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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：AU2004240221A1
公开(公告)日：2005-07-07
申请号：AU2004240221
申请日：2004-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONGILLO DOMINIC J JR , GREGG SHAWN J
Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (180, an airfoil (20), and a damper (24). The airfoil (20) includes a base (28), a tip (30), a pressure side wall (36), a suction side wall (38), and a cavity (40) disposed therebetween. The cavity (40) extends substantially between the base (28) and the tip (30), and includes a first cavity portion (44), a second cavity portion (46), and a channel (42) disposed between the first cavity portion (44) and the second cavity portion (46). A plurality of first pedestals (48) are disposed within the first cavity portion (44) adjacent the channel (42), and a plurality of second pedestals (48) are disposed within the second cavity portion (46) adjacent the channel (42). The damper (24) is selectively received within the channel (42).
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公开(公告)号：NO20045502L
公开(公告)日：2005-06-20
申请号：NO20045502
申请日：2004-12-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GREGG SHAWN J
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) includes a base (28), a tip (30), a pressure side wall (36), a suction side wall (38), and at least one cavity (40) disposed therebetween, and a channel (42). The damper (24) is selectively received within the channel (42). The channel (42) is disposed within the cavity (40) between a first wall portion (36) and a second wall portion (38). At least one of the first wall portion and the second wall portion includes a plurality of raised features (66) extending outwardly from the wall into the channel (42). The features (66) are spaced apart from one another. The raised features (66) extend between the damper (24) and the wall portion from which they extend outwardly. A plurality of tortuous flow passages (68) are formed between the damper (24), the respective wall portion, and the raised features (66) extendng therebetween. Substantially all of the tortuous passages include at least one portion that extends at least partially in a lengthwise direction and at least one portion that extends at least partially in a widthwise direction.
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公开(公告)号：CA2486988A1
公开(公告)日：2005-06-19
申请号：CA2486988
申请日：2004-11-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONGILLO DOMINIC J JR , GREGG SHAWN J
Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a roo t (18), an airfoil (20), and a damper (24). The airfoil (20) includes a base (28), a ti p (30), a pressure side wall (36), a suction side wall (38), and a cavity (40) disposed therebetween. The cavity (40) extends substantially between the base (28) and the tip (30), an d includes a first cavity portion (44), a second cavity portion (46), and a channel (42) dispos ed between the first cavity portion (44) and the second cavity portion (46). A plurality of first pedestals (48) are disposed within the first cavity portion (44) adjacent the channel (42), and a plurality of second pedestals (48) are disposed within the second cavity portion (46) adjacent the channel (42). The damper (24) is selectively received within th e channel (42).
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公开(公告)号：NO20050623D0
公开(公告)日：2005-02-04
申请号：NO20050623
申请日：2005-02-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND , GREGG SHAWN J , PROPHETER TRACY , 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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Patent Agency Ranking
公开(公告)号：DE602005000796T2
公开(公告)日：2007-08-16
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：AU2004240224B2
公开(公告)日：2007-02-08
申请号：AU2004240224
申请日：2004-12-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , GREGG SHAWN J , PROPHETER TRACY A , 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：SG116582A1
公开(公告)日：2005-11-28
申请号：SG200501576
申请日：2005-03-15
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DOMINIC MONGILLO , GREGG SHAWN J , RUTHANN MERCADANTE
IPC: F01D20060101 , F01D5/00 , F01D5/12 , F01D5/14 , F01D5/18 , F01D9/02 , F01D25/12 , F02C7/00 , F02C7/16
Abstract: A hollow airfoil (22) comprises a leading edge wall portion (42), a plurality of cavities (48,50,52), one or more crossover ribs (46), a plurality of cooling apertures (54), and a plurality of impingement apertures (56). The cavities are disposed adjacent the leading edge wall portion (42), between the leading edge wall portion (42) and a first rib (44). The crossover ribs (46) extend between the leading edge wall portion (42) and the first rib (44), and at least one crossover rib (46) is disposed between a pair of the cavities (48,50,52). The cooling apertures (54) are disposed in the leading edge wall portion (42), providing a passage through which cooling air can exit the cavities. The impingement apertures (56) are disposed in the first rib (44), providing a passage through which cooling air can enter the cavities. At least one of the impingement apertures (56) is contiguous with one of the crossover ribs (46).
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公开(公告)号：NO20051410L
公开(公告)日：2005-11-07
申请号：NO20051410
申请日：2005-03-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GREGG SHAWN J , MONGRILLO DOMINIC J , MERCADANTE RUTHANN
IPC: F01D20060101 , F01D5/00 , F01D5/12 , F01D5/14 , F01D5/18 , F01D9/02 , F01D25/12 , F02C7/00 , F02C7/16
Abstract: A hollow airfoil (22) comprises a leading edge wall portion (42), a plurality of cavities (48,50,52), one or more crossover ribs (46), a plurality of cooling apertures (54), and a plurality of impingement apertures (56). The cavities are disposed adjacent the leading edge wall portion (42), between the leading edge wall portion (42) and a first rib (44). The crossover ribs (46) extend between the leading edge wall portion (42) and the first rib (44), and at least one crossover rib (46) is disposed between a pair of the cavities (48,50,52). The cooling apertures (54) are disposed in the leading edge wall portion (42), providing a passage through which cooling air can exit the cavities. The impingement apertures (56) are disposed in the first rib (44), providing a passage through which cooling air can enter the cavities. At least one of the impingement apertures (56) is contiguous with one of the crossover ribs (46).
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公开(公告)号：SG113614A1
公开(公告)日：2005-08-29
申请号：SG200500637
申请日：2005-02-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , OTERO EDWIN , GREGG SHAWN J , PROPHETER TRACY A
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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