Splitter for Air Bleed Manifold

Patent metadata

Field	Value
Publication number	US-2015354457-A1
Application number	US-201314762092-A
Country	US
Kind code	A1
Filing date	Dec 18, 2013
Priority date	Mar 14, 2013
Publication date	Dec 10, 2015
Grant date	—

Abstract

A splitter for protecting parts of a gas turbine engine is provided. The splitter segregates the flow of hot and cold gases into the air bleed manifold around the high compressor section to reduce maximum temperatures and minimize the temperature gradients of engine parts, especially inner case flanges The splitter divides the air bleed manifold into an annular inner cavity and an outer cavity. The splitter directs relatively cold air from the high compressor bleed ducts into the inner cavity and relatively hot air from the aft hub into the outer cavity, away from the inner case flanges.

First claim

What is claimed is:

1 . A splitter for a gas turbine engine, the gas turbine engine comprising a high pressure compressor section including a plurality of stages of circumferentially arrayed stators and rotating blades, each stator extending radially outward between a rotary disk stack and an inboard surface of an inner case, the inner case being circumferentially segmented into multiple inner case segments joined by inner case flanges, an outer case substantially concentric with the inner case, the outer case and inner case forming an air bleed manifold, the air bleed manifold defining a cavity supplied with cold air from high compressor bleed ducts and hot air from an aft hub, the splitter configured to direct the cold air into an annular inner cavity between the splitter and the inner case and across the inner case flanges, and the hot air into an outer cavity between the splitter and the outer case.

2 . The splitter of claim 1 wherein:
the splitter has an aft end and defines openings disposed around the aft end through which the cold air can flow.

3 . The splitter of claim 2 wherein:
the openings are circumferentially arranged slits.

4 . The splitter of claim 3 further comprising:
a body; and
a circular deflector disposed aft of the body and configured to prevent inflow of hot air into the inner cavity.

5 . The splitter of claim 4 wherein the deflector is further configured to direct the cold air into a radially outward flow path.

6 . A jet engine comprising:
a high pressure compressor section including a plurality of stages of circumferentially arrayed stators and rotating blades, each stator extending radially outward between a rotary disk stack and an inboard surface of an inner case, the inner case being circumferentially segmented into multiple inner case segments joined by inner case flanges; an outer case substantially concentric with the inner case, the outer case and inner case defining an air bleed manifold, the air bleed manifold defining a cavity supplied with cold air from high compressor bleed ducts and hot air from an aft hub; and a splitter configured to direct the cold air into an inner cavity between the splitter and the inner case and across the inner case flanges, and the hot air into an outer cavity between the splitter and the outer case.

7 . The jet engine of claim 6 wherein:
the splitter has an aft end and defines openings disposed around the aft end through which the cold air can flow.

8 . The jet engine of claim 7 wherein:
the openings are circumferentially arranged slits.

9 . The jet engine of claim 6 wherein the splitter comprises a body, the jet engine further comprising:
a circular deflector disposed aft of the splitter body and configured to prevent inflow of hot air into the inner cavity.

10 . The jet engine of claim 6 wherein the deflector is affixed to the splitter.

11 . The jet engine of claim 6 wherein the deflector is an undivided unitary part of the splitter.

12 . The jet engine of claim 6 wherein the deflector is further configured to direct the cold air into a radially outward flow path.

13 . A method of minimizing the temperature gradients of jet engine parts, the jet engine comprising an inner case circumferentially segmented into multiple inner case segments joined by inner case flanges, an outer case substantially concentric with the inner case, the outer case and inner case defining an air bleed manifold in which hot and cold air are mixed, the method comprising the step of:
installing a splitter configured to direct the cold air into an inner cavity between the splitter and the inner case and across the inner case flanges and to direct the hot air into an outer cavity between the splitter and the outer case.

14 . The method of claim 13 comprising the further step of:
allowing the cold air to exit the inner cavity through openings disposed in an aft end of the splitter.

15 . The method of claim 14 comprising the further step of:
using a circular deflector to deflect the hot air away from the openings.

16 . The method of claim 15 comprising the further step of:
using the deflector to direct the cold air into a radially outward flow path and into the outer cavity.

Assignees

• United Technologies Corp

Inventors

• Rioux Philip Robert
• Saftler Rishon

Classifications

• Y10T29/49828

  Progressively advancing of work assembly station or assembled portion of work · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F05D2240/12

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

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F02C6/08 Primary

  the gas being bled from the gas-turbine compressor · CPC title