AIRCRAFT TURBOFAN ENGINE Russian patent published in 2005 - IPC

FIELD: aircraft industry.

SUBSTANCE: proposed turbofan engine contains fan with support stages, fan straightening vane assembly, high pressure compressor, combustion chamber, high-and low-pressure turbines, common reactive nozzle for flows of air from fan and gas from turbine duct. Mixer is installed at turbine duct outlet in which walls form circumferentially alternating outer and inner channels. Engine is mounted in nacelle and is connected with aircraft air intake. Distance L between peripheral trailing edges of fan blades and peripheral leading edges of vanes of fan straightening vane assembly in direction along axis of fan rotation and projection L1 of peripheral chord of sections between leading and trailing edges of fan blades onto axis of its rotation are described by relation L=(0.707-0.866)L1 3.16. Number Z of fan blades and number Z1 of vanes of fan straightening vanes assembly are related by the following equation Z1=(0.707-0.866)Z 3.16. Length of air intake of aircraft and outlet diameter D of air intake are related by the following equation L2=(0.188-0.228)D 3.16. Area at engine inlet f_in and area of section in neck of air intake F_n are related by the following equation f_in=(0.346...0.386)F_n·3.16 where 3.16 is acoustic parameter of engine fan duct corresponding logarithmic scale of 5 dB.

EFFECT: improved efficiency of fan noise damping without material losses in engine thrust.

2 cl, 1 dwg