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公开(公告)号:WO2014099077A3
公开(公告)日:2014-09-04
申请号:PCT/US2013061704
申请日:2013-09-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor: GREGG SHAWN J , OTERO EDWIN
CPC classification number: F02C3/14 , F23R3/28 , F23R3/50 , F23R2900/00014
Abstract: A gas turbine engine includes a multiple of Nozzle Guide Vanes (NGVs) arranged asymmetrically and a multiple of NGVs clocked with respect to the multiple of fuel nozzles around a 360 degree circumference.
Abstract translation: 燃气涡轮发动机包括多个不对称布置的喷嘴引导叶片(NGV)和多个围绕360度圆周相对于多个燃料喷嘴计时的NGV。
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公开(公告)号:WO2013172903A3
公开(公告)日:2014-01-09
申请号:PCT/US2013027232
申请日:2013-02-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor: LEVINE JEFFREY R , GREGG SHAWN J
CPC classification number: F01D5/188 , Y02T50/676
Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.
Abstract translation: 翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面,并且从根部到尖端部分径向延伸,根部和末端部分限定了它们之间的跨度。 热涂层从翼型的根部朝向翼型的末端部分延伸。 与根部中的最小跨度相比,热涂层的相对涂层厚度在末端部分的全跨度处降低至少30%。
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公开(公告)号:WO2014028095A2
公开(公告)日:2014-02-20
申请号:PCT/US2013044032
申请日:2013-06-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor: LUTJEN PAUL M , GREGG SHAWN J , DABBS THURMAN CARLO , BLANEY KEN F , KEENE RUSSELL E , CHICK BRUCE E
CPC classification number: F01D11/08 , F01D1/02 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括壁,前钩和后钩。 该壁在前钩和后钩之间延伸,其适于将叶片外部空气密封件安装到燃气涡轮发动机的壳体上。 壁包括沿壁的至少一部分延伸的芯通道。 芯通道径向和轴向地延伸穿过后钩的一部分,以沿着后钩的后缘与一个或多个孔连通。
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公开(公告)号:WO2014105236A3
公开(公告)日:2014-08-21
申请号:PCT/US2013061857
申请日:2013-09-26
Applicant: UNITED TECHNOLOGIES CORP , RILEY SARAH , BOEKE MARK A , DEGRAY JEFFREY J , GREGG SHAWN J
Inventor: RILEY SARAH , BOEKE MARK A , DEGRAY JEFFREY J , GREGG SHAWN J
CPC classification number: F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个人字形的跳闸条从一个表面延伸到冷却通道中,沿一个长度的跳闸条高度。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部提供,所述第一和第二径向延伸的腿部彼此周向地间隔开并且通过周向通道彼此连接。 一对翼型件从相同的内平台径向延伸。 跳闸带沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 跳闸条高度沿长度变化。
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5.
公开(公告)号:WO2014099075A3
公开(公告)日:2014-08-21
申请号:PCT/US2013061699
申请日:2013-09-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor: GREGG SHAWN J , LOW KEVIN J
CPC classification number: F02C3/14 , F23R3/28 , F23R3/50 , F23R2900/00014
Abstract: A combustor of a gas turbine engine includes a multiple of fuel nozzles arranged asymmetrically.
Abstract translation: 燃气涡轮发动机的燃烧器包括不对称排列的多个燃料喷嘴。
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公开(公告)号:DE602005008311D1
公开(公告)日:2008-09-04
申请号:DE602005008311
申请日:2005-05-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor: MONGILLO JR DOMINIC J , LEVINE JEFFREY R , GREGG SHAWN J , PIETRASZKIEWICZ EDWARD
Abstract: A rotor blade (14) is provided that includes a root (20) and a hollow airfoil (22). The hollow airfoil (22) has a cavity defined by a suction side wall (38), a pressure side wall (36), a leading edge (32), a trailing edge (34), a base (28), and a tip (30). An internal passage configuration (40) is disposed within the cavity. The configuration includes a passage (50) disposed adjacent the leading edge (32), and an axially extending passage (52) disposed adjacent the tip (30). The first passage (50) is connected to the second passage (52). The second passage (52) includes an opening disposed at the trailing edge (34) of the airfoil. A conduit (42) is disposed within the root (20) that is operable to permit airflow through the root (20) and into the leading edge passage (50), wherein the conduit (42) provides the primary path into the leading edge passage (42).
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公开(公告)号:NO20051410A
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
CPC classification number: F01D5/187 , F05D2250/70 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
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公开(公告)号:CA2500503A1
公开(公告)日:2005-11-06
申请号:CA2500503
申请日:2005-03-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor: GREGG SHAWN J , MERCADANTE RUTHANN , MONGILLO DOMINIC J
IPC: F01D20060101 , F01D5/00 , F01D5/12 , F01D5/14 , F01D5/18 , F01D9/02 , F01D25/12 , F02C7/00 , F02C7/16
Abstract: According to the present invention, a hollow airfoil is provided that comprises a leading edge wall portion, a plurality of cavities, one or more crossover ribs, a plurality of cooling apertures, and a plurality of impingement ribs. The cavities are disposed adjacent the leading edge wall portion, between the leading edge wall portion and a first rib. The crossover ribs extend between the leading edge wall portion and the first ri b, and at least one crossover rib is disposed between a pair of the cavities. The cooling apertures are disposed in the leading edge wall portion, providing a passage through which cooling air can exit the cavities. The impingement apertures are disposed in the first rib, providing a passage through which cooling air can enter the cavities. At least one of th e impingement apertures is contiguous with one of the crossover ribs.
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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:NO20045502A
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
CPC classification number: F01D5/187 , F01D5/16 , F01D5/189 , F01D5/26 , F05D2240/126 , F05D2260/22141 , Y10S416/50
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