Gas turbine engine with integrated air cycle machine

Patent metadata

Field	Value
Publication number	US-11073091-B2
Application number	US-201816008628-A
Country	US
Kind code	B2
Filing date	Jun 14, 2018
Priority date	Jun 14, 2018
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A gas turbine engine includes: a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine; a secondary flowpath connected in flow communication with the primary flowpath; and an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein: the air cycle rotor is coupled in mechanical driving relationship with the at least one engine rotor; the air cycle rotor is coupled in fluid flow communication with the secondary flowpath; and the air cycle rotor is coupled in fluid flow communication with at least one heat exchanger.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine;
a secondary flowpath connected in flow communication with the primary flowpath, wherein the secondary flowpath is positioned radially inward of the primary flowpath, relative to the centerline axis; and
an air cycle machine including an air cycle rotor including an at least one air cycle compressor and at least one air cycle expander, wherein:
the air cycle rotor is integrated into the at least one engine rotor;
the air cycle rotor is in fluid flow communication with the secondary flowpath;
the air cycle rotor is in fluid flow communication with at least one heat exchanger, and
the air cycle rotor includes an annular rotor disk with a forward face and an aft face opposed from the forward face, the forward face including an array of compressor blades extending therefrom to define the at least one air cycle compressor and the aft face including an array of expander blades extending therefrom to define the at least one air cycle expander.

2. The engine of claim 1 further comprising:
a casing defining a portion of the primary flowpath; and
a core nacelle surrounding the casing, wherein the air cycle rotor is positioned radially inward of the casing.

3. The engine of claim 1 further comprising:
a casing defining a portion of the primary flowpath;
a core nacelle surrounding the casing; and
a fan nacelle surrounding the core nacelle, wherein the air cycle rotor is positioned radially inward of the casing.

4. The engine of claim 1 wherein a casing defines a portion of the primary flowpath and the air cycle rotor is positioned radially inward of the casing.

5. The engine of claim 1 wherein the air cycle rotor is positioned radially inward of the primary flowpath of the engine, relative to the centerline axis.

6. The engine of claim 1 wherein the engine includes a positioned downstream of the compressor, and the heat exchanger is formed integrally with the diffuser.

7. The engine of claim 6 wherein the air cycle rotor is disposed radially inward of the diffuser.

8. The engine of claim 6 wherein an annular forward wall structure is positioned inboard of the diffuser and axially forward of the air cycle rotor and an annular aft wall structure is positioned inboard of the diffuser and aft of the air cycle rotor.

9. The engine of claim 8 wherein an array of air cycle compressor outlet vanes are positioned between the annular forward wall structure and the diffuser downstream of the at least one air cycle compressor and an array of air cycle compressor inlet vanes are positioned between the annular forward wall structure and an inner rotating seal upstream of the at least one air cycle compressor.

10. The engine of claim 8 wherein an array of air cycle nozzle vanes are positioned between the annular aft wall structure and the diffuser upstream of the at least one air cycle expander and an array of air cycle outlet guide vanes are positioned between the annular aft wall structure and a compressor discharge seal downstream of the at least one air cycle expander.

11. The engine of claim 1 wherein a casing surrounds at least one of the compressor, the combustor, and the turbine, and the heat exchanger is positioned outside the casing.

12. The engine of claim 11 further comprising a nacelle surrounding the casing, wherein the heat exchanger is positioned outside the nacelle.

13. A method of cooling air in a gas turbine engine of the type including a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine, the method comprising:
a secondary flowpath connected in flow communication with the primary flowpath, wherein the secondary flowpath is positioned radially inward of the primary flowpath, relative to the centerline axis; and
bleeding air from the compressor from the primary flowpath into a secondary flowpath;
cooling the air bled from the compressor using an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein the air cycle rotor is mechanically driven by the at least one engine rotor;
passing the compressed air from the air cycle compressor to a heat exchanger and rejecting heat from the compressed air;
passing the compressed air from the heat exchanger through the air cycle expander,
wherein the air cycle rotor is integrated into the at least one engine rotor, and wherein the air cycle rotor includes an annular rotor disk having opposed a forward face and an aft face, the forward face including an array of compressor blades extending therefrom to define the at least one air cycle compressor and the aft face including an array of expander blades extending therefrom to define the at least one air cycle expander.

14. The method of claim 13 further comprising passing the air from the air cycle expander to a different part of the engine.

15. The method of claim 13 wherein a casing defines a portion of the primary flowpath and the air cycle rotor is positioned radially inward of the casing.

16. The method of claim 13 wherein the air cycle rotor is positioned radially inward of the primary flowpath of the engine, relative to the centerline axis.

Assignees

• Gen Electric

Inventors

• Johnson Steven Douglas
• Rambo Jeffrey

Classifications

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02C7/185

  Cooling means for reducing the temperature of the cooling air or gas · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title