公开(公告)号：EP2836682B1

公开(公告)日：2018-11-14

申请号：EP13775907.2

申请日：2013-01-25

Applicant: United Technologies Corporation

Inventor： SNYDER, Daniel A. ,  LANA, Kyle, Charles ,  SANDOVAL, Jonathan, Perry ,  VIRKLER, Scott, Daniel ,  TARASKEVICH, Jaimie ,  OTERO, Edwin

IPC: F01D5/26 ,  F01D5/22 ,  F01D5/30 ,  F01D11/00

CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

公开(公告)号：EP3054103A1

公开(公告)日：2016-08-10

申请号：EP15197568.7

申请日：2015-12-02

Applicant: United Technologies Corporation

Inventor： SNYDER, Daniel A. ,  OTERO, Edwin ,  KIRONN, Lexia ,  TWELVES, Jr., Wendell V. ,  BUTCHER, Evan

IPC: F01D11/00 ,  F01D5/22 ,  F01D25/06 ,  B22F3/105 ,  B22F5/00 ,  B22F7/00 ,  B29C67/00

CPC classification number: F01D5/22 ,  B22F3/1055 ,  B22F5/009 ,  B22F7/00 ,  B29C64/153 ,  B33Y80/00 ,  F01D11/006 ,  F01D11/008 ,  F01D25/06 ,  F05D2230/22 ,  F05D2260/96 ,  Y02P10/295

Abstract: A damper-seal assembly (70) for a gas turbine engine (20) includes an additively manufactured seal (72) and an additively manufactured damper (74). The damper (74) is additively manufactured within a damper retention area (112) while the seal (72) is additively manufactured to form an inseparable assembly.

Abstract translation: 一种用于燃气涡轮发动机（20）一种阻尼器密封组件（70）包括在添加制造密封件（72），并添加制造阻尼器（74）。 所述阻尼器（74）相加，而密封件（72）相加地制造以形成不可分离组件的阻尼器保留区（112）内制成。

公开(公告)号：EP3026217A1

公开(公告)日：2016-06-01

申请号：EP15183436.3

申请日：2015-09-02

Applicant: United Technologies Corporation

Inventor： SNYDER, Daniel A. ,  CORCORAN, Christopher

IPC: F01D5/30

Abstract: A segmented sideplate for use in a gas turbine engine (20) is described. The segmented sideplate includes a first plate (100; 600) having a first circumferential edge (205) configured to interface with a complementary circumferential edge. The segmented sideplate also includes a second plate (102; 602) having a second circumferential edge (207) configured to interface with the first circumferential edge (205).

Abstract translation: 描述了用于燃气涡轮发动机（20）的分段侧板。 分段侧板包括具有第一周缘（205）的第一板（100; 600），第一圆周边缘（205）被配置为与互补圆周边缘相接合。 分段侧板还包括具有第二圆周边缘（207）的第二板（102; 602），第二圆周边缘被配置为与第一周向边缘（205）相接合。

公开(公告)号：EP2998514A3

公开(公告)日：2016-05-25

申请号：EP15178896.5

申请日：2015-07-29

Applicant: United Technologies Corporation

Inventor： SNYDER, Daniel A.

IPC: F01D5/22 ,  F01D11/00 ,  F16J15/08

CPC classification number: F01D11/006 ,  F01D5/12 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/22 ,  F16J15/0887

Abstract: A rotatable sealing structure for a gas turbine engine (20) includes a first blade (64) and a second blade (64). A seal (80) is arranged between the blades (64) and has a body (80) that is configured for operative association with the first and second blades (64) in a first orientation and in a second orientation to seal a gap (76) defined between the blades (64).

公开(公告)号：EP2998514A2

公开(公告)日：2016-03-23

申请号：EP15178896.5

申请日：2015-07-29

Applicant: United Technologies Corporation

Inventor： SNYDER, Daniel A.

IPC: F01D5/22 ,  F01D11/00 ,  F16J15/08

CPC classification number: F01D11/006 ,  F01D5/12 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/22 ,  F16J15/0887

Abstract: A rotatable sealing structure for a gas turbine engine (20) includes a first blade (64) and a second blade (64). A seal (80) is arranged between the blades (64) and has a body (80) that is configured for operative association with the first and second blades (64) in a first orientation and in a second orientation to seal a gap (76) defined between the blades (64).

Abstract translation: 一种用于燃气涡轮发动机（20）的可旋转密封结构包括第一叶片（64）和第二叶片（64）。 密封件（80）布置在叶片（64）之间并且具有主体（80），其被构造成在第一取向和第二取向上与第一和第二叶片（64）有效联接以密封间隙（76 ）限定在叶片（64）之间。