公开(公告)号：US11473444B2

公开(公告)日：2022-10-18

申请号：US16677760

申请日：2019-11-08

Applicant: United Technologies Corporation

Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach

IPC: F01D25/12 ,  F01D9/02 ,  F01D5/28 ,  F01D5/18 ,  F01D9/06 ,  F01D11/00

Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.

公开(公告)号：US20210148245A1

公开(公告)日：2021-05-20

申请号：US16686540

申请日：2019-11-18

Applicant: United Technologies Corporation

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

IPC: F01D11/10 ,  F01D25/14

Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.

公开(公告)号：US20210140341A1

公开(公告)日：2021-05-13

申请号：US16677760

申请日：2019-11-08

Applicant: United Technologies Corporation

Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach

IPC: F01D25/12 ,  F01D9/02

Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.

公开(公告)号：US20200348023A1

公开(公告)日：2020-11-05

申请号：US16402707

申请日：2019-05-03

Applicant: United Technologies Corporation

Inventor： Corneil S. Paauwe ,  Eva Wong ,  San Quach ,  Jeremy Styborski ,  Caroline Karanian ,  Lauryn M. Curtis ,  Steven D. Porter ,  Zhongtao Dai

IPC: F23R3/00 ,  F23R3/04 ,  F02C7/18

Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface opposite the first surface of the second component; and a cooling circuit formed in the second component, the cooling circuit including an inlet at the second surface of the second component, an outlet at the first surface of the second component, an inward surface, and an outward surface, the inward surface and the outward surface being in a facing spaced relationship extending from the inlet to the outlet defining an airflow passageway therebetween, wherein the airflow passageway includes a parallel portion that is oriented about parallel to at least one of the first surface of the second component and the second surface of the second component.

公开(公告)号：US10823415B2

公开(公告)日：2020-11-03

申请号：US15995508

申请日：2018-06-01

Applicant: United Technologies Corporation

Inventor： Kristy Rose Riley ,  John R. Battye ,  Joanne V. Rampersad ,  San Quach

IPC: F23R3/60 ,  F23R3/00 ,  F02C3/04 ,  F23R3/28 ,  F23R3/10

Abstract: A deflector panel for a combustor of a gas turbine engine includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge including a panel scallop at least partially defining a deflector opening receptive of a fuel nozzle of the combustor. A combustor of a gas turbine engine includes a combustor shell at least partially defining a combustion zone therein, and a deflector assembly operably connected to the combustor shell. The deflector assembly includes a plurality of circumferentially abutted deflector panels. Each deflector panel includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge includes a panel scallop at least partially defining a deflector opening. A fuel nozzle extends through the deflector opening.

公开(公告)号：US10801407B2

公开(公告)日：2020-10-13

申请号：US14749000

申请日：2015-06-24

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley

IPC: B22C9/10 ,  F02C7/12 ,  F01D5/18 ,  F01D5/28 ,  F01D5/14 ,  F02C3/04

Abstract: A core assembly includes a core that includes an exterior surface that has a recessed area that extends along the exterior surface. An insert includes a contact surface that corresponds to the recessed area.

公开(公告)号：US10718521B2

公开(公告)日：2020-07-21

申请号：US15440641

申请日：2017-02-23

Applicant: United Technologies Corporation

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

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/60 ,  F23R3/50 ,  F02C3/04

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; 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 includes a discontinuous rail end surface.

公开(公告)号：US20200149742A1

公开(公告)日：2020-05-14

申请号：US16727178

申请日：2019-12-26

Applicant: United Technologies Corporation

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

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/18 ,  F23R3/60

Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.

公开(公告)号：US20200149409A1

公开(公告)日：2020-05-14

申请号：US16734464

申请日：2020-01-06

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F04D29/58 ,  F04D29/32

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

公开(公告)号：US10570748B2

公开(公告)日：2020-02-25

申请号：US15866557

申请日：2018-01-10

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.