GAS TURBINE ENGINE (VARIANTS) Russian patent published in 2019 - IPC F02C7/06 F02K3/06 

FIELD: engine building.

SUBSTANCE: gas turbine engine comprises a low pressure compressor, a first bearing unit, a second bearing unit, a low pressure compressor hub. Low pressure compressor is installed along engine axis. First bearing assembly supports, at least partially, inner shaft arranged along said axis. Second bearing assembly at least partially supports outer shaft arranged along said axis. Low pressure compressor hub is installed on inner shaft and passes to low pressure compressor between first and second bearing assemblies. Low pressure compressor hub is connected to the second stage disc of the said low pressure compressor, and the low pressure compressor is three-stage. Inner shaft is made with possibility of rotation of fan through a gear assembly. Low-pressure compressor hub comprises a truncated cone section arranged between the first and second bearing assemblies, wherein the truncated cone section extends forward about the first bearing assembly. Said fan comprises blades designed to force air along inner circuit into low pressure compressor and along external outline through outlet guide vanes.

EFFECT: minimizing the total loads transmitted to the gear assembly; possibility of obtaining relatively less complex bearing compartment creates conditions for use of less rigid tolerances for manufacturing and requires fewer seals, which minimizes number of potential sources of oil leaks and reduces weight; additional advantages consist in reduction of sizes of oil tank and cooling device, as well as in reduction of amount of oil in lubricating system of engine; disclosed architecture also reduces the effective load transfer chain for the gear assembly and reduces the amount of heat and oil consumption.

10 cl, 8 dwg