-
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.
-
公开(公告)号：JPH11107702A
公开(公告)日：1999-04-20
申请号：JP22391698
申请日：1998-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KRAUSE DAVID A , MONGILLO DOMINIC J JR , SOECHTING FRIEDRICH O , ZELESKY MARK F
IPC: F01D5/18
Abstract: PROBLEM TO BE SOLVED: To provide a coolable airfoil or vane, which can operate at a high temperature for a long time but requires a minimal amount of coolant. SOLUTION: A blade or vane for a gas turbine engine includes a main cooling system 42 having a series of intermediate passages 44, 46a, 46b, 46c, and 48, and a subordinate cooling system 92 having a series of cooling ducts 94 (94a to 94h). The ducts of subordinate cooling system 92, being parallel to and having the same radial extent with the intermediate passages, are installed between the intermediate passages 44, etc., and outer surface 28 of the airfoil and within a surrounding wall 16. The ducts are installed within high temperature load regions 104 and 106 in the direction of a chord so as to maximize efficiency. The ducts are recommended to have the same extent in the direction of a chord in several intermediate passages in order to avoid an excessive rise in coolant temperature within the intermediate passages. The length of the duct in the direction of a chord is limited so as not to generate a temperature gradient, with could lead to failure, at airfoil wall 16.
-
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.
-
公开(公告)号：JP2001164902A
公开(公告)日：2001-06-19
申请号：JP37577898
申请日：1998-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MARTIN G TABITA , JAMES P DOWNES , SOECHTING FRIEDRICH O , AUXIER THOMAS A
Abstract: PROBLEM TO BE SOLVED: To provide a device to perform proper cooling along the front edge of a hollow airfoil, have a position adapted for a variable stagnation line, generate a cooling airfilm, having uniformity and permanency, in a position situated downstream from the front edges on the two side part of the airfoil and further, minimize a stress generating at the wall of the airfoil. SOLUTION: A hollow airfoil 16 comprises a body; a trench 18; and a plurality of cooling holes 38 formed in the trench. The body is extended in the direction of a chord between a front edge 26 and a rear edge and extended in the direction of a span between an outside radial surface and an inside radial direction and contains an external wall 24 to surround a cavity 22. A trench 18 is situated at an external wall 24 along the front edge 26 and extended in the direction of a span, and aligned with a stagnation line (a stagnation point 42) extending along the front edge 26.
-
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.
-
Patent Agency Ranking
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.
-
公开(公告)号：JP2001065304A
公开(公告)日：2001-03-13
申请号：JP2000232601
申请日：2000-08-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WILLIAM A VASUNAKKU , SOECHTING FRIEDRICH O , KAREN A TOLL , GARRY A ZESU
Abstract: PROBLEM TO BE SOLVED: To control the movement of the core gas flow toward the radial boundary at both of inner and outer sides of a core gas passage by increasing a speed of the core gas flow for preventing the generation of the secondary flow of the core gas flow toward a wall in an area where a front edge of a blade is adjacent to the wall. SOLUTION: A turbine of a gas turbine engine has a plurality of stationary blade segments 26 on a plurality of stationary blade stages. Each stationary blade segment 26 has at least one blade 28 extending between platforms 30, 32 as the inner and outer walls. Here, a means 38 for changing the direction of the core gas flow is used for separating the core gas flow of high temperature from a region where a front edge 50 of the blade 28 is adjacent to the walls 30, 32. Whereby a speed of the core gas flow is increased, the pressure gradient is reduced, and the secondary core gas flow in the directions of walls 30, 32 can be reduced. A fillet 48 extending in the longitudinal direction or the height direction from the front edge 50 of the blade 28 forms the means 38.
-
公开(公告)号：JPH11229809A
公开(公告)日：1999-08-24
申请号：JP34109798
申请日：1998-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRZIREMBEL HANS R , SOECHTING FRIEDRICH O
Abstract: PROBLEM TO BE SOLVED: To provide an air foil having a trailing edge cooling device which is capable of controlling high cycle fatigue, increasing the film cooling downstream, and is furthermore simple to produce. SOLUTION: A hollow air foil 10 is provided with a pressure side wall 12, an intake side wall 14, a cavity formed in between the pressure side and the intake side wall, a plurality of cooling holes provided in the pressure side wall 12, and a plurality of ducts 42 each extending between the cavity and a cooling hole 18. Each duct 42 has a cross section that includes a first wall 54 adjacent to the intake side wall 14, a pair of duct side walls 58, and a second wall 56 adjacent to the pressure side wall 12. A pair of fillets 60, 62 is also provided so as to extend between the pair of duct side walls 58 and the second wall 56. Each duct 42 may include a protrusion adjacent to each cooling hole 18.
-
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.
-
公开(公告)号：DE69836156D1
公开(公告)日：2006-11-23
申请号：DE69836156
申请日：1998-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KRAUSE DAVID A , MONGILLO DOMINIC J JR , SOECHTING FRIEDRICH O , ZELESKY MARK F
IPC: F01D5/18
-
-
-
-
-
-
-
-
-
Search Results
45
records
(took 0.123 seconds)
