Patent ID: 9328694
Filing Date: 2016-05-03
CPC Classification: F02K

Claim Text:
1. An aircraft gas turbine thrust-reversing device, comprising: an engine cowling of a gas-turbine engine, the engine cowling including a front area and a rear area, the rear area being displaceable in an axial direction of the gas-turbine engine between a closed forward thrust position and a rearwardly displaced thrust reversal position, wherein, when the rear area is in the rearwardly displaced thrust reversal position, an annular free space is opened between the rear area and the front area; a plurality of deflecting elements positioned circumferentially around the gas-turbine engine and being coupled to the rear area to move axially along the gas-turbine engine with the rear area, wherein, in the closed forward thrust position, the plurality of deflecting elements are positioned within the front area, telescoping rail elements, each including a partial circular arc shape with a concave side facing toward an interior of the gas-turbine engine, and each mounting and guiding one of the plurality of deflecting elements along the partial circular arc shape between the closed forward thrust position and the rearwardly displaced thrust reversal position; wherein, during displacement of the rear area from the closed forward thrust position to the rearwardly displaced thrust reversal position, each of the plurality of deflecting elements is displaced by the rear area to move along the partial circular arc shape until a rear end area of each of the plurality of deflecting elements is in contact with a cowling of a core engine of the gas-turbine engine.