公开(公告)号：EP3036404A4

公开(公告)日：2017-03-22

申请号：EP14837668

申请日：2014-08-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  HUDSON ERIC A

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C7/042 ,  F02C7/18 ,  F04D29/58

CPC classification number: F01D17/162 ,  F01D9/065 ,  F01D11/24 ,  F01D17/16 ,  F02C7/12 ,  F05D2260/205

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.

公开(公告)号：EP2864595A4

公开(公告)日：2016-06-15

申请号：EP13833861

申请日：2013-06-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THOLEN SUSAN M ,  MONGILLO DOMINIC J ,  LUTJEN PAUL M ,  KNAPP JAMES N ,  ROSS VIRGINIA L ,  EARL JONATHAN J ,  HUDSON ERIC A

IPC: F01D11/08 ,  F01D25/12 ,  F02C7/28

CPC classification number: F01D25/12 ,  B22C9/103 ,  F01D11/08

Abstract: A hybrid sacrificial core for forming an impingement space and an internal cooling passageway network separate from the impingement space of a part may comprise a ceramic core having a first surface portion for forming the impingement space, and a refractory metal core that forms a plurality of passages of the internal cooling passageway network.

Abstract translation: 用于形成冲击空间和与部件的冲击空间分离的内部冷却通道网络的混合牺牲芯可以包括具有用于形成冲击空间的第一表面部分的陶瓷芯和形成多个通道的难熔金属芯 的内部冷却通道网络。

公开(公告)号：EP2959149A4

公开(公告)日：2016-03-23

申请号：EP14754278

申请日：2014-02-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERGE GARY D ,  CARLTON RICHARD A ,  HUDSON ERIC A

IPC: F02K3/06 ,  F02C3/107 ,  F02C7/24

CPC classification number: F02C3/073 ,  F02C3/107 ,  F02C3/14 ,  F02C7/24 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2230/52 ,  F05D2230/60 ,  Y10T29/49236

Abstract: A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed.