Performance of a Subsonic Compressor Airfoil with Upstream, End-Wall Injection Flow

Master's Thesis


The performance of a compressor stator airfoil was studied experimentally and computationally. In gas-turbine engines, stators are located directly downstream of rotor blades and contribute to the static pressure rise in the compressor. The experimental setup utilized a high-speed, subsonic linear cascade. The independent variables studied were airfoil incidence angle and mass flow rate of end-wall injection upstream of the stator. The end-wall injection was intended to simulate upstream “leakage” through hardware gaps in the end-walls of gas-turbine engines. The exit of the cascade was interrogated by a five-hole-probe and a total pressure Kiel probe to provide total pressure measurements, which were used to calculate total pressure loss coefficients at the exit of the test section. Computational studies were completed to examine the end-wall flow physics and entropy generating mechanisms through the stator section. The experimental results showed a distinct decrease in the downstream total pressure field with end-wall injection flow, and the impact of the upstream injection on the stator loss coefficient was not a function of the incidence angle. The computational investigation found that the majority of the end-wall injection’s effect on the downstream total pressure field was observed as an increase in the size of the secondary flows on the suction-side of the stator near the upper end-wall.


Attribute NameValues
Author Aaron J. Pope
Contributor Scott C. Morris, Research Director
Contributor Stanislav Gordeyev, Committee Member
Contributor Thomas Juliano, Committee Member
Contributor Aleksandar Jemcov, Research Director
Degree Level Master's Thesis
Degree Discipline Aerospace and Mechanical Engineering
Degree Name Master of Science in Aerospace Engineering
Banner Code
  • MSAE

Defense Date
  • 2020-03-18

Submission Date 2020-04-13
  • cascade

  • compressor

  • propulsion

  • leakage

  • endwall injection

Record Visibility Public
Content License
  • All rights reserved

Departments and Units
Catalog Record


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