公开(公告)号：EP3084178B1

公开(公告)日：2018-03-28

申请号：EP14871637.6

申请日：2014-12-08

Applicant: United Technologies Corporation

Inventor： CLARKSON, Steven ,  BERGETHON, Richard B.

IPC: F02C7/05

CPC classification number: F04D29/526 ,  F01D21/045 ,  F02C7/045 ,  F02C7/05 ,  F02K3/06 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672

Abstract: A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.

公开(公告)号：EP3084178A1

公开(公告)日：2016-10-26

申请号：EP14871637.6

申请日：2014-12-08

Applicant: United Technologies Corporation

Inventor： CLARKSON, Steven ,  BERGETHON, Richard B.

IPC: F02C7/05

CPC classification number: F04D29/526 ,  F01D21/045 ,  F02C7/045 ,  F02C7/05 ,  F02K3/06 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672

Abstract: A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.

Abstract translation: 一种用于燃气涡轮发动机的衬里的衬里组件包括具有至少两个轴向相邻段的蜂窝芯，该蜂窝芯包括前段和后段。 耐冲击层靠着蜂窝状前段并径向向内布置。 在耐冲击层和尾部段的至少一部分上限定相对基本上不中断的流动路径的径向内部层抵靠耐冲击层和蜂窝尾部段并在径向内部延伸。

公开(公告)号：EP3058198A1

公开(公告)日：2016-08-24

申请号：EP14853438.1

申请日：2014-05-23

Applicant: United Technologies Corporation

Inventor： KLING, Colin J. ,  CLARKSON, Steven

IPC: F02C7/04 ,  F02C7/20 ,  F01D5/02 ,  B64C11/14

CPC classification number: F02C7/04 ,  B64C11/14 ,  F01D5/066 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/31 ,  F05D2260/37

Abstract: A nose cone may have a spinner including a main portion and an axially extending stepped portion. The nose cone may also have an annular aft support ring radially secured to the axially extending stepped portion. The nose cone may further include a fairing, which may be secured to the stepped portion.

Abstract translation: 鼻锥可以具有包括主要部分和轴向延伸的阶梯部分的旋转器。 鼻锥体还可以具有径向固定到轴向延伸的阶梯部分的环形后支撑环。 鼻锥可以进一步包括可以固定到阶梯部分的整流罩。

公开(公告)号：EP3034835A1

公开(公告)日：2016-06-22

申请号：EP15200195.4

申请日：2015-12-15

Applicant: United Technologies Corporation

Inventor： CLARKSON, Steven ,  VAN NESS, Daniel L. ,  REMBISH, Paul Thomas

IPC: F02C7/047 ,  F02C9/18 ,  F01D17/10 ,  F04D27/02

CPC classification number: F01D25/10 ,  F01D17/105 ,  F01D25/02 ,  F01D25/18 ,  F01D25/24 ,  F02C7/047 ,  F02C9/18 ,  F04D27/0215 ,  F04D29/522 ,  F04D29/584 ,  F04D29/5853 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/4031 ,  Y02T50/675

Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.

Abstract translation: 用于燃气涡轮发动机的壳体包括限定轴向延伸的芯流动路径的壳体主体，连接与外部环境流体连通的芯流动路径的径向延伸的放气管道，以及横跨排气管道的结构支撑构件。 润滑剂管道连接到壳体并且与结构支撑构件热连通。

公开(公告)号：EP3034814A1

公开(公告)日：2016-06-22

申请号：EP15200081.6

申请日：2015-12-15

Applicant: United Technologies Corporation

Inventor： CLARKSON, Steven ,  ROBERTSON, Thomas J. JR.

IPC: F01D21/04 ,  F01D25/24 ,  F02K3/06

CPC classification number: F01D25/24 ,  F01D21/045 ,  F01D25/005 ,  F02K3/06 ,  F05D2230/60 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2300/603 ,  Y02T50/672

Abstract: A method of making a liner (100; 200) for a turbomachinery case (26) includes overlaying a reinforcing layer (102; 202, 204) and a release layer (104; 206). The method also includes spiral coiling the reinforcing layer and the release layer about an axis (A) of the liner such that a radially inner surface (112) of the release layer radially overlays a radially outer surface (108) of the reinforcing layer.

Abstract translation: 制造用于涡轮机械壳体（26）的衬套（100; 200）的方法包括覆盖加强层（102; 202,204）和释放层（104; 206）。 该方法还包括围绕衬套的轴线（A）螺旋卷绕加强层和释放层，使得脱模层的径向内表面（112）径向覆盖加强层的径向外表面（108）。

公开(公告)号：EP2904214A1

公开(公告)日：2015-08-12

申请号：EP13844100.1

申请日：2013-02-22

Applicant: United Technologies Corporation

Inventor： ROBERTSON, Thomas J. ,  VOLETI, Sreenivasa R. ,  COSTA, Mark W. ,  CLARKSON, Steven

IPC: F01D5/28 ,  F01D5/14 ,  F02C7/00 ,  F02K3/00

CPC classification number: F01D25/24 ,  F01D5/021 ,  F01D5/147 ,  F01D5/28 ,  F01D21/045 ,  F01D25/30 ,  F05D2220/30 ,  F05D2240/24 ,  F05D2250/283 ,  F05D2300/121 ,  F05D2300/173 ,  F05D2300/612 ,  Y02T50/672

Abstract: A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.