公开(公告)号：US20210025595A1

公开(公告)日：2021-01-28

申请号：US16520853

申请日：2019-07-24

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Ryan Lundgreen

IPC: F23R3/42

Abstract: A gas turbine engine, including: a diffuser case defining an inner shroud and an outer shroud; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

公开(公告)号：US11262071B2

公开(公告)日：2022-03-01

申请号：US16520853

申请日：2019-07-24

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Ryan Lundgreen

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/42

Abstract: A gas turbine engine, including: a diffuser case defining an inner shroud and an outer shroud; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

公开(公告)号：US11156363B2

公开(公告)日：2021-10-26

申请号：US16212791

申请日：2018-12-07

Applicant: United Technologies Corporation

Inventor： Stephen K. Kramer ,  Ryan Lundgreen ,  Robin Prenter

IPC: F23R3/00 ,  F23R3/42

Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and a plurality of pin fins extending away from the second surface of the second component, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween, wherein the plurality of pin fins extend into the cooling channel, wherein each of the plurality of pin fins have a pointed ellipse shape.

公开(公告)号：US11073024B2

公开(公告)日：2021-07-27

申请号：US16220396

申请日：2018-12-14

Applicant: United Technologies Corporation

Inventor： Christopher Perron ,  Justin M. Aniello ,  Shawn M. McMahon ,  Mohamed Hassan ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  David Barger ,  Brett Alan Bartling ,  Nicholas J. Madonna ,  Robin Prenter ,  Ryan Lundgreen ,  Christopher Cosher

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D25/14 ,  F01D25/24

Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

公开(公告)号：US20200182470A1

公开(公告)日：2020-06-11

申请号：US16212791

申请日：2018-12-07

Applicant: United Technologies Corporation

Inventor： Stephen K. Kramer ,  Ryan Lundgreen ,  Robin Prenter

IPC: F23R3/42

Abstract: A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and a plurality of pin fins extending away from the second surface of the second component, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween, wherein the plurality of pin fins extend into the cooling channel, wherein each of the plurality of pin fins have a pointed ellipse shape.

公开(公告)号：US11078796B2

公开(公告)日：2021-08-03

申请号：US16220400

申请日：2018-12-14

Applicant: United Technologies Corporation

Inventor： Christopher Perron ,  Justin M. Aniello ,  Shawn M. McMahon ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  David Barger ,  Brett Alan Bartling ,  Nicholas J. Madonna ,  Robin Prenter ,  Ryan Lundgreen ,  Christopher Cosher ,  Mohamed Hassan

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/24 ,  F01D25/12 ,  F01D25/14

Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.

公开(公告)号：US11008872B2

公开(公告)日：2021-05-18

申请号：US16220398

申请日：2018-12-14

Applicant: United Technologies Corporation

Inventor： Christopher Perron ,  Justin M. Aniello ,  Shawn M. McMahon ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  David Barger ,  Brett Alan Bartling ,  Nicholas J. Madonna ,  Robin Prenter ,  Ryan Lundgreen ,  Christopher Cosher ,  Mohamed Hassan

IPC: F01D5/18 ,  F01D9/04

Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

公开(公告)号：US20210054753A1

公开(公告)日：2021-02-25

申请号：US16531430

申请日：2019-08-05

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Ricardo Trindade ,  Ryan Lundgreen

IPC: F01D9/06 ,  F01D5/08

Abstract: A diffuser case for a gas turbine engine including: a pre-diffuser; a diffuser case defining a dump region, an inner shroud, and an outer shroud, the pre-diffuser being fluidly connected to the inner shroud and the outer shroud through the dump region; a tangential onboard injector module fluidly connected to the inner shroud through inlet orifice located in the diffuser case proximate an aft end of the inner shroud; and an inlet extender initiating at the inlet orifice of the tangential onboard injector module, extends through the inner shroud, and terminates at a distal end proximate the pre-diffuser.