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公开(公告)号：DE602004028203D1
公开(公告)日：2010-09-02
申请号：DE602004028203
申请日：2004-10-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BEALS JAMES T , PERSKY JOSHUA , SHAH DILIP M , SEETHARAMAN VENKAT , BOSE SUDHANGSHU , SNYDER JACOB , SANTELER KEITH , VERNER CARL , MURRAY STEPHEN D , MARCIN JOHN J , GUPTA DINESH , BALES DANIEL A , PAULONIS DANIEL F , COTNOIR GLENN , WIEDEMER JOHN
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公开(公告)号：CA2484564A1
公开(公告)日：2005-04-15
申请号：CA2484564
申请日：2004-10-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BOSE SUDHANGSHU , SEETHARAMAN VENKAT , VERNER CARL , SANTELER KEITH , SNYDER JACOB , WIEDEMER JOHN , COTNOIR GLENN , PAULONIS DANIEL FRANCIS , BALES DANIEL A , MURRAY STEPHEN D , BEALS JAMES T , GUPTA DINESH , PERSKY JOSHUA , SHAH DILIP M , MARCIN JOHN J
Abstract: A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating comprises at least one oxide and a silicon containing material. In a second embodiment, the coating comprises an oxide selected from the group consisting of calcia, magnesia, alumina, zirconia, chromic, yttria , silica, hafnia, and mixtures thereof. In a third embodiment, the coating comprises a nitride selected from the group consisting of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.
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公开(公告)号：DE602005000449D1
公开(公告)日：2007-03-08
申请号：DE602005000449
申请日：2005-03-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , SANTELER KEITH , GAYMAN SCOTT W , COUCH ERIC
Abstract: A turbine airfoil includes a plurality of cooling circuits (22) embedded within the pressure and suction sidewalls (28,30) and a first and a second flow passage (32f,32g). The first flow passage (32f) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the pressure sidewall (28) and the second flow passage (32g) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the suction sidewall (30).
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公开(公告)号：CA2495740A1
公开(公告)日：2005-08-03
申请号：CA2495740
申请日：2005-02-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TELLER BRET , CUNHA FRANK , SANTELER KEITH
Abstract: A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro- circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro- circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal connective efficiency, high film coverage, and high cooling effectiveness.
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Patent Agency Ranking
公开(公告)号：AT474680T
公开(公告)日：2010-08-15
申请号：AT04256369
申请日：2004-10-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BEALS JAMES T , PERSKY JOSHUA , SHAH DILIP M , SEETHARAMAN VENKAT , BOSE SUDHANGSHU , SNYDER JACOB , SANTELER KEITH , VERNER CARL , MURRAY STEPHEN D , MARCIN JOHN J , GUPTA DINESH , BALES DANIEL A , PAULONIS DANIEL F , COTNOIR GLENN , WIEDEMER JOHN
Abstract: A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating comprises at least one oxide and a silicon containing material. In a second embodiment, the coating comprises an oxide selected from the group consisting of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating comprises a nitride selected from the group consisting of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.
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公开(公告)号：PL1577498T3
公开(公告)日：2007-06-29
申请号：PL05251603
申请日：2005-03-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , SANTELER KEITH , GAYMAN SCOTT W , COUCH ERIC
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公开(公告)号：DE602005027139D1
公开(公告)日：2011-05-12
申请号：DE602005027139
申请日：2005-02-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SANTELER KEITH , TELLER BRET , CUNHA FRANK
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公开(公告)号：DE602005000449T2
公开(公告)日：2007-08-23
申请号：DE602005000449
申请日：2005-03-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , SANTELER KEITH , GAYMAN SCOTT W , COUCH ERIC
Abstract: A turbine airfoil includes a plurality of cooling circuits (22) embedded within the pressure and suction sidewalls (28,30) and a first and a second flow passage (32f,32g). The first flow passage (32f) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the pressure sidewall (28) and the second flow passage (32g) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the suction sidewall (30).
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公开(公告)号：CA2497755A1
公开(公告)日：2005-09-16
申请号：CA2497755
申请日：2005-02-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SANTELER KEITH , CUNHA J FRANK , COUCH ERIC , GAYMAN SCOTT W
Abstract: A turbine airfoil includes a plurality of cooling circuits embedded within t he pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.
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