Cascade type aircraft engine thrust reverser with hidden link actuator

• US 5,228,641 A
• Filed: 08/15/1991
• Issued: 07/20/1993
• Est. Priority Date: 08/15/1991
• Status: Expired due to Term

• Current Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Remlaoui, Jihad I.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Ellis, Christopher P.
• Application Number:
  US07/745,148
• Time in Patent Office: 705 Days
• Field of Search: 244/110 B, 244/23 D, 244/12.5, 239/265.29, 239/265.31, 60/226.2
• US Class Current: 244/110.00B
• CPC Class Codes: F02K 1/72 the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A thrust reverser for use with fan jet type aircraft gas turbine engines. A ring around the aft edge of the nacelle is translatable aft to uncover a series of cascade sets, each of which includes a plurality of turning vanes that direct air passing through the cascades in a reverse direction. The actuation system includes a hydraulic cylinder or the like in islands between cascade sets. A blocker door assembly is positioned within the nacelle adjacent to each cascade set during normal engine operation, with the blocker door forming a portion of the inner streamlined wall of the nacelle. The forward end of the door is hingedly secured to a cascade door support and does not move during deployment of the ring. The aft end of the door is hingedly secured to a link, the other end of which is secured to the moving ring. As the ring is translated aft, the door pivots to a position blocking at least part of the air flow through the duct between nacelle and engine core and directs it outwardly though the cascade set. The actuation system is entirely outside the air flow stream both during normal flight operations and reverse thrust operations, avoiding any undesirable interference or drag during these operations.

Claims

1. A thrust reverser system for a fan jet engine which comprises:

a ring forming the aft portion of an engine nacelle;

an engine core within said nacelle forming an air flow duct therebetween;

extensible means for translating said ring aft from a stowed position to a deployed position uncovering a gap between ring and nacelle body;

a plurality of cascade sets positioned in said gap and secured to said nacelle body;

a plurality of islands separating said cascade sets said extensible means being located in said islands between said cascade sets entirely outside the air flow stream both during normal flight and reverse thrust operations;

a plurality of blocker doors, each forming the inner wall of said nacelle adjacent to each of said cascade sets when said ring is in a stowed position;

each blocker door hingedly attached at the forward end to said ring; and

a single link member hingedly connected between the aft end of each blocker door and the aft end of the corresponding cascade set;

whereby as said ring is translated aft by said extensible means to uncover said cascade sets, said blocker door is pivoted to a position substantially blocking air flow through said duct and directing that air flow to the corresponding cascade set.

2. The thrust reverser system according to claim 1 wherein said extensible means is a hydraulic system.

3. The thrust reverser system according to claim 1 wherein all of the actuation components are entirely out of the path of air flow through said duct during normal engine flight operation and entirely out of the air flow deflected by said blocker doors through said cascade sets during reverse thrust operation.

4. The thrust reverser system according to claim 1 wherein blocker doors in the deployed position extend from said nacelle in an inwardly and rearwardly direction toward said core.

5. In a thrust reverser system for a fan jet aircraft turbine engine having a nacelle including an engine body and a ring forming the aft portion of the nacelle, an engine core within said nacelle forming an air duct therebetween, means for translating said ring aft and uncovering an gap between said nacelle body and ring, a plurality of cascade sets in said gap and secured to said nacelle body, a plurality of islands separating said cascade sets and a blocker door associated with each cascade set;

the improvement comprising;

each blocker door forming the inner wall of said nacelle adjacent to each cascade set when said ring is in the forward position;

each blocker door hingedly attached at the forward end to said ring;

a single link connected between the aft end of each blocker door and the aft end of each cascade set;

said translating means positioned within said islands and out of the path of air through said duct during normal engine flight operation and entirely out of the air flow deflected by said blocker doors through said cascade sets during reverse thrust operation;

whereby as said ring is translated aft to uncover said cascade sets, said blocker doors are pivoted to positions substantially blocking air flow through said duct and directing that air flow through said cascade sets.

6. The improvement according to claim 5 wherein blocker doors in the deployed position extend from said nacelle in an inwardly and rearwardly direction toward said core.