FR2554172A1 - AIR INTAKE FILTER FOR AIRCRAFT ENGINES, PARTICULARLY FOR HELICOPTER ENGINES - Google Patents

Abstract

AN AIR INTAKE FILTER 4 FOR AN AIRCRAFT ENGINE, MORE PARTICULARLY FOR A HELICOPTER ENGINE, IS PROVIDED IN WHICH A BOX 5 WITH ITS OWN INTERIOR COMPARTMENT 14, 15 IS SPECIALLY SHAPED IN A MANNER TO BE DEFINED, BEFORE ADMISSION OF 'AIR RESPECTIVE 2, A BEDROOM 36 COMMUNICATING WITH THE EXTERIOR THROUGH SEPARATION CHANNELS 37 WHICH EXTEND THROUGH COMPARTMENT 14, 15 AND COMMUNICATE WITH THIS, THE COMPARTMENT COMMUNICATING WITH THE EXTERIOR BY A DUCT 22 WHICH SUPPORTS ONE FAN 31.

Description

2S54172

  1. The present invention relates to a filter

  air intake for aircraft engines and, more particularly

  lorely, for helicopter engine. On a plane,

  as in any other motor vehicle, one must be sure

  rer that the air admitted into the engine does not contain any impurities, their presence could damage the engine or have a negative effect on its performance and efficiency. Filtering the intake air of an engine

  is particularly important in the case of helicopters

  because of their ability to function close

  ground and the presence of dust raised by the rotors, especially when flying over

  dry or sandy terrain.In helicopter types-

  res known, the engine air intake is general-

  protected by filters, which generally include-

  a dust separation box, in which

  intake air is introduced. As the air passes through the boot, there is 2 suspended dust.

  extracted and trapped inside the bowl itself

  you. The latter has a drainage orifice which allows trapped dust to be evacuated under pressure, the pressure generally being established inside the box by connecting it, by means of an external pipe.

  re either to the engine exhaust pipes or to the

helicopter weavers.

  The types of filters known, mentioned above,

  suffer from a number of disadvantages, in particular

  link in terms of dimensions and weight, and the problem that being equipped with an outer pipe, they are in one piece with the helicopter and not constitute a separate unit, allowing to have a set free of trouble and easy to maintain or to constitute an accessory which should only be used when it is needed. The object of the present invention is a filter

  not suffering from any of the disadvantages mentioned above.

  According to the present invention, an ad filter

  air mission for aircraft engines, more particularly-

  for helicopter engine, is characterized in that

  that it includes, in combination, a bootmaker having a com-

  interior compartment designed to define a chamber at the front of a respective air intake of a motor of the dust separation channels passing through the housing for

  make the room communicate with the outside, each room

  communicating with the interior compartment, and a

  dust exhaust pipe extending to the ex-

  inside of the bootmaker and communicating with the compartment; a fan rotating inside the exhaust pipe, and an mpyen. actuation supported by the

  case to control the fan.

  The present invention will be well understood during

  the following description made in conjunction with the drawings

attached in which:

  Figure 1 is a sectional view, with parts

  parts omitted in order to make it clearer, of a part 3. of a helicopter comprising a filter according to the present invention; Figure 2 is a side view of a detail of Figure 1; Figure 3 is an end view of the detail of

Figure 2.

  In Figure 1, reference 1 represents a fuser-

  helicopter flight which generally includes, at its

  met, a compartment 2 containing the entry of an admission-

  air flow 3 for the drive motor (not shown)

  ment of the rotor (not shown) of the helicopter. Compartment 2 is fully protected outside by

  a filter, represented as a whole by the reference-

  this 4, which comprises a box 5 having in essential section-

  L-shaped and includes an upper arm 6 extending outward from a first point

  of fuselage 1 in a direction essentially horizontal-

  tale and a lateral arm 7 communicating with the outer lateral end of the arm 6 and extending downward from this end to. a second point of

fuselage 1.

  The arm 6 has essentially the shape of a parallel

  the rectangular elepiped, bounded by an upper wall 8, a lower wall 9 opposite the compartment 2 and essentially parallel to the wall 8 and an inner side wall 10 along the upper side edge

  on which is provided a support 11 designed to allow

  be the articulation, by making it easily removable, of the filter 4 on the fuselage 1. The arm 6 is limited to

  front and rear by two walls 12 and 13, essen-

  tally in the shape of an L when viewed from above and which extend to the arm 7. With the walls 8, 9 and 10, the walls 12 and 13 define a compartment 14 in the form of a substantially rectangular parallelepiped,

  including an outer lateral end opposite to the side

  king 10, communicates with the upper end of an 4. inner compartment 15 of the arm 7 limited to the ends

  front and rear through walls 12 and 13.

