Abstract: A support system for the aft end of fan jet gas turbine engines which reduces engine bending in operation while accommodating radial and longitudinal thermal expansion forces. A plurality of inwardly extending small flanges are provided on a first ring, which may form part of the engine core cowl, that is secured to the pylon supporting the overall engine. A plurality of outwardly extending small flanges are provided on a second ring, which is secured to, or otherwise forms a part of, the engine. These flanges are spaced in adjacent pairs, one on each ring. Torque links are connected between these pairs of flanges. The torque links support the engine aft end against bending and flexing forces while accommodating thermal expansion forces.

Abstract: A support system for the aft end of fan jet gas turbine engines which reduces engine bending in operation while accommodating radial and longitudinal thermal expension forces. A first radial ring secured to the engine structure core cowl and the overall engine support pylon has a plurality of spaced longitudinal grooves. A second, cooperating radial ring secured to the engine has a plurality of outwardly extending tabs sized to fit within the first ring grooves. The tabs do not extend fully into the grooves at ambient temperatures. When operation of the engine begins, the engine heats up to a relatively high temperature. Radial thermal expansion is accommodated by expansion of the inner ring, causing the tabs to move deeper into the grooves. Longitudinal thermal expansion is accommodated by slippage of the tabs along the grooves in a longitudinal direction. Meanwhile, the engine is supported against bending and flexing beyond the amount permitted by the space between tab ends and bottoms of the grooves.