Twin target thrust reverser module

Patent metadata

Field	Value
Publication number	US-10161358-B2
Application number	US-201414773958-A
Country	US
Kind code	B2
Filing date	Mar 13, 2014
Priority date	Mar 14, 2013
Publication date	Dec 25, 2018
Grant date	Dec 25, 2018

Abstract

A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.

First claim

What is claimed is:

1. A nozzle assembly for a dual gas turbine engine propulsion system comprising:
a housing mountable to an airframe structure and defining a first nozzle proximate to a first bypass passage of a first gas turbine engine and second nozzle proximate a second bypass passage of a second gas turbine engine;
first and second upper doors supported within the housing;
first and second lower doors supported within the housing; wherein each of the first and second upper doors and the first and second lower doors are pivotally mounted to the same common housing for movement between an open position, a stowed position and a deployed position, wherein in the deployed position, airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second bypass passages, in the stowed position, airflow through the first and second bypass passage is not blocked by the first and second upper and lower doors and in the open position an eft end of the first and second upper and lower doors is moved radially outward of the stowed position;
an actuator system supported on the housing and disposed between the first nozzle and the second nozzle to drive both the first and second upper doors and the first and second lower doors between the stowed position, the deployed position and the open position.

2. The nozzle assembly as recited in claim 1 , wherein the first and second upper doors and the first and second lower doors close on a centerline of corresponding ones of the first and second bypass passages to redirect both bypass airflows and core airflows.

3. The nozzle assembly as recited in claim 1 , wherein the actuator system is a single actuator disposed between the first and second bypass passages and coupled to each of the first and second upper doors and the first and second lower doors.

4. The nozzle assembly as recited in claim 1 , including three actuator systems for moving the first and second upper doors and the first and second lower doors between the stowed position and deployed position.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M

Classifications

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/62

  by blocking the rearward discharge by means of flaps · CPC title

• F02K1/60

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• F05D2240/40

  Use of a multiplicity of similar components · CPC title