  The compartment 15 is limited by an inner side wall 16 and an outer side wall 17, joined, respectively, to the outer ends of the

  walls 9 and 8 and joined by a lower wall 18, comprising

  externally carrying an angle 19 designed to be

  removably connected to the fuselage 1.

  At the lower end, compartment 15

  has a projecting part 20 which communicates externally

  rement through a round hole 21 formed in

  the wall 17 and in which the internal end is engaged

  of a pipe 22. The latter presents a

  flange 23 for mounting on the wall 17 from which

  the it extends outward to support

  a pipe 24 directed downwards at its straight end

  bre. The pipe 22 internally supports, by means of support elements 25, a tubular body 26 defining inside the pipe. 22, a passage 27 of annular section, which communicates externally, on one side,

  with line 24 and, on the other side, with the compar-

  15. The tubular body 26 contains an electric motor.

  plate 28 supplied by a cable 29 and comprising an output shaft 30 facing the compartment 15 and on which is mounted an exhaust fan 31 enclosed in an inner part 32 of the pipe 22 which extends inside the projecting part 20 of compartment 15. In an alternative arrangement not shown,

  the output shaft 30 is directed outwards and sup-

  carries the fan 31 inside the part of the pipe 22 which extends to the outside of the compartment, while the electric motor 28 is housed at least

  partially inside compartment 15.

  5. As shown in FIG. 3, the walls 12 and 13 are in one piece with two plates 33 and 34, the outer edge 35 of which is suitably shaped to

  be matched to the outer surface of the fuselage 1 and

  finish, with the latter and the walls 9 and 16, a chamber 36 which communicates with the air intake 3 of the engine

  the helicopter (not shown) -

  Room 36 communicates with a certain name.

  bre of pipes 37 in truncated cone which are mounted at

  o10 through walls 9 and 16, with their small ends

  te dimension inside the respective compartments 14 and 15. Each pipe 37 engages, with a radial clearance, in a respective cylindrical pipe 38 which is mounted in

  the relative wall 8, 17 and defined with the relative pipe

  ve 37, an annular opening 39 communicating with the respective compartment 14,15. A centrifugal element 40 is fixedly mounted inside a part

inlet of each pipe 38.

  While walking, air, and dust

  in suspension are forcibly driven at a relative speed.

  Vement high in the conduits 38 both by the movement imparted by the blades (not shown) of the rotor. (not shown) of the helicopter 1 and by the vacuum created by the motors inside the chamber 36. The air incoming is

  then subjected to vortices by the elements 40 so

  re that the suspended dust can be precipitated

  tee inside the compartments 14 and 15 of the case 5 via the openings 39, while a part

  incoming air progresses, after filtering, into the

  bre 36 passing through the conduits 37. The combined effect of air pressure, gravity and vacuum created by the fan 31 is such that the separated dust falls into the projecting part 20 of the compartment 15, o it is evacuated via the annular channel 27 of the pipe 22, the latter possibly in certain

applications to be deleted.

  6. When not needed, the filter 4 can be removed in a few minutes, and replaced by a sieve, by simply removing the angle 19 and releasing it

support 11.

  The present invention is not limited to the exemplary embodiments which have just been described, it

  is on the contrary subject to modifications and

  laughing who will appear to those skilled in the art.

7.

Claims (3)

  1 - Air intake filter for engine   aircraft, especially for helicopter engines   tere, characterized in that it comprises, in combination, a shoemaker (5) having an interior compartment (14, 15)   designed to define a chamber (36) at the front of an ad-   respective air mission of a respective engine, ca-   dust separation channels (37) formed through the housing (5) to allow communication with   outside the chamber (3.), each channel (37) commu-   connecting with the interior compartment (14, 15), and a dust exhaust line (22) extending towards   the outside of the case (5) and communicating with the comparator   timent (14, 15); a fan (31) housed in rotation inside the exhaust pipe (22) and a means   actuator (28) supported by the boot (5) for drag the fan (31).   2 - Filter according to claim 1, character-   in that the actuating means (28) is housed   inside the exhaust pipe (22).   3 - Filter according to claim 1 or the re-   vendication 2, characterized in that the exhaust pipe   pement (22) extends from a lower part in   projection (20) of the compartment (14, 15).