Patent Application
20190285000
This application claims the benefit of the French patent application No. 1852135 filed on Mar. 13, 2018, the entire disclosures of which are incorporated herein by way of reference.
The present invention relates to a propulsion system for an aircraft comprising a dual-flow jet engine and an air-drawing system with reduced bulk. The present invention relates also to an aircraft comprising at least one such propulsion system.
The dual-flow jet engine conventionally comprises an engine core supplied with air by a fan and comprising a compression stage, a combustion stage and an exhaust stage.
The air-drawing system 500 draws hot air from the dual-flow jet engine at the compression stage 504 and delivers it to an air system 506, such as, for example, the conditioned-air system of the cabin of the aircraft.
To regulate the temperature of the hot air thus delivered to the air system 506, the air from the compression stage 504 passes through a heat exchanger 508 which is supplied also with cold air drawn from the secondary jet 510 of the dual-flow jet engine.
After having passed through the heat exchanger 508 and having picked up calories from the hot air, the cold air which has thus been reheated is discharged outwards through an openwork grating 512 arranged on the surface of the pylon.
The flow of cold air from the secondary jet 510 is regulated by a valve 514 which is controlled by a motor 516 which controls the opening or the closing of the valve 514 according to the temperature requirements of the air system 506.
Although such an installation gives good results, it is relatively bulky, in particular because the dual-flow jet engines have increasingly great diameters. Indeed, because of this dimensional increase, the dual-flow jet engine is fixed as close as possible to the air foil, which reduces the space available for the drawing system.
One object of the present invention is to propose a propulsion system for an aircraft comprising a dual-flow jet engine and an air-drawing system with reduced bulk.
To this end, there is proposed a propulsion system for an aircraft comprising an air system, said propulsion system comprising:
the propulsion system being characterized in that the air-drawing system comprises a shutter which is arranged at the openwork grating and which is displaced by a motor between an open position in which the shutter does not block the holes of the openwork grating and a closed position in which the shutter blocks the holes of the openwork grating.
The shutter makes it possible, depending on whether it is open or closed, to regulate the flow of cool air entering into the heat exchanger and allows for a space saving.
Advantageously, the shutter is mounted to be translationally mobile against the openwork grating on the interior side of said openwork grating.
Advantageously, the motor is arranged outside the cold pipeline, the propulsion system comprises a rod which transmits the movements of the motor to the shutter and the propulsion system comprises a sealing system installed at the point where the rod passes through the wall of the cold pipeline.
The invention also proposes an aircraft comprising an air system and at least one propulsion system according to one of the preceding variants.
The features of the invention mentioned above, and others, will become more clearly apparent on reading the following description of an exemplary embodiment, the description being given in relation to the attached drawings, in which:
In the following description, the terms relating to a position are taken with reference to an aircraft in normal position of advance, that is to say as is represented in
Throughout the following description, by convention, the direction X corresponds to the longitudinal direction of the dual-flow jet engine 110, this direction being parallel to the longitudinal axis of the aircraft 100. Also, the direction Y corresponds to the direction oriented transversely relative to the dual-flow jet engine 110, and the direction Z corresponds to the vertical direction or to the height, these three directions X, Y, Z being mutually orthogonal.
The propulsion system 120 comprises a fairing 112 which constitutes the outer skin of the dual-flow jet engine 110 and of the pylon 106 and which has an openwork grating 114 having holes that are here in the form of slits. In the embodiment of the invention presented in
The dual-flow jet engine 110 comprises an engine core supplied with air by a fan and comprising a compression stage 202 (
The air-drawing system 200 draws hot air from the dual-flow jet engine 110 at the compression stage 202 and delivers it to an air system 206, such as, for example, the conditioned-air system of the cabin of the aircraft 100.
To regulate the temperature of the hot air thus delivered to the air system 206, the air-drawing system 200 comprises a heat exchanger 208 which is thus supplied with hot air from the compression stage 202 and with cold air drawn from the secondary jet 204 of the dual-flow jet engine 110.
After having passed through the heat exchanger 208 and having picked up calories from the hot air, the cold air which has thus been reheated is discharged to the outside through the openwork grating 114.
Thus, the air-drawing system 200 comprises a hot pipeline 250 fluidically connected between the compression stage 202 and the air system 206, and passing through the heat exchanger 208, and a cold pipeline 252 fluidically connected between the secondary jet 204 and the openwork grating 114 and passing through the heat exchanger 208. The heat exchange which takes place in the heat exchanger 208 is effected between the cold air present in the cold pipeline 252 and the hot air present in the hot pipeline 250. The cold pipeline 252 widens at the openwork grating 114 in order to encompass all of the openwork grating 114.
To regulate the flow of cold air from the secondary jet 204, the air-drawing system 200 comprises a shutter 210 which is arranged at the openwork grating 114. The shutter 210 is mobile between an open position in which the shutter 210 does not block the holes of the openwork grating 114 and a closed position in which the shutter 210 blocks the holes of the openwork grating 114. Thus, in open position, the air from the heat exchanger 208 passes through the openwork grating 114 and, in closed position, the air from the heat exchanger 208 does not pass through the openwork grating 114.
The position of the shutter 210 is controlled by a motor 212 which displaces the shutter 210 from the open position to the closed position and vice versa and can make it take different intermediate positions between these two extreme positions. The motor 212 is controlled by a control unit of the aircraft 100 according to the temperature requirements of the air system 206.
When the shutter 210 is in open position, the air from the secondary jet 204 can be discharged through the holes of the openwork grating 114, and there is then creation of an air flow from the secondary jet 204 to the openwork grating 114 through the heat exchanger 208 by virtue of the pressure difference between the outside pressure and the pressure in the secondary jet 204.
Conversely, when the shutter 210 is in closed position, the air from the secondary jet 204 has no opening to be discharged, and there is therefore no flow of air in the heat exchanger 208.
The incorporation of the discharge and regulation function at the openwork grating 114 allows for a space saving, which facilitates the incorporation of the air-drawing system 200 in the propulsion system 120. In particular, it is possible to distance the heat exchanger 208 from the wing 104, which limits the impact of the air from the openwork grating 114 on the wing 104, and access to the air-drawing system 200 is facilitated since it is accessible directly by the removal of the cover forming the openwork grating 114.
According to the embodiment of the invention presented here, the shutter 210 is mounted to be translationally mobile between the open position and the closed position, in a direction parallel to the longitudinal axis x. The translation of the shutter 210 is produced by any appropriate guideway systems.
To limit the impact of the shutter 210, the latter is arranged on the interior side of said openwork grating 114.
Obviously, it is possible to provide a different displacement of the shutter 210 such as, for example, a rotational or translational displacement in a different direction.
In the embodiment of the invention presented in
If the motor 212 is arranged inside the cold pipeline 252, in particular at the point where it widens in the vicinity of the openwork grating 114, it is not necessary to provide for the rod to pass through the wall of the cold pipeline 252, or a sealing system.
While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.
| Number | Date | Country | Kind |
|---|---|---|---|
| 1852135 | Mar 2018 | FR | national |
