Propulsion assembly for an aircraft
A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.
1. A propulsion assembly for an aircraft, comprising:
a nacelle,
a propulsion system arranged inside the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle positioned downstream of the combustion chamber and delimited by a rear portion of the fairing, referred to as nozzle wall, and ensuring a discharge of combustion gases originating from combustion of fuel in the combustion chamber,
a fuel tank,
a supply pipe that connects the tank and the combustion chamber,
a cowling sealingly fastened to the nozzle wall and on the outside thereof, wherein the cowling and the nozzle wall define between them a chamber, and
a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall,
wherein the heat exchanger system has a pipe portion arranged in said chamber, and
wherein the exchange of heat energy takes place at this pipe portion,
wherein the nozzle wall has passing therethrough a plurality of orifices that open on one side into the exhaust nozzle and on the other side into the chamber,
wherein the heat exchanger system has a circulation pipe in which a heat transfer fluid circulates, a pump configured to move the heat transfer fluid in the circulation pipe, and a heat exchanger arranged between the supply pipe and the circulation pipe, and
wherein said pipe portion of the heat exchanger system is a portion of the circulation pipe.
2. The propulsion assembly according to claim 1 , wherein the pipe portion of the heat exchanger system has at least one turn that surrounds the nozzle wall.
3. The propulsion assembly according to claim 1 , wherein a diameter of the orifices is between 1 mm and 3 mm.
4. The propulsion assembly according to claim 1 ,
wherein a diameter of the orifices is between 0.4 mm and 1 mm, and
wherein the nozzle wall has passing through it at least one upstream orifice and at least one downstream orifice of which the diameters are between 20 mm and 40 mm.
5. The propulsion assembly according to claim 1 , wherein said pipe portion of the heat exchanger system is constituted of a single continuous duct.
6. An aircraft having at least one propulsion assembly according to claim 1 .
7. A propulsion assembly for an aircraft, comprising:
a nacelle,
a propulsion system arranged inside the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle positioned downstream of the combustion chamber and delimited by a rear portion of the fairing, referred to as nozzle wall, and ensuring a discharge of combustion gases originating from combustion of fuel in the combustion chamber,
a fuel tank,
a supply pipe that connects the tank and the combustion chamber,
a cowling sealingly fastened to the nozzle wall and on the outside thereof, wherein the cowling and the nozzle wall define between them a chamber, and
a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall,
wherein the heat exchanger system has a pipe portion arranged in said chamber, and
wherein the exchange of heat energy takes place at this pipe portion,
wherein the nozzle wall has passing therethrough a plurality of orifices that open on one side into the exhaust nozzle and on the other side into the chamber,
wherein a diameter of the orifices is between 0.4 mm and 1 mm, and
wherein the nozzle wall has passing through it at least one upstream orifice and at least one downstream orifice of which the diameters are between 20 mm and 40 mm.
8. The propulsion assembly according to claim 7 , wherein the pipe portion of the heat exchanger system is a portion of the supply pipe.
9. The propulsion assembly according to claim 8 , further comprising:
a leak detector provided at said pipe portion,
a controller connected to the leak detection means, and
a valve mounted on the supply pipe downstream of the pipe portion and made to open and close by the controller.