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公开(公告)号：JP2003269384A
公开(公告)日：2003-09-25
申请号：JP2003061211
申请日：2003-03-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： STAUBACH J BRENT , WAGNER JOEL H , AGGARWALA ANDREW S
Abstract: PROBLEM TO BE SOLVED: To provide an end wall having a nonaxissymmetric trough for reducing an interference loss between a shock wave and an end wall. SOLUTION: An end wall shape reducing shock wave power in transonic turbine machine airfoil, includes the nonaxissymmetric trough 30 extending up to a point in the vicinity of a rear edge part of at least one flow passage 24 from a front part of at least the one flow passage 24. COPYRIGHT: (C)2003,JPO
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公开(公告)号：JP2002364305A
公开(公告)日：2002-12-18
申请号：JP2002137990
申请日：2002-05-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KOHLI ATUL , WAGNER JOEL H , AGGARWALA ANDREW S
Abstract: PROBLEM TO BE SOLVED: To provide a film cooling system with high cost performance for facilitating the sideways expansion and secure adhesion of a cooling jet 70 over a high temperature face 24 of an article. SOLUTION: The article having a wall with the high temperature face 24 such as a blade or vane of a turbine engine comprises a recess 48 characterized by a descending side face 52 and an ascending side face 54. A cooling hole 6 bored on the wall 24 includes an outlet located on the ascending side face 54. When the article is operated, the cooling jet 70 is discharged from the outlet and a primary fluid flow F flowing on the ascending side face 54 is locally over-accelerated by the recess 48. The local over-acceleration of the primary fluid flow F turns the cooling jet 70 to flow on the high temperature face 24 to facilitate sideways expansion of the jet and formation of a protective cooling film continuing sideways together with the expanded jet.
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公开(公告)号：WO2015147930A3
公开(公告)日：2015-11-26
申请号：PCT/US2014071582
申请日：2014-12-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAKKA PITCHAIAH VIJAY , AGGARWALA ANDREW S , PRAISNER THOMAS J , SPANGLER BRANDON W
CPC classification number: F01D25/12 , F01D5/12 , F01D5/145 , F01D9/02 , F02C3/04 , F05D2220/323 , F05D2240/35 , F05D2240/81 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.
Abstract translation: 翼型组件在至少一个平台的后边缘中具有至少一个冷却孔，用于冷却轴向下游的翼型根部和/或尖端区域中的至少一个。 翼型组件可以是与以低模式因子操作的燃烧器相连的高压涡轮机第一级叶片。
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公开(公告)号：WO2013130181A3
公开(公告)日：2015-06-11
申请号：PCT/US2013020962
申请日：2013-01-10
Applicant: UNITED TECHNOLOGIES CORP , AGGARWALA ANDREW S , PRAISNER THOMAS J
Inventor： AGGARWALA ANDREW S , PRAISNER THOMAS J
IPC: F01D5/30
CPC classification number: F01D5/143 , F05D2240/80 , F05D2260/60 , Y02T50/673
Abstract: An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.
Abstract translation: 翼型平台包括前缘部分和后缘部分。 后缘部分包括具有凸形流路轮廓的第一区域，具有从凸形流路轮廓的下游延伸的中间流路轮廓的第二区域以及具有从中间流路轮廓向下延伸的凹或线性流路轮廓的第三区域 平台的后缘部分的下游端。
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公开(公告)号：WO2015130254A3
公开(公告)日：2015-12-17
申请号：PCT/US2013068039
申请日：2013-11-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZELESKY MARK F , AGGARWALA ANDREW S
CPC classification number: F01D5/20 , Y02T50/673
Abstract: A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.
Abstract translation: 涡轮翼型件包括吸入侧壁，压力侧壁，末端壁和末端泄漏控制通道。 每个侧壁从翼型基部沿弦向在前缘和后缘之间沿翼展方向延伸。 尖端壁从前缘沿着弦向延伸到后缘并且连接吸入和压力侧壁的相应的外部翼展方向端部。 尖端泄漏控制通道具有入口和出口，凹入到尖端壁的外表面中。 通道的入口开始靠近翼型压力侧壁和顶壁的接合处。 通道的出口终止于末端壁和吸入侧壁的接合处的凹入部分。
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Patent Agency Ranking
公开(公告)号：WO2014074190A3
公开(公告)日：2014-07-17
申请号：PCT/US2013054944
申请日：2013-08-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRAISNER THOMAS J , AGGARWALA ANDREW S , NASH TIMOTHY CHARLES , ALLEN-BRADLEY EUNICE , GROVER ERIC A
CPC classification number: F01D9/02 , F01D5/143 , F01D5/145 , F04D29/324 , F04D29/542 , F04D29/681 , Y02T50/673
Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.
Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上周向间隔开，从而在相邻翼型之间限定多个流动通道。 翼型阵列还可以包括凸出的轮廓区域，该凸形轮廓区域从靠近所述多个翼型件中的至少一个的前缘的所述多个翼型件中的至少一个的第一侧面的端壁延伸，并且在所述多个翼型件中的凹形轮廓区域 并且延伸穿过所述多个流动通道中的所述至少一个。
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公开(公告)号：WO2015112273A2
公开(公告)日：2015-07-30
申请号：PCT/US2014069424
申请日：2014-12-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZELESKY MARK F , AGGARWALA ANDREW S
IPC: F01D5/18
CPC classification number: F01D5/20 , F05D2240/126 , F05D2260/205 , Y02T50/673 , Y02T50/676
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel.
Abstract translation: 除了别的之外，根据本公开的示例性方面的翼型包括吸入侧壁和压力侧壁，每个侧壁从翼型基部沿翼展方向延伸并且在前缘和后缘之间沿弦向延伸。 尖端壁从前缘向后缘弦向延伸并且连接吸入和压力侧壁的相应的外部翼展方向端部。 尖端泄漏控制通道凹入尖端壁中，尖端泄漏控制通道包括在第一控制通道叶片侧壁与由相应尖端泄漏控制叶片建立的第二控制通道叶片侧壁之间延伸的控制通道底板。 内部冷却腔设置在吸入侧壁和压力侧壁之间，并且通道冷却孔将来自内部冷却腔的气流供给到尖端泄漏控制通道。
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公开(公告)号：WO2014070279A3
公开(公告)日：2014-07-10
申请号：PCT/US2013054949
申请日：2013-08-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AGGARWALA ANDREW S , GROVER ERIC A
CPC classification number: F01D5/143 , F04D29/321 , F04D29/681 , F05D2240/303 , F05D2240/80 , F05D2250/711 , F05D2250/712 , Y02T50/673
Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages.
Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁，以及从端壁径向突出的多个翼型件。 每个翼型可以具有在前缘和后缘之间沿弦轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上沿圆周间隔开，从而在相邻翼型件之间限定多个流动通道。 翼型阵列可进一步包括从靠近所述多个翼型件中的至少一个的前缘的端壁和靠近所述多个流动通道中的至少一个的中间的端壁中的凹形轮廓区域延伸的凸形轮廓区域。
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公开(公告)号：WO2014070280A3
公开(公告)日：2014-06-26
申请号：PCT/US2013054953
申请日：2013-08-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： PRAISNER THOMAS J , AGGARWALA ANDREW S , GROVER ERIC A , JUREK RENEE J
CPC classification number: F01D5/145 , F01D5/143 , F04D29/324 , F04D29/329 , F04D29/547 , F04D29/681 , F05D2240/123 , F05D2240/305 , F05D2250/712 , Y02T50/673
Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.
Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间沿弦向轴向延伸的第一侧和相对的第二侧。 翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。 翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和凸形轮廓区域的后端的端壁中的凹形轮廓区域。
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公开(公告)号：GB2388162B
公开(公告)日：2004-11-24
申请号：GB0305320
申请日：2003-03-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： STAUBACH J BRENT , WAGNER JOEL H , AGGARWALA ANDREW S
Abstract: The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trailing edge portion of the at least one flow passage.
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