Turbojet comprising a bleeding system for bleeding air in said turbojet

Patent metadata

Field	Value
Publication number	US-10012146-B2
Application number	US-201514623152-A
Country	US
Kind code	B2
Filing date	Feb 16, 2015
Priority date	Feb 17, 2014
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

A turbojet comprising a low-pressure compressor, a high-pressure compressor and a bleeding system configured to bleed air in the turbojet and to deliver the air to an air system. The bleeding system comprises a first air intake configured to bleed air at low pressure, a second air intake configured to bleed air at high pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to an outlet of the second valve, a high-pressure valve connected to the second air intake, a control valve connected to the air system, and a controller to control opening and closing of the valves depending on a pressure at the first air intake.

First claim

The invention claimed is:

1. A turbojet comprising:
a low-pressure compressor,
a high-pressure compressor with a plurality of compression stages in which a pressure rises, from upstream to downstream in a direction of displacement of a flow of air, from a low pressure to a high pressure, and
a bleeding system configured to bleed air in the turbojet and to deliver said bled air to an air system, the bleeding system comprising:
a first air intake configured to bleed low-pressure air,
a second air intake configured to bleed high-pressure air in the high-pressure compressor,
a first valve having an inlet fluidically connected to the first air intake,
a second valve having an inlet fluidically connected to the first air intake,
a third compressor having an inlet fluidically connected to an outlet of the second valve,
a check valve having an inlet fluidically connected to an outlet of the first valve and to an outlet of the third compressor, and which prevents air from moving toward the third compressor and the first valve,
a high-pressure valve fluidically connected to the second air intake,
a cooler configured to cool air passing therethrough, an outlet of the high-pressure valve fluidically connected to an inlet of the cooler,
a control valve configured to control a pressure of air passing therethrough, an outlet of the cooler and an outlet of the check valve each fluidically connected to an inlet of the control valve, and an outlet of the control valve fluidically connected to the air system,
a controller configured to control an opening and a closing of the high-pressure valve, the first valve, the second valve and the control valve, and
a pressure sensor configured to measure a pressure value at the first air intake and to transmit information concerning the pressure value to the controller,
wherein the opening and the closing of the high-pressure valve, the first valve, the second valve and the control valve depends on the pressure value measured at the first air intake, and
wherein the inlet of the control valve is configured to receive air from one of the outlet of the first valve and the outlet of the third compressor, depending on the opening and the closing of each of the high-pressure valve, the first valve, and the second valve.

2. The turbojet as claimed in claim 1 , wherein the first air intake is configured to bleed low-pressure air at a plurality of low-pressure stages of the high-pressure compressor.

3. The turbojet as claimed in 1 , wherein the bleeding system further comprises:
a compression valve having an inlet fluidically connected to the outlet of the second valve, and
a turbine having an inlet fluidically connected to an outlet of the compression valve and configured to drive the third compressor,
the controller configured to control an opening and a closing of the compression valve.

4. An aircraft comprising the turbojet as claimed in claim 1 .

5. A method for controlling the turbojet as claimed in claim 1 , the control method comprising:
a first control step during which the controller orders the opening of the first valve, the closing of the second valve, and the closing of the high-pressure valve when the pressure at the first air intake is above a first threshold,
a second control step during which the controller orders the closing of the first valve, the opening of the second valve, and the closing of the high-pressure valve when the pressure at the first air intake is below the first threshold and above a second threshold, and
a third control step during which the controller orders the closing of the first valve, the closing of the second valve, and the opening of the high-pressure valve when the pressure at the first air intake is below the second threshold.

6. The method as claimed in claim 5 , the turbojet further comprising a compression valve and a turbine, and the controller ordering an opening of the compression valve during the second control step.

7. The method as claimed in claim 5 , wherein the first threshold is approximately 20 psia.

8. The method as claimed in claim 5 , wherein the second threshold is approximately 15 psia.

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Pelagatti Olivier
• Deguin Thomas
• Bodet Ronan

Classifications

• F02C9/18

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

• F02C3/10

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

• F02C6/04

  Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output (F02C6/18 takes precedence {; for a fluidised-bed combustor F02C3/205}) · CPC title

• B64D13/02

  the air being pressurised · CPC title

• B64D2013/0648

  with energy recovery means, e.g. using turbines · CPC title