Recuperator for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10830141-B2
Application number	US-201715843260-A
Country	US
Kind code	B2
Filing date	Dec 15, 2017
Priority date	Dec 15, 2017
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A recuperator includes a monolithic heat exchanger core having a first side proximal to a combustor inlet and a turbine outlet, and a second side that includes an exhaust outlet. A compressed air inlet is located on the second side, and a compressed air outlet is located on the first side. The compressed air outlet supplies air to a combustor. A first plurality of passageways connects the compressed air inlet to the compressed air outlet. A turbine exhaust inlet is located on the first side, and a turbine exhaust outlet is located on the second side. A second plurality of passageways connects the turbine exhaust inlet to the turbine exhaust outlet. The first and second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates.

First claim

The invention claimed is:

1. A recuperator comprising:
a monolithic heat exchanger core having a first side proximal to a combustor inlet and turbine outlet, and a second side axially opposed to the first side;
a compressed air inlet located on the second side and at a radially outer portion of the second side of the heat exchanger core, the compressed air inlet configured to receive air axially through the second side;
a compressed air outlet located on the first side and at a radially outer portion of the first side of the heat exchanger core, the compressed air outlet configured to discharge the air axially out through the second side for supplying the air to a combustor;
a first plurality of passageways connecting the compressed air inlet to the compressed air outlet;
a turbine exhaust inlet located on the first side and radially inward of the compressed air outlet;
a turbine exhaust outlet located on the second side and radially inward of the compressed air inlet; and
a second plurality of passageways connecting the turbine exhaust inlet to the turbine exhaust outlet;
wherein the first plurality of passageways and the second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates, and wherein each of the first plurality of passageways is adjacent to one of the second plurality of passageways.

2. The recuperator of claim 1 , wherein the first plurality of passageways includes a radially outer passageway and a radially inner passageway, the radially outer passageway having a shorter axial length than the radially inner passageway, wherein the resulting configuration of the compressed air inlet is tapered in an axial-radial plane.

3. The recuperator of claim 2 , wherein the compressed air inlet is tapered by about 45 degrees in the axial-radial plane.

4. The recuperator of claim 1 further comprising a combustor inlet plenum located adjacent the compressed air outlet and radially outward from the turbine exhaust inlet, the combustor inlet plenum configured to direct the air from the compressed air outlet to the combustor, wherein the compressed air outlet is tapered by about 45 degrees in an axial-radial plane.

5. The recuperator of claim 1 , wherein the parting plates are joined by a plurality of fins, and wherein the fins increase thermal transfer to the parting plates.

6. The recuperator of claim 5 , wherein the fins are formed at a variable angle comprising a curved surface with respect to the parting plates.

7. The recuperator of claim 1 , further comprising:
an outer casing located radially outward of the heat exchanger core, the outer casing directing compressed air axially aft to the compressed air inlet.

8. A gas turbine engine comprising:
a compressor;
a combustor fluidly connected with the compressor;
a turbine fluidly connected with the combustor;
a recuperator fluidly connected to the compressor and the combustor, the recuperator comprising:
a monolithic heat exchanger core having a first side proximal to a combustor inlet and turbine outlet, and a second side axially opposed to the first side;
a compressed air inlet located on the second side and at a radially outer portion of the second side of the heat exchanger core, the compressed air inlet configured to receive air axially through the second side;
a compressed air outlet located on the first side and at a radially outer portion of the first side of the heat exchanger core, the compressed air outlet configured to discharge the air axially out through the first side for supplying the air to the combustor;
a first plurality of passageways connecting the compressed air inlet to the compressed air outlet;
a turbine exhaust inlet located on the first side and radially inward of the compressed air outlet;
a turbine exhaust outlet located on the second side and radially inward of the compressed air inlet; and
a second plurality of passageways connecting the turbine exhaust inlet to the turbine exhaust outlet;
wherein the first plurality of passageways and the second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates, and wherein each of the first plurality of passageways is adjacent to one of the second plurality of passageways.

9. The gas turbine engine of claim 8 , wherein the first plurality of passageways includes a radially outer passageway and a radially inner passageway, the radially outer passageway having a shorter axial length than the radially inner passageway, wherein the resulting configuration of the compressed air inlet is tapered in an axial-radial plane.

10. The gas turbine engine of claim 9 , wherein the compressed air inlet is tapered by about 45 degrees in the axial-radial plane.

11. The gas turbine engine of claim 8 further comprising a combustor inlet plenum located adjacent the compressed air outlet and radially outward from the turbine exhaust inlet, the combustor inlet plenum configured to direct the air from the compressed air outlet to the combustor, wherein the compressed air outlet is tapered by about 45 degrees in an axial-radial plane.

12. The gas turbine engine of claim 8 , wherein the parting plates are joined by a plurality of fins, and wherein the fins increase thermal transfer to the parting plates.

13. The gas turbine engine of claim 12 , wherein the fins are formed at a variable angle comprising a curved surface with respect to the parting plates.

14. The gas turbine engine of claim 8 , further comprising:
an outer casing located radially outward of the heat exchanger core, the outer casing directing compressed air axially aft to the compressed air inlet.

15. The gas turbine engine of claim 8 , wherein the compressor is a centrifugal compressor.

16. A heat exchanger comprising:
a monolithic heat exchanger core having a first side and a second side axially opposed to the first side;
a first inlet located on the second side and at a radially outer portion of the second side of the heat exchanger core, the first inlet configured to receive air axially through the second side;
a first outlet located on the first side and at a radially outer portion of the first side of the heat exchanger core, the first outlet configured to discharge the air axially out through the first side;
a first plurality of passageways connecting the first inlet to the first outlet;
a second inlet located on the first side and radially inward of the first outlet;
a second outlet located on the second side and radially inward of the first inlet; and
a second plurality of passageways connecting the second inlet to the second outlet;
wherein the first plurality of passageways and the second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates, and wherein each of the first plurality of passageways is adjacent to one of the second plurality of passageways.

17. The heat exchanger of claim 16 , wherein the first plurality of passageways includes a radially outer passageway and a radially inner passageway, the radially outer passageway having a shorter axial length than the radially inner passageway, wherein the resulting configuration of the first inlet is tapered in an axial-radial plane.

18. The heat exchanger of claim 17 , wherein the first inlet is tapered by about 45 degrees

Assignees

• Gen Electric

Inventors

• Gerstler William Dwight
• Erno Daniel Jason
• Devendorf Brian Lewis
• Pruzinsky Kevin Kenneth

Classifications

• F02C7/08 Primary

  Heating air supply before combustion, e.g. by exhaust gases · CPC title

• F05D2250/71

  curved · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title

• F05D2230/53

  by integrally manufacturing a component, e.g. by milling from a billet or one piece construction · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title