U.S. Patent Specifications
Aircraft Engineering and Aerospace Technology
Article publication date: 1 May 1947
An engine of the character described comprising a centrifugal compressor having intake eyes symmetrically disposed on opposite sides of its plane of rotation and a plurality of outlets symmetrically disposed in circular disposition about its axis of rotation, a corresponding and similarly disposed plurality of air ducts leading from said outlets towards one side of said plane, an axial flow turbine arranged coaxial with said compressor on the same side thereof as that of said ducts and adapted to directly mechanically drive the compressor, a plurality of combustion chambers arranged in circular disposition around said axis, an air duct connecting each of said outlets to one of said chambers, means for introducing fuel into each of said chambers for continuous combustion therein, a combustion product duct leading from each of said chambers to said turbine on the side thereof to which said compressor is located, the construction formed by said air ducts, combustion chambers and combustion product ducts constituting a skeleton structure leaving open access through which air is permitted to enter the compressor intake eye situated nearer the turbine, and an exhaust conduit leading axially away from the side of the turbine opposite to the side to which said combustion products are admitted.
(1947), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 19 No. 5, pp. 175-176. https://doi.org/10.1108/eb031511
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