公开(公告)号：US10808933B2

公开(公告)日：2020-10-20

申请号：US16001349

申请日：2018-06-06

Applicant: Raytheon Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

IPC: F23R3/10 ,  F02C3/04 ,  F01D5/08 ,  F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18

Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.

公开(公告)号：US20220056847A1

公开(公告)日：2022-02-24

申请号：US17519887

申请日：2021-11-05

Applicant: Raytheon Technologies Corporation

Inventor： James D. Hill ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02C3/107 ,  F01D25/12 ,  F02C6/08

Abstract: A gas turbine engine comprises a compressor section and a turbine section, the compressor section having a last compressor stage. High pressure cooling air is tapped from a location downstream of the last compressor stage and passed through a heat exchanger. Lower pressure air passes across the heat exchanger to cool the high pressure cooling air. A housing surrounds the compressor section and the turbine section and there being a space radially outwardly of the housing, and a mixing chamber received in the space radially outwardly of the housing, the mixing chamber receiving the high pressure cooling air downstream of the heat exchanger, and further receiving air at a temperature higher than a temperature of the high pressure cooling air downstream of the heat exchanger. Mixed air from the mixing chamber is returned into the housing and utilized to cool at least the turbine section.