Turbojet comprising a bleeding system for bleeding air in said turbojet

Patent metadata

Field	Value
Publication number	US-9885284-B2
Application number	US-201514623037-A
Country	US
Kind code	B2
Filing date	Feb 16, 2015
Priority date	Feb 17, 2014
Publication date	Feb 6, 2018
Grant date	Feb 6, 2018

Abstract

A turbojet comprising a high-pressure compressor with several compression stages in which the pressure rises in a direction of air flow, from a low pressure to a high pressure, passing through intermediate pressures, and a system to bleed air in the turbojet and deliver the air to an air system. The bleeding system comprises a first air intake to bleed air at low pressure, a second air intake to bleed air at an intermediate pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to the second valve outlet, a high-pressure valve connected to the second air intake, and a control valve connected to the air system, and a controller to control the opening and closing of the valves depending on the pressures at the first and second air intakes.

First claim

The invention claimed is:

1. A method for controlling a turbojet, the turbojet including a high-pressure compressor with a number of compression stages in which pressure rises, from upstream to downstream in a direction of displacement of air, by passing through a succession of pressures, and a bleeding system configured to bleed air in said turbojet and to deliver said bled air to an air system, the bleeding system comprising: a first air intake configured to bleed air at low pressure in the high-pressure compressor, a second air intake configured to bleed air at an intermediate pressure in the high-pressure compressor, a check valve having an inlet fluidically connected to the first air intake and preventing bled air from moving toward the first air intake, a first valve having an inlet fluidically connected to an outlet of the check valve, a second valve having an inlet fluidically connected to the outlet of the check valve, a second compressor having an inlet fluidically connected to an outlet of the second 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 being fluidically connected to an inlet of the cooler, and an outlet of the cooler being fluidically connected to the inlet of the first valve and the outlet of the cooler being fluidically connected to the inlet of the second valve, a control valve configured to control a pressure of a flow of air passing therethrough, an outlet of the first valve and an outlet of the second compressor each being fluidically connected to an inlet of the control valve, and an outlet of the control valve being fluidically connected to the air system, a low-pressure sensor configured to measure a first pressure value at the first air intake and to transmit information concerning the first pressure value to a controller, an intermediate pressure sensor configured to measure a second pressure value at the second air intake and to transmit information concerning the second pressure value to the controller, and the controller being configured to control an opening and closing of each of the high-pressure valve, the first valve, the second valve and the control valve depending on the first pressure value at the first air intake and the second pressure value at the second air intake, and wherein, the method comprises:
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 first pressure value 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 first pressure value at the first air intake is below the first threshold and above a second threshold,
a third control step during which the controller orders the opening of the first valve, the closing of the second valve, and the opening of the high-pressure valve when the first pressure value at the first air intake is below the second threshold and the second pressure value at the second air intake is above the first threshold, and
a fourth control step during which the controller orders the closing of the first valve, the opening of the second valve, and the opening of the high-pressure valve when the second pressure value at the second air intake is below the first threshold and above the second threshold.

2. The method as claimed in claim 1 , wherein the turbojet 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 compressor, and the method further comprises ordering an opening of the compression valve during the second control step and during the fourth control step.

3. The method as claimed in claim 1 , wherein the first threshold is 20 psia.

4. The method as claimed in claim 1 , wherein the second threshold is 15 psia.

5. A turbojet comprising:
a high-pressure compressor with a number of compression stages in which pressure rises, from upstream to downstream in a direction of displacement of air, by passing through a succession of pressures, and
a bleeding system configured to bleed air in said turbojet and to deliver said bled air to an air system, the bleeding system comprising:
a first air intake configured to bleed air at low pressure in the high-pressure compressor,
a second air intake configured to bleed air at an intermediate pressure in the high-pressure compressor,
a check valve having an inlet fluidically connected to the first air intake and preventing bled air from moving toward the first air intake,
a first valve having an inlet fluidically connected to an outlet of the check valve,
a second valve having an inlet fluidically connected to the outlet of the check valve,
a second compressor having an inlet fluidically connected to an outlet of the second 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 being fluidically connected to an inlet of the cooler, the cooler configured to receive air from the high-pressure valve, and an outlet of the cooler being fluidically connected to the inlet of the first valve and the outlet of the cooler being fluidically connected to the inlet of the second valve,
a control valve configured to control a pressure of a flow of air passing therethrough, an outlet of the first valve and an outlet of the second compressor each connected to an inlet of the control valve, and an outlet of the control valve being fluidically connected to the air system,
a low-pressure sensor configured to measure a first pressure value at the first air intake and to transmit information concerning the first pressure value to a controller,
an intermediate pressure sensor configured to measure a second pressure value at the second air intake and to transmit information concerning the second pressure value to the controller, and
the controller being configured to control an opening and closing of each of the high-pressure valve, the first valve, the second valve and the control valve depending on the first pressure value at the first air intake and the second pressure value at the second air intake,
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 second compressor, depending on the controlled opening and closing of each of the high-pressure valve, the first valve, and the second valve.

6. The turbojet as claimed in claim 5 , further comprising:
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 second compressor,
the controller being configured to control an opening and closing of the compression valve.

7. An aircraft comprising the turbojet as claimed in claim 5 .

Assignees

• 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

• B64D2013/0648

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

• B64D13/04

  Automatic control of pressure · CPC title

• B64D2013/0644

  including electric motors or generators · CPC title