Abstract

A propulsion device including an unducted upstream propeller and a counter-rotating and coaxial downstream propeller. At least one blade of the upstream propeller is configured to generate a corotating secondary vortex for acting upstream of the downstream propeller to destabilize a blade tip vortex of the same at least one blade.

IPC Classes  ?

• B64C 11/18 - Aerodynamic features
• F01D 5/14 - Form or construction
• B64C 11/48 - Units of two or more coaxial propellers
• F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
• F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
• B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants

Abstract

The invention relates to a rotor of a turbomachine compressor, comprising a bladed rotor disk, the radially outer end of which is provided with a wall (10) forming the inner end of an annular channel for the flow of a primary gas stream and formed from a plurality of angular sections (12), each one being defined between two consecutive blades (14, 16) of the disk in a circumferential direction (17), and comprising a cambered part (22) that is convex in the axial direction (25) and in the circumferential direction (17), in addition to, upstream of said cambered part (22), a hollow part (24) that is concave in the axial direction (25) and in the circumferential direction (17), and has an essentially punctiform base (28).

IPC Classes  ?

• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F01D 5/14 - Form or construction