End-wall and profile losses in a low-speed axial flow compressor rotor

B. Lakshminarayana, N. Sitaram, J. Zhang

Research output: Contribution to journalArticlepeer-review

24 Scopus citations


The blade-to-blade variation of relative stagnation pressure losses in the tip region inside the rotor of a single-stage, axial-flow compressor is presented and interpreted in this paper. The losses are measured at two flow coefficients (one at the design point and the other at the near peak pressure rise point) to discern the effect of blade loading on the end-wall losses. The tip clearance losses are foundto increase with an increase in the pressure rise coefficient. The losses away from the tip region and near the hub regions are measured downstream. The losses are integrated and interpreted in this paper.

Original languageEnglish (US)
Pages (from-to)22-31
Number of pages10
JournalJournal of Engineering for Gas Turbines and Power
Issue number1
StatePublished - Jan 1986

All Science Journal Classification (ASJC) codes

  • Nuclear Energy and Engineering
  • Fuel Technology
  • Aerospace Engineering
  • Energy Engineering and Power Technology
  • Mechanical Engineering


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