公开(公告)号：US11073285B2

公开(公告)日：2021-07-27

申请号：US16448414

申请日：2019-06-21

Applicant: United Technologies Corporation

Inventor： San Quach ,  Jeremy Styborski ,  Caroline Karanian

IPC: F23R3/00 ,  F23R3/06 ,  F23R3/50

Abstract: A combustor of a gas turbine engine including a first forward liner panel. The forward liner panel including a liner panel forward edge, a liner panel aft edge opposite of the liner panel forward edge, and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor.

公开(公告)号：US20210222878A1

公开(公告)日：2021-07-22

申请号：US16746210

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Caroline Karanian ,  John T. Ols

IPC: F23R3/00

Abstract: A gas turbine engine includes a turbine section including a first vane stage. The gas turbine engine further includes a combustor disposed forward of the first vane stage. The combustor includes a combustion chamber in fluid communication with the first vane stage. The combustion chamber is radially defined between a first shell and a second shell. The first shell includes a first seal assembly at an aft end of the first shell. The first seal assembly includes a conformal seal forming a first seal between the first shell and a forward face of the first vane stage. The second shell includes a second seal assembly at an aft end of the second shell. The second seal assembly includes a brush seal forming a second seal between the second shell and the forward face of the first vane stage.

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：US20200157959A1

公开(公告)日：2020-05-21

申请号：US16195925

申请日：2018-11-20

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Steven D. Porter ,  Caroline Karanian

IPC: F01D11/00 ,  F01D9/02 ,  F23R3/00

Abstract: A gas turbine engine includes a combustor disposed about an engine central axis and a circumferential row of vanes adjacent an exit region of the combustor. The combustor includes a combustor wall and a combustion chamber. The combustor wall has a lip at the exit region. Each vane includes a platform and an airfoil section extending from the platform. The forward edges of the platforms are adjacent the lip of the combustor wall. The lip defines a first annular slot and the forward edges of the vanes collectively define a second annular slot. The first and second annular slots together define an annular seal slot. An annular feather seal is entrapped in the annular seal slot between the combustor wall and the platform.

公开(公告)号：US20170362960A1

公开(公告)日：2017-12-21

申请号：US15188170

申请日：2016-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher Treat ,  Jeffrey H. Huang ,  Caroline Karanian

IPC: F01D25/24 ,  F01D25/28

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/237 ,  F05D2230/30

Abstract: A stiffness boss for a turbine case of a gas turbine engine is disclosed. The stiffness boss includes a head portion disposed on an outer case surface of the turbine case, the head portion configured to provide rigidity in response to a transverse load being applied to the turbine case in a transverse direction. The stiffness boss also includes a leg portion disposed on the outer case surface of the turbine case and connected to the head portion, the leg portion configured to provide rigidity in response to an axial load being applied to the turbine case in an axial direction, such that deformation of the turbine case is resisted.