END-WALL AND PROFILE LOSSES IN A LOW-SPEED AXIAL FLOW COMPRESSOR ROTOR.

B. Lakshminarayana, N. Sitaram, Jianhua Zhang

Research output: Contribution to journalConference article

Abstract

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. 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 found to 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.

Original languageEnglish (US)
JournalAmerican Society of Mechanical Engineers (Paper)
StatePublished - Jan 1 1985

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Axial-flow compressors
Rotors
Turbomachine blades

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Cite this

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title = "END-WALL AND PROFILE LOSSES IN A LOW-SPEED AXIAL FLOW COMPRESSOR ROTOR.",
abstract = "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. 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 found to 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.",
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year = "1985",
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END-WALL AND PROFILE LOSSES IN A LOW-SPEED AXIAL FLOW COMPRESSOR ROTOR. / Lakshminarayana, B.; Sitaram, N.; Zhang, Jianhua.

In: American Society of Mechanical Engineers (Paper), 01.01.1985.

Research output: Contribution to journalConference article

TY - JOUR

T1 - END-WALL AND PROFILE LOSSES IN A LOW-SPEED AXIAL FLOW COMPRESSOR ROTOR.

AU - Lakshminarayana, B.

AU - Sitaram, N.

AU - Zhang, Jianhua

PY - 1985/1/1

Y1 - 1985/1/1

N2 - 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. 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 found to 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.

AB - 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. 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 found to 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.

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M3 - Conference article

JO - [No source information available]

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