公开(公告)号：US10316668B2

公开(公告)日：2019-06-11

申请号：US14765390

申请日：2014-01-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mosheshe Camara-Khary Blake ,  Lisa K. Osborne ,  Thomas N. Slavens

IPC: F01D5/14 ,  F01D5/18 ,  F01D9/06 ,  F01D25/08

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall that forms a portion of an outer periphery of at least one cavity and at least one curved turbulator that extends from said wall.

公开(公告)号：US10247099B2

公开(公告)日：2019-04-02

申请号：US15023010

申请日：2014-10-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Thomas N. Slavens

IPC: F01D5/18 ,  F02C7/18 ,  F01D25/12

Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

公开(公告)号：US10240464B2

公开(公告)日：2019-03-26

申请号：US15035837

申请日：2014-11-05

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F01D9/02 ,  F01D5/18 ,  F01D25/12

Abstract: A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.

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：US20180334909A1

公开(公告)日：2018-11-22

申请号：US16048466

申请日：2018-07-30

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Joel H. Wagner ,  Thomas N. Slavens

IPC: F01D5/18 ,  F23R3/00 ,  B22F3/105 ,  B23P15/26 ,  F01D5/14 ,  F02C7/18 ,  F01D25/24 ,  F01D25/12 ,  F01D25/08 ,  F01D11/08 ,  F01D9/02 ,  B33Y80/00 ,  B33Y70/00 ,  B33Y10/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.

公开(公告)号：US20180298820A1

公开(公告)日：2018-10-18

申请号：US16010864

申请日：2018-06-18

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F02C7/12 ,  F01D25/12 ,  F01D9/02 ,  F01D9/04 ,  F01D25/08

Abstract: A variable vane pack includes an inner platform, an outer platform, radially outward of the inner platform, a plurality of vanes connecting the inner platform to the outer platform, wherein the outer platform comprises a platform body and an impingement plate, the impingement plate having a radially inward impingement plate, a radially outward pressure distribution plate, and an impingement plenum defined between the radially inward impingement plate and the radially outward pressure distribution plate.

公开(公告)号：US10066549B2

公开(公告)日：2018-09-04

申请号：US14706033

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F02C7/12 ,  F01D9/04 ,  F01D9/02 ,  F01D25/08 ,  F01D25/12

Abstract: A variable vane pack includes an inner platform, an outer platform, radially outward of the inner platform, a plurality of vanes connecting the inner platform to the outer platform, wherein the outer platform comprises a platform body and an impingement plate, the impingement plate having a radially inward impingement plate, a radially outward pressure distribution plate, and an impingement plenum defined between the radially inward impingement plate and the radially outward pressure distribution plate.

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：US09932835B2

公开(公告)日：2018-04-03

申请号：US14698269

申请日：2015-04-28

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Thomas J. Martin ,  Brooks E. Snyder

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2220/30 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2250/25 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/2212

Abstract: An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage.

公开(公告)号：US20170234447A1

公开(公告)日：2017-08-17

申请号：US15042985

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： Timothy J. Jennings ,  Thomas N. Slavens

IPC: F16K31/00 ,  F03G7/06 ,  F02C3/04

CPC classification number: F16K31/002 ,  F01D5/08 ,  F01D5/18 ,  F02C3/04 ,  F02C7/12 ,  F03G7/065 ,  F05D2300/505 ,  Y02T50/676

Abstract: Methods and systems for modulating airflow may include a metering device comprising a face, an aperture through the face being defined by an aperture rim, and a metering appendage disposed adjacent to the aperture and coupled to the aperture rim and/or the face. The metering appendage may comprise a shape memory alloy and may be configured to transition from a first geometry to a second geometry.