Bypass air-pump system within the core engine to provide air for an environmental control system in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9394803-B2
Application number	US-201213419679-A
Country	US
Kind code	B2
Filing date	Mar 14, 2012
Priority date	Mar 14, 2012
Publication date	Jul 19, 2016
Grant date	Jul 19, 2016

Abstract

An engine comprises a fan configured to produce propulsive thrust from a fan discharge air stream. A bypass duct is located between a cowl and an engine core, the bypass duct is fluidly coupled to the fan. The bypass duct contains the air stream created by the fan. A pump system provides the air to an environmental control system. The pump system comprises an impeller having an inlet for receiving the air from the duct and an outlet for discharging the air to the environmental control system. An intake manifold is configured to receive the air from the bypass duct and to deliver the air to the inlet. A single discharge manifold is configured to deliver the air from the outlet to the environmental control system.

First claim

What is claimed is:

1. An engine comprising:
a fan configured to produce propulsive thrust from a fan discharge air stream;
a bypass duct located between a cowl and an engine core, said bypass duct fluidly coupled to said fan without being fluidly connected to the compressor;
said bypass duct containing said fan discharge air stream created by said fan;
a pump system for providing said fan discharge air stream to an environmental control system;
said pump system comprising an impeller having an inlet for receiving said fan discharge air stream from said bypass duct and an outlet for discharging said fan discharge air stream to said environmental control system;
an intake manifold configured to receive said fan discharge air stream from said bypass duct and to deliver said fan discharge air stream to said inlet; and
a single discharge manifold configured to deliver fan discharge air stream from said outlet to said environmental control system.

2. The engine according to claim 1 , wherein said environmental control system includes an aircraft precooler and said discharge manifold delivers said fan discharge air stream to said aircraft precooler.

3. The engine according to claim 1 , further comprising a valve incorporated into said discharge manifold to control the flow of said fan discharge air stream through said discharge manifold.

4. The engine according to claim 1 , wherein said pump system further comprises a towershaft for driving said impeller.

5. The engine according to claim 4 , further comprising a spool and said towershaft being connected to said spool by a drive gear.

6. The engine according to claim 5 , wherein said spool is a low spool connected to a fan.

7. The engine according to claim 5 , wherein said spool is a high spool connected to a high pressure compressor.

8. A pump system for providing fan discharge air to an environmental control system, said pump system comprising:
a bypass duct located between a cowl and an engine core;
an air intake for receiving a said fan discharge air from a supply of air taken from said bypass duct, and wherein said bypass duct is fluidly coupled to said fan, without being fluidly connected to the compressor;
an impeller having an intake for receiving said fan discharge air and an outlet for discharging said discharge air; and
a single discharge manifold for delivering said fan discharge air from said outlet to said environmental control system.

9. The pump system of claim 8 , further comprising a towershaft for driving said impeller.

10. The pump system of claim 9 , wherein said towershaft is driven by a spool of an engine.

11. The pump system of claim 10 , wherein said spool is a low spool.

12. The pump system of claim 10 , wherein said spool is a high spool.

13. The pump system of claim 10 , wherein said towershaft is connected to said spool by a drive gear.

14. The pump system of claim 8 , further comprising a valve incorporated into said single discharge manifold.

Assignees

• Suciu Gabriel L
• Glahn Jorn A
• Merry Brian D
• Dye Christopher M
• United Technologies Corp

Inventors

• Suciu Gabriel L
• Glahn Jorn A
• Merry Brian D
• Dye Christopher M

Classifications

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F02C6/08

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

• F01D15/08 Primary

  Adaptations for driving, or combinations with, pumps · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title