公开(公告)号：US20160237901A1

公开(公告)日：2016-08-18

申请号：US14745564

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Gabriel L. Suciu ,  Brian D. Merry

IPC: F02C7/141 ,  F02C7/36 ,  F02C7/32

CPC classification number: F02C6/08 ,  F02C7/143 ,  F02K3/115 ,  F05D2260/211 ,  Y02T50/676

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor includes a downstream connection that delivers discharge pressure air to an upstream location in the high pressure turbine and a second tap from an intermediate pressure location within the cooling compressor. The second tap is connected to a downstream location within the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 冷却压缩机包括下游连接，其将排出压力空气输送到高压涡轮机中的上游位置，以及从冷却压缩机内的中间压力位置输出第二分接头。 第二分接头连接到高压涡轮机内的下游位置。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

公开(公告)号：US20160195272A1

公开(公告)日：2016-07-07

申请号：US14971573

申请日：2015-12-16

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  Philip J. Kirsopp ,  David A. Litton ,  Mark F. Zelesky ,  Dennis M. Moura ,  Aaron S. Butler

IPC: F23R3/00 ,  C23C14/08 ,  C23C4/11 ,  C23C4/134 ,  F02C7/28 ,  C23C4/129 ,  C23C14/32 ,  F01D5/28 ,  F01D9/02 ,  C23C14/30 ,  C23C28/00

CPC classification number: F23R3/002 ,  C23C4/02 ,  C23C4/11 ,  C23C4/129 ,  C23C4/134 ,  C23C4/18 ,  C23C14/08 ,  C23C14/083 ,  C23C14/30 ,  C23C14/325 ,  F01D5/288 ,  F05D2230/90 ,  F23R3/007 ,  F23R2900/00018 ,  Y02E20/344 ,  Y02T50/672

Abstract: The present disclosure relates to methods for coating gas turbine engine components, such as combustor panels. In one embodiment, a method includes forming a first layer to a substrate to form a bond coat, and forming a second layer over the first layer. The second layer may be formed by a material having a thermal conductivity within the range of 4.45 to 30 Kcal/(m hoC). According to one or more embodiments, the first layer may be formed by at least one of a high velocity oxy-fuel (HVOF) source, an electric-arc source and low pressure plasma spraying. According to one or more embodiments, the second layer, and as a result a thermal barrier coating, may be formed by at least one of air plasma spraying, suspension plasma spraying, and electronic beam physical vapor deposition.

Abstract translation: 本公开涉及用于涂覆燃气涡轮发动机部件（例如燃烧器面板）的方法。 在一个实施方案中，一种方法包括将第一层形成至基底以形成粘合涂层，以及在第一层上形成第二层。 第二层可以由导热率在4.45至30Kcal /（m·hoC）范围内的材料形成。 根据一个或多个实施例，第一层可以由高速氧 - 燃料（HVOF）源，电弧源和低压等离子体喷涂中的至少一种形成。 根据一个或多个实施例，可以通过空气等离子体喷涂，悬浮等离子体喷涂和电子束物理气相沉积中的至少一种来形成第二层，并由此形成热障涂层。

公开(公告)号：US20160177733A1

公开(公告)日：2016-06-23

申请号：US14639507

申请日：2015-03-05

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Gaurav M. Patel ,  Jeffery Scott Hembree ,  San Quach ,  Mark F. Zelesky ,  David J. Candelori ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F01D5/28 ,  F01D11/08 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D5/186 ,  B23P2700/06 ,  F01D5/147 ,  F01D5/288 ,  F01D9/041 ,  F01D11/08 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/90 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/676

Abstract: A method of forming a component for use in a gas turbine engine comprises the steps of determining a desired shape for a cooling hole on a gas turbine engine component, and determining the likely deposition of a coating to be provided on the component into the cooling hole. An intermediate cooling hole is formed that has an enlarged area from the desired shape to account for deposition of the coating. The component is then coated. A component and an intermediate component for use in a gas turbine engine are also disclosed.

Abstract translation: 一种形成用于燃气涡轮发动机的部件的方法包括以下步骤：确定燃气涡轮发动机部件上的冷却孔的期望形状，以及确定要提供到部件上的涂层可能沉积到冷却孔 。 形成中间冷却孔，该中间冷却孔具有从期望形状的放大区域以解决涂层的沉积。 然后将组分涂覆。 还公开了一种用于燃气涡轮发动机的部件和中间部件。

公开(公告)号：US20160160760A1

公开(公告)日：2016-06-09

申请号：US14216014

申请日：2014-03-17

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Mark F. Zelesky

IPC: F02C7/18

CPC classification number: F02C7/18 ,  F01D11/122 ,  F05D2240/11 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine component for a gas turbine engine includes a multiple of self-opening cooling passages each of which defines a self-opening cooling passage axis that extends through a gas path surface.

Abstract translation: 用于燃气涡轮发动机的涡轮机部件包括多个自开式冷却通道，每个冷却通道限定了延伸穿过气体通道表面的自开式冷却通道轴线。

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。

公开(公告)号：US20160032416A1

公开(公告)日：2016-02-04

申请号：US14883060

申请日：2015-10-14

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Dominic J. Mongillo, Jr. ,  Matthew A. Devore ,  Steven Bruce Gautschi ,  Benjamin T. Fisk

IPC: C21D9/00 ,  B22F3/10 ,  B22F3/105 ,  B23K15/00 ,  B22F5/04

CPC classification number: B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  B22F3/1017 ,  B22F3/105 ,  B22F3/1055 ,  B22F5/04 ,  B23K15/0086 ,  B33Y10/00 ,  B33Y80/00 ,  C21D9/0068 ,  F01D5/187 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  Y02P10/292 ,  Y02P10/295

Abstract: A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. An exterior wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the exterior wall to provide an impingement cavity between the exterior wall and the impingement wall. Multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall.

Abstract translation: 一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积在彼此上。 参考与翼型的特定横截面相关的CAD数据，这些层彼此连接。 翼型件被制造成具有通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 外墙在前缘提供外部翼型表面。 冲击壁与外壁一体地形成，以在外壁和冲击壁之间提供冲击腔。 多个冲击孔设置在冲击壁上。 冲击孔横向穿过冲击壁间隔开。

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.

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/02

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。

公开(公告)号：US20150252682A1

公开(公告)日：2015-09-10

申请号：US14721223

申请日：2015-05-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sergey Mironets ,  Edward F. Pietraszkiewicz ,  Alexander Staroselsky ,  Mark F. Zelesky

IPC: F01D11/12 ,  F01D5/14

CPC classification number: F01D11/12 ,  F01D5/14 ,  F01D11/122 ,  F05D2230/236 ,  F05D2240/11 ,  Y02T50/672 ,  Y02T50/6765 ,  Y10T29/49236

Abstract: A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face.

Abstract translation: 刀片外部空气密封（BOAS）包括由金属合金制成的主体，主体包括与前部接口相对的面和后部接口，所述面包括空腔。 在空腔内的非金属插入件使得插入件与表面齐平。

公开(公告)号：US09115590B2

公开(公告)日：2015-08-25

申请号：US13627072

申请日：2012-09-26

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Mark F. Zelesky ,  Edwin Otero

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。 冷却回路设置在翼型的内部。 冷却回路包括在翼型件内径向延伸的第一芯腔。 第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。

公开(公告)号：US20140127013A1

公开(公告)日：2014-05-08

申请号：US13627072

申请日：2012-09-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Mark F. Zelesky ,  Edwin Otero

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。 冷却回路设置在翼型的内部。 冷却回路包括在翼型件内径向延伸的第一芯腔。 第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。