Recuperator for gas turbine engine

Patent metadata

Field	Value
Publication number	US-9388741-B2
Application number	US-201213664579-A
Country	US
Kind code	B2
Filing date	Oct 31, 2012
Priority date	Oct 31, 2012
Publication date	Jul 12, 2016
Grant date	Jul 12, 2016

Abstract

A recuperator inserted in the exhaust duct of a gas turbine engine includes a casing surrounding a core having spiral cross channels. Inlet and outlet openings are defined in the casing for the passage of hot exhaust gases through the exhaust channels in the core. Feeder members extend radially across the outlet opening for passing the pre-combustion stage air through the air channels of the core, and header members extend radially across the inlet opening of the casing for receiving and redirecting air from the air channels in the core towards the combustor section. The feeder and header members each have a tapered configuration from the casing to the axial center of the casing so as to maintain a relatively constant pressure over the radial extent of the respective feeders and headers.

First claim

The invention claimed is:

1. A gas turbine engine having a compressor section, a combustor section and a turbine section with a gas exhaust duct downstream of the turbine section, the gas turbine engine further comprising a recuperator disposed in the gas exhaust duct, the recuperator including a casing of circular cross-section surrounding at least a core having channels including pre-combustion stage air channels and exhaust gas channels for directing hot gases from the turbine section into heat exchange relationship with pre-combustion stage air passing through respective channels, and inlet and outlet openings defined in the casing for the passage of said hot gases through the exhaust gas channels in the core, feeder members extending radially across the outlet opening for passing the pre-combustion stage air through the air channels of the core, and header members extending radially across the inlet opening of the casing for receiving and redirecting air from the pre-combustion stage air channels in the core towards the combustor section, the feeder and header members each having a tapered configuration from the casing to the axial center of the casing so as to maintain a relatively constant pressure over the radial extent of the respective feeders and headers, wherein an outer casing surrounds the casing surrouding the core and defines air ducts in fluid communication with the compressor section and the feeder members for conducting the pre-combustin stage air to the feeder members and separate air ducts for conducting the hot air from the header memebers to the combustor section.

2. The gas turbine engine as defined in claim 1 wherein the feeder and header members have the tapered configuration of a frusto-pyramid with a base at the periphery of the casing.

3. The gas turbine engine is defined in claim 1 wherein the feeder and header members have a hollow pyramidal shape with a base of the pyramid in fluid communication with the respective air ducts formed between the core casing and the outer casing.

4. The gas turbine engine as defined in claim 1 wherein multiple cores are provided with respective casings that have respective inlets and outlets.

5. The gas turbine engine as defined in claim 1 wherein multiple cores are provided in a single casing having a unitary inlet and multiple outlets.

6. A gas turbine engine to be located in a exhaust duct of a gas turbine engine having a compressor section, a combustor section and a turbine section, with the exhaust duct downstream of the turbine section, the recuperator comprising: a casing containing at least a core made up of exhaust gas channels for the passage of hot gases from the turbine section in heat exchange relationship with pre-combustion stage air, and inlet and outlet openings defined in the casing for the passage of hot gases through the exhaust gas channels in the core; the casing defined by a thin wall interrupted by a an expansion portion of the thin wall, allowing the thin wall to expand or contract in response to at least one of thermal stresses and vibrations, wherein an outer casing surrounds and is spaced apart from the casing surrounding the core, to form air passage ducts leading to the core, the outer casing defined by a thin wall interrupted by an expansion portion of the thin wall, allowing the thin wall to expand and contract in response to at least one of thermal stresses and vibrations.

7. The recuperator as defined in claim 6 wherein the expansion portion is in the form of corrugations in the thin wall forming bellows.

8. The recuperator is defined in claim 6 wherein the casing has a circular cross-section and the expansion portion is a circumferential band.

9. The recuperator as defined in claim 6 wherein multiple cores are provided in a single casing having a unitary inlet and multiple outlets.

10. The recuperator as defined in claim 6 wherein multiple cores are provided with respective casings that have respective inlets and outlets.

11. A recuperator to be located in an exhaust duct of a gas turbine engine having a compressor section, a combustor section and a turbine section, with the exhaust duct downstream of the turbine section, the recuperator comprising: a casing of circular cross-section containing at least a core made up of exhaust gas channels for the passage of hot gases from the turbine section in heat exchange relationship with pre-combustion stage air, and inlet and outlet openings defined in the casing for the passage of hot gases through the exhaust gas channels in the core; the casing is defined by a thin wall interrupted by an expansion portion of the thin wall allowing the thin wall to expand or contract in response to at least one of thermal stresses and vibrations, the expansion porion including at least one of a circumferential band and corrugations in the thin all forming bellows; feeder members extending radially across the outlet opening for passing the air through the air channels of the core; header members extending radially across the inlet opening of the casing for receiving and redirecting air from the air channels in the core towards the combustor section; the feeder and header members each having an inverse tapered configuration relative to an axial center of the casing so as to maintain a relatively constant pressure over the radial extent of the respective feeder and header members.

12. The recuperator as defined in claim 11 wherein the thin wall of the casing is approximately 1 mm thick.

Assignees

• Pratt & Whitney Canada

Inventors

• Gekht Eugene
• Julien André

Classifications

• F28D9/04

  the conduits being formed by spirally-wound plates or laminae · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F28D21/001

  for thermal power plants or industrial processes · CPC title

• F02C7/10 Primary

  by means of regenerative heat-exchangers · CPC title