Supply of air to an air-conditioning circuit of an aircraft cabin from its turboprop engine

Patent metadata

Field	Value
Publication number	US-10703487-B2
Application number	US-201515115116-A
Country	US
Kind code	B2
Filing date	Jan 29, 2015
Priority date	Jan 31, 2014
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

Abstract

An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

First claim

The invention claimed is:

1. An aircraft turboprop engine comprising at least one low-pressure body comprising one turbine rotor and one high-pressure body comprising a compressor rotor and a turbine rotor connected to each other by a shaft, the low-pressure body further comprising a shaft connecting the turbine rotor to a gearbox driving a propulsion propeller, said gearbox being a single gearbox, the turboprop engine further comprising means, an air inlet of which is supplied with air by a conduit and an outlet of which is connected to a pipe that supplies air to an air-conditioning circuit of an aircraft cabin, wherein said means comprise at least one air compressor comprising the air inlet and the air outlet, said at least one air compressor being carried by said gearbox, and a rotor of said at least one compressor being mechanically coupled in said gearbox to a shaft of the propulsion propeller driven by the low-pressure body.

2. The turboprop engine according to claim 1 , wherein the air inlet of the at least one air compressor is connected to an air inlet sleeve of the turboprop engine for taking off air from the turboprop engine.

3. The turboprop engine according to claim 1 , wherein the air inlet of the at least one air compressor is connected to a compressor of the turboprop engine for taking off air from the turboprop engine.

4. The turboprop engine according to claim 1 , wherein the air inlet of the at least one air compressor is connected to the outside of the turboprop engine for taking off air outside the turboprop engine.

5. The turboprop engine according to claim 2 , wherein a heat exchanger is either mounted between the air inlet of the at least one air compressor and the means for taking off air or between two compressors or between two compressor stages.

6. The turboprop engine according to claim 1 , wherein the pipe connected to said air-conditioning circuit is equipped with at least one regulation means such as a valve.

7. The turboprop engine according to claim 6 , wherein said turboprop engine comprises a pneumatic starter, an air inlet of which is connected to said pipe.

8. The turboprop engine according to claim 6 , wherein the pipe is equipped with a heat exchanger.

9. The turboprop engine according to claim 1 , wherein the engine is configured so that the speed of rotation of the low-pressure body is substantially constant whatever the operating conditions.

10. The turboprop engine according to claim 1 , wherein the rotor of said at least one air compressor is connected to the gearbox by a gear train comprising pinions, and preferably without a radial shaft.

11. A method for supplying air to an air-conditioning circuit of a cabin of an aircraft that is equipped with at least one turboprop engine comprising at least one low-pressure body comprising one turbine rotor and one high-pressure body comprising a compressor rotor and a turbine rotor connected to each other by a shaft, the low pressure body comprising a shaft connecting the turbine rotor to a gearbox driving a propulsion propeller, wherein the air-conditioning circuit is supplied with air by at least one dedicated air compressor, said at least one dedicated air compressor being carried by said gearbox and the rotor of said at least one dedicated air compressor being coupled to the low-pressure body by means of said gearbox.

Assignees

• Safran Aircraft Engines
• Safran
• Safran Power Units

Inventors

• Parmentier Nicolas Claude
• Froment Pierre
• Rideau Jean-François
• Thoraval Bruno

Classifications

• Y02T50/60

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

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title

• B64D13/02

  the air being pressurised · CPC title

• F04D29/5833

  flow schemes and regulation thereto · CPC title

• F05D2240/60

  Shafts · CPC title