Bleed air systems for use with aircraft and related methods

Patent metadata

Field	Value
Publication number	US-9810158-B2
Application number	US-201414242570-A
Country	US
Kind code	B2
Filing date	Apr 1, 2014
Priority date	Apr 1, 2014
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.

First claim

What is claimed is:

1. A bleed air system for an aircraft comprising:
a turbo-compressor comprising a compressor, a turbine, and a first drive shaft coupled between the compressor and the turbine, the first drive shaft to enable the turbine to selectively drive the compressor, the compressor having a compressor inlet and a compressor outlet, the compressor outlet to be fluidly coupled to a system of the aircraft that receives pressurized air, the compressor inlet to receive bleed air from a low-pressure compressor of an engine of the aircraft;
a gearbox operatively coupled to the first drive shaft to drive the compressor, the gearbox operatively coupled to and powered by a second drive shaft extending from the engine; and
a clutch disposed between the first drive shaft and the gearbox to selectively connect the first drive shaft to the gearbox to enable the engine to drive the turbo-compressor.

2. The bleed air system as defined in claim 1 , wherein the system is at least one of an environmental control system or an anti-icing system.

3. The bleed air system as defined in claim 1 , wherein the turbine includes a turbine inlet fluidly coupled to a high-pressure compressor of the engine.

4. The bleed air system as defined in claim 1 further comprising a processor to control the clutch to:
engage the first drive shaft with the gearbox when the aircraft is operating in a first flight condition; and
disengage the first drive shaft from the gearbox when the aircraft is operating in a second flight condition.

5. The bleed air system as defined in claim 4 , wherein the first flight condition occurs when the aircraft is operating at cruise.

6. The bleed air system as defined in claim 5 , wherein the second flight condition occurs when the aircraft is operating at idle or during a descent.

7. The bleed air system as defined in claim 1 further comprising a high pressure air source fluidly coupled to a turbine inlet of the turbine, the high pressure air source to be supplied to the turbine inlet to start the engine.

8. The bleed air system as defined in claim 1 further comprising a passageway to fluidly couple a bleed air port of the engine to an air bearing of the first drive shaft, the passageway to provide pressurized air to operate the air bearing.

9. The bleed air system as defined in claim 1 , wherein the compressor is to be operatively coupled to the engine via a constant gear ratio.

10. An aircraft comprising:
a gas turbine engine including a low-pressure compressor and a combustor downstream from the low-pressure compressor;
a fan disposed upstream from the low-pressure compressor, the fan mechanically coupled to, and driven by, the gas turbine engine;
a turbo-compressor including:
a compressor having a compressor inlet fluidly coupled to the low-pressure compressor of the gas turbine engine and a compressor outlet fluidly coupled to a system of the aircraft; and
a turbine operatively coupled to the compressor to selectively drive the compressor;

a gearbox operatively coupled to the turbo-compressor; and
a clutch disposed between the turbo-compressor and the gearbox to selectively connect the turbo-compressor to the gearbox to enable the gas turbine engine to drive the turbo-compressor.

11. The aircraft as defined in claim 10 further comprising a variable speed transmission disposed between the clutch and the gearbox, the variable speed transmission to operate the compressor at a plurality of different speeds.

12. The aircraft as defined in claim 10 , wherein the turbo-compressor is operatively coupled to a third drive shaft of a high-pressure compressor of the gas turbine engine.

13. A method comprising:
coupling a first drive shaft of a turbo-compressor to a gearbox via a clutch, the turbo-compressor comprising a compressor and a turbine operatively coupled via the first drive shaft, the first drive shaft to enable the turbine to selectively drive the compressor;
coupling the gearbox to a second drive shaft extending from an aircraft engine;
fluidly coupling a compressor outlet of the compressor to a system of an aircraft that is to receive pressurized air;
fluidly coupling a compressor inlet of the compressor to a bleed air port of a low-pressure compressor of the aircraft engine; and
using the clutch to selectively connect the first drive shaft to the gearbox to enable the second drive shaft to power the compressor to supply pressurized air to the system.

14. A method as defined in claim 13 , wherein the second drive shaft is used to power the compressor in a first mode, further comprising using the turbine to power the compressor and supply pressurized air to the system in a second mode.

15. A method as defined in claim 13 further comprising using the turbine of the turbo-compressor to start the engine by supplying pressurized air to a turbine inlet to rotate the first drive shaft.

Assignees

• Boeing Co

Inventors

• Foutch David W
• Mackin Steve G

Classifications

• F02C7/32

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

• F02C3/10

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

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F02C7/047

  Heating to prevent icing · CPC title

• B64D2013/064

  comprising more than one system, e.g. dual systems · CPC title