REDUCTION GEAR FOR HIGH-SPEED AND SMALL-SIZE FAN DRIVE TURBINE Russian patent published in 2017 - IPC F02C7/20 F02K3/68 F02C7/36 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises a flexible support for a fan drive gear set. The first turbine section has a first output area and is capable to rotate at first speed. The second turbine section has a second output area and is capable to rotate at second speed which exceeds the first speed. The first characterizing parameter is the product of the square of the first speed and the first output area, the second characterizing parameter is the product of the square of the second speed and the second area of the output. The ratio of the first characterizing parameter to the second characterizing parameter ranges from 0.5 to 1.5. Frame has a lateral rigidity of the frame and a transverse rigidity of the frame, and flexible support has transverse rigidity of flexible support and lateral rigidity of flexible support. The lateral rigidity of the flexible support is less than said lateral rigidity of the frame, and said transverse rigidity of the flexible support is less than said transverse rigidity of the frame. The ratio of the thrust force provided by said engine to the volume of the turbine section including said high pressure turbine and said low-pressure turbine is greater than or equal to 1.5 and less than or equal to 5.5 lbs-force/inm³, at that said thrust is designed static thrust at take-off from sea level.

EFFECT: reduction of turbine section concerning both diameter and axial length, increase of efficiency and extension of service life of gas turbine engine.

18 cl, 11 dwg, 1 tbl