GAS TURBINE ENGINE WITH HIGH-SPEED TURBINE SECTION OF LOW PRESSURE Russian patent published in 2017 - IPC F02K3/72 F02C3/67 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises a fan, a compressor section which is in fluid communication with a fan and comprising the first compressor section and the second compressor section, a combustion chamber section which is in fluid communication with the compressor section, a turbine section which is in fluid communication with the combustion chamber section. The turbine section includes the first turbine section and the second turbine section. The first turbine section and the first compressor section are rotatable in the first direction, and the second turbine section and the second compressor section are rotatable in the second direction opposite to the first. The first turbine section has the first area of the outlet section at the first exit point and is rotatable at the first speed. The second turbine section has the second outlet section area at the second exit point and is rotatable at the second speed exceeding the first speed. The first characterizing parameter is defined as the product of the square of the first speed and the first area. 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. A reducer is provided between the fan and a low-pressure spool driven by the first turbine section, whereby the fan is able to rotate at a lower speed than the first turbine section.

EFFECT: increased efficiency of the gas turbine engine.

20 cl, 3 dwg