Investigation of Gas Dynamic Effects of 3D Leading Edge on a Rotor Flow Field of a High-Pressure Turbine

Document Type : Original Article

Authors

1 Faculty of Engineering Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University,Tehran, Iran

2 azad olom tahghighat

Abstract

The flow within a high-pressure turbine is strongly influenced by upstream flow distribution. Due to the high level of pressure, the probable roughnesses of the rotor blade's leading-edge (LE) can form vortices which can cause flow separation and blade stall. In the present work, the geometric changes of the rotor's leading-edge, which have occurred during the manufacturing process, and its influence on the flow field and on the turbine's performance were studied. The main aim of this work is to provide new criteria for acceptance of produced blades. To this end, a three-dimensional numerical analysis with the aim of observation of flow field was conducted and the results were validated with existing experimental results. Based on statistical results of manufactured blades, three types of geometric changes were applied to the blades leading edge and analyzed. The results show that the changes made on geometry, have reduced the ratio of lift over drag. These changes, affect the angle of attack and the out-flow angle, which also reduces the blades loading and lead the flow toward, separation. In contrast, in areas of the blade were separation does not occur, the temperature distribution is more uniform.

Keywords

References

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History

  • Receive Date: 04 March 2019
  • Revise Date: 26 April 2019
  • Accept Date: 27 August 2019
  • Publish Date: 22 June 2019

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