Simulation of a propeller disk presented by distribution of velocities

Abstract

Purpose

This paper aimed to study the simulation and describe the turbulent fluid flow through a symmetrical tube with a propeller disk set inside it. The Navier–Stokes equations with the model of turbulence (k-ω) are used to describe this problem in space and time.

Design/methodology/approach

The propeller disk is represented by the distribution of the vector of velocities along its radius. The main purpose is to describe the boundary conditions at the inlet, at the outlet and special compatible conditions for the simulation of the propeller disk on the both sides. A one-side modification of the Riemann problem is used for the boundary value conditions. Total pressure and total density values and the angle of attack equal to zero are to be used preferentially at the inlet, whereas pressure should be used at the outlet. At the back side of the propeller disk, it is advantageous to use total density and total pressure distributions coming from the distribution of axial velocities on the disk and the total state values at the inlet, with extra-added velocities of rotation. At the front side of the propeller disk, it is preferable to use the distribution of the flowing mass known from the state values computed on the disk.

Findings

This set of boundary conditions allows simulation of the air flow twisting behind the propeller/fan including increases in the corresponding pressure.

Practical implications

The advantage of this approach is the possibility to solve axial cuts of air ducts. Similarly, it is possible to solve air flow around the engine nacelle of the propeller aircraft. By this approach, it is possible to separate the design of the axial cut air duct from the propeller solution.

Originality/value

This approach has been used for new air duct designed on the operating conditions with Star-CCM+ solver.

Citation

Žižkovský, N., Pelant, J. and Kyncl, M. (2014), "Simulation of a propeller disk presented by distribution of velocities", Aircraft Engineering and Aerospace Technology, Vol. 86 No. 3, pp. 225-227. https://doi.org/10.1108/AEAT-01-2013-0002