公开(公告)号：US10808548B2

公开(公告)日：2020-10-20

申请号：US15832478

申请日：2017-12-05

Applicant: Raytheon Technologies Corporation

Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, Jr.

IPC: F01D5/18 ,  F02C9/18 ,  F02C3/04

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage. The resupply hole has an exit at the skin passage and the exit has a diffuser.

公开(公告)号：US11041391B2

公开(公告)日：2021-06-22

申请号：US16852728

申请日：2020-04-20

Applicant: Raytheon Technologies Corporation

Inventor： Steven D. Porter ,  Shawn M. McMahon ,  Kevin Zacchera ,  Noah Wadsworth ,  Christopher Whitfield ,  Sean D. Bradshaw ,  Dennis M. Moura ,  David Bitzko ,  Alex J. Schneider

IPC: F01D9/02 ,  F01D11/00 ,  F01D25/12 ,  F01D9/04

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.

公开(公告)号：US20210396388A1

公开(公告)日：2021-12-23

申请号：US17466999

申请日：2021-09-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Dominic Mongillo, JR. ,  Christopher Whitfield ,  Tracy Phropheter-Hinckley

IPC: F23R3/04 ,  F23R3/00 ,  F23R3/06 ,  F23R3/02

Abstract: A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow.

公开(公告)号：US10781697B2

公开(公告)日：2020-09-22

申请号：US15832455

申请日：2017-12-05

Applicant: Raytheon Technologies Corporation

Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, Jr.

IPC: F01D5/18 ,  F02C9/18 ,  F02C3/04

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an first angle relative to the direction of fluid flow in the core passage. The first angle lies in a plane parallel to the thickness direction. The centerline of the resupply hole is arranged at a second angle relative to the direction of fluid flow in the core passage. The second angle lies in a plane parallel to the width direction. The second angle is at an acute angle. The first and second angles are configured to provide a low turbulence flow region in the skin passage.