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# Accession Number:

## ADA076204

# Title:

## Boundary Layer and Wake Modifications to Compressor Design Systems: The Effect of Blade-to-Blade Flow Variations on the Mean Flow Field of a Transonic Rotor.

# Descriptive Note:

## Final rept. 1 Sep 76-31 Aug 78,

# Corporate Author:

## MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE AND PLASMA DYNAMICS LAB

# Report Date:

## 1979-03-01

# Pagination or Media Count:

##
218.0

# Abstract:

## The effect of blade-to-blade flow variations on the mean flow field of a highly loaded transonic axial flow compressor was invesitaged. The theoretical approach centered around modeling of three important phenomena associated with blade-to-blade flow fluctuations, which control the mean momentum and energy transfer processes. Apparent stresses were introduced into the mean flow momentum equations by pitchwise averaging. Loss concept of mean relative total pressure, due to conversion of mean flow kinetic energy to the energy of fluctuations, was introduced. Based on this concept, mean rothalpy and the production of apparent entropy were defined. An expression for mean rothalpy variation along the streamline was derived by pitchwise averaging of the energy equation. Mean flow equations suitable for the streamline curvature computational scheme were developed which include these three effects. Apparent stresses, mean rothalpy and apparent entropy variations were calculated from measured velocity fluctuations. The revised streamline curvature procedure was then used to predict the axisymmetric peripheral mean flow. The agreement of rotor outlet tangential velocity is excellent reproducing an unusual peak which is not explainable by usual techniques. The results showed that 3-D inviscid effects do not significantly modify the mean flow, and that the direct effect of apparent stresses on the mean flow is also small.

# Distribution Statement:

## APPROVED FOR PUBLIC RELEASE

#