Patent ID: 8479491
Filing Date: 2013-07-09
Classification: F01D,F02K,F05D,Y10T

Abstract:
1. A gas turbine engine having a nacelle comprising a fan case and a thrust reverser assembly disposed axially aft of the fan case, the thrust reverser assembly comprising a fixed structure configured to be translated to separate from the fan case, the fixed structure of the thrust reverser assembly being capable of coupling and decoupling from the fan case with a clamping system, the clamping system comprising: flanges associated with the fan case; and flanges associated with the fixed structure of the thrust reverser assembly and adapted for simultaneous mating with the flanges of the fan case when the fan case and the thrust reverser assembly are axially moved into engagement with each other; and a plurality of over-center clamping mechanisms, a first of the over-center clamping mechanisms being mounted to the fixed structure of the thrust reverser assembly and adapted to clamp a first of the flanges of the fixed structure with a first of the flanges of the fan case, a second of the over-center clamping mechanisms being mounted to the fan case and adapted to clamp a second of the flanges of the fixed structure with a second of the flanges of the fan case.