Wet pipe device for turbojet engines

• US 4,466,573 A
• Filed: 06/28/1983
• Issued: 08/21/1984
• Est. Priority Date: 01/25/1980
• Status: Expired due to Term

• Current Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Original Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Inventors: Mandet, Gerard M. F., Camboulives, AndreA. M. L.
• Primary Examiner(s): Love, John J.
• Assistant Examiner(s): Forman, Michael J.
• Application Number:
  US06/508,415
• Time in Patent Office: 420 Days
• Field of Search: 239/265.33, 239/265.37, 239/265.39, 239/265.41, 239/265.19, 60/271
• US Class Current: 239/265.41
• CPC Class Codes: F02K 1/1207 of one series of flaps hinged at their upstream ends on a fixed structure F02K1/1215 - F02K1/1292 take precedence
• CPC Class Codes: F02K 1/1223 of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Jet pipe device for turbojet engines, having at least one annular assembly of flaps with variable inclinations with respect to the axis of the assembly. The device has an assembly of control elements, each of which is associated with a flap to control the inclination of this flap; a synchronizing device interconnecting all of the racking lever; and an annular support element carrying both the flaps and the control devices.

Claims

1. A jet pipe device for a turbojet engine having an annular stationary canal structure defining a passage for gaseous fluids wherein the device comprises:

(a) an annular support ring attached to the stationary canal structure so as to prevent relative movement therebetween in a direction parallel to a longitudinal axis of the turbojet engine, the annular support ring attached so as to be coaxial with the stationary canal structure;

(b) a plurality of convergent flaps pivotally attached to the annular support ring such that they define an annular convergent flap assembly, each of the convergent flaps having a free end which is movable in a generally radial direction toward and away from the longitduinal axis of the turbojet engine to constrict or expand the passage for the gaseous fluids;

(c) a plurality of control means connected between the convergent flaps and the annular support ring to selectively cause each convergent flap to pivot abouts its attachment to the annular support ring and move its free end toward or away from the longitudinal axis of the turbojet engine wherein each control means comprises;

(i) a force generating element having a first stationary part attached to the annular support ring and a second part extendable and retractable with respect to the first part, the second part having a distal end;

(ii) a rocking lever pivotally attached to the annular support ring and having a first bearing surface;

(iii) connecting means connecting the distal end of the second part to the rocking lever; and

,

(iv) a second bearing surface on the convergent flap which contacts the first bearing surface on the rocking lever such that, as the second part extends and retracts with respect to the first part, the rocking lever pivots, thereby causing the convergent flap to pivot about its attachment to the annular support ring; and

,

(d) synchronizing means interconnecting each control means such that all of the convergent flaps move at the same time in the same direction.

2. The jet pipe device of claim 1 wherein the annular support ring is toroidal in shape with a circular cross-section.

3. The jet pipe device of claim 1 wherein the force generating element is an hydraulic jack having its cylinder attached to the annular support ring and its piston rod attached to the rocking lever.

4. The jet pipe device of claim 1 wherein the force generating element is a pneumatic jack having its cylinder attached to the annular support ring and its piston rod attached to the rocking lever.

5. The jet pipe device of claim 1 wherein the synchronizing means comprises:

(a) a plurality of pairs of reversing levers each having a first end pivotally attached to the annular support ring and a second end;

(b) means interconnecting the pair of reversing levers such that they move about their pivot axis together;

(c) a first tie rod connecting the second end of one of the pair of reversing levers to a first rocking lever; and

,

(d) a second tie rod connecting the second end of the other of the pair of reversing levers to a second rocking lever adjacent the first rocking lever.

6. The jet pipe device of claim 5 wherein the longitudinal axes of the tie rods are parallel to the axis of the stationary canal structure.

7. The jet pipe device of claim 1 wherein the first bearing surface rolls on the second bearing surface without sliding during the movement of the rocking levers and convergent flaps.

8. The jet pipe device of claim 1 wherein the plurality of convergent flaps are attached to the annular support ring at their upstream edge and the second bearing surface is located near the downstream edge of the convergent flaps, the directions being relative to the direction of flow of the gaseous fluids.

9. The jet pipe device of claim 8 further comprising:

(a) a plurality of divergent flaps having a proximal edge pivotally attached to the downstream edge of one of the convergent flaps and a distal edge;

(b) a plurality of cold flaps located radially outwardly of the convergent and divergent flaps with respect to the longitudinal axis of the stationary canal structure, each of the cold flaps having an upstream edge and a downstream edge;

(c) means pivotally connecting the downstream edge of a cold flap to the distal edge of a divergent flap; and

(d) means pivotally connecting the upstream edge of the cold flap to the annular support ring.