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公开(公告)号：US20190078785A1
公开(公告)日：2019-03-14
申请号：US15698967
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Atul Kohli , Benjamin D. Bellows , Brandon W. Spangler , David J. Hyland , Dennis M. Moura , Dustin W. Davis , Mark F. Zelesky , Ricardo Trindade , Stephen K. Kramer , Steven Bruce Gautschi , Trevor Rudy
CPC classification number: F23R3/60 , F23R3/002 , F23R3/06 , F23R3/54 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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公开(公告)号：US20160208619A1
公开(公告)日：2016-07-21
申请号：US14602035
申请日：2015-01-21
Applicant: United Technologies Corporation
Inventor： San Quach , Atul Kohli , Matthew A. Devore , Steven Bruce Gautschi
IPC: F01D5/18
Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.
Abstract translation: 提供翼型。 所述翼型件可以包括十字交叉，与所述十字架流体连通的冲击室以及设置在所述冲击室的第一表面上的第一跳闸条。 还提供冷却系统。 冷却系统可以包括冲击室，冲击室的第一表面上的第一跳闸条和在冲击室的第二表面上的第二跳闸条。 还提供内部冷却的发动机部件。 内部冷却部分可以包括与交叉流体连通的交叉和冲击室。 十字架可以构造成将空气引向冲击室的第一表面。 第一跳闸条可以设置在冲击室的第一表面上。
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公开(公告)号：US20160047251A1
公开(公告)日：2016-02-18
申请号：US14800792
申请日：2015-07-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jinquan Xu , Atul Kohli , Dominic J. Mongillo , Glenn Levasseur , Mark F. Zelesky
IPC: F01D5/18
CPC classification number: F01D5/189 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component has a cooling hole with a metering section. The metering section includes a convex surface and a concave surface, with a first arcuate channel connecting an end of the convex surface and an end of the concave surface. The end of the convex surface and the end of the concave surface define a dimension that is smaller than a diameter of the arcuate channel.
Abstract translation: 燃气涡轮发动机部件具有带计量部的冷却孔。 计量部分包括凸表面和凹表面，其中第一弧形通道连接凸表面的端部和凹表面的端部。 凸表面的端部和凹面的端部限定了小于弧形通道的直径的尺寸。
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公开(公告)号：US20150354365A1
公开(公告)日：2015-12-10
申请号：US14728514
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Wolfgang Balzer , Thomas J. Praisner , Atul Kohli , Mark F. Zelesky , Dominic J. Mongillo, JR.
Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.
Abstract translation: 用于燃气涡轮发动机的翼型件包括具有压力和吸力侧面的翼型件，其在前缘和后缘处接合。 翼型件从支撑件沿径向方向延伸跨度。 0％跨度和100％跨度位置分别对应于支撑件和末端处的翼型。 前缘和后缘在轴向上彼此间隔开一个轴向弦。 在跨距位置处的翼型件的横截面具有与压力侧和吸力侧相切的直径。 直径对应于横截面内最大的圆形配件。 直径与轴向弦的比例在50％至95％的跨度位置之间至少为0.4。
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公开(公告)号：US10690346B2
公开(公告)日：2020-06-23
申请号：US15476431
申请日：2017-03-31
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Atul Kohli , Dustin W. Davis , Ricardo Trindade , Steven Bruce Gautschi , Brandon W. Spangler , Trevor Rudy , Benjamin Bellows , Dave J. Hyland , James B. Hoke , Stephen K. Kramer , Dennis M. Moura
Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.
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Patent Agency Ranking
公开(公告)号：US10301964B2
公开(公告)日：2019-05-28
申请号：US14620727
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Atul Kohli
Abstract: One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a baffle provided in an internal cavity of the component. The baffle includes a wall having an orifice therethrough, and the baffle further includes a lobe extending from the wall and at least partially covering the orifice.
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公开(公告)号：US20180340426A1
公开(公告)日：2018-11-29
申请号：US15605458
申请日：2017-05-25
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Wolfgang Balzer , Atul Kohli
Abstract: In one embodiment, a component for a gas turbine engine is provided. The component including: an airfoil having a tip portion; a tip shelf located in the tip portion; a first plurality of cooling openings located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of a pressure side of the tip portion.
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公开(公告)号：US20180073369A1
公开(公告)日：2018-03-15
申请号：US15266855
申请日：2016-09-15
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Dominic J. Mongillo , Atul Kohli
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F04D29/083 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/303 , F05D2250/38 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges to provide an exterior airfoil surface. The pressure and suction side walls are spaced apart from one another in a thickness direction. A stagnation line is located near the leading edge. A cooling passage is provided between the pressure and suction side walls. The showerhead cooling holes are arranged at least one of adjacent to or on the stagnation line. At least one of the showerhead cooling holes has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole is arranged on each of opposing sides of the stagnation line. Each showerhead cooling hole has the diffuser with a first diffuser angle that expands downstream in the thickness direction in opposing directions from one another when separated by the stagnation line.
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公开(公告)号：US20170234151A1
公开(公告)日：2017-08-17
申请号：US15114196
申请日：2015-01-28
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Atul Kohli
IPC: F01D9/06
CPC classification number: F01D9/065 , F01D5/188 , F01D5/189 , F05D2240/127 , F05D2260/201 , F05D2260/2212 , Y02T50/676
Abstract: An engine component assembly includes at least one cavity that is in communication with a source of cooling air. An insert disposed within the cavity includes a plurality of scoops protruding into a flow of cooling air for directing cooling air through the insert and against an inner surface of the cavity.
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公开(公告)号：US20170159454A1
公开(公告)日：2017-06-08
申请号：US14961685
申请日：2015-12-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Atul Kohli
CPC classification number: F01D5/188 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/126 , F05D2240/127 , F05D2240/35 , F05D2250/14 , F05D2250/25 , F05D2260/2212 , F05D2260/22141 , F05D2260/232 , F23R3/002 , F23R3/04
Abstract: A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; and at least one rib extending upwardly from the exterior surface of the baffle insert, wherein the plurality of trip strips and the at least one rib are spaced from an interior surface of the internal cooling cavity.
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