公开(公告)号：US11585291B2

公开(公告)日：2023-02-21

申请号：US17018795

申请日：2020-09-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Marc J. Muldoon ,  Jonathan Rheaume ,  Stephen H. Taylor

IPC: F02K1/36 ,  F02C7/18 ,  F02K1/38 ,  F01D15/10 ,  F02C7/32

Abstract: An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.

公开(公告)号：US12140050B2

公开(公告)日：2024-11-12

申请号：US18109448

申请日：2023-02-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Malcolm P. MacDonald ,  Stephen H. Taylor ,  Ram Ranjan

IPC: F01K23/10 ,  F01K25/10

Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.

公开(公告)号：US20240102417A1

公开(公告)日：2024-03-28

申请号：US17951972

申请日：2022-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Stephen H. Taylor ,  Alan Retersdorf ,  Oliver V. Atassi ,  Nathan A. Snape

IPC: F02C6/08 ,  F02C9/18 ,  F02G5/00 ,  F02K3/02

CPC classification number: F02C6/08 ,  F02C9/18 ,  F02G5/00 ,  F02K3/02

Abstract: A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.

公开(公告)号：US20230313737A1

公开(公告)日：2023-10-05

申请号：US18109441

申请日：2023-02-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Malcolm P. MacDonald ,  Stephen H. Taylor

IPC: F02C6/18 ,  B64D27/10 ,  B64D33/08

CPC classification number: F02C6/18 ,  B64D27/10 ,  B64D33/08

Abstract: A propulsion system for an aircraft includes a core flow path in communication with a compressor section, combustor section and a turbine section. A first bottoming cycle system includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the core engine. The first bottoming cycle is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.

公开(公告)号：US20210380260A1

公开(公告)日：2021-12-09

申请号：US17411529

申请日：2021-08-25

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian Merry ,  Stephen H. Taylor ,  Charles E. Lents

IPC: B64D13/08 ,  F02C6/08 ,  F02C9/18 ,  F02K3/115 ,  B64D27/10 ,  F01D15/10 ,  F02C3/04 ,  F02K3/06 ,  H02K7/18 ,  F02C7/18 ,  F02K3/04

Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.