公开(公告)号：WO2014138078A1

公开(公告)日：2014-09-12

申请号：PCT/US2014/020342

申请日：2014-03-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BROOMER, Mark ,  ROY THILL, Carson A. ,  DAVIS, Timothy M. ,  CHEROLIS, Anthony P. ,  HAZZARD, Robert L. ,  MCGARRAH, Craig R. ,  CHOUNG, Conway ,  KEENE, Russell E.

IPC: F01D11/02 ,  F01D11/00 ,  F02C7/28

CPC classification number: F01D11/08 ,  F01D5/14 ,  F01D9/02 ,  F01D11/003 ,  F01D11/005 ,  F01D25/246

Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.

Abstract translation: 用于涡轮发动机的组件包括涡轮发动机第一部件，涡轮发动机第二部件和附接到第一部件的柔性密封件。 柔性密封件至少部分地密封第一部件和第二部件之间的间隙。 柔性密封件包括安装件和密封地接合第二部件的手指密封件。 安装件包括密封地接合第一部件的凸台。

公开(公告)号：WO2014160641A1

公开(公告)日：2014-10-02

申请号：PCT/US2014/031581

申请日：2014-03-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： CORCORAN, Christopher ,  CHEROLIS, Anthony P.

IPC: F01D11/00 ,  F01D11/22 ,  F02C7/28 ,  F01D5/14

CPC classification number: F01D11/008 ,  F01D5/02 ,  F01D5/147 ,  F01D11/006 ,  F01D15/12 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/97

Abstract: A turbine engine assembly arranged relative to an axis includes a rotor blade and a feather seal with an L-shaped geometry. The rotor blade includes an airfoil and a base. The airfoil extends axially between an upstream leading edge and a downstream trailing edge, and radially out from the base. The base includes a neck and a pocket. The neck extends axially to a downstream surface. The pocket extends laterally into the neck. The feather seal extends laterally into the pocket, and includes a downstream leg that extends substantially along the downstream surface.

Abstract translation: 相对于轴线布置的涡轮发动机组件包括转子叶片和具有L形几何形状的羽毛密封件。 转子叶片包括翼型件和底座。 翼型件在上游前缘和下游后缘之间轴向延伸，并从底座径向延伸。 底座包括一个颈部和一个口袋。 颈部轴向延伸到下游表面。 口袋横向延伸到颈部。 羽毛密封件横向延伸到袋中，并且包括基本沿着下游表面延伸的下游腿部。

公开(公告)号：WO2014169193A1

公开(公告)日：2014-10-16

申请号：PCT/US2014/033770

申请日：2014-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BANKS, Anton G. ,  CHEROLIS, Anthony P. ,  KASTEL, Donald

IPC: F01D9/02 ,  F01D9/04 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D11/005 ,  F01D9/02 ,  F01D9/04 ,  F01D9/041 ,  F01D9/047 ,  F01D11/00 ,  F01D11/003 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2260/20 ,  F05D2260/97

Abstract: A nozzle segment for a gas turbine engine includes an arcuate outer vane platform segment. An arcuate inner vane platform segment spaced from the arcuate outer vane platform segment. A multiple of airfoils between the arcuate inner vane platform segment and the arcuate outer vane platform segment, the arcuate outer vane platform segment includes a scallop slot and a seal that seals the scallop slot.

Abstract translation: 用于燃气涡轮发动机的喷嘴段包括弓形外叶片平台段。 与弓形外叶片平台段间隔开的弧形内叶片平台段。 弧形内叶片平台段与弧形外叶片平台段之间的多个翼型，弓形外叶片平台段包括扇贝槽和密封扇贝槽的密封。