U.S. Patent Specifications

Abstract

In a gas turbine engine, the combination comprising elastic fluid apparatus having a bladed rotor member forming the inner boundary for at least a portion of a fluid flow path of said apparatus and across which the rotor blades of said member extend; a first annular shell structure forming the outer boundary for said fluid flow path portion; a second annular shell structure disposed about and spaced outwardly from said first shell structure to form a second annular fluid flow path therebetween; first and second support means disposed upstream and downstream respectively of said apparatus; means connecting the ends of said second annular shell structure to said first and second support means; means connecting one end of said first shell structure to one of said support means; and means on the other of said support means for supporting the other end of said first shell structure so as to permit axial sliding movements of said latter end relative to said latter support means.

Citation

(1959), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 31 No. 9, pp. 290-290. https://doi.org/10.1108/eb033162