Societe De Construction Des Avions Hurel-dubois

Societe De Construction Des Avions Hurel-dubois (societe Anonyme)

Aircelle Limited

Societe Hispano Suiza

Societe De Constructio Des Avions Hurel-dubois

Robert R Standish

Bernard Laboure

Alain Fournier

Robert Schegerin

Pascal J Meyer

Jean-Paul Rene Hogie

Guy B Vauchel

Joel Frank

A turboprop engine includes a power jet mounted coaxially to the engine axis (X-X'), and has a fan case and a gas ejecting system provided with two afterbody half-cowlings () each of which is pivotable around an axis (A) between open and closed positions, wherein the half-cowlings are connected to the downstream of the fan case through a 'V-blade/V-groove' system. In a first embodiment, the pivot axes (A) make an angle &#x3b1;&#x3e;3&#xb0; to the engine axis (X, X&#x2032;) and a joint plane (Z-Z) between the afterbody half-cowlings and the downstream of the fan case makes to the plane (Y, Y&#x2032;) perpendicular to the engine axis (X, X&#x2032;) an angle &#x3b2; in such a way that the difference between the angle &#x3b1; and the angle &#x3b2; is less than or equal to 3&#xb0;. In the other embodiment, the axes are converged to each other in a downstream direction.

Turboprop unit for aircraft with improved aerodynamic installation

The cascade-type thrust reverser comprises a cowling in which there is formed an opening which, when in a direct thrust mode, is closed by a sliding cowl and which, in a thrust-reversal mode, is uncovered by the translation of the said sliding cowl, a fan duct being defined between an interior skin and an exterior skin, said exterior skin having a radius Re in the plane transversal to the longitudinal axis of the reverser and passing through the upstream end of the sliding cowl in the direct thrust mode, and said interior skin having, downstream of this upstream plane, a maximum radius Ri in a plane parallel to the upstream plane, the upstream end of the said sliding cowl substantially blocking the fan duct upstream of the said downstream plane in a thrust-reversal mode, the said radius Re being less than the radius Ri.

Cascade-type reversers for jet engines

The invention concerns a backblast gas structure for jet engine comprising a thrust reversal system with two downstream doors. The invention is characterized in that the two tilt-up doors articulated about axes (,) are mounted on two side beams (,) with free downstream edges (,) comprising protuberances (,). The door downstream edges (,) having median zones (,) forming an angle (A) with the lateral parts (,), such that when the doors are in retracted position in direct jet, the beam (,) edges (,) of the doors are found in the same plane (P,), thereby constituting a gas exhaust outlet which is planar and substantially circular. The invention aims at improving the power package performance in direct jet.

Backblast gas structure equipped with thrust reverser with two rear doors and planar exhaust area

The thrust reverser for a turbo-fan engine is comprised of: a plurality of oors located in openings radially spaced in a shroud enclosing the engine and canalizing the jet flow from the engine, the doors being adapted to be pivoted, within a fixed structure, from a stowed position, in which they do not interfere with the jet flow, to a deployed position in which they block the jet flow and deflect it through the openings; an actuator having a body attached to the fixed structure and a rod attached to the center of each pivoting door for moving the door from the stowed position to the deployed position, and vice versa; and sealing elements comprising a main seal provided on the fixed structure and a separate annular seal located around the actuator body, the sealing elements mating with each door, when in the stowed position, and with the fixed structure to prevent pressure leakage of the jet flow.

Sealing for a pivoting door reverser

The thrust reverser has an external cowl and a fixed engine core cowl, defining together an annular duct through which high bypass fan air is driven rearwardly. The external cowl has a section adapted to be translated between forward and rearward positions, under control of linear actuators. The translating section includes openings fitted with doors pivotally mounted on the translating section and linked to the engine core cowl so that the translating section translating movement in a rearwardly direction causes the doors to pivot from a stowed position in which they close the openings and a deployed position in which they block the annular duct. The thrust reverser includes only two such doors, the surface area occupied by each door representing more than 30% of the peripheral surface area of the inner wall of a portion of the translating section limited by the vertical planes including the upstream end of the translating section and the pivot axis of the door, respectively.

