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Unsteady numerical investigation on gas ingestion into the rotor-stator disk cavities of a 1.5-stage turbine

Published online by Cambridge University Press:  18 February 2022

Z. He ,
J. Zhou Open the ORCID record for J. Zhou [Opens in a new window] ,
C. Yang ,
B. Li  and
J. Qian
Z. He
Affiliation:
School of Aeronautical Engineering, Civil Aviation University of China, Tianjin300300, China
J. Zhou*
Affiliation:
School of Aeronautical Engineering, Civil Aviation University of China, Tianjin300300, China
C. Yang
Affiliation:
School of Aeronautical Engineering, Civil Aviation University of China, Tianjin300300, China
B. Li
Affiliation:
School of Aeronautical Engineering, Civil Aviation University of China, Tianjin300300, China
J. Qian
Affiliation:
Engineering Training Center, Civil Aviation University of China, Tianjin300300, China
*
*Corresponding author. Email: zhoujx769115367@163.com
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Abstract

To investigate the downstream rim seal gas ingestion characteristics of a 1.5-stage turbine, the URANS equations were solved numerically using the SST turbulence model. The effects of different purge flow rates and the second vane on the ingestion characteristics of the aft cavity and the nonuniform fluctuations of the main gas path pressure are analysed. The results showed that the aft cavity is affected by the combined effects of the blade and the second vane, and the potential field at the leading edge of the second vane greatly influence the airflow variation in the aft cavity, which enhances the ingress of the mainstream into the wheel-space. The front purge flow weakens the egress between the suction side of the blade and the suction side of the second vane. The potential field at the leading edge of the second vane suppresses the nonuniform distribution of airflow in the aft cavity caused by the rotational effect of the blade.

Keywords

Computational fluid dynamicGas turbineRim sealIngressAft cavity
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1304 , October 2022 , pp. 1718 - 1735
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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