GAS TURBINE ENGINE WITH AFT LOCATION OF OPEN PROPELLER FAN Russian patent published in 2013 - IPC F02K3/62 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine is designed with aft location of an open propeller fan with a gas generator and a gas channel in a sleeve of the propeller fan at outlet from the gas generator, and with shanks of blades of the propeller fan located in hollow racks. On external side from the gas channel there is an annular air cavity connected at inlet to outlet from the first stage of the gas generator compressor, and at outlet - to atmosphere via forward and aft labyrinth seals located before rotors of the propeller fan and also via racks and an additional nozzle in an aft cone of the sleeve of the propeller fan. Labyrinth seals are connected at outlet to directed opposite to incoming air flow additional annular forward and aft air intakes located on the sleeve between forward and aft rotor of the propeller fan correspondingly. An additional nozzle is designed with possibility of adjustment of its flow area.

EFFECT: increasing reliability and economy of the engine by eliminating parasitic leakages from the gas annular channel of the propeller fan.

5 dwg