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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：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：JP2000186504A
公开(公告)日：2000-07-04
申请号：JP36051599
申请日：1999-12-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TABBITA MARTIN G , DOWNS JAMES P , SOECHTING FRIEDRICH O , THOMAS A OUKIYAA , STEINBAUER JR FREDERICK
Abstract: PROBLEM TO BE SOLVED: To form a uniform and stable cooling air film in the downstream of the front edge on both sides of an air foil by expanding the space between adjacent openings to reduce a high stress area, eliminating uncooled areas in the individual cooling points and between them, and eliminating uncooled areas in the middle of the cooling opening and on its downstream. SOLUTION: A tubine blade 10 of a gas turbine engine has a root part 12, a platform 14, an air foil 16 and a blade tip 18. The air foil 16 has one, two or more inner cavities surrounded with an outer wall 22, and at least one of them is located in the vicinity of the front edge 24 of the air foil 16 and plural cooling openings 26. The cooling openings 26 are arranged along the front edge 24 to provide a passage for allowing cooling air to pass through the outer wall 22. Plural first and second openings are provided and respectively directed toward the suction side part 28 and the pressure side part 30. The flow of cooling air crosses the front edge 24 to perform suitable cooling.
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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：DE69828757D1
公开(公告)日：2005-03-03
申请号：DE69828757
申请日：1998-12-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TABBITA MARTIN G , DOWNS JAMES P , SOECHTING FRIEDRICH , AUXIER THOMAS A
IPC: F01D5/18
Abstract: A hollow airfoil 10 is provided with a trench 18 which is aligned with a stagnation line 42 extending along the leading edge 26. Cooling air apertures 38 extend between an inner cavity of the airfoil and the trench 18 to supply cooling air thereto.
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Patent Agency Ranking
公开(公告)号：DE69520778D1
公开(公告)日：2001-05-31
申请号：DE69520778
申请日：1995-11-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DOWNS JAMES P , RUANO EDUARDO
Abstract: Layers (14, 16) of thermally conductive material are applied to an object (10) such that second layers (16) of thermally conductive material are distributed amongst first layers (14) of thermally conductive material. A first layer (14) of thermally conductive material is less thermally conductive than a second layer (16) at any particular temperature. Thermal energy travelling through the layers to the object is impeded by the lower thermally conductive of the first layers, and substantially dispersed in a lateral direction by the higher thermally conductive of the second layers, thereby minimizing any thermal gradients that might otherwise exist within the object.
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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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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：DE69930916T2
公开(公告)日：2006-08-31
申请号：DE69930916
申请日：1999-12-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TABBITA MARTIN G , DOWNS JAMES P , SOECHTING FRIEDRICH O
Abstract: A hollow airfoil 16 is provided which includes a body having an external wall 22 and an internal cavity 20. The external wall 22 includes a suction side portion 28 and a pressure side portion 30. The portions extend chordwise between a leading edge 24 and a trailing edge 32 and spanwise between an inner radial surface 14 and an outer radial surface 18. A stagnation line 40 extends along the leading edge 24. A plurality of cooling apertures 26, are disposed spanwise along the leading edge 14. In one embodiment the apertures 26 coincide with the stagnation line 40 and extend through the external wall 22 along a helical path. The apertures 26 are alternately directed towards the suction side portion 28 and the pressure side portions 30 of the airfoil 16. The apertures 26 may open into a leading edge trench 34. In another embodiment (FIGS. 10 and 11) the apertures 26 are disposed on either side of the stagnation line 40.
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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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