TURBINE WHEEL ROTOR OF AXIAL-FLOW GAS TURBINE FOR OXYGEN-KEROSENE LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2006 - IPC F01D5/28 B22F5/04 

FIELD: turbine building.

SUBSTANCE: invention relates to design of solid wheel rotors of axial-flow gas turbines, mainly to turbopump sets of liquid-propellant rocket engines. Proposed wheel rotor of axial-flow gas turbine of oxygen-kerosene liquid-propellant rocket engine has disk, root and peripheral parts of blades, leading and trailing edges of blades and turbine rotary shroud in peripheral part of blades. Turbine wheel rotor members are made of nickel-based alloy and are permanently interconnected. Disk and root part of blades are made of high heat-resistant alloy containing 40-70% of nickel. Turbine rotary shroud, peripheral part, leading and trailing edges of blades are made of alloy containing 77-90% of nickel featuring high resistance to ignition in oxidizing medium.

EFFECT: improved reliability of turbine wheel rotor.

4 cl, 1 dwg