LOW-NOISE COMPRESSOR ROTOR FOR REDUCER TURBO-FAN ENGINE Russian patent published in 2018 - IPC F02C3/06 

FIELD: engine devices and pumps.

SUBSTANCE: gas turbine engine comprises a fan, a turbine section and a reduction gear. The turbine section has a first turbine rotor designed to drive a compressor rotor. Reduction gear provides for reduction of fan speed relative to input speed from fan drive turbine rotor. The compressor rotor has a certain number of compressor blades in at least one of a plurality of rows of compressor rotor, which operate at least part of time with angular rotation rate. The said number of compressor blades in said at least one row and said angular speed of rotation are such that the following inequality is valid for said at least one row of compressor rotor: (number of blades × angular rotation rate)/(60 seconds/minute)≥5500 Hz; and the angular rotation rate is expressed in the number of revolutions per minute. Said angular rotation rate is the rotation rate in the section of the landing approach. The turbine section comprises the rotor of the high-pressure turbine and the rotor of the first turbine, wherein the fan drive turbine rotor being the rotor of the first turbine. The rotor of the compressor is the rotor of the reduced pressure compressor, and the rotor of the pressure turbine drives the rotor of the high-pressure compressor. The reduction gear is arranged between the rotor of the first turbine and the rotor of the compressor.

EFFECT: improvement of the gas turbine engine so that the noises produced by it offset by frequency less sensitive to human hearing.

13 cl, 3 dwg