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公开(公告)号：JP2001164903A
公开(公告)日：2001-06-19
申请号：JP2000346058
申请日：2000-11-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SOECHTING FRIEDRICH O , WILLIAM A VASUNAKKU , AUXIER THOMAS A , DOWNS JAMES P , CALHOUN WILLIAM H , HAYES DOUGLAS A
Abstract: PROBLEM TO BE SOLVED: To provide a device and a method of cooling a wall 12 used in a gas turbine engine. SOLUTION: A microcircuit 10 to cool the wall 12 of a gas turbine engine contains a cooling air passage 11 having a plurality of segments 36 interconnected in series by one or more chambers 38, an inlet hole 40, and an outlet hole 42. The inlet hole 40 is connected to a cooling air passage 11 on one side of the wall 12 and the outlet hole 42 is connected to the cooling air passage on the other side of the wall 12. Cooling air on the inlet hole 40 side of the wall 12 flows in the cooling air passage 11 through the inlet hole 40 and flows out through the outlet hole 42.
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公开(公告)号：JPH10325364A
公开(公告)日：1998-12-08
申请号：JP15531498
申请日：1998-05-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： NARCUS ANDREW R , HAYES DOUGLAS A , AUXIER THOMAS A
Abstract: PROBLEM TO BE SOLVED: To improve efficiency by suppressing work quantity of work lost for cooling to minimum. SOLUTION: A bypass air valve 20 has a liner 36 and a strap 34. The liner 36 has a plurality of first regions 46 and second regions 48. Each first region 46 has a plurality of first openings 52. Each second region 48 has a plurality of second openings 56. The strap 34 has a plurality of openings 78 and third regions 76. Each third region 76 has a plurality of third openings 80. When the valve is opened, the first region 46 is arranged in line with the opening 78. In addition, the third region 76 is arranged substantially in line with the second region 48. When the valve is closed, the first region 46 is arranged substantially in line with the third region 76, while the second region 48 is arranged in line with the opening 78.
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公开(公告)号：JP2001107705A
公开(公告)日：2001-04-17
申请号：JP2000303468
申请日：2000-10-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KVASNAK WILLIAM S , LAFLEUR RONALD S , SOECHTING FRIEDRICH O , JOE CHRISTOPHER R , MOROSO JOE , HAYES DOUGLAS A
Abstract: PROBLEM TO BE SOLVED: To provide a cooling device and method for a wall for provide a convection cooling inside the wall. SOLUTION: This cooling circuit 22 having one or more inlet openings 40 and one or more outlet openings 44 is arranged between a first wall part and a second wall part. The inlet opening 40 provides a cooling air flow passage led to the cooling circuit 22, while the outlet opening 44 provides a cooling air passage led out of the cooling circuit 22. The cooling circuit 22 includes a plurality of first pedestals 34 extended between the first and second wall parts. The first pedestals are arranged in at least one line 48. In one preferred embodiment, the first pedestals are separated from each other by inner-line spacings 50 in any line 48, while the adjacent pedestals in the adjacent lines are spaced from separated from each other by across-line spacings 52. The inner-line spacing 50 exceeds the across-like spacing 52.
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公开(公告)号：JP2001020703A
公开(公告)日：2001-01-23
申请号：JP2000188966
申请日：2000-06-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AUXIER THOMAS A , DOWNS JAMES P , KVASNAK WILLIAM S , SOECHTING FRIEDRICH O , CALHOUN WILLIAM H , HAYES DOUGLAS A
Abstract: PROBLEM TO BE SOLVED: To provide a method and device for cooling a rotor blade wall by utilizing a smaller amount of cooling air than in conventional cooling methods and devices. SOLUTION: This method for cooling a wall 12 of a rotor blade 21 includes a step for providing the wall 12 having inner and outer faces, a step for disposing in the wall 12 a cooling micro circuit 10 with a passage for cooling air extending between the inner and outer faces, and a step for enhancing heat transfer to a fluid from the wall 12 to the passage by increasing an average heat transfer coefficient per unit flow rate in the micro circuit 10. This method and device can be adjusted so as to substantially coincide with a thermal profile of the wall 10 at that place.
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公开(公告)号：DE60041366D1
公开(公告)日：2009-02-26
申请号：DE60041366
申请日：2000-06-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AUXIER THOMAS A , DOWNS JAMES P , CALHOUN WILLIAM H , KVASNAK WILLIAM S , SOECHTING FRIEDRICH O , HAYES DOUGLAS A
Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.
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Patent Agency Ranking
公开(公告)号：DE60031185D1
公开(公告)日：2006-11-16
申请号：DE60031185
申请日：2000-06-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AUXIER THOMAS A , DOWNS JAMES P , CALHOUN WILLIAM H , KVASNAK WILLIAM S , SOECHTING FRIEDRICH O , HAYES DOUGLAS A
Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.
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公开(公告)号：DE60025074T2
公开(公告)日：2006-06-29
申请号：DE60025074
申请日：2000-06-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AUXIER THOMAS A , KVASNAK WILLIAM S , DOWNS JAMES P , SOECHTING FRIEDRICH O , CALHOUN WILLIAM H , HAYES DOUGLAS A
Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.
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公开(公告)号：DE60031185T2
公开(公告)日：2007-08-23
申请号：DE60031185
申请日：2000-06-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AUXIER THOMAS A , DOWNS JAMES P , CALHOUN WILLIAM H , KVASNAK WILLIAM S , SOECHTING FRIEDRICH O , HAYES DOUGLAS A
Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.
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公开(公告)号：DE69811562T2
公开(公告)日：2003-08-28
申请号：DE69811562
申请日：1998-05-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： NARCUS ANDREW R , HAYES DOUGLAS A , AUXIER THOMAS A
Abstract: A bypass air valve for a gas turbine engine is provided which includes a liner 36, a strap 34, and means 40 for selectively actuating the valve. The liner 36 includes an inner radial surface 42, an outer radial surface 44, a plurality of first regions 46, and a plurality of second regions 48. Each first region 46 includes a plurality of first apertures 52. Each second region 48 includes a plurality of second apertures 56. The strap 34 includes a plurality of openings 78 and a plurality of third regions 76. Each third region 76 includes a plurality of third apertures 80. The valve may be selectively actuated into an open or a closed position. In the open position, the first regions 46 are substantially aligned with the openings 78 and the third regions 76 are substantially aligned with the second regions 48. In the closed position, the first regions 46 are substantially aligned with the third regions 76 and the second regions 48 are substantially aligned with the openings 78.
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公开(公告)号：DE69811562D1
公开(公告)日：2003-04-03
申请号：DE69811562
申请日：1998-05-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： NARCUS ANDREW R , HAYES DOUGLAS A , AUXIER THOMAS A
Abstract: A bypass air valve for a gas turbine engine is provided which includes a liner 36, a strap 34, and means 40 for selectively actuating the valve. The liner 36 includes an inner radial surface 42, an outer radial surface 44, a plurality of first regions 46, and a plurality of second regions 48. Each first region 46 includes a plurality of first apertures 52. Each second region 48 includes a plurality of second apertures 56. The strap 34 includes a plurality of openings 78 and a plurality of third regions 76. Each third region 76 includes a plurality of third apertures 80. The valve may be selectively actuated into an open or a closed position. In the open position, the first regions 46 are substantially aligned with the openings 78 and the third regions 76 are substantially aligned with the second regions 48. In the closed position, the first regions 46 are substantially aligned with the third regions 76 and the second regions 48 are substantially aligned with the openings 78.
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