AXIAL DISPLACEMENT ENGINE, GAS TURBINE ENGINE, AND AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2011 - IPC F01C1/107 F02C3/02 F02K5/00 

FIELD: engines and pumps.

SUBSTANCE: proposed engine 8 comprises inlet 20 displaced along axis from 22 and located downstream thereof. Inner and outer main parts 12, 14 have displaced inner and outer axes 16, 18, respectively. At least, one of inner and outer main parts 12, 14 may rotate about one of inner and outer axes 16, 18. Said inner and outer part have intersecting inner and outer screw vanes 17, 27. Said inner and outer axes 16, 18 make axes of screw surfaces of said vanes. Inner and outer screw vanes 17, 27 run along inward and outward radii, respectively. Core assembly 15 has first, second and third sections 24, 26, 28 running downward along the flow between inlet 20 and outlet 22. Inner and outer screw vanes 17, 27 have first, second and thirds pitch angles 34, 36, 38 in said first, second and third sections 24, 26, 28, respectively. First pitch angle 34 are smaller than second pitch angles 36, while third pitch angles 38 are greater than second pitch angles 36. Combustion section 40 runs downward along the axis from second section 26 via, at least, part 42 of third section 28.

EFFECT: may be used as gas generator for aircraft gas turbine engine including two-stage turbofan engine.

10 cl, 11 dwg