Axial turbine blades geometry impact of small-sized turbojet engines on the turbine efficiency

DOI: 10.34759/vst-2020-1-191-200

Аuthors

Varsegov V. L.^*, Abdullah B. N.^**,

Kazan National Research Technical University named after A.N. Tupolev, 10, Karl Marks str., Kazan, 420111, Russia

*e-mail: varsegov@gmail.com
**e-mail: Kuragorony@gmail.com

Abstract

Small-sized turbojet engines are employed for unmanned aerial vehicles (UAV). Due to low efficiency and thrust-to-weight ratio, they are limited to short range applications. However, transition from rated idle mode to MAXIMAL mode at high altitude takes time, which requires further development to improve efficiency of these gas turbines.

When creating promising small-sized turbojet engines, the problem of turbines gas-dynamic efficiency increasing inevitably arises, as it directly affects the fuel efficiency of the engine, and ultimately determines its competitiveness.

The presented article considers profile losses, i.e. the flow separation from the surface of the rotor blade profile. The issue of the setting angle β_set and the angle at the rotor blade inlet β_x effect on the turbine efficiency is under consideration.

The main task of the calculation consists in determining optimal shape of the axial turbine rotor blades to ensure the required parameters and characteristics of the turbine at continuum flow and minimum energy losses with specified values of the angles at the inlet and setting angles.

The article presents also the results of a numerical study of the turbine air-gas channel, i.e. the joint operation of the turbine guide blades and the rotor blades, to assess the quality of the rotor blades geometry to improve the turbine efficiency.

In this work, the 3D computational model was constructed in the SolidWorks program with subsequent computational grid applying with Turbo Grid program. The flow was simulated by the SST turbulent viscosity model.

Keywords:

axial turbine of a small turbojet engine, rotor blades profiling, geometry optimization of axial turbine of a small turbojet engine, turbine efficiency, profile losses

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