Bleed valve assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10233845-B2
Application number	US-201615287782-A
Country	US
Kind code	B2
Filing date	Oct 7, 2016
Priority date	Oct 7, 2016
Publication date	Mar 19, 2019
Grant date	Mar 19, 2019

Abstract

A gas turbine engine includes a first compressor, a casing surrounding the first compressor, and a liner extending forward from the first compressor. The gas turbine engine also includes a core turbine frame assembly extending between the liner and the casing and a bleed air assembly. The bleed air assembly includes a bleed valve positioned in the liner, and a duct in airflow communication with the bleed valve and defining in outlet. The duct is positioned within the core turbine frame assembly and extends to the casing.

First claim

What is claimed is:

1. A gas turbine engine defining an axial direction, the gas turbine engine comprising:
a first compressor;
a second compressor located downstream of the first compressor:
a casing surrounding the first compressor;
a liner extending aft from the first compressor to the second compressor, the liner at least partially defining a core air flowpath from the first compressor to the second compressor;
a core turbine frame assembly extending between the liner and the casing, the core turbine frame assembly comprising a forward frame member and an aft frame member, the forward frame member and the aft frame member each being positioned aft of the first compressor and forward of the second compressor and extending from the liner to the casing; and
a bleed air assembly comprising;
a bleed valve positioned in the liner, the bleed valve comprising a door assembly configured to move between an open position and a closed position, wherein the door assembly comprises a transition passage which pivots with the door assembly as the door assembly moves between the open position and the closed position; and
a duct in airflow communication with the bleed valve, the duct including a liner structure positioned within the core turbine frame assembly and between the forward frame member and the aft frame member, the liner structure defining an outlet of the duct, and the duct extending to the casing,
wherein the aft frame member intersects the casing at a first position, the forward frame member intersects the casing at a second position, and wherein the outlet is positioned at the casing at a location forward of the first position and aft of the second position, the outlet being configured to exhaust a bleed air flow through the casing at the location of the outlet.

2. The gas turbine engine of claim 1 , wherein the transition passage is aligned with the duct when the door assembly is in the open position.

3. The gas turbine engine of claim 2 , wherein the transition passage is misaligned with the duct when the door assembly is in the closed position.

4. The gas turbine engine of claim 2 , wherein the transition passage is in airflow communication with the core air flowpath and the duct when the door assembly is in the open position.

5. The gas turbine engine of claim 1 , wherein the bleed valve is a first bleed valve, wherein the bleed air assembly further comprises a second bleed valve, and wherein the duct is in airflow communication with the first bleed valve and the second bleed valve.

6. The gas turbine engine of claim 1 , wherein the liner is an outer flowpath liner, the gas turbine engine further comprises an inner flowpath liner, and the inner flowpath liner and the outer flowpath liner together define a portion of the core air flowpath extending between the first compressor and the second compressor.

7. The gas turbine engine of claim 1 , wherein the first compressor, the casing, the liner, and the bleed air assembly are configured as part of an engine core of the gas turbine engine, and wherein the gas turbine engine further comprises:
an outer nacelle at least partially surrounding the engine core and defining a bypass passage with the casing, wherein the outlet of the duct is in airflow communication with the bypass passage through the casing.

8. The gas turbine engine of claim 1 , wherein the casing defines an opening, wherein the outlet of the duct is positioned at the opening of the casing.

9. The gas turbine engine of claim 7 , wherein the bleed air assembly comprises a plate positioned in, or over, the outlet of the duct, and wherein the plate defines a plurality of airflow holes.

Assignees

• Gen Electric

Inventors

• Moniz Thomas Ory
• Rose Joseph George
• Sage Patrick Sean
• Clements Jeffrey Donald
• Glover Jeffrey

Classifications

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F04D29/522

  especially adapted for elastic fluid pumps · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F02C7/00

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F02C6/08

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