公开(公告)号：US10378573B2

公开(公告)日：2019-08-13

申请号：US15657423

申请日：2017-07-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew Chuckta ,  Matthew D. Parekh

IPC: F16B21/12 ,  F01D17/16

Abstract: A retaining pin having anti-rotation features is provided. The retaining pin may comprise a pin shaft coupled to a retaining flange. The pin shaft may be inserted into a structural member proximate a shaft and a nut. The retaining flange may comprise an anti-rotation void defined by a first arm and a second arm and configured to engage the shaft. In response to the nut coupling the retaining flange to the shaft, the retaining pin may at least partially reduce movement and rotation of the shaft relative to the retaining pin.

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：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：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：US11156359B2

公开(公告)日：2021-10-26

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 ,  F02C7/18 ,  F23R3/60 ,  F23R3/06

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：US11098612B2

公开(公告)日：2021-08-24

申请号：US16686609

申请日：2019-11-18

Applicant: United Technologies Corporation

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

IPC: F01D25/12 ,  F01D11/00

Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.

公开(公告)号：US10830434B2

公开(公告)日：2020-11-10

申请号：US15440677

申请日：2017-02-23

Applicant: United Technologies Corporation

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

IPC: F23R3/00 ,  F23R3/50 ,  F23R3/60 ,  F27D1/00

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：US20190024694A1

公开(公告)日：2019-01-24

申请号：US15657423

申请日：2017-07-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew Chuckta ,  Matthew D. Parekh

IPC: F16B21/12

CPC classification number: F16B21/12 ,  F01D17/16

Abstract: A retaining pin having anti-rotation features is provided. The retaining pin may comprise a pin shaft coupled to a retaining flange. The pin shaft may be inserted into a structural member proximate a shaft and a nut. The retaining flange may comprise an anti-rotation void defined by a first arm and a second arm and configured to engage the shaft. In response to the nut coupling the retaining flange to the shaft, the retaining pin may at least partially reduce movement and rotation of the shaft relative to the retaining pin.

公开(公告)号：US11384654B2

公开(公告)日：2022-07-12

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.