GB1007120A - - Google Patents

Abstract

1,007,120. Gas turbine jet engines. ROLLS-ROYCE Ltd. Sept. 18, 1964 [Sept. 25, 1963], No. 37826/63. Heading F1J. A gas turbine jet propulsion engine of the bypass type comprises compressor means, combustion equipment, turbine means and an exhaust duct mounted in flow series, a by-pass duct through which air may flow from the compressor means to the exhaust duct thus by-passing the combustion equipment and turbine means, the by-pass air mixing with the turbine exhaust gases in a mixing zone within the exhaust duct, an auxiliary turbine being mounted within the exhaust duct downstream of the mixing zone and a fan being drivingly connected to the auxiliary turbine. The engine shown comprises a low pressure compressor 11 and a high pressure compressor 12, combustion equipment 13, a high pressure turbine 14 and low pressure turbine 15, the low pressure compressor and low pressure turbine being mounted on a common shaft 31, and the high pressure compressor and high pressure turbine being mounted on a common shaft 32, a portion of air from the low pressure compressor passing through by-pass duct 20 to mix with the gases discharging from the turbine 15 in the mixing zone 21. An auxiliary turbine 22 is disposed within the duct through which the mixture of turbine exhaust gases and by-pass air flows to the outlet nozzle, the turbine blades carrying a row of fan blades 23 which are disposed within a duct 24. The auxiliary turbine is mounted on a shaft 30 which may be drivingly connected to the shaft 31 as shown or may be independent.