Flow sleeve for thermal control of a double-wall turbine shell and related method

Patent metadata

Field	Value
Publication number	US-9453429-B2
Application number	US-201313794136-A
Country	US
Kind code	B2
Filing date	Mar 11, 2013
Priority date	Mar 11, 2013
Publication date	Sep 27, 2016
Grant date	Sep 27, 2016

Abstract

A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.

First claim

What is claimed is:

1. A flow sleeve adapted for securement to an inside surface of a casing, the flow sleeve comprising:
at least two arcuate segments, each arcuate segment comprising a base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel between said sidewalls for directing air supplied to said sleeve in circumferential directions;
plural flow openings in said base for directing air in a radially inward direction, and
an attachment feature for securing the sleeve to the inside surface of the casing provides, when the flow sleeve is installed, a substantially uniform radial gap between said sidewalls and said inside surface, thereby permitting air to flow axially in opposite directions along the inside surface of the outer casing.

2. The flow sleeve of claim 1 wherein at least one circumferentially-extending fin is provided proximate opposite ends of said base to at least partially form flow passages at said opposite ends of said base.

3. The flow sleeve of claim 1 wherein plural fins are arranged proximate opposite ends of said base, thereby creating plural flow passages, each flow passage adapted to direct air toward at least one respective, radially-oriented aperture in said base.

4. The flow sleeve of claim 1 and further comprising at least one defined flow passage along said base, and a surface feature on said base within said flow passage for capturing and diverting air in said at least one defined flow passage into a radially-oriented aperture in said base.

5. The flow sleeve of claim 3 wherein said at least one radially-oriented aperture comprises inlets to radially-oriented jet nozzle projecting from an underside of said base.

6. The flow sleeve of claim 1 wherein said sidewalls are curved relative to the inside surface of the outer casing such that, when installed, a radial gap is formed between said sidewalls and said inside surface thereby permitting air to flow axially in opposite directions along the inside surface of the outer casing.

7. The flow sleeve of claim 1 further comprising plural radially-oriented jet nozzles in selected portions of said base.

8. A flow sleeve adapted for securement to an inside surface of a casing, the flow sleeve comprising:
at least two arcuate segments, each arcuate segment comprising a base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel between said sidewalls for directing air supplied to said sleeve in circumferential directions, wherein said at least two arcuate segments comprise four arcuate segments, each having a circumferential extent of from greater than 0 degrees to substantially 90 degrees, and
plural flow openings in said base for directing air in a radially inward direction.

9. A turbine casing comprising:
inner and outer shells adapted to enclose one or more turbine stages in a gas turbine engine, said inner and outer shells forming a cavity radially therebetween, said outer shell provided with an air inlet to said cavity;
a flow sleeve secured to an inside surface of said outer shell, within said cavity, said flow sleeve comprising at least two arcuate segments, each arcuate segment comprising a base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel radially inward of said air inlet, said flow channel defined by said base, said sidewalls and said inside surface; said flow channel adapted to flow air in opposite circumferential and axial directions along said inside surface; and
plural flow openings in said base for directing some of the air in said flow channel radially into said cavity.

10. The turbine casing of claim 9 wherein at least one circumferentially-extending fin is provided proximate opposite ends of said base to at least partially form flow passages at said opposite ends of said base.

11. The turbine casing of claim 10 wherein plural fins are arranged proximate opposite ends of said base, thereby creating plural flow passages, each flow passage adapted to direct air toward at least one respective, radially-oriented aperture in said base.

12. The turbine casing of claim 9 and further comprising at least one defined flow passage along said base, and a surface feature on said base within said flow passage for capturing and diverting air in said at least one defined flow passage through a radially-oriented aperture in said base and into said cavity.

13. The turbine casing of claim 12 wherein said apertures comprise inlets to radially-oriented jet nozzles projecting from an underside of said base into said cavity.

14. The turbine casing of claim 9 wherein said sidewalls are curved relative to the inside surface of the outer casing such that, when installed, a radial gap is formed between said sidewalls and said inside surface thereby permitting air in said flow channel to flow axially in opposite directions along the inside surface of said outer shell.

15. The turbine casing of claim 9 wherein an attachment feature for securing the sleeve to the inside surface of the casing provides, when the flow sleeve is installed, a substantially uniform radial gap between said sidewalls and said inside surface, thereby permitting air to flow axially in opposite directions along the inside surface of the outer casing.

16. The turbine casing of claim 9 wherein said at least two arcuate segments comprise four arcuate segments, each having a circumferential extent of from >0 degrees to substantially 90 degrees.

17. The turbine casing of claim 9 further comprising plural radially-inwardly-oriented jet nozzles in selected portions of said base.

18. A turbine casing comprising:
at least one shell adapted to enclose one or more turbine stages in a gas turbine engine;
an air inlet in said at least one shell;
a flow sleeve secured to an inside surface of said at least one shell, said flow sleeve comprising at least two arcuate segments, each arcuate segment comprising a base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by said base, said sidewalls and said inside surface, said air inlet aligned with said flow channel; wherein said flow sleeve is configured to distribute air flowing in said channel into spaces proximate said one or more turbine stages in circumferential, radial and axial directions, including along said inside surface of said at least one shell.

19. The turbine casing of claim 18 wherein said at least one shell comprises inner and outer shells adapted to enclose one or more turbine stages in the gas turbine engine, said inner and outer shells forming a cavity radially therebetween; and wherein said an annular sleeve is secured to an inside surface of said outer shell within said cavity.

Assignees

• Gen Electric

Inventors

• Danescu Radu Ioan
• Johnson David Martin
• Black Kenneth Damon
• Cox Christopher Paul
• Bozkurt Ozgur

Classifications

• F01D19/02 Primary

  dependent on temperature of component parts, e.g. of turbine-casing · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D25/08 Primary

  Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title