公开(公告)号：US11773780B2

公开(公告)日：2023-10-03

申请号：US17587050

申请日：2022-01-28

Applicant: Raytheon Technologies Corporation

Inventor： Joseph Turney

IPC: F02C7/18 ,  F02C9/18 ,  F02C6/08 ,  F02C7/32 ,  F02K3/06 ,  F16K15/14

CPC classification number: F02C7/185 ,  F02C7/32 ,  F02C9/18 ,  F02K3/06 ,  F16K15/147 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/4031

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.

公开(公告)号：US12038179B2

公开(公告)日：2024-07-16

申请号：US17226444

申请日：2021-04-09

Applicant: Raytheon Technologies Corporation

Inventor： Joseph Turney ,  Christopher Britton Greene ,  Peter A T Cocks ,  Andrzej Ernest Kuczek ,  James M. Donohue

IPC: F23R7/00 ,  F02K7/02 ,  F23C15/00 ,  F23R3/00

CPC classification number: F23R7/00 ,  F02K7/02 ,  F23C15/00 ,  F23R3/002 ,  F05D2250/25 ,  F23R2900/03043

Abstract: A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.

公开(公告)号：US20230220999A1

公开(公告)日：2023-07-13

申请号：US17226444

申请日：2021-04-09

Applicant: Raytheon Technologies Corporation

Inventor： Joseph Turney ,  Christopher Britton Greene ,  Peter AT Cocks ,  Andrzej Ernest Kuczek ,  James M. Donohue

IPC: F02K7/02 ,  F23C15/00 ,  F23R7/00 ,  F23R3/00

CPC classification number: F02K7/02 ,  F23C15/00 ,  F23R7/00 ,  F23R3/002

Abstract: A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.

公开(公告)号：US20220154645A1

公开(公告)日：2022-05-19

申请号：US17587050

申请日：2022-01-28

Applicant: Raytheon Technologies Corporation

Inventor： Joseph Turney

IPC: F02C7/18 ,  F02C7/32 ,  F02C9/18 ,  F02K3/06 ,  F16K15/14

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.

公开(公告)号：US20210363925A1

公开(公告)日：2021-11-25

申请号：US17392653

申请日：2021-08-03

Applicant: Raytheon Technologies Corporation

Inventor： Joseph Turney ,  Michael K. Ikeda

IPC: F02C7/232 ,  F02C7/143 ,  F16K17/20

Abstract: A gas turbine engine includes a main compressor section and a main turbine section. A cooling air supply system cools a location in at least one of the main compressor section and the main turbine section. The cooling air supply system includes a tap for tapping cooling air compressed by the main compressor section, connected for passing the cooling air through a heat exchanger and to a boost compressor, and then to the cooling location in the at least one of the main compressor section and the main turbine section. A fuel supply system has a fuel tank for delivering fuel to a fuel pump. At least one valve for selectively returning fuel downstream of the main pump back to an upstream location. At least one return turbine drives at least one fluid moving device in the air cooling system.