Aircraft bleed air and engine starter systems and related methods

Patent metadata

Field	Value
Publication number	US-10100744-B2
Application number	US-201514744398-A
Country	US
Kind code	B2
Filing date	Jun 19, 2015
Priority date	Jun 19, 2015
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

Example bleed air and engine starter systems are described herein that employ a shaft-driven compressor to start an aircraft engine and/or to supply pressurized air to one or more systems of an aircraft. An example compressor includes a housing and an impeller disposed within a cavity of the housing. The impeller is operatively coupled to a drive shaft. The compressor includes a first port in the housing to direct onto the impeller to rotate the impeller when the compressor is operating in a first mode. In the first mode, the impeller is to drive the drive shaft. The compressor also includes a second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode. In the second mode, the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air.

First claim

What is claimed is:

1. A compressor comprising:
a housing;
an impeller disposed within a cavity of the housing, the impeller operatively coupled to a drive shaft;
a first port in the housing oriented to provide air to the impeller when the impeller is operating in a first mode, wherein in the first mode the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air; and
a second port in the housing to direct air onto the impeller to rotate the impeller when the compressor is operating in a second mode, wherein in the second mode the impeller is to drive the drive shaft, wherein the second port includes a plurality of nozzles disposed around the cavity and oriented to direct air onto the impeller.

2. The compressor of claim 1 , wherein the impeller has a first end and a second end opposite the first end, the second port positioned to direct air onto the impeller in a location between the first end and the second end of the impeller.

3. The compressor of claim 2 , wherein the first port is positioned adjacent the first end of the impeller.

4. The compressor of claim 1 further including a manifold, the plurality of nozzles fluidly coupled to the manifold.

5. The compressor of claim 1 , wherein the first port is aligned with a rotational axis of the impeller.

6. The compressor of claim 1 , wherein the impeller is to rotate in one direction when the compressor is operating in the first mode and the impeller is to rotate in an opposite direction when the compressor is operating in the second mode.

7. A compressor comprising:
a housing;
an impeller disposed within a cavity of the housing, the impeller operatively coupled to a drive shaft;
a first port in the housing oriented to provide air to the impeller when the impeller is operating in a first mode, wherein in the first mode the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air; and
a second port in the housing to direct air onto the impeller to rotate the impeller when the compressor is operating in a second mode, wherein in the second mode the impeller is to drive the drive shaft, wherein the drive shaft is a drive shaft of an aircraft engine, and wherein the impeller is operatively coupled to the drive shaft of the aircraft engine during the first mode and the second mode.

8. An apparatus comprising:
a compressor having a compressor inlet and a compressor outlet, the compressor operatively coupled to an engine of an aircraft via a drive shaft;
a first conduit to fluidly couple a low-pressure bleed air port from the engine to the compressor inlet;
a second conduit to fluidly couple the compressor outlet to a system of the aircraft to receive pressurized air; and
a third conduit to fluidly couple a high pressure air source to the compressor, wherein the compressor is to be driven by the drive shaft during a first operation, and the compressor is to drive the drive shaft during a second operation.

9. The apparatus of claim 8 , wherein the third conduit is fluidly coupled to a nozzle disposed within a cavity of the compressor, the nozzle located between the compressor inlet and the compressor outlet.

10. The apparatus of claim 8 , wherein the compressor includes an impeller, and wherein the impeller is to rotate in one direction during the first operation and in the opposite direction during the second operation.

11. The apparatus of claim 8 , wherein the first operation occurs when the aircraft is operating at cruise and the second operation is an engine startup operation.

12. The apparatus of claim 8 further including a reverse gear operatively coupled between the compressor and the drive shaft, the reverse gear to reverse a direction of rotation supplied to the drive shaft by the compressor during the second operation.

13. The apparatus of claim 8 further including a valve disposed in the third conduit, the valve to be in a closed position during the first operation.

14. A method comprising:
directing low pressure air into a compressor inlet of a compressor during a first operation, the compressor having an impeller in a housing, the impeller operatively coupled to an aircraft engine via a drive shaft, the impeller to be driven by the aircraft engine during the first operation to increase a pressure of the low pressure air to a higher pressure at a compressor outlet of the compressor; and
directing high pressure air into the compressor to rotate the impeller during a second operation.

15. The method of claim 14 , wherein the impeller rotates in one direction during the first operation and in an opposite direction during the second operation.

16. The method of claim 14 , wherein the compressor includes a plurality of nozzles disposed around the impeller between the compressor inlet and the compressor outlet.

17. The method of claim 16 , wherein the high pressure air is to be directed through the nozzles and onto blades of the impeller to rotate the impeller during the second operation.

18. The method of claim 14 , wherein the second operation is an engine startup operation.

19. The method of claim 18 , wherein the first operation occurs when the aircraft engine is operating at a cruise speed.

Assignees

• Boeing Co

Inventors

• Mackin Steve G
• Foutch David W
• Landre Eric G

Classifications

• F02C6/08

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

• F02C7/27 Primary

  Fluid drives (turbine starters F02C7/277) · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

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