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公开(公告)号：WO2014028090A3
公开(公告)日：2014-05-01
申请号：PCT/US2013042969
申请日：2013-05-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LUTJEN PAUL M , DABBS THURMAN CARLO
CPC classification number: F04D29/164 , F01D11/08 , F04D29/526 , F05D2240/11 , F05D2260/201 , Y02T50/676
Abstract: A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.
Abstract translation: 根据本公开的示例性实施例的叶片外部空气密封件（BOAS）节段可以包括密封体，该密封体具有径向内面和径向外面，该径向内面和径向外面在第一配合面和第二配合面之间沿周向延伸， 前缘面和后缘面。 第一配合面，第二配合面，径向外面和径向内面中的至少一个可以包括内壁，该内壁具有凸缘和从凸缘径向向内的底切通道，该凸缘沿着凸缘的长度不间断地延伸。
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Patent Agency Ranking
公开(公告)号：WO2014028095A2
公开(公告)日：2014-02-20
申请号：PCT/US2013044032
申请日：2013-06-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LUTJEN PAUL M , GREGG SHAWN J , DABBS THURMAN CARLO , BLANEY KEN F , KEENE RUSSELL E , CHICK BRUCE E
CPC classification number: F01D11/08 , F01D1/02 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括壁，前钩和后钩。 该壁在前钩和后钩之间延伸，其适于将叶片外部空气密封件安装到燃气涡轮发动机的壳体上。 壁包括沿壁的至少一部分延伸的芯通道。 芯通道径向和轴向地延伸穿过后钩的一部分，以沿着后钩的后缘与一个或多个孔连通。
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公开(公告)号：SG11201404364TA
公开(公告)日：2014-10-30
申请号：SG11201404364T
申请日：2013-03-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PAPPLE MICHAEL , ENNACER MOHAMMED , DABBS THURMAN CARLO , LUTJEN PAUL M , CAPRARIO JOSEPH T , BERGMAN RUSSELL J , GREGG SHAWN J
Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.
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公开(公告)号：EP2855857A4
公开(公告)日：2016-06-08
申请号：EP13829503
申请日：2013-06-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LUTJEN PAUL M , GREGG SHAWN J , DABBS THURMAN CARLO , BLANEY KEN F , KEENE RUSSELL E , CHICK BRUCE E
CPC classification number: F01D11/08 , F01D1/02 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
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公开(公告)号：EP2834498A4
公开(公告)日：2016-07-06
申请号：EP13772338
申请日：2013-03-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BERGMAN RUSSELL J , GREGG SHAWN J , PAPPLE MICHAEL , LUTJEN PAUL M , CAPRARIO JOSEPH T , ENNACER MOHAMMED , DABBS THURMAN CARLO
CPC classification number: F01D25/246 , F01D25/14 , F05D2240/81
Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.
Abstract translation: 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一增压室流体连通，并且与定子叶片的翼型内的第一翼型冷却通道形成流体连通。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。
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公开(公告)号：EP2855891A4
公开(公告)日：2016-03-02
申请号：EP13829661
申请日：2013-05-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LUTJEN PAUL M , DABBS THURMAN CARLO
CPC classification number: F04D29/164 , F01D11/08 , F04D29/526 , F05D2240/11 , F05D2260/201 , Y02T50/676
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