GAS TURBINE ENGINE Russian patent published in 2017 - IPC F02K3/06 F02C3/107 F01D25/18 

FIELD: engine devices and pumps.

SUBSTANCE: gas turbine engine contains a fan, a compressor section, a combustion chamber in fluid communication with the compressor section, a fan drive turbine communicating with the combustion chamber, a geared system, a flexible support and a lubrication system. The geared system is designed to provide a speed reduction between the fan drive turbine and the fan and to transmit the input power from the fan drive turbine with an efficiency that exceeds 98% and less than 100% to the fan. The flexible support provides support for parts of the geared system. The support moves away from the fixed engine structure to compensate for at least radial movement between the geared system and the fixed structure. The lubrication system is designed to supply grease to the gear system and remove heat energy from the geared system. The fan drive turbine has the first outlet sectional area and is rotatable at the first speed and the engine further comprises of the second turbine having the second outlet sectional area and rotatable at a speed greater than the first speed of rotation. The first characterizing parameter is defined as the product of the square of the first speed and the first area, and the second characterizing parameter is defined as the product of the square of the second speed and the second area. The ratio of the first characterizing parameter to the second characterizing parameter is from 0.5 to 1.5.

EFFECT: invention makes it possible to increase the efficiency of a gas turbine engine.

11 cl, 1 tbl, 5 dwg