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公开(公告)号：DE602005000796D1
公开(公告)日：2007-05-16
申请号：DE602005000796
申请日：2005-05-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MAGOWAN JOHN W , KRAUSE DAVID , GREGG SHAWN J , CUCINELLA FRANK THOMAS , SURACE RAYMOND C , MONGILLO JR DOMINIC J
Abstract: A rotor blade (14) is provided having a hollow airfoil (72) and a root (20). The hollow airfoil (22) has a cavity (40) and one or more cooling apertures (32,76,90). The root (20) is attached to the airfoil (22), and has a leading edge conduit (42), at least one mid-body conduit (44), and a trailing edge conduit (46). The conduits are operable to permit airflow through the root and into the cavity. Each conduit (42,44,46) has a centerline (58,74,88). The leading edge conduit (42) includes an inlet (48) having a forward side (50), a suction side (52), and a pressure side (56) that diverge from the centerline (58) of the leading edge conduit (42), and an aft side (52). Each of the mid-body conduits (44) includes an inlet (64) having a suction side (66) and a pressure side (68) that diverge from the centerline (74) of the mid-body conduit (44), and an aft side (70) and a forward side (72). The trailing edge conduit (46) includes an inlet (78) having a suction side (84) and a pressure side (86) that diverge from the centerline (88) of the trailing edge conduit (46). The trailing edge conduit inlet (78) further includes a forward side (82) and an aft side (80).
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公开(公告)号：AU2004240224A1
公开(公告)日：2005-08-18
申请号：AU2004240224
申请日：2004-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , PROPHETER TRACY A , GREGG SHAWN J , OTERO EDWIN
Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).
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公开(公告)号：CA2487476A1
公开(公告)日：2005-08-13
申请号：CA2487476
申请日：2004-11-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PROPHETER TRACY A , SURACE RAYMOND C
Abstract: A rotor blade for a rotor assembly is provided that includes a root, an airfoil, a platform and a damper. The airfoil has at least one cavity. The platform is disposed between the root and the airfoil. The platform includes an inner surface, an outer surface, and a damper aperture disposed in the inner surface. The damper has a body a nd a base. The base and the damper aperture have mating geometries that enable the base to rotate within the damper aperture without substantial impediment from the mating geometries.
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公开(公告)号：CA2501160A1
公开(公告)日：2005-11-27
申请号：CA2501160
申请日：2005-03-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , PROPHETER TRACY A
Abstract: A rotor blade damper is provided that includes a body having a base, a tip, a first contact surface, a second contact surface, a trailing edge surface, and a leading edge surface. The trailing edge and the leading edge surfaces extend between the contact surfaces. The first contact surface, second contact surface, trailing edge surface, and leading edge surface all extend lengthwise between the base and the tip. The body includes at least one cooling aperture disposed adjacent the base, that has a diameter that is approximately equal to or greater than the width of the trailing edge surface adjacent the tip. The body tapers between the base and the tip such that a first widthwis e cross-sectional area adjacent the base is greater than a second widthwise cross-sectional ar ea adjacent the tip.
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公开(公告)号：AU2004240227B8
公开(公告)日：2005-09-01
申请号：AU2004240227
申请日：2004-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , PROPHETER TRACY A
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Patent Agency Ranking
公开(公告)号：CA2487490A1
公开(公告)日：2005-08-04
申请号：CA2487490
申请日：2004-11-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , OTERO EDWIN , GREGG SHAWN J , PROPHETER TRACY A
Abstract: A rotor blade for a rotor assembly is provided that includes a root, an airfoil, and a damper. The airfoil has a length, a base, a tip, a first side wall, a second side wall and at least one cavity. The length extends the base and the tip. The at least one cavity is disposed between the side walls and the channel is defined by a first wall portion and a second wall portion. The damper, which is selectively received within the channel includes a first bearing surface, a second bearing surface, a forward surfac e and an aft surface, all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage within the channel. The passage has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of t he present invention, the damper has an arcuate lengthwise extending centerline.
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公开(公告)号：DE60221074T2
公开(公告)日：2008-03-13
申请号：DE60221074
申请日：2002-05-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , MERRY BRIAN , DOLANSKY GREGORY M , REINHARDT GREGORY E
Abstract: The present invention relates to a method for repairing a turbine blade 10 having a crack 16 in a trailing edge portion 26 of the blade 10. The disclosed method comprises the steps of cutting back a first surface 18 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located, and cutting back a second surface 20 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located. Each cut back step comprises cutting back the respective surface 18,20 by a depth L greater than the length of the crack 16 and less than the trailing edge radius to remove the crack 16 and form a cut back trailing edge portion 28. A compound radius is used to prevent a blunt transition into the trailing edge 12 that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade 10 to increase service life. Prior to applying the coating, the tip portion 46 of the turbine blade 10 is modified to account for the change in the thermal characteristics of the turbine blade 10.
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公开(公告)号：DE602005001085T2
公开(公告)日：2007-11-22
申请号：DE602005001085
申请日：2005-03-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PROPHETER TRACY A , SURACE RAYMOND C
Abstract: A rotor blade damper (48) is provided that includes a body (58) having a base (60), a tip (62), a first contact surface (64), a second contact surface (66), a trailing edge surface (68), and a leading edge surface (70). The trailing edge and the leading edge surfaces (68,70) extend between the contact surfaces (64,66). The first contact surface (64), second contact surface (66), trailing edge surface (68), and leading edge surface (70) all extend lengthwise between the base (60) and the tip (62). The body (58) includes at least one cooling aperture (82) disposed adjacent the base (60), that has a diameter that is approximately equal to or greater than the width of the trailing edge surface (68) adjacent the tip (62). The body (58) tapers between the base (60) and the tip (62) such that a first widthwise cross-sectional area adjacent the base (60) is greater than a second widthwise cross-sectional area adjacent the tip (62).
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公开(公告)号：PL1602801T3
公开(公告)日：2007-09-28
申请号：PL05251996
申请日：2005-03-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PROPHETER TRACY A , SURACE RAYMOND C
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公开(公告)号：SG117530A1
公开(公告)日：2005-12-29
申请号：SG200501860
申请日：2005-03-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PROPHETER TRACY A , SURACE RAYMOND C
Abstract: A rotor blade damper (48) is provided that includes a body (58) having a base (60), a tip (62), a first contact surface (64), a second contact surface (66), a trailing edge surface (68), and a leading edge surface (70). The trailing edge and the leading edge surfaces (68,70) extend between the contact surfaces (64,66). The first contact surface (64), second contact surface (66), trailing edge surface (68), and leading edge surface (70) all extend lengthwise between the base (60) and the tip (62). The body (58) includes at least one cooling aperture (82) disposed adjacent the base (60), that has a diameter that is approximately equal to or greater than the width of the trailing edge surface (68) adjacent the tip (62). The body (58) tapers between the base (60) and the tip (62) such that a first widthwise cross-sectional area adjacent the base (60) is greater than a second widthwise cross-sectional area adjacent the tip (62).
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