American Institute of Aeronautics and Astronautics Inc. (AIAA)
Doi
Abstract
The thermal expansion mismatch between heat-resisting metals and high-temperature composite materials is explored as a method of achieving thermally-driven morphing in elevated-temperature environments, with an eye towards applications in variable-geometry hot structures in gas turbine engines. Three concepts are presented and demonstrated. The first thermal morphing system is a bimorph laminate which exploits the CTE mismatch between a titanium metal matrix composite and its parent titanium matrix material. The second concept is similar to the first, but uses a diffusion-bonded austenitic stainless steel alloy as the high expansion layer. The third concept utilizes a carbon fiber, silicon carbide matrix ceramic matrix composite joined to a stainless steel skin in a trailing-edge flap arrangement. Furnace-based experiments of cantilever-mounted specimens are performed to evaluate the displacement response of the metal-matrix and ceramic-matrix concepts at temperatures up to 606°C and 1035°C, respectively.</p
