GB594207B - Improvements in internal combustion turbine plant for propulsion - Google Patents

Abstract

594,207. Gas turbines. SMITH, D.M., and METROPOLITAN - VICKERS ELECTRICAL CO., Ltd. June 28, 1945, No. 16556. [Class 110 (iii)] [Also in Group XXXIII] A gas turbine propulsion plant, for an aircraft or other craft, in which the power is used partly in a jet and partly in a power turbine directly coupled to contra-rotating tractor airscrews, comprises an axial flow compressor, an annular combustion chamber or annularly arranged group of chambers followed by compressor turbine all in axial alignment and a contra-rotational power turbine driving the air-screws exhausting to a coaxial propulsion jet, the power turbine and jet being mounted with their axis offset or eccentric to the axis of the axial flow compressor, annular combustion chamber and compressor turbine. In a gas turbine propulsion plant, Fig. 1, the air is compressed in an axial flow compressor 1, passes to an annular combustion chamber 2 which discharges through the compressor turbine 4a to the propelling nozzle 7a. Combustion gases are taken from the combustion chamber 2 through a pipe 15 to a power turbine 12a, 13a which is mounted with its axis offset from the axis of the axial compressor, annular combustion chamber and compressor turbine and drives directly the contra-rotating tractor propellers 8, 9. In a modification, air taken from the discharge of the compressor 1 is used to support combustion in an annular combustion chamber mounted coaxial with the power turbine. In a further modification, the exhaust gases from the turbine 4a do not pass to the propulsion jet 7a but are taken direct to the intake of the power turbine 12a, 13a.