Methods and apparatus to adjust bleed ports on an aircraft engine

Patent metadata

Field	Value
Publication number	US-10626801-B2
Application number	US-201715489383-A
Country	US
Kind code	B2
Filing date	Apr 17, 2017
Priority date	Oct 15, 2013
Publication date	Apr 21, 2020
Grant date	Apr 21, 2020

Abstract

An example method to extract bleed air from an aircraft engine includes extracting, via a plenum positioned in a compressor of the aircraft engine, bleed air from a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor. The plenum is configured to combine the extracted bleed air from the first and second bleed ports and fluidly couple the extracted bleed air to one or more systems of an aircraft. The method includes regulating a pressure of the extracted bleed air in the plenum by adjusting a flow of bleed air through the first bleed port via a first valve associated with the first bleed port and adjusting a flow of bleed air through the second port via a second valve associated with the second bleed port.

First claim

The invention claimed is:

1. A method to extract bleed air from an aircraft engine, the method comprising:
extracting, via a plenum positioned in a compressor of the aircraft engine, bleed air from a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor, the plenum configured to combine the extracted bleed air from the first and second bleed ports and fluidly couple the extracted bleed air to one or more systems of an aircraft; and
regulating a pressure of the extracted bleed air in the plenum by adjusting a flow of bleed air through the first bleed port via a first valve associated with the first bleed port and adjusting a flow of bleed air through the second port via a second valve associated with the second bleed port, the first valve including a first pair of sleeves and the second valve including a second pair of sleeves, and the regulating of the pressure of the extracted bleed air includes moving at least one of the first pair of sleeves to control the flow of bleed air through the first bleed port or the second pair of sleeves to control the flow of bleed air through the second bleed port.

2. The method of claim 1 , further including controlling the first valve and the second valve simultaneously to adjust the flow of bleed air through the respective first and second bleed ports to regulate the pressure of the extracted bleed air in the plenum.

3. The method of claim 1 , further including controlling the first valve independently relative to the second valve to adjust the flow of bleed air through the respective first and second bleed ports to regulate the pressure of the extracted bleed air in the plenum.

4. The method of claim 1 , wherein the first stage provides bleed air having a first pressure and the second stage provides bleed air having a second pressure, the second pressure being greater than the first pressure, and wherein regulating the pressure of the extracted bleed air includes regulating the pressure such that pressure of the extracted bleed air within the plenum is between the first pressure and the second pressure.

5. The method of claim 1 , wherein regulating the pressure of the extracted bleed air in the plenum occurs during operation of the aircraft engine.

6. The method of claim 1 , wherein the first stage provides bleed air having a first pressure and the second stage provides bleed air having a second pressure, the second pressure being higher than the first pressure, and further including moving the first valve towards a closed position to restrict bleed air from the first bleed port to the plenum and simultaneously moving the second valve towards an open position to allow bleed air from the second bleed port to the plenum to increase the pressure of the extracted bleed air in the plenum.

7. An apparatus for bleeding air from a multi-stage compressor of an aircraft engine, the apparatus comprising:
a compressor including a first bleed port and a second bleed port, wherein the first bleed port is associated with a first stage of a compressor and a second bleed port is associated with a second stage of the compressor;
a fluid conduit to channel bleed air from at least one of the first bleed port or the second bleed port to one or more systems of an aircraft;
a bleed port selection mechanism proximate the first bleed port and the second bleed port, the bleed port selection mechanism including a first valve having a first pair of sleeves associated with the first bleed port to control fluid flow from the first bleed port to the fluid conduit, and a second valve having a second pair of sleeves associated with the second bleed port to control fluid flow from the second bleed port to the fluid conduit; and
a control system configured to:
extract bleed air from at least one of the first bleed port associated with the first stage of the compressor or the second bleed port associated with the second stage of the compressor via the bleed port selection mechanism, the bleed port selection mechanism configured to combine the extracted bleed air from the first and second bleed ports; and
regulate a pressure of the extracted bleed air by adjusting a flow of bleed air through the first bleed port and the second port, wherein the adjusting of the flow of bleed air through the first bleed port and the second bleed port includes moving at least one of the first pair of sleeves to control a flow of bleed air through the first bleed port or the second pair of sleeves to control a flow of bleed air through the second bleed port.

8. The apparatus of claim 7 , wherein the first pair of sleeves includes a first sleeve and a second sleeve, the first sleeve being concentric relative to the second sleeve, and wherein the first sleeve includes a first aperture and the second sleeve includes a second aperture.

9. The apparatus of claim 8 , wherein the first sleeve is to move relative to the second sleeve between a first position at which the first aperture and the second aperture align to enable fluid flow from the first bleed port to the fluid conduit, and a second position at which the first aperture is not aligned with at least one of the second aperture or an outlet of the first bleed port to restrict fluid flow from the first bleed port to the fluid conduit.

10. The apparatus of claim 7 , wherein the second pair of sleeves includes a third sleeve and a fourth sleeve, the third sleeve being concentric relative to the fourth sleeve, and wherein the third sleeve includes a third aperture and the fourth sleeve includes a fourth aperture.

11. The apparatus of claim 10 , wherein the third sleeve is to move relative to the fourth sleeve between a first position at which the third aperture and the fourth aperture align to enable fluid flow from the second bleed port to the fluid conduit, and a second position at which the third aperture is not aligned with at least one of the fourth aperture or an outlet of the second bleed port to restrict fluid flow from the second bleed port to the fluid conduit.

12. The apparatus of claim 7 , further comprising an actuator associated with at least one of the first pair of sleeves or the second pair of sleeves, the actuator configured to move the at least one of the first pair of sleeves or the second pair of sleeves relative to the first bleed port or the second bleed port, respectively.

13. The apparatus of claim 7 , wherein the first pair of sleeves is controllable independently from the second pair of sleeves.

14. The apparatus of claim 7 , further comprising a linkage assembly coupled to the first pair of sleeves and the second pair of sleeves to enable simultaneous control of the first pair of sleeves and the second pair of sleeves.

15. An apparatus, comprising:
a compressor case including a first bleed port associated with a first stage of a compressor and a second bleed port associated with a second stage of the compressor;
a plenum connected to the compressor case to define a plenum cavity, the plenum fluidly coupling the first and second bleed ports to a fluid conduit to provide bleed air to one or more systems of an aircraft; and
a bleed port selection mechanism located within the plenum cavity, the bleed port selection mechanism including a first valve associated with the first bleed port and a second valve associated with the second bleed port, the first valve including a first sleeve and a second sleeve, the first sleeve having a first aperture and the second sleeve having a second aperture, the bleed port selection mechanism is to move at least one of the first sleeve or the second sleeve relat

Assignees

• Boeing Co

Inventors

• Mackin Steve G
• Thomas Sean C
• Debronsky Brian W

Classifications

• B64D27/16

  of jet type · CPC title

• F01D17/105

  by passing part of the fluid · CPC title

• F04D27/023

  Details or means for fluid extraction · CPC title

• F04D27/0215

  Arrangements therefor, e.g. bleed or by-pass valves · CPC title

• F05D2270/65

  Pneumatic actuators · CPC title