公开(公告)号：US10107128B2

公开(公告)日：2018-10-23

申请号：US14830812

申请日：2015-08-20

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Dominic J. Mongillo, Jr. ,  Matthew A. Devore

IPC: F01D11/08 ,  F01D25/12

Abstract: A gas turbine engine component includes a wall portion and a leading edge cooling channel that extends through the wall portion. The leading edge cooling channel includes at least one first cooling passage separated from at least one serpentine cooling passage.

公开(公告)号：US10077680B2

公开(公告)日：2018-09-18

申请号：US14504719

申请日：2014-10-02

Applicant: United Technologies Corporation

Inventor： Anne-Marie B. Thibodeau ,  Bruce E. Chick ,  Thurman Carlo Dabbs ,  James N. Knapp ,  Dmitriy A. Romanov ,  Russell E. Keene ,  Jeffrey Vincent Anastas

IPC: F01D11/08 ,  F01D25/24 ,  F01D11/12

CPC classification number: F01D25/246 ,  F01D11/08 ,  F01D11/125 ,  F05D2240/11 ,  F05D2260/202

Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

公开(公告)号：US09856748B2

公开(公告)日：2018-01-02

申请号：US14625370

申请日：2015-02-18

Applicant: United Technologies Corporation

Inventor： Blaine M. Johnston ,  Mark A. Torrance ,  Steven G. Lemieux ,  Dmitriy A. Romanov

IPC: H05K7/20 ,  F01D25/12 ,  F01D11/20 ,  F01D17/02 ,  G01B21/16 ,  G01S7/02 ,  G01S13/08 ,  G01M15/14

CPC classification number: F01D25/12 ,  F01D11/20 ,  F01D17/02 ,  G01B21/16 ,  G01S7/02 ,  G01S13/08 ,  G01S2007/027 ,  Y02T50/675

Abstract: A probe cooling system for a gas turbine engine includes a probe housing and a bushing disposed between an end of the probe housing and a gas path, the bushing extending from the end of the probe housing to form a cavity. The system also includes a first plenum defined within the probe housing and configured to direct air from an internal cooling air supply towards the cavity. The system also includes a second plenum defined between the bushing and the probe housing and configured to direct air from the internal cooling air supply towards the cavity.

公开(公告)号：US20160237851A1

公开(公告)日：2016-08-18

申请号：US14625370

申请日：2015-02-18

Applicant: United Technologies Corporation

Inventor： Blaine M. Johnston ,  Mark A. Torrance ,  Steven G. Lemieux ,  Dmitriy A. Romanov

IPC: F01D25/12 ,  F01D11/02 ,  F01D25/24

CPC classification number: F01D25/12 ,  F01D11/20 ,  F01D17/02 ,  G01B21/16 ,  G01S7/02 ,  G01S13/08 ,  G01S2007/027 ,  Y02T50/675

Abstract: A probe cooling system for a gas turbine engine includes a probe housing and a bushing disposed between an end of the probe housing and a gas path, the bushing extending from the end of the probe housing to form a cavity. The system also includes a first plenum defined within the probe housing and configured to direct air from an internal cooling air supply towards the cavity. The system also includes a second plenum defined between the bushing and the probe housing and configured to direct air from the internal cooling air supply towards the cavity.

Abstract translation: 用于燃气涡轮发动机的探针冷却系统包括探针壳体和布置在探针壳体的端部与气体路径之间的衬套，衬套从探针壳体的端部延伸以形成空腔。 该系统还包括限定在探测器壳体内并被配置为将空气从内部冷却空气供应引导到空腔的第一增压室。 该系统还包括限定在衬套和探针壳体之间的第二增压室，并且构造成将来自内部冷却空气源的空气引向空腔。

公开(公告)号：US20160061113A1

公开(公告)日：2016-03-03

申请号：US14841054

申请日：2015-08-31

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Paul M. Lutjen

IPC: F02C7/18 ,  F01D25/12 ,  F01D11/08 ,  F01D9/04 ,  F02C3/04 ,  F02C7/28

CPC classification number: F02C7/18 ,  B22C9/04 ,  B22C9/10 ,  F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/204 ,  F05D2300/13 ,  Y02T50/676

Abstract: A turbine component includes a main body with an upstream end and a downstream end. A cooling passage network is interior to the main body and has multiple cooling passages. A shared passage wall in the cooling passage network includes a cross passage opening connecting each passage partially defined by the shared passage wall. The cross passage further including a pressure balancing feature operable to reduce a local pressure differential in a fluid pressure in each adjacent passage at the cross passage.

Abstract translation: 涡轮机部件包括具有上游端和下游端的主体。 冷却通道网络在主体的内部并且具有多个冷却通道。 冷却通道网络中的共用通道壁包括连接由共用通道壁部分限定的每个通道的横向通道开口。 十字通道还包括压力平衡特征，其可操作以减少交叉通道中每个相邻通道中的流体压力的局部压力差。