Arrangement of thrust reverser flap link rods on the internal fixed structure of a turbojet engine nacelle

• US 8,876,018 B2
• Filed: 10/22/2012
• Issued: 11/04/2014
• Est. Priority Date: 04/20/2010
• Status: Expired due to Fees

• Current Assignee: Safran Nacelles
• Original Assignee: Aircelle (Safran SA)
• Inventors: Vauchel, Guy Bernard, Segat, Peter
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): Goyal, Arun
• Application Number:
  US13/656,948
• Publication Number:
  US 20130062434A1
• Time in Patent Office: 743 Days
• Field of Search: 602/262, 602/30, 239/265.11, 239/265.19, 239/265.23, 239/265.33
• US Class Current: 239/265.19
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: B64D 33/04 of exhaust outlets or jet pipes exhaust outlets for combustion engines in general F01N; jet pipes or nozzles for jet-propulsion plants per se F02K; plants characterised by the form or arrangement of the jet pipe or nozzle F02K ; attitude, flight direction, or altitude control by jet reaction B64C
• CPC Class Codes: F02K 1/62 by blocking the rearward discharge by means of flaps
• 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: F02K 1/763 with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• CPC Class Codes: F16C 7/02 Constructions of connecting-rods with constant length
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 74/2158 Spring

Abstract

An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring.

Claims

1. An arrangement comprising a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle, the internal fixed structure defining, with a movable cowl, an annular passage through which an air flow passes, wherein said link rod is connected to the internal fixed structure by an elastic means comprising a spring and wherein said spring is fastened in a hollow area of said internal fixed structure, the hollow area formed through a surface of the internal fixed structure and provided with an opening for passage of said link rod.

2. The arrangement according to claim 1, wherein said spring is U-shaped with two branches.

3. The arrangement according to claim 2, wherein a concavity of said spring is oriented toward an upstream direction of said nacelle.

4. The arrangement according to claim 1, wherein said spring is a torsion spring.

5. The arrangement according to claim 1, wherein said link rod is connected to said spring by a connecting pin, and wherein shells with oblong openings receiving ends of said pin, are capable of retaining said pin in the event the spring breaks.

6. The arrangement according to claim 1, wherein when the internal fixed structure is made from a composite sandwich material, the hollow area is formed in a monolithic part of that material.

7. The arrangement according to claim 1, wherein said hollow area is bordered by a flange which itself is bordered by a thermally insulating cushion of a surface of the internal fixed structure.

8. The arrangement according to claim 7, wherein a protective cover is attached on the flange.

9. The arrangement according to claim 1, further comprising a stop limiting an uplift of the spring in a reverser mode.

10. An aircraft turbojet engine nacelle, comprising at least one arrangement according to claim 1.