公开(公告)号：US20200032656A1

公开(公告)日：2020-01-30

申请号：US16419137

申请日：2019-05-22

Applicant: United Technologies Corporation

Inventor： San Quach ,  Alberto A. Mateo ,  Jeffrey T. Morton ,  Jason Shenny ,  Gregory Anselmi

IPC: F01D5/18

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

公开(公告)号：US20200024957A1

公开(公告)日：2020-01-23

申请号：US16239689

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Steven Bruce Gautschi

IPC: F01D5/14 ,  B22C9/10 ,  F01D5/18 ,  F01D5/28

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

公开(公告)号：US20200018188A1

公开(公告)日：2020-01-16

申请号：US16031057

申请日：2018-07-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alberto A. Mateo ,  Tracy A. Propheter-Hinckley ,  San Quach

IPC: F01D25/26 ,  F16M13/02 ,  F04D29/54 ,  F01D9/06

Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.

公开(公告)号：US10386067B2

公开(公告)日：2019-08-20

申请号：US15266036

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott A. Elliott ,  Robert M. Sonntag ,  John S. Tu ,  Anthony Van ,  Joseph J. Sedor ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Neil B. Ridgeway ,  Gerard V. Cadieux ,  Jeffrey Leon ,  Monica Pacheco-Tougas ,  Lisa A. Jenkins ,  Lisa Tse ,  Andrew Cervoni ,  Frank J. Trzcinski

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/12 ,  F23R3/44 ,  F23R3/50

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

公开(公告)号：US10370976B2

公开(公告)日：2019-08-06

申请号：US15679442

申请日：2017-08-17

Applicant: United Technologies Corporation

Inventor： San Quach ,  Alberto A. Mateo ,  Jeffrey T. Morton ,  Jason Shenny ,  Gregory Anselmi

IPC: F01D5/18

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

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：US20190055845A1

公开(公告)日：2019-02-21

申请号：US15679442

申请日：2017-08-17

Applicant: United Technologies Corporation

Inventor： San Quach ,  Alberto A. Mateo ,  Jeffrey T. Morton ,  Jason Shenny ,  Gregory Anselmi

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/52 ,  F05D2260/202

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.

公开(公告)号：US20190003316A1

公开(公告)日：2019-01-03

申请号：US15638021

申请日：2017-06-29

Applicant: United Technologies Corporation

Inventor： Jeffrey T. Morton ,  San Quach

IPC: F01D5/18

Abstract: An airfoil for a gas turbine engine may comprise an airfoil body having an outer diameter (OD) end extending between a leading edge and a trailing edge and having an ID end located opposite the airfoil body from the OD end. The airfoil body defines a helical skin cooling passage extending between the ID end of the airfoil and the OD end of the airfoil. The airfoil body may further define a main body core. The helical skin cooling passage may thermally shield the main body core.

公开(公告)号：US20180238545A1

公开(公告)日：2018-08-23

申请号：US15440739

申请日：2017-02-23

Applicant: United Technologies Corporation

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

IPC: F23R3/00 ,  F23R3/60

Abstract: A combustor for a gas turbine engine includes a support shell with an angled shell interface; 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 adjacent to the angled shell interface; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail adjacent to the angled shell interface.

公开(公告)号：US10012089B2

公开(公告)日：2018-07-03

申请号：US14704022

申请日：2015-05-05

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/20 ,  F01D5/18 ,  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 according to an exemplary aspect of the present disclosure 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 extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.