PROPELLER FAN GAS TURBINE ENGINE Russian patent published in 2011 - IPC F02K3/04 

FIELD: engines and pumps.

SUBSTANCE: propeller fan gas turbine engine includes gas generator, mixer of gas and air at the outlet of which is located at the inlet to gas air channel of the fan sleeve. Fan blades are installed on radial thrust bearings. Trailing edge of mixer on its periphery is located downstream gas of entering edge of air intake of gas-air channels of sleeve of propeller fan. Radial thrust bearings of blades are installed on inner side from gas-air channel. Roots of blades in gas-air channel are enclosed in aerodynamic fairings. Propeller fan is provided with gas-air channel nozzle. Ratio of outer diameter of sleeve fairing of propeller fan to outer diameter of gas generator fairing is 0.8-1.1. Ratio of outer diameter of sleeve fairing of propeller fan to covering value of entering edge of mixer on its periphery and entering edge of air intake of gas-air channel of sleeve of propeller fan is 5-40.

EFFECT: higher reliability and economy of propeller fan gas turbine engine by providing reduced temperature of blades of propeller fan in all operating modes of engine and minimising the outer diameter of propeller fan sleeve.

2 dwg