US 4,865,256 AGranted

Turbojet engine having a thrust reverser door and variable exhaust cross-section

AssigneeSociete anonyme dite Hispano-Suiza

InventorsLionel F. G. J. Durand, Xavier R. Y. Lore

Life of this patent

Estimating the term…

Loading patent…

Abstract

A thrust reversing system acting on a cold flow air duct of a turbofan-type turbojet engine is disclosed wherein the thrust reversing doors conform to a turbojet engine housing formed as a body revolution about a central longitudinal axis. The thrust reversing doors function to selectively divert the air passing through the cold flow air duct into a reverse thrust direction and also serve to vary the cross-section of the air duct. When the thrust reversing doors are in the forward thrust position, the downstream edges of the doors may be adjusted in a radial direction to vary the cross-section of the duct. The thrust reversing door is pivotable about a pair of axes, which may extend generally transverse to the longitudinal axis of the engine. The door is pivotally attached to a pair of link arms by a primary pivot which defines the first pivot axis. The link arms are attached to a fixed portion of a turbojet engine structure by a secondary pivot which define the second pivot axis. Individual actuators are provided for moving the door about the first pivot axis and for moving the link arms about the second pivot axis.

Claims19

Dependent claims

A thrust reverser for a turbofan type turbojet engine having an exhaust duct for exhausting hot engine gases comprising:

(a) a housing formed as a body of revolution about a longitudinal axis located about the exhaust duct so as to define a generally annular cold flow air duct therebetween, the housing defining at least one generally laterally extending thrust reversing opening;
(b) a thrust reversing door having upstream and downstream edge portions;
(c) a plurality of link arms;
(d) first pivot means attaching the thrust reversing door to the link arms such that the door may pivot about a first pivot axis;
(e) second pivot means attaching the link arms to a stationary portion of the turbojet engine such that the link arms may pivot about a second pivot axis;
(f) primary actuating means operatively connected to the thrust reversing door so as to move the door about the first pivot axis between a forward thrust position in which the door covers the thrust reversing opening, and a thrust reversing position in which the door uncovers the thrust reversing opening and substantially blocks the cold flow air duct to direct air outwardly through the thrust reversing opening;
and,
(g) secondary actuating means operatively connected to at least one of the link arms to pivot the link arms about the second pivot axis thereby radially displacing the downstream edge portion of the thrust reversing door when in the forward thrust position to vary the cross-section of the cold flow air duct.

5 more elements

Dependencies are inferred from the claim text.