公开(公告)号：US20160024952A1

公开(公告)日：2016-01-28

申请号：US14774025

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jorge I. Farah ,  Andrew D. Burdick

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

Abstract: An assembly for a turbine engine includes a case, a guide vane arrangement and a flexible seal ring. The case extends circumferentially around an axis, and includes a first seal land. The guide vane arrangement is located radially within the case, and includes a second seal land. The seal ring at least partially seals a gap between the first seal land and the second seal land. The seal ring includes a first leg and a second leg that is connected to the first leg at a corner of the seal ring. The first leg is axially engaged with the first seal land. The second leg is axially engaged with the second seal land.

Abstract translation: 用于涡轮发动机的组件包括壳体，导向叶片装置和柔性密封环。 壳体围绕轴线周向延伸，并且包括第一密封区域。 引导叶片装置径向位于壳体内，并包括第二密封区域。 密封环至少部分地密封第一密封区域和第二密封区域之间的间隙。 密封环包括第一腿部和第二腿部，该第一腿部和第二腿部在密封环的角部处连接到第一腿部。 第一腿部与第一密封区域轴向接合。 第二腿部与第二密封区域轴向接合。

公开(公告)号：US10598036B2

公开(公告)日：2020-03-24

申请号：US14774025

申请日：2014-03-12

Applicant: United Technologies Corporation

Inventor： Jorge I. Farah ,  Andrew D. Burdick

IPC: F01D11/00 ,  F01D25/24 ,  F02C7/28 ,  F01D9/02

Abstract: An assembly for a turbine engine includes a case, a guide vane arrangement and a flexible seal ring. The case extends circumferentially around an axis, and includes a first seal land. The guide vane arrangement is located radially within the case, and includes a second seal land. The seal ring at least partially seals a gap between the first seal land and the second seal land. The seal ring includes a first leg and a second leg that is connected to the first leg at a corner of the seal ring. The first leg is axially engaged with the first seal land. The second leg is axially engaged with the second seal land.

公开(公告)号：US20190040796A1

公开(公告)日：2019-02-07

申请号：US15668135

申请日：2017-08-03

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Andrew D. Burdick

IPC: F02C7/18 ,  F23R3/00 ,  F01D5/18 ,  F01D25/24 ,  F01D25/14 ,  F28F3/02

Abstract: A gas turbine engine cooling arrangement includes a component and a pedestal. The component of a gas turbine engine has a first surface and a second surface disposed opposite the first surface. The pedestal is disposed on the second surface. The pedestal has an outer surface extending along a first axis away from the second surface between a pedestal base and a pedestal top. A first lobe is defined by the outer surface and extends along an axis that is disposed parallel to the first axis.

公开(公告)号：US10012090B2

公开(公告)日：2018-07-03

申请号：US14804865

申请日：2015-07-21

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder ,  Andrew D. Burdick

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2250/322 ,  F05D2260/2212 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall.

公开(公告)号：US09803559B2

公开(公告)日：2017-10-31

申请号：US14615665

申请日：2015-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew D. Burdick ,  Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Hudson ,  Michael G. McCaffrey

IPC: F02C3/04 ,  F02C9/20 ,  F01D5/14 ,  F01D11/02 ,  F01D17/16 ,  F01D9/02

CPC classification number: F02C9/20 ,  F01D5/148 ,  F01D9/02 ,  F01D11/025 ,  F01D17/162 ,  F02C3/04 ,  F05D2240/122 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T137/0536

Abstract: One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion.

公开(公告)号：US20170241281A1

公开(公告)日：2017-08-24

申请号：US15052457

申请日：2016-02-24

Applicant: United Technologies Corporation

Inventor： Christopher Treat ,  Nicholas W. Kantany ,  Andrew D. Burdick ,  Michael C. Pezzetti, JR.

IPC: F01D11/00 ,  F16J9/24

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/246 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/58 ,  F05D2260/30 ,  F05D2260/36 ,  F16J9/24 ,  F16J15/3272 ,  Y02T50/671

Abstract: A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.

公开(公告)号：US20160177736A1

公开(公告)日：2016-06-23

申请号：US14804424

申请日：2015-07-21

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder ,  Andrew D. Burdick

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/306 ,  F05D2250/314 ,  F05D2260/201 ,  Y02T50/676

Abstract: An airfoil structure for a gas turbine engine includes an airfoil that includes a suction side cooling circuit with at least two segments that are connected by at least one impingement passage.

Abstract translation: 用于燃气涡轮发动机的翼型结构包括一个翼型件，其包括具有至少两个段的吸入侧冷却回路，所述至少两个段由至少一个冲击通道连接。