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公开(公告)号：WO2014120324A2
公开(公告)日：2014-08-07
申请号：PCT/US2013070362
申请日：2013-11-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BLAIR MICHAEL F , PROPHETER-HINCKLEY TRACY A , ZELESKY MARK F
CPC classification number: F01D25/12 , F01D25/10 , F02C7/14 , F05D2260/205 , F05D2260/213 , F05D2260/232 , F28D15/00 , F28F1/124 , F28F1/40 , F28F7/02 , F28F2255/18 , Y02T50/676
Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
Abstract translation: 涡轮发动机系统包括热源，热交换器，冷却介质入口和冷却介质出口。 热源包括第一通道。 热交换器包括第二通道和第三通道。 第一和第二通道配置在闭环电路中。 第三通道在开环电路中配置在入口和出口之间。
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公开(公告)号：DE602007000674D1
公开(公告)日：2009-04-23
申请号：DE602007000674
申请日：2007-08-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LUTJEN PAUL M , HOFF RICHARD W , PAGE RICHARD H , GATES ROGER J , BLAIR MICHAEL F
IPC: B22C9/10
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公开(公告)号：SG125088A1
公开(公告)日：2006-09-29
申请号：SG200303390
申请日：2003-06-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAPER SAMUEL DAVID , BLAIR MICHAEL F , ALAHYARI ABBAS A
IPC: B81B1/00 , B81B7/04 , F01D5/00 , F01D5/18 , F01D9/02 , F01D25/12 , F01D25/24 , F02C7/18 , F02C7/28 , F23M5/08 , F23R3/00 , F23R3/06 , F25D9/00 , F28F13/02
Abstract: An embedded microcircuit (5) for producing an improved cooling film over a surface of a part, comprises an inlet through which a coolant gas may enter, a circuit channel (29) extending from the inlet through which the coolant gas may flow, and a slot film hole (31) formed at a terminus of the circuit channel (29) through which the coolant gas may exit a part.
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公开(公告)号：SG139617A1
公开(公告)日：2008-02-29
申请号：SG2007028566
申请日：2007-04-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： THOLEN SUSAN M , LUTJEN PAUL M , PAGE RICHARD H , HOFF RICHARD W , GATES ROGER J , BLAIR MICHAEL F
Abstract: BLADE OUTER AIR SEAL CORES AND MANUFACTURE METHODS A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion.
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公开(公告)号：AU2003204541B2
公开(公告)日：2005-07-07
申请号：AU2003204541
申请日：2003-06-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALAHYARI ABBAS A , BLAIR MICHAEL F , DRAPER SAMUEL DAVID
IPC: B81B1/00 , B81B7/04 , F01D5/18 , F01D9/02 , F01D25/12 , F01D25/24 , F02C7/18 , F02C7/28 , F23M5/08 , F23R3/00 , F23R3/06 , F25D9/00 , F28F13/02 , F02C007/18 , F01P001/00 , F01D025/12 , F02C007/12
Abstract: An embedded microcircuit (5) for producing an improved cooling film over a surface of a part, comprises an inlet through which a coolant gas may enter, a circuit channel (29) extending from the inlet through which the coolant gas may flow, and a slot film hole (31) formed at a terminus of the circuit channel (29) through which the coolant gas may exit a part.
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Patent Agency Ranking
公开(公告)号：AU2003204541A1
公开(公告)日：2004-01-22
申请号：AU2003204541
申请日：2003-06-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALAHYARI ABBAS A , BLAIR MICHAEL F , DRAPER SAMUEL DAVID
IPC: B81B1/00 , B81B7/04 , F01D5/18 , F01D9/02 , F01D25/12 , F01D25/24 , F02C7/18 , F02C7/28 , F23M5/08 , F23R3/00 , F23R3/06 , F25D9/00 , F28F13/02 , F01P1/00 , F02C7/12
Abstract: An embedded microcircuit (5) for producing an improved cooling film over a surface of a part, comprises an inlet through which a coolant gas may enter, a circuit channel (29) extending from the inlet through which the coolant gas may flow, and a slot film hole (31) formed at a terminus of the circuit channel (29) through which the coolant gas may exit a part.
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公开(公告)号：CA2432490A1
公开(公告)日：2003-12-19
申请号：CA2432490
申请日：2003-06-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BLAIR MICHAEL F , ALAHYARI ABBAS A , DRAPER SAMUEL DAVID
IPC: B81B1/00 , B81B7/04 , F01D5/18 , F01D9/02 , F01D25/12 , F01D25/24 , F02C7/18 , F02C7/28 , F23M5/08 , F23R3/00 , F23R3/06 , F25D9/00 , F28F13/02 , B21D53/00 , F28F7/00 , B23P15/00
Abstract: An embedded microcircuit for producing an improved cooling film over a surface of a part, comprising an inlet through which a coolant gas may enter, a circuit channel extending from the inlet through which the coolant gas may flow, and a slot film hole formed at a terminus of the circuit channel through which the coolant gas may exit a part.
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8.发明公开GAS TURBINE ENGINE SYSTEMS AND RELATED METHODS INVOLVING VANE-BLADE COUNT RATIOS GREATER THAN UNITY 审中-公开燃气涡轮发动机系统和与叶轮的数量比大于单位相关手续
公开(公告)号：EP2798185A4
公开(公告)日：2015-08-26
申请号：EP12863767
申请日：2012-12-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHARMA OM P , BLAIR MICHAEL F
CPC classification number: F02C3/14 , F01D1/04 , F01D5/142 , F02C7/18 , F05D2220/3212 , F05D2240/12 , F05D2260/202
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公开(公告)号：EP2920444A4
公开(公告)日：2015-12-02
申请号：EP13873218
申请日：2013-11-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BLAIR MICHAEL F , PROPHETER-HINCKLEY TRACY A , ZELESKY MARK F
CPC classification number: F01D25/12 , F01D25/10 , F02C7/14 , F05D2260/205 , F05D2260/213 , F05D2260/232 , F28D15/00 , F28F1/124 , F28F1/40 , F28F7/02 , F28F2255/18 , Y02T50/676
Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
Abstract translation: 涡轮发动机系统包括热源，热交换器，冷却介质入口和冷却介质出口。 热源包括第一通道。 热交换器包括第二通道和第三通道。 第一通道和第二通道配置在闭环回路中。 第三通道在开环回路中配置在入口和出口之间。
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公开(公告)号：EP2798174A4
公开(公告)日：2015-08-19
申请号：EP12871456
申请日：2012-12-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHARMA OM P , BLAIR MICHAEL F
CPC classification number: F01D5/06 , F01D5/186 , F05D2260/231
Abstract: An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five.
Abstract translation: 示例性的燃气涡轮发动机包括涡轮机部分，其可操作以将旋转能量赋予压缩机部分。 涡轮部分至少包括低压涡轮机和高压涡轮机，而低压涡轮机中的多个级数为三级至五级。
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