초록

The present invention relates to a thrust reverser cascade element of an aircraft gas turbine with a rigid frame and with several thrust reverser profiles mounted in the frame, wherein the thrust reverser cascade element is made of fiber-plastic composite.

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1. A thrust reverser cascade of an aircraft gas turbine, comprising: first and second thrust reverser cascade elements, each comprising: a rigid frame comprising two opposite straight frame struts and two opposite curved frame struts;a plurality of thrust reverser profiles fixed to and formed as one

1. A thrust reverser cascade of an aircraft gas turbine, comprising: first and second thrust reverser cascade elements, each comprising: a rigid frame comprising two opposite straight frame struts and two opposite curved frame struts;a plurality of thrust reverser profiles fixed to and formed as one piece with the rigid frame, each of the plurality of thrust reverser profiles having opposite ends and a central portion extending from one of the opposite ends to another of the opposite ends;wherein the plurality of thrust reverser profiles are connected only at the opposite ends to the rigid frame;wherein the central portions of the plurality of thrust reverser profiles are free from the rigid frame except through the opposite ends;wherein each of the plurality of thrust reverser profiles is free from the others of the plurality of thrust reverser profiles except through the opposite ends;wherein each of the plurality of thrust reverser profiles is arched or curved in a longitudinal direction of the each of the plurality of thrust reverser profiles;wherein the first and second thrust reverser cascade elements are made from fiber reinforced plastic;wherein the first and second thrust reverser cascade elements are arranged side-by-side with one another such that one of the two opposite straight frame struts of the first thrust reverser cascade element is positioned adjacent one of the two opposite straight frame struts of the second thrust reverser cascade element to thereby form a centerline between the first and second thrust reverser cascade elements, the centerline being parallel with an axis of the aircraft gas turbine, the plurality of thrust reverser profiles of the first and second thrust reverser cascade elements converging together toward the centerline such that the plurality of thrust reverser profiles of the first thrust reverser cascade element form a mirror image with the plurality of thrust reverser profiles of the second thrust reverser cascade element. 2. The thrust reverser cascade in accordance with claim 1, wherein the plurality of thrust reverser profiles are arranged substantially parallel to one another. 3. The thrust reverser cascade in accordance with claim 1, wherein each of the plurality of thrust reverser profiles includes a flow profile in cross-section. 4. The thrust reverser cascade in accordance with claim 1: wherein a first portion of the plurality of thrust reverser profiles are connected between a first one of the two opposite curved frame struts and a first one of the two opposite straight frame struts;wherein a second portion of the plurality of thrust reverser profiles are connected between the first one of the two opposite straight frame struts and a second one of the two opposite straight frame struts;wherein a third portion of the plurality of thrust reverser profiles are connected between the second one of the two opposite straight frame struts and a second one of the two opposite curved frame struts. 5. The thrust reverser cascade in accordance with claim 1 and further comprising a plurality of further thrust reverser cascade elements, each of the further thrust reverser cascade elements including a plurality of thrust reverser profiles arranged in a rectangular grid.