Gas turbine engine with compressor bleed valve including at least two open positions

Patent metadata

Field	Value
Publication number	US-11248535-B2
Application number	US-201916401225-A
Country	US
Kind code	B2
Filing date	May 2, 2019
Priority date	May 31, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

A gas turbine engine comprising: a compressor; a first turbine; and a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; wherein the first compressor bleed valve is configured to release bleed air to a downstream location in the engine, the downstream location being downstream of the first turbine; wherein the first compressor bleed valve is configured to open wherein the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a compressor;
a turbine;
a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor;
a second compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor;
a bypass duct configured to carry a bypass airflow;
a first bleed duct; and
a second bleed duct; wherein
the first compressor bleed valve is configured to release bleed air to a downstream location in the engine through the first bleed duct, the downstream location being downstream of the turbine;
the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor, and configured to close;
the second compressor bleed valve is located downstream of the first compressor bleed valve; and
the second compressor bleed valve is configured to release bleed air into the bypass airflow through the second bleed duct.

2. The gas turbine engine according to claim 1 , wherein:
the compressor is a multi-stage compressor; and
the second compressor bleed valve is located at a higher stage of the compressor than the first compressor bleed valve.

3. The gas turbine engine according to claim 1 , wherein a portion of the first bleed duct passes through the second bleed duct, and the first and second bleed ducts are not in fluid communication with each other.

4. The gas turbine engine according to claim 1 , wherein the bypass duct comprises a deflector configured to deflect bleed air from the second compressor bleed valve in order to promote mixing of the bleed air with the air in the bypass duct.

5. The gas turbine engine according to claim 1 , wherein the downstream location is a tail bearing housing.

6. The gas turbine engine according to claim 1 , wherein the turbine is a low pressure turbine,
wherein the engine further comprises a high pressure turbine.

7. The gas turbine engine according to claim 1 , wherein:
the first compressor bleed valve comprises a multi-position bellcrank and a flapper; and
the bellcrank is configured to control the position of the flapper to control the opening amount of the first compressor bleed valve.

8. The gas turbine engine according to claim 7 , wherein the position of the multi-position bellcrank is controlled by an actuator.

9. The gas turbine engine according to claim 1 , wherein the first compressor bleed valve is configured to move to an opening amount which is continuously variable between fully open and fully closed.

10. The gas turbine engine according to claim 1 , wherein:
the opening amount of the first compressor bleed valve is controlled by a difference in pressure of a control fluid across a control component separate from the first compressor bleed valve and mechanically coupled to the first compressor bleed valve; and
the difference in pressure across the control component is controlled by metered flow of a control fluid from a hydromechanical device.

11. The gas turbine engine according to claim 10 , wherein the control fluid is a hydraulic fluid.

12. The gas turbine engine according to claim 10 , wherein the control fluid is fuel.

13. The gas turbine engine according to claim 1 , wherein:
the opening amount of the first compressor bleed valve is controlled by a difference in pressure of a control fluid across a control component mounted to the first compressor bleed valve, the control fluid being supplied from a central source of pressurised control fluid; and the difference in pressure is controlled by a hydromechanical device.

14. The gas turbine engine according to claim 1 , wherein the engine comprises:
a high pressure turbine;
a low pressure turbine;
a low pressure compressor; and
a high pressure compressor;
wherein the compressor with which the first compressor bleed valve is in fluid communication is the high pressure compressor; and
the turbine downstream of which the downstream location is located is the high pressure turbine.

15. The gas turbine engine according to claim 14 , further comprising a core shaft connecting the low pressure turbine to the low pressure compressor;
wherein the high pressure turbine, low pressure compressor, low pressure turbine, high pressure compressor and core shaft are comprised in an engine core;
wherein the engine further comprises:
a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and
a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft.

16. The gas turbine engine according to claim 15 , wherein:
the core shaft is a first core shaft;
the engine comprises a second core shaft connecting the high pressure turbine to the high pressure compressor; and
the high pressure turbine, high pressure compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.

Assignees

• Rolls Royce Plc

Inventors

• Peace Richard
• Goulds Robert

Classifications

• F05D2270/3015

  differential pressure · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F02C9/18 Primary

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F04D27/023

  Details or means for fluid extraction · CPC title