Improvements in internal combustion engines through which a continuous gaseous stream is flowing and in particular in turbo-jet and turbo-prop engines

摘要

726,491. Gas turbine plant. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES O.N.E.R.A. July 13, 1953 [July 16, 1952], No. 19410/53. Class 110 (3). [Also in Group XII] The combustion chamber of a gas turbine engine is supplied with fuel through a main ejector 3 and auxiliary injectors 7, fuel being supplied by a pump 11 through a spring-loaded slide valve 9. As the fuel pressure rises, the valve member 12 first allows fuel to pass through conduit 4 to the main injector and then through further conduits 8a, 8b, 8c to the auxiliary injectors 7.