公开(公告)号：US20180306113A1

公开(公告)日：2018-10-25

申请号：US15491047

申请日：2017-04-19

Applicant: United Technologies Corporation

Inventor： Jeffrey T. Morton ,  San Quach

IPC: F02C7/18 ,  F23R3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A combustor section of a turbine engine includes a first liner panel including a first end rail. The first end rail includes a protruding heat transfer feature. A second liner panel includes a second end rail disposed proximate the first end rail. The second end rail includes a recess matching the protruding heat transfer feature of the first end rail. A turbine engine and a method of assembling a combustor assembly of a gas turbine engine are also disclosed.

公开(公告)号：US20180283695A1

公开(公告)日：2018-10-04

申请号：US15477926

申请日：2017-04-03

Applicant: United Technologies Corporation

Inventor： San Quach ,  Robert M. Sonntag ,  Donald W. Peters

IPC: F23R3/60 ,  F23R3/00

Abstract: A gas turbine engine and a combustor panel assembly are disclosed. The gas turbine engine includes a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.

公开(公告)号：US20180274373A1

公开(公告)日：2018-09-27

申请号：US15995884

申请日：2018-06-01

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.

公开(公告)号：US20180238179A1

公开(公告)日：2018-08-23

申请号：US15440677

申请日：2017-02-23

Applicant: United Technologies Corporation

Inventor： San Quach ,  Jeffrey T. Morton ,  Matthew D. Parekh

IPC: F01D9/02 ,  F23R3/00 ,  F23R3/14 ,  F27D1/00 ,  F27D99/00 ,  F23M5/04 ,  F23M5/08

Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.

公开(公告)号：US10041358B2

公开(公告)日：2018-08-07

申请号：US14696601

申请日：2015-04-27

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  San Quach

IPC: F01D5/18 ,  F01D5/20

Abstract: A blade for a gas turbine engine includes an airfoil having a tip with a terminal end surface and multiple squealer pockets recessed into the terminal end surface. A method of cooling a blade includes the steps of providing cooling fluid to a first squealer pocket in an airfoil tip, and providing cooling fluid to a second squealer pocket in the airfoil tip in an amount that is different than that provided to the first squealer pocket.

公开(公告)号：US20180209287A1

公开(公告)日：2018-07-26

申请号：US15416900

申请日：2017-01-26

Applicant: United Technologies Corporation

Inventor： Jeffrey T. Morton ,  San Quach

IPC: F01D9/06 ,  F02C3/04

CPC classification number: F01D9/065 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/323 ,  F05D2250/324 ,  F05D2260/204 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component of a gas turbine engine is provided. The component may include an external surface with a skin cavity adjacent the external surface. The skin cavity may be defined by a hot-side surface and a cool-side surface with the hot-side surface between the cool-side surface and the external surface. A flat portion may be disposed on the hot-side surface and may, for example, define a wall-thickness check region. A protrusion may be disposed on the cool-side surface opposite the flat portion on the hot-side surface. The hot-side surface and the cool-side surface may tend to increase a heat transfer coefficient along the flat portion of the hot-side surface, which may also define a wall thickness check region.

公开(公告)号：US09976444B2

公开(公告)日：2018-05-22

申请号：US15196091

申请日：2016-06-29

Applicant: United Technologies Corporation

Inventor： Fred NguyenLoc ,  San Quach

IPC: F01D25/18 ,  F01D15/12 ,  F01D25/24 ,  F16H57/04 ,  F16N31/02

CPC classification number: F01D25/18 ,  F01D15/12 ,  F01D25/24 ,  F05D2260/602 ,  F16H57/0409 ,  F16H57/0423 ,  F16H57/0441 ,  F16H57/045 ,  F16N31/02

Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.

公开(公告)号：US09976423B2

公开(公告)日：2018-05-22

申请号：US14862422

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： San Quach ,  Christopher King ,  Steven Bruce Gautschi ,  David J. Candelori

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.

公开(公告)号：US20180038593A1

公开(公告)日：2018-02-08

申请号：US15228029

申请日：2016-08-04

Applicant: United Technologies Corporation

Inventor： San Quach ,  Brian T. Hazel ,  Kaitlin M. Tomeo ,  Robert Selinsky, JR. ,  Aaron S. Butler ,  John S. Tu ,  William F. Werkheiser ,  Jessica L. Serra

IPC: F23R3/00 ,  F02C3/04 ,  F02C7/24

Abstract: A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.

公开(公告)号：US20170335692A1

公开(公告)日：2017-11-23

申请号：US15159890

申请日：2016-05-20

Applicant: United Technologies Corporation

Inventor： Christopher King ,  Tracy A. Propheter-Hinckley ,  San Quach

IPC: F01D5/18 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F01D25/08

CPC classification number: F01D5/187 ,  B22C9/103 ,  F01D9/02 ,  F01D25/08 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2260/202 ,  F05D2300/13

Abstract: Refractory metal cores for manufacturing components of gas turbine engines, manufactured components, and related methods are provided. A refractory metal core includes a trunk configured to attach to a cavity core structure, a first branch extending from the trunk and configured to form a first portion of a cooling circuit in the component, and a second branch extending from the trunk and configured to form a second portion of the cooling circuit in the component. The first branch and the second branch are configured to define fluid exits at two different locations on an exterior of the component.