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Numerical Investigation of Influence of Radial Inlet Distortion on Compressor Performance in 2-Stage Turbocharging System

[+] Author Affiliations
Jinke Chen, Xinqian Zheng, Chenfang Wang, Weilin Zhuge, Yangjun Zhang

Tsinghua University, Beijing, China

Paper No. GT2014-26530, pp. V01BT24A016; 8 pages
  • ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
  • Volume 1B: Marine; Microturbines, Turbochargers and Small Turbomachines; Steam Turbines
  • Düsseldorf, Germany, June 16–20, 2014
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4558-5
  • Copyright © 2014 by ASME


As the result of strict emission regulations and the demand of fuel reduction, an increasing number of engines are highly boosted with complex two-stage turbocharging systems.

In a two-stage turbocharging system, an additional intercooler between LP compressor and HP compressor is usually used to reduce the inlet temperature of the HP compressor for extending its life and reducing the compression work. Spatial restrictions of the turbocharging system lead to reduced distances between different components of the two-stage turbocharging system. Consequently, each component’s performance is influenced by the upstream and downstream ones. The high pressure compressor performance is affected by the inlet flow condition, which is significantly distorted by the intercooler.

In this paper, the characteristics of flow distortion caused by the intercooler and its evolution process are analyzed. Performances of the downstream high pressure compressor under uniform inlet condition and distorted inlet condition caused by the intercooler are analyzed and compared. The results show that the inlet distortion caused by intercooler deteriorates the compressor pressure ratio, flow range, and efficiency.

Copyright © 2014 by ASME
Topics: Compressors



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