Combustion chamber for liquid fuel is intended to the turbocharger - reactors, gas turbines, or other applications

摘要

757,332. Generating combustion products under pressure. LUCAS (INDUSTRIES), Ltd., J. Aug. 3, 1954 [June 11, 1953], No. 16099/53. Class 51(1). In a combustion chamber of a gas turbine engine or a jet propulsion engine, fuel is supplied to the flame tube in the form of a spray directed towards the upstream end and air is supplied through a short axially directed cylindrical air duct at the upstream end of the flame tube, swirling means being provided around the upstream end of the duct to impart swirl to the air flowing into the duct. The upstream end of the duct is closed. A flame tube a is disposed within an outer casing and fuel is sprayed in an upstream direction through injector n. The upstream end of the flame tube comprises a hollow nose piece e constructed of overlapping sheet metal parts forming between them a narrow air passage f. The end of the flame tube also comprises a hemispherical part b formed of two (or more) overlapping parts which form a narrow air inlet passage c. At the centre of the part b is disposed a short duct g, the upstream end of the duct being closed by a blank plate h. Air inlets i are formed of the upstream end of the duct by means of inclined vanes j, the air entering the duct tangentially. The downstream end of the duct is flared outwardly to form a flange m which with the adjacent part b forms the air inlet c.