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

Patent metadata

Field	Value
Publication number	US-2016348534-A1
Application number	US-201615236544-A
Country	US
Kind code	A1
Filing date	Aug 15, 2016
Priority date	Mar 11, 2013
Publication date	Dec 1, 2016
Grant date	—

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:
arcuate segments each including a base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel between the pair of sidewalls for directing air supplied to the sleeve in circumferential directions; and flow openings in the base configured to direct air in a radially inward direction, wherein each of the arcuate segments is configured to be aligned with a respective one of compressor discharge air inlets on the casing.

2 . The flow sleeve of claim 1 wherein the arcuate segments each include fins extending from the base towards the inside surface of the casing, and the fins are proximate each of opposite ends of the base.

3 . The flow sleeve of claim 1 wherein the arcuate segments each include 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 gas turbine casing comprising:
inner and outer shells adapted to enclose one or more turbine stages in a gas turbine engine; a cavity between the inner and outer shells, wherein a radially outer wall of the cavity is formed by the outer shell and an radially inner wall of the cavity is formed by the inner shell; a compressor discharge air inlet on the outer shell, and an arcuate segment in the cavity and including a base and sidewalls at opposite sides of the base, wherein the base includes a center section aligned with the compressor discharge air inlet along a radial line and the base has a length in a circumferential direction greater than a width in a direction of an axis of the gas turbine.

9 . The gas turbine casing of claim 8 wherein the arcuate segment is one of a plurality of arcuate segments arranged in an annulus in the cavity and each arcuate segment is aligned with a respective compressor discharge air inlet.

10 . The gas turbine casing of claim 8 wherein the arcuate segments each include circumferentially-extending fins proximate each of opposite ends of the base; and
at least one circumferentially oriented flow passage at each of the opposite ends of the base, wherein each flow passage is between and defined by the fins at one of the opposite ends.

11 . The gas turbine casing of claim 10 further comprising a scoop on the base and an aperture in the base, wherein the scoop is aligned with the flow passage along the circumferential direction and is between one of the opposite ends and the flow passage and the scoop is configured to direct air from the flow passage into the aperture.

12 . The gas turbine casing of claim 11 wherein the aperture is aligned with a radially-oriented jet nozzle projecting from a side of the base opposite to a side of the base facing the outer shell.

13 . The gas turbine casing of claim 8 wherein the sidewalls are curved relative to an inside surface of the outer casing, and a radial gap is formed between the sidewalls and the inside surface.

Assignees

• Gen Electric

Inventors

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

Classifications

• 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

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D25/26

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