Engine bleed air with compressor surge management

Patent metadata

Field	Value
Publication number	US-10533501-B2
Application number	US-201615186722-A
Country	US
Kind code	B2
Filing date	Jun 20, 2016
Priority date	Jun 20, 2016
Publication date	Jan 14, 2020
Grant date	Jan 14, 2020

Abstract

A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a main compressor section including a low pressure compressor section and a high pressure compressor section;
a booster compressor including an inlet and an outlet, the inlet receiving airflow from the low compressor section and the outlet providing airflow to a pneumatic system;
a recirculation passage communicating airflow from the booster compressor outlet to a passage in communication with the inlet receiving airflow from the low pressure compressor section, wherein a pressure reduction valve is disposed within the recirculation passage for reducing a pressure of airflow to enable mixing with the airflow from the low compressor section; and
a flow splitter valve controlling airflow from the booster compressor outlet to the recirculation passage and the pneumatic system based on airflow output from the booster compressor, wherein the pressure reduction valve is downstream of the flow splitter valve and the low pressure compressor section supplies airflow through a first passage to the booster compressor inlet and the high pressure compressor section supplies airflow through a second passage directly to the pneumatic system separate from the booster compressor.

2. The gas turbine engine as recited in claim 1 , including a heat exchanger for cooling airflow through the recirculation passage prior to the inlet of the booster compressor.

3. The gas turbine engine as recited in claim 2 , wherein the second passage may extend through the heat exchanger separate from airflow through the recirculation passage for cooling airflow supplied directly to the pneumatic system from the high pressure compressor section.

4. The gas turbine engine as recited in claim 2 , including a first control valve controlling airflow from the high pressure compressor to the second passage.

5. The gas turbine engine as recited in claim 2 , including a turbine coupled to the booster compressor for driving the booster compressor, the turbine driven by airflow through a turbine inlet from the main compressor section.

6. The gas turbine engine as recited in claim 5 , including a mixing valve combining airflow from the booster compressor and the turbine for communication to the pneumatic system.

7. A bleed air system for a gas turbine engine, the bleed air system comprising:
a booster compressor including an inlet and an outlet, the inlet receiving airflow from a main compressor section of the gas turbine engine and the outlet providing airflow to a pneumatic system;
a first passage to the booster compressor inlet from a low pressure section of the main compressor; and
a second passage bypassing the booster compressor for supplying airflow from a high pressure section of the main compressor directly to the pneumatic system;
a recirculation passage between the inlet from the low pressure section of the main compressor and the outlet of the booster compressor;
a pressure reduction valve disposed within the recirculation passages for reducing a pressure of airflow to enable mixing of airflow from the low pressure section of the main compressor within the inlet; and
a flow splitter valve controlling airflow from the booster compressor outlet to the recirculation passages and the pneumatic system based on airflow output from the booster compressor, wherein the pressure reduction valve is downstream of the flow splitter valve.

8. The bleed air system as recited in claim 7 , including a heat exchanger for cooling airflow through the recirculation passage prior to the inlet of the booster compressor.

9. The bleed air system as recited in claim 8 , wherein the second passage extends through the heat exchanger separate from airflow through the recirculation passage for cooling airflow supplied directly to the pneumatic system from the high pressure section.

10. The bleed air system as recited in claim 8 , including a turbine coupled to drive the booster compressor, the turbine driven by airflow from the main compressor section.

11. The bleed air system as recited in claim 8 , including an electric motor or an accessory gearbox driven through a mechanical coupling to an engine shaft used to drive the booster compressor.

12. A method of controlling engine bleed airflow comprising:
configuring a booster compressor to receive engine bleed air from a low pressure compressor section of gas turbine engine through an inlet;
compressing the engine bleed air from the low pressure section with the booster compressor and supplying the compressed engine bleed air to an outlet passage;
controlling airflow from the outlet passage between a pneumatic system with a recirculation path with a flow splitter valve for directing airflow between from the outlet passage to the pneumatic system and the recirculation passage, wherein a pressure reduction valve is disposed within the recirculation passages for reducing airflow through the recirculation passage to enable mixing with airflow from the low pressure compressor section supplied to the inlet of the booster compressor; and
supplying airflow from the main compressor directly to the pneumatic system and bypassing the booster compressor responsive to airflow from the main compressor being within a predefined temperature range.

13. The method as recited in claim 12 , including cooling airflow in the recirculation passage with a heat exchanger.

14. The method as recited in claim 13 , including routing airflow from the main compressor through the heat exchanger, separate from airflow through the recirculation passage prior to the pneumatic system.

15. The method as recited in claim 13 , including driving a turbine coupled to the booster compressor with airflow from the main compressor and mixing airflow exhausted from the turbine with airflow from the outlet of the booster compressor.

Assignees

• United Technologies Corp

Inventors

• Taylor Stephen H
• Lents Charles E
• Suciu Gabriel L
• Merry Brian D
• Chandler Jesse M

Classifications

• F02C6/08

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

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02K3/06

  with front fan · CPC title

• F02C9/24 Primary

  Control of the pressure level in closed cycles · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title