Supply of air to an air-conditioning circuit of an aircraft cabin from its turboprop engine
View Patent ↗An aircraft turboprop engine ( 310 ) including at least a low-pressure body ( 12 ) and a high-pressure body ( 14 ), possibly also an intermediate-pressure body. At least one of the bodies includes a compressor. The low-pressure body drives a first gearbox ( 16 ) The turboprop engine also includes at least one load compressor ( 60 ) for supplying air to an air-conditioning circuit of an aircraft cabin. A rotor ( 61 ) of the load compressor is coupled to the low-pressure body. The load compressor ( 60 ) includes an air inlet ( 62 ) connected to a conduit ( 72 ) to bleed air from the compressor of the turboprop engine when all of the aforementioned bodies include only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies include at least two compressors.
1. An aircraft turboprop engine comprising at least one low-pressure body and one high-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propulsion propeller by means of a first gearbox mechanically coupled to the propulsion propeller, the turboprop engine further comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means comprise at least one load compressor, the rotor of which is mechanically coupled to a shaft of the low-pressure body by means of said first gearbox, said load compressor comprising an air inlet connected to a single take-off port of the turboprop engine for taking off air from:
the compressor of the low pressure body of the turboprop engine, when the turboprop engine is a double body turboprop engine comprising one low-pressure body and one high-pressure body, or
the compressor of the low-pressure body or of an intermediate-pressure body of the turboprop engine, when the turboprop engine is a triple body turboprop engine comprising one low-pressure body, one intermediate pressure body, and one high-pressure body.
2. The aircraft turboprop engine according to claim 1 , wherein a heat exchanger is mounted upstream or downstream of the load compressor.
3. The aircraft turboprop engine according to claim 2 , wherein each compressor comprises compressor stages and wherein the single take-off port takes off air from at maximum a fourth stage of said compressor stages.
4. The aircraft turboprop engine according to claim 1 , wherein said engine comprises two load compressors and wherein a heat exchanger is mounted between said two load compressors.
5. The aircraft turboprop engine according to claim 4 , wherein said turboprop engine comprises a pneumatic starter, an air inlet of which is connected to a pipe.
6. The aircraft turboprop engine according to claim 5 , wherein the pipe is equipped with a heat exchanger.
7. The aircraft turboprop engine according to claim 6 , wherein each compressor comprises compressor stages and wherein the single take-off port takes off air from at maximum a fourth stage of said compressor stages.
8. The aircraft turboprop engine according to claim 5 , wherein each compressor comprises compressor stages and wherein the single take-off port takes off air from at maximum a fourth stage of said compressor stages.
9. The aircraft turboprop engine according to claim 4 , wherein each compressor comprises compressor stages and wherein the single take-off port takes off air from at maximum a fourth stage of said compressor stages.
10. The aircraft turboprop engine according to claim 1 , wherein the load compressor comprises an air outlet connected to a pipe supplying air to said air-conditioning circuit, said pipe being equipped with at least one regulation means.
11. The aircraft turboprop engine according to claim 10 , wherein each compressor comprises compressor stages and wherein the single take-off port takes off air from at maximum a fourth stage of said compressor stages.
12. The aircraft turboprop engine according to claim 1 , wherein said turboprop engine is configured so that the speed of rotation of the low-pressure body is substantially constant in steps, the speed of rotation of the low-pressure body obeying a discrete speed by which said speed is constant during a same flight phase, whatever the operating conditions.
13. The aircraft turboprop engine according to claim 1 , wherein each compressor comprises compressor stages and wherein the single take-off port takes off air from at maximum a fourth stage of said compressor stages.
14. The aircraft turboprop engine according to claim 1 , wherein said turboprop engine comprises the at least one load compressor having at least two load compressor stages, and wherein a heat exchanger is mounted between said at least two load compressor stages.
15. The aircraft turboprop engine according to claim 1 , wherein a heat exchanger is mounted between said at least one load compressor and:
the compressor of the low pressure body of the turboprop engine, when the turboprop engine is a double body turboprop engine comprising one low-pressure body and one high-pressure body, or
the compressor of the low-pressure body or of the intermediate-pressure body of the turboprop engine, when the turboprop engine is a triple body turboprop engine comprising one low-pressure body, one intermediate pressure body, and one high-pressure body.
16. 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 and one high-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propulsion propeller by means of a first gearbox mechanically coupled to the propulsion propeller wherein said method comprises the steps involving taking off air from:
the compressor of the low pressure body of the turboprop engine, when the turboprop engine is a double body turboprop engine comprising one low-pressure body and one high-pressure body, or
the compressor of the low-pressure body or of an intermediate-pressure body of the turboprop engine, when the turboprop engine is a triple body turboprop engine comprising one low-pressure body, one intermediate pressure body, and one high-pressure body,
for supplying at least one dedicated load compressor, a rotor of which is mechanically coupled to a shaft of the low pressure body by means of said first gearbox, with the air taken off and driving the rotor of said load compressor by means of the low-pressure body of the turboprop engine.
17. An aircraft turboprop engine comprising one low-pressure body and one high-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propulsion propeller by means of a first gearbox mechanically coupled to the propulsion propeller, the turboprop engine further comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means comprise at least one load compressor, the rotor of which is mechanically coupled to a shaft of the low-pressure body by means of said first gearbox, said load compressor comprising an air inlet connected to a single take-off port of the turboprop engine for taking off air from the compressor of the low pressure body of the turboprop engine.
18. An aircraft turboprop engine comprising one low-pressure body, one high-pressure body, and also an intermediate-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propulsion propeller by means of a first gearbox mechanically coupled to the propulsion propeller, the turboprop engine further comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means comprise at least one load compressor, the rotor of which is mechanically coupled to a shaft of the low-pressure body by means of said first gearbox, said load compressor comprising an air inlet connected to a single take-off port of the turboprop engine for taking off air from the compressor of the low-pressure body or of the intermediate-pressure body of the turboprop engine.