： Louis R. Mouza , Philip R. Rioux
CPC classification number: F04D29/083 , F01D11/18 , F01D25/243 , F01D25/246 , F04D29/023 , F04D29/164 , F04D29/526 , F04D29/584 , F05D2300/50212
Abstract: Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material.
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