公开(公告)号：US20160032732A1

公开(公告)日：2016-02-04

申请号：US14841324

申请日：2015-08-31

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: F01D5/18 ,  B22C9/10 ,  B22C9/24 ,  B22F3/105

CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/101 ,  B22C9/24 ,  B22F3/1055 ,  B22F5/10 ,  B33Y10/00 ,  B33Y80/00 ,  C22C28/00 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2260/20 ,  F05D2300/131 ,  Y02P10/292 ,  Y02P10/295

Abstract: An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm).

Abstract translation: 用于燃气涡轮发动机的翼型包括具有通过间隔开的压力和吸力侧连接的前缘和后缘的主体，以提供由周壁限定的外部翼面。 内壁布置在周边壁的内部和附近，以在其间提供冷却通道。 具有第一和第二部分的冷却通道是锥形的并且分别具有第一和第二厚度。 第一厚度大于第二厚度。 第二厚度小于0.060英寸（1.52毫米）。

公开(公告)号：US20160025006A1

公开(公告)日：2016-01-28

申请号：US14807602

申请日：2015-07-23

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Mark F. Zelesky

IPC: F02C7/08

CPC classification number: F02C7/08 ,  F02C7/18 ,  F02C7/264 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A self-cooled orifice structure, that may be for a combustor of a gas turbine engine includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous first wall extending axially between the hot and cold side panels and spaced radially outward from a centerline. The structure may further include a first plurality of helical vanes projecting laterally, radially, inward from the first wall for flowing cooling air in a spiraling fashion through the cold side panel, then through the hot side panel.

Abstract translation: 可以用于燃气涡轮发动机的燃烧器的自冷式孔结构包括热侧板，与热侧板间隔开的冷侧板，以及在热侧板和冷侧板之间轴向延伸的连续第一壁，以及 与中心线径向向外间隔开。 该结构还可以包括从第一壁横向，径向向内突出的第一多个螺旋叶片，用于使冷却空气以螺旋方式流过冷侧面板，然后通过热侧面板。

公开(公告)号：US20160003477A1

公开(公告)日：2016-01-07

申请号：US14790970

申请日：2015-07-02

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

Abstract translation: 可以用于燃气涡轮发动机的燃烧器的自冷却孔结构，并且还可以是稀释孔结构，包括热侧板，与热侧板间隔开的冷侧板，以及连续的内壁，其延伸 在热和冷侧板之间并且限定具有中心线并且轴向地通过热和冷侧板的孔口。 该结构的多个端壁位于由冷热侧板和内壁部分限定的冷却腔中。 每个端壁在热侧面板和冷侧面板之间延伸并与之接合，并与下一个相邻的端壁沿圆周间隔开。 多个入口孔延伸穿过冷侧面板并且与空腔流体连通，并且多个入口孔中的每一个靠近多个端壁中的相应一个的第一侧。 多个出口孔延伸穿过热侧面板并且与空腔流体连通，并且多个出口孔中的每一个与多个端壁中的相应一个端壁的相对的第二侧相关联。

公开(公告)号：US20150160097A1

公开(公告)日：2015-06-11

申请号：US14564774

申请日：2014-12-09

Applicant: United Technologies Corporation

Inventor： Charles W. Haldeman ,  Andrew Consiglio ,  Mark F. Zelesky ,  Joel H. Wagner

IPC: G01M15/14 ,  G01J5/00 ,  F01D21/00

CPC classification number: G01J5/0088 ,  F01D5/284 ,  F01D5/288 ,  F01D21/003 ,  F01D21/12 ,  F05D2260/80 ,  G01J5/0022 ,  G01J5/0066 ,  G01J2005/0077

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

Abstract translation: 一种系统包括具有一个或多个检查端口的涡轮机。 LWIR传感器位于涡轮机的检查口中，以感测涡轮机组件发出的热能。 成像装置可以可操作地连接到LWIR传感器，以基于感测的热能将来自LWIR传感器的信号转换成涡轮机组件的热图像。 在一些实施例中，LWIR传感器被配置成对陶瓷涂覆的涡轮叶片进行成像。

公开(公告)号：US11268401B2

公开(公告)日：2022-03-08

申请号：US15022039

申请日：2014-08-21

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Bryan P. Dube ,  Jesse R. Christophel

IPC: F01D25/00 ,  F01D5/28 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C3/04

Abstract: An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

公开(公告)号：US11261800B2

公开(公告)日：2022-03-01

申请号：US16168943

申请日：2018-10-24

Applicant: United Technologies Corporation

Inventor： Christopher J. Hanlon ,  James F. Krenzer ,  Becky E. Rose ,  Mark F. Zelesky

IPC: F02C9/18 ,  F02C6/08 ,  F02C7/052 ,  F02C7/057 ,  F02C9/44 ,  F02K3/075 ,  F04D27/02

Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.

公开(公告)号：US11181005B2

公开(公告)日：2021-11-23

申请号：US15983904

申请日：2018-05-18

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Stephen K. Kramer

IPC: F01D11/08 ,  F01D9/04 ,  F23R3/00 ,  F01D11/00

Abstract: An assembly for a gas turbine engine includes a vane assembly having an inner platform and an airfoil section extending from the inner platform. A first combustor panel extends at least partially along the vane from upstream of the vane, and a blade outer air seal extends at least partially along the vane from downstream of the vane. The first combustor panel and the blade outer air seal define a platform gap located between a leading edge of the airfoil section of the vane and a trailing edge of the airfoil section of the vane.

公开(公告)号：US11085325B2

公开(公告)日：2021-08-10

申请号：US16033356

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D15/12 ,  F01D25/12 ,  F28F1/40 ,  F28F7/02 ,  F28D15/00 ,  F28F1/12 ,  F01D25/10 ,  F02C7/14

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US10935243B2

公开(公告)日：2021-03-02

申请号：US15365179

申请日：2016-11-30

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Randal G. McKinney

IPC: F23R3/00 ,  F02C3/04

Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.

公开(公告)号：US20210054749A1

公开(公告)日：2021-02-25

申请号：US16549187

申请日：2019-08-23

Applicant: United Technologies Corporation

Inventor： Richard Wesley Jackson ,  Adam P. Generale ,  Xuan Liu ,  Mark F. Zelesky

IPC: F01D5/28 ,  C04B35/50 ,  C04B35/48

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.