Thrust reverser for high bypass fan engine

The invention relates to a thrust reverser for a bypass jet engine that reverses the fan flow. The thrust reverser is installed in the fixed outer cowl and is comprised of pivoting doors that block the fan flow in order to create reverse thrust. A translating annular nozzle is located aft of the pivoting doors in the stowed position, preventing in flight inadvertent deployment. When the nozzle are translated aft, the doors are free to pivot and, at the same time, the section of the fan nozzle can be adjusted to produce more or less fan flow.

Thrust reverser with adjustable section nozzle for aircraft jet engine

A thrust reverser with pivoting doors for a jet aircraft engine, with a system for security against in-flight deployment of a thrust reverser. The system has two independent locking assemblies, the first being a primary lock and the second being a safety lock that is positioned away from the first lock to avoid damage from a ruptured piece of the engine turbine disk. The first lock is hydraulically controlled and the second lock is electrically controlled and entirely independent, thus assuring an in-flight inadvertent deployment will not occur as a result from failures, faulty commands or inadequate maintenance.

Thrust reverser with doors for aircraft engine, equipped with safety

A thrust reverser comprised of two pivoting doors for engines mounted on an aircraft rear fuselage. For thrust reversal, the two pivoting doors are rotated into the mixed flow by two actuators, one actuator per door. On the extremities of each pivoting door, efflux flow turning devices are installed. These devices are removable boxes comprised of deflectors that can be oriented to turn the flow. Two boxes are required for each pivoting door.

Forward mounted pivoting door reverser with efflux control device

The invention relates to thrust reversers with doors for a jet engine. The upstream edge of the reverser doors is equipped with a deflecting structure consisting of a rigid frame (10, 12, 13) fixed to the door and delimiting a space (14) capped by a stiffener (15). In the space (14) are housed vanes (16) with aerodynamic profile in the form of a wing which is inclined by an angle a with respect to the plane of the frame (10, 12, 13) in order to orient laterally the flow of the gases which is diverted by the reverser. This arrangement makes it possible to reduce, or even to prevent, re-ingestion by the engine of the diverted gases, or interference of the latter with the wing structure of the aircraft.

Thrust reversal assembly for controlling sidewardly diverted flow

An improvement made to jet-engine thrust reversers and, more particularly, to reversers called tilting-door reversers. The doors are equipped, on their upstream portion, with a flow-deflecting overlay 90 which, in the open-door position, is in a position close to a line PM parallel to the axis of the engine 1, the overlay making with the inner door skin an angle B greater than 90.degree., preferably between 105.degree. and 110.degree.. The invention is more particularly applicable to dual-flow engines.

Jet-engine thrust reversers

A thrust reverser door for a turbofan-type turobjet engine thrust reversing system is disclosed defining a gas flow passage between inner and outer panels of the door. The passae has an inlet formed through the inner panel of the thrust reverser door and an outlet, directs a portion of the gas flowing through a cold flow air duct in a forward direction. The gas flowing in the forward direction inpinges upon gases flowing through a laterally facing opening in the housing in order to provide a forward component to this gas flow. A moveable flap may be attached to the thrust reverser door in order to cover the inlet to the passageway when the device is operated in the forward thrust mode.

Thrust reverser door having an exhaust gas passage

Thrust reverser for a jet engine of the type with doors equipped with auxiliary flaps. The invention relates to thrust reversers with doors 13 having a front deflector 15. The door is equipped, on its inner face, with one or two auxiliary flaps 16 articulated about axles 17 and controlled by a lever 21 articulated on the door at 22 and stressed into a retracted flap position by means of a spring 24. At the end of closure of the door, the end 31 of the lever interacts with a stop 33 which ensures that the lever tilts and that the flap 16 moves away from the door 13.

Growing community of inventors

Gazeran, France

Robert R Standish