GB803423A - Improvements in or relating to jet propulsion engines - Google Patents

Abstract

803,423. Jet-propulsion engines. BOULET, G., and RECHERCHES ETUDES PRODUCTION R.E.P. Feb. 7, 1955 [Feb. 13, 1954], No. 3500/55. Class 110 (3). A continuous flow jetpropulsion engine comprising an open-ended pipe for the circulation of a gas according to a thermodynamic cycle, in which the gas is heated and it is only after expansion that the gas is compressed from the low to the high-pressure part of the cycle and is cooled during flow at the low pressure, has the gas flow circuit folded back on itself so that the gas after expansion is cooled by the gas flow at the high pressure before it is heated. Air entering the intake 2 of the casing 1 passes at constant velocity to the burners 21. During its passage, the air is heated by the exhaust gases of the turbine 4 passing through the tubes 6. After further heating by the burners 21, the air is expanded in the passage formed between the casing 1 and the division wall 20 and then passed through the guide blades 5 and turbine 4. The turbine exhaust gases pass through the tubes 6, which are provided with cooling ribs 7 to the throat 10 of a diffuser 11 where its pressure is again raised to atmospheric. A longitudinally adjustable bullet 13 allows the amount of diffusion to be controlled. The turbine 4 drives through a shaft 18 speed-reduction gearing and control gear contained in a housing 17. In a modification, the turbine 4 is omitted and a diffuser leading into the intake 2, provided.