Gas turbine engine and thrust reverser assembly therefore
AssigneeUnited Technologies Corporation
InventorsNigel David Sawyers-Abbott, James Power
Life of this patent
Estimating the term…
Abstract
The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.
Claims14
A thrust reverser assembly for a gas turbine engine having a core engine, the thrust reverser assembly comprising:
- a nacelle surrounding the core engine and defining a bypass duct radially therebetween, the nacelle comprising an axially translating cowl;
- an actuator mounted to the nacelle, the actuator adapted to axially translate, the actuator being coupled to the translating cowl and is adapted to axially translate the translating cowl;
- an axially translating structure in communication with the nacelle and/or the translating cowl, the axially translating structure having at least one opening that is exposed to the bypass duct when the translating cowl is translated in an aft direction;
- a blocker door pivotally coupled to the translating structure, the blocker door comprising a slider track disposed on the blocker door and including a camming surface;
- a slider assembly mounted to the actuator and engaging the slider track, the slider assembly being adapted to slide in the slider track as the actuator moves axially;
- wherein interaction between the slider assembly and the camming surface of the slider track causes the blocker door to move from a stowed position to a deployed position by pivoting relative to the translating structure;
- and
- wherein the blocker door projects into the bypass duct and diverts bypass air within the bypass duct through the at least one opening of the translating structure when the blocker door is in the deployed position.
A high-bypass gas turbofan engine having a core engine and a thrust reverser assembly, the thrust reverser assembly comprising:
- a nacelle surrounding the core engine and defining a bypass duct radially therebetween, the nacelle comprising an axially translating cowl;
- an actuator mounted to the nacelle, the actuator adapted to axially translate, the actuator being coupled to the translating cowl and is adapted to axially translate the translating cowl;
- an axially translating structure in communication with the nacelle and/or the translating cowl, the axially translating structure having at least one opening that is exposed to the bypass duct when the translating cowl is translated in an aft direction;
- a blocker door pivotally coupled to the translating structure, the blocker door comprising a slider track disposed on the blocker door and including a camming surface;
- a slider assembly mounted to the actuator and engaging the slider track, the slider assembly being adapted to slide in the slider track as the actuator moves axially;
- wherein interaction between the slider assembly and the camming surface of the slider track causes the blocker door to move from a stowed position to a deployed position by pivoting relative to the translating structure;
- and
- wherein the blocker door projects into the bypass duct and diverts bypass air within the bypass duct through the at least one opening of the translating structure when the blocker door is in the deployed position.
Dependencies are inferred from the claim text.