Methods and apparatus to adjust bleed ports on an aircraft engine

Patent metadata

Field	Value
Publication number	US-9657647-B2
Application number	US-201414189846-A
Country	US
Kind code	B2
Filing date	Feb 25, 2014
Priority date	Oct 15, 2013
Publication date	May 23, 2017
Grant date	May 23, 2017

Abstract

Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A 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. The apparatus includes 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 for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.

First claim

The invention claimed is:

1. An apparatus for bleeding air from a multi-stage compressor of an aircraft engine, the apparatus comprising:
a compressor case comprising a plurality of bleed ports, 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 for providing 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 portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port, the portion being movable between a first position in which the portion is associated with the first bleed port to a second position in which the portion is associated with the second bleed port.

2. The apparatus of claim 1 , wherein the portion includes a first portion and a second portion, the second portion proximate the second bleed port and operable to prevent fluid flow through the second bleed port.

3. The apparatus of claim 2 , wherein the first portion is controllable independently from the second portion.

4. The apparatus of claim 1 , further comprising a guide between the first position and the second position.

5. An apparatus, comprising:
a compressor of a turbofan engine, the compressor comprising a compressor case including a first aperture and a second aperture, the first aperture being associated with one of a plurality of stages of the compressor, the second aperture being associated with another one of the plurality of stages of the compressor;
a bleed band comprising a first end and a second end, the bleed band to at least partially surround the compressor case, the bleed band being movable between a first location associated with the first aperture to a second location associated with the second aperture; and
an actuator coupled to the first end of the bleed band, the actuator to move the first end between a first position in which the bleed band at least partially covers the first aperture to substantially prevent fluid flow through the first aperture to a second position in which the bleed band is disposed a distance apart from the first aperture to enable fluid flow through the first aperture.

6. The apparatus of claim 5 , wherein the bleed band further comprises a protrusion configured to be received in the first aperture when the bleed band is in the first position.

7. A method for selecting a bleed stage of an engine of an aircraft, the method comprising:
flowing fluid through a compressor of the engine, the compressor including a first compressor stage, a second compressor stage, a compressor case surrounding the compressor and first and second bleed ports associated with the first and second compressor stages, respectively;
bleeding at least a portion of the fluid through the first bleed port or the second bleed port into a plenum fluidly coupling the first and second bleed ports to a system of the aircraft; and
actuating a bleed port selection mechanism disposed within the plenum to at least partially prevent fluid flow through one of the first bleed port or the second bleed port without affecting fluid flow through the other one of the first bleed port or the second bleed port, the actuating of the bleed port selection mechanism includes moving a portion of the bleed port selection mechanism between a first position in which the portion is associated with the first bleed port to a second position in which the portion is associated with the second bleed port.

8. The method of claim 7 , wherein the actuating of the bleed port selection mechanism occurs while the engine is idling.

9. The apparatus of claim 1 , wherein the portion is a bleed band, when the bleed band is in the first position, the bleed band to prevent the fluid flow through the first bleed port, when the bleed band is in the second position, the bleed band to prevent the fluid flow through the second bleed port.

10. The apparatus of claim 2 , further including a bleed band comprising the first portion and the second portion.

Assignees

• Boeing Co

Inventors

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

Classifications

• F04D27/0215

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

• F01D17/105

  by passing part of the fluid · CPC title

• B64D15/04

  Hot gas application · CPC title

• F02C6/08

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