GAS TURBINE ENGINE Russian patent published in 2014 - IPC F01D21/04 F01D5/02 F04D29/32 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine (1) comprises a body of drives (2) with a compressor (4) arranged downstream along the air flow (3) with front straightening (8) and working (9) titanium blades along the flow. On the front tail (12) of the compressor shaft (13) there is a geared wheel (14) for driving of units. On the geared wheel there is a thrust radial end (16) arranged as directed to the body of the drives (2), and on the body of drives there is a support radial surface (17) that responds to the end (16). The ratio of the minimum axial distance H between the inlet edge of the front working blade and outlet edge of the guide blade of the compressor to the axial distance h between the thrust end of the geared wheel and the support surface of the body of drives is within 1.1…3.

EFFECT: by exclusion of failures of compressor titanium blades in case of damage of its radial and thrust bearing, gas turbine engine reliability increases.

2 dwg