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公开(公告)号：US10533445B2
公开(公告)日：2020-01-14
申请号：US15244203
申请日：2016-08-23
Applicant: United Technologies Corporation
Inventor： Anton G. Banks , Christopher Corcoran , Bryan P. Dube
Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.
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公开(公告)号：US10301958B2
公开(公告)日：2019-05-28
申请号：US15021945
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： Matthew Andrew Hough , Christopher Corcoran , Jeffrey S. Beattie
Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.
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公开(公告)号：US10145246B2
公开(公告)日：2018-12-04
申请号：US14820786
申请日：2015-08-07
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Yafet Girma , Christopher Corcoran
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a first reference plane extending in a spanwise direction and through a thickness of the internal wall. A first cavity and a second cavity are separated by the internal wall. A plurality of crossover passages within the internal wall connects the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The plurality of crossover passages are distributed in the spanwise direction and arranged such that the passage axis of each of the plurality of cooling passages intersects a surface of the second cavity. The plurality of crossover passages include a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane. The passage axis of each of the first set of crossover passages is arranged at a first vertical angle relative to a spanwise axis, and the passage axis of each of the second set of crossover passages is arranged at a second, different vertical angle relative to the spanwise axis. A casting core for an airfoil is also disclosed.
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公开(公告)号：US20170268365A1
公开(公告)日：2017-09-21
申请号：US15071306
申请日：2016-03-16
Applicant: United Technologies Corporation
Inventor： Christopher Corcoran , Michael G. McCaffrey , Benjamin F. Hagan
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D5/284 , F01D9/04 , F01D11/12 , F01D11/122 , F01D25/246 , F05D2230/60 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2260/30 , Y02T50/672
Abstract: A seal arc segment includes a body including a radially inner surface and a radially outer surface. The radially inner surface and the radially outer surface are located between a first circumferential end and a second circumferential end. A recessed portion defines a cavity in the radially outer surface. A notch is located in an edge of the recessed portion adjacent the first circumferential end.
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5.发明申请公开(公告)号：US20170002663A1
公开(公告)日：2017-01-05
申请号：US14790231
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： San Quach , Scott D. Lewis , Steven Bruce Gautschi , Christopher King , Christopher Corcoran , David Donald Chapdelaine
IPC: F01D5/18
CPC classification number: F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.
Abstract translation: 燃气涡轮发动机翼型件包括提供沿径向方向延伸到尖端的外部翼面表面的主体。 外表面具有向前方向的前缘和向后方的后缘。 尖端包括具有凹陷表面的尖叫口袋。 冷却通道设置在体内。 每个冷却孔从冷却通道的入口延伸到凹陷表面处的出口。 入口和出口相对于凹入表面以角度方向成一定角度布置。 角度方向朝着前后方向中的至少一个方向。
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Patent Agency Ranking
公开(公告)号：US10563525B2
公开(公告)日：2020-02-18
申请号：US15038536
申请日：2014-11-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew Andrew Hough , Christopher Corcoran , Jeffrey S. Beattie
Abstract: A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.
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公开(公告)号：US09835032B2
公开(公告)日：2017-12-05
申请号：US14727194
申请日：2015-06-01
Applicant: United Technologies Corporation
Inventor： David Richard Griffin , Zachary Mott , Christopher Corcoran , Ross Wilson , Jason D Himes
CPC classification number: F01D5/082 , F01D5/081 , F01D5/3007 , F05D2220/32 , F05D2230/12 , F05D2230/30 , F05D2240/81 , F05D2250/294 , F05D2260/20 , F05D2300/177 , Y02T50/676
Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.
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公开(公告)号：US20160376903A1
公开(公告)日：2016-12-29
申请号：US14748876
申请日：2015-06-24
Applicant: United Technologies Corporation
Inventor： Christopher Corcoran , Daniel A. Snyder
CPC classification number: F01D11/006 , F01D5/081 , F01D5/22 , F01D5/3015 , F01D11/008 , F02C7/18 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2250/72 , F05D2260/20 , F16J15/02 , Y02T50/676
Abstract: A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a first condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
Abstract translation: 用于燃气涡轮发动机的密封结构包括具有带槽的轮辋和冷却通道的转子。 转子可绕轴线转动。 第一和第二叶片布置在槽中并且分别包括在与冷却通道流体连通的凹穴内彼此面对的第一和第二搁架。 第一和第二个货架形成一个开口。 可口密封件布置在口袋内，并且具有构造成与四个取向中的任何一个中的第一和第二刀片操作关联的主体，以在第一状态下密封开口。 密封件包括分别从相对的第一和第二面延伸的第一和第二突起。 在第一状态下，第一凸起支撑在轮辋上。
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公开(公告)号：US20160333701A1
公开(公告)日：2016-11-17
申请号：US14710397
申请日：2015-05-12
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Christopher Corcoran
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2250/11 , F05D2250/13 , F05D2250/14 , F05D2250/141 , F05D2250/183 , F05D2260/201 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil having one-sided pedestals is disclosed. The airfoil may define various cavities, such as an inflow feed cavity, an impingement cavity, and an outflow cavity. The various cavities may be connected by crossover sections such as an inflow crossover section and an outflow crossover section. Cooling air may be conducted into the inflow feed cavity, out of the inflow feed cavity through an inflow crossover section into an impingement cavity, and through an impingement cavity. The cooling air may be conducted out of the impingement cavity and into an outflow cavity through an outflow crossover section. Various cavities may include one-wall pedestals. One-wall pedestals may be structures extending from a wall of a cavity into the void of the cavity, whereupon cooling air may impinge, effectuating convective cooling.
Abstract translation: 公开了具有单面基座的翼型件。 翼型件可以限定各种空腔，例如流入进料腔，冲击腔和流出腔。 各种空腔可以通过交叉部分连接，例如流入交叉部分和流出交叉部分。 冷却空气可以通过流入交叉部分进入入口进料腔，从流入进料腔中进入冲击腔，并通过冲击腔。 冷却空气可以通过流出交叉部分被从冲击腔导入流出腔。 各种空腔可以包括单壁基座。 单壁基座可以是从空腔壁延伸到空腔的结构，于是冷却空气可能会撞击，从而实现对流冷却。
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公开(公告)号：US09284845B2
公开(公告)日：2016-03-15
申请号：US14250166
申请日：2014-04-10
Applicant: United Technologies Corporation
IPC: F01D5/20
CPC classification number: F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.
Abstract translation: 翼型件包括从根部延伸到翼型的尖端部分的压力和吸力表面。 翼型件还包括在其间限定弦长的前缘和后缘。 沿着压力表面和尖端搁板壁之间的尖端部分形成尖端搁板，顶部搁板壁在压力表面和吸力表面之间分开。 沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。 尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。 尖叫口袋从前缘测量的弦长的10％范围内延伸，以终止从后缘测得的弦长的85％以下。
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