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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.
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公开(公告)号：JP2002349205A
公开(公告)日：2002-12-04
申请号：JP2002113376
申请日：2002-04-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BALKCUM III J TYSON , LIANG GEORGE , REMLEY TIMOTHY J , WILLIAMS CHRISTOPHER CHARLES , PRZIREMBEL HANS R
Abstract: PROBLEM TO BE SOLVED: To provide a lightweight hollow shrouded turbine blade. SOLUTION: A turbine blade 10 includes an airfoil part 16 and a hollow blade tip shroud 18 connected to the airfoil part 16. The hollow tip shroud 18 preferably has a cast partitioned structure and a plurality of ribs 22. Those rib 22 function as load bearing structures and form a plurality of shroud core parts 42, 44, 46, 48, 50, and 52. Each shroud core part is connected to a cooling fluid supply source and includes a plurality of holes for supplying cooling fluid to an outer surface part of the shroud.
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公开(公告)号：CA1058083A
公开(公告)日：1979-07-10
申请号：CA257995
申请日：1976-07-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRZIREMBEL HANS R
IPC: F01D5/18
Abstract: TURBOMACHINERY VANE OR BLADE WITH COOLED PLATFORMS A turbomachinery vane or blade with cooled platforms including provision for film cooling the inner and outer surfaces of the platform forward portion, including cooling fluid cavities in the platform on both the pressure. and suction sides of the vane or blade airfoil for cooling this region of the platform by a combination of impingement, convection and film cooling, and a selective array of drilled holes extending through the platform trailing edge for convection cooling thereof.
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公开(公告)号：DE602005022654D1
公开(公告)日：2010-09-16
申请号：DE602005022654
申请日：2005-04-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KVASNAK WILLIAM S , LANDIS KENNETH K , PRZIREMBEL HANS R
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Patent Agency Ranking
公开(公告)号：DE60213328T2
公开(公告)日：2007-07-26
申请号：DE60213328
申请日：2002-04-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BALKCUM J TYSON III , LIANG GEORGE , REMLEY TIMOTHY J , WILLIAMS CHRISTOPHER CHARLES , PRZIREMBEL HANS R
Abstract: The turbine blade (10) comprises an airfoil section (16) and a hollow blade tip shroud (18) joined to the airfoil section (16). The hollow tip shroud (18) is preferably a cast, compartmentalized structure and has a plurality of ribs (40) acting as load bearing structures and defining a plurality of shroud core sections (42,44,46,48,50,52). Each of the shroud core sections (42,44,46,48,50,52) communicates with a supply of cooling fluid and has a plurality of apertures (66) for supplying cooling fluid to exterior portions of the shroud.
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公开(公告)号：DE60213328D1
公开(公告)日：2006-09-07
申请号：DE60213328
申请日：2002-04-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BALKCUM J TYSON III , LIANG GEORGE , REMLEY TIMOTHY J , WILLIAMS CHRISTOPHER CHARLES , PRZIREMBEL HANS R
Abstract: The turbine blade (10) comprises an airfoil section (16) and a hollow blade tip shroud (18) joined to the airfoil section (16). The hollow tip shroud (18) is preferably a cast, compartmentalized structure and has a plurality of ribs (40) acting as load bearing structures and defining a plurality of shroud core sections (42,44,46,48,50,52). Each of the shroud core sections (42,44,46,48,50,52) communicates with a supply of cooling fluid and has a plurality of apertures (66) for supplying cooling fluid to exterior portions of the shroud.
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公开(公告)号：DE69821443T2
公开(公告)日：2004-12-16
申请号：DE69821443
申请日：1998-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRZIREMBEL HANS R , SOECHTING FRIEDRICH O
Abstract: A hollow airfoil has a pressure side wall 12, a suction side wall 14, a cavity 16 formed between the pressure and suction side walls, a plurality of cooling ports 18 disposed within the pressure side wall 12, and a plurality of passages 42, each extending between the cavity 16 and one of the cooling ports 18. Each passage 42 has a first wall 54 adjacent the suction side wall 14, a pair of passage 58 side walls extending substantially toward the pressure side wall 12, and a second wall 56 adjacent the pressure side wall 12. Each passage further includes a pair of fillets 60,62 extending between the passage side walls 58 and the second wall 56. Alternatively, or in addition, each passage 42 includes a jog adjacent each cooling port 18 so as to extend parallel to the pressure side wall 12.
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公开(公告)号：DE69821443D1
公开(公告)日：2004-03-11
申请号：DE69821443
申请日：1998-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRZIREMBEL HANS R , SOECHTING FRIEDRICH O
Abstract: A hollow airfoil has a pressure side wall 12, a suction side wall 14, a cavity 16 formed between the pressure and suction side walls, a plurality of cooling ports 18 disposed within the pressure side wall 12, and a plurality of passages 42, each extending between the cavity 16 and one of the cooling ports 18. Each passage 42 has a first wall 54 adjacent the suction side wall 14, a pair of passage 58 side walls extending substantially toward the pressure side wall 12, and a second wall 56 adjacent the pressure side wall 12. Each passage further includes a pair of fillets 60,62 extending between the passage side walls 58 and the second wall 56. Alternatively, or in addition, each passage 42 includes a jog adjacent each cooling port 18 so as to extend parallel to the pressure side wall 12.
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公开(公告)号：CA1118688A
公开(公告)日：1982-02-23
申请号：CA322117
申请日：1979-02-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRZIREMBEL HANS R , MOORE WILLIAM A
IPC: F01D5/18
Abstract: TURBINE BLADE A convectively cooled turbine blade has two distinct cooling air passage systems. The first system cools the blade leading edge and emits cooling air through outlet passageways in the leading edge arranged in showerhead array. The second system includes a three-pass series flow passage through the remainder of the blade. Air flow from the second system emits along the trailing edge through an array of slots generally configured in the form of a Venetian blind.
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