Author

Mosebach

Date of Award

12-1995

Degree Name

Master of Science in Engineering

Department

Mechanical and Aerospace Engineering

Department

Mechanical and Aeronautical Engineering

First Advisor

Dr. Daniel Dorney

Second Advisor

