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AssigneesRolls-Royce Deutschland Ltd & Co KG, Liebherr-Aerospace Lindenberg GmbH
InventorsPredrag TODOROVIC, Uwe SCHUMANN, Frank MUELLER, Dirk METZLER-STOERMER
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The present invention relates to an aircraft gas turbine comprising an engine cowling that has a rear area, with respect to the direction of the flow, which has a thrust-reverser device, wherein the rear area is embodied in such a manner as to be translatable in the axial direction, characterized in that the rear area is mounted in a translatable manner at two rails that are arranged in parallel to each other, and that it comprises a gear rack that is mounted at each rail, respectively, with the gear rack being in mesh with a respective cog wheel, which is coupled to a common motor via a gear unit, respectively.
Aircraft gas turbine comprising an engine cowling which has a rear area, with respect to the direction of the current, that has a thrust-reverser device, wherein the rear area is embodied in such a way as to be translatable in the axial direction, characterized in that the rear area is mounted in a translatable manner on two rails that are arranged in parallel to each other and that it comprises respectively one gear rack mounted on each rail, with the gear rack being in mesh with one cog wheel, respectively, which is respectively coupled to a common motor via a gear unit
Dependencies are inferred from the claim text.