Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part I

Maksim Smirnov; Aleksandr Sebelev; Nikolai Zabelin; Natalia Kuklina

doi:10.29008/ETC2017-100

12^th European Conference on Turbomachinery Fluid dynamics & Thermodynamics

Paper ID:

ETC2017-100

Main Topic:

Axial Turbines

https://doi.org/10.29008/ETC2017-100

Authors

Maksim Smirnov - Peter the Great Saint-Petersburg Polytechnic University
Aleksandr Sebelev - Peter the Great Saint-Petersburg Polytechnic University
Nikolai Zabelin - Peter the Great Saint-Petersburg Polytechnic University
Natalia Kuklina - Peter the Great Saint-Petersburg Polytechnic University

Abstract

The paper focuses on methods for an efficiency increasing of supersonic axial impulse turbines. There was chosen the axial turbine stage with axisymmetric nozzles and mean diameter 103.5 mm as the base model for a numerical and experimental investigation. There were chosen two modifications of the base design to provide an efficiency increasing: modification of the rotor leading edge design and modification of the rotor hub endwall design. The effect of these two factors on the turbine efficiency was analyzed separately. A preliminary numerical investigation showed that the rotor hub endwall modification provided an efficiency increasing up to 2% in comparison with the base model. Meanwhile, modification of the rotor leading edge shape did not provided significant efficiency increasing in comparison with the base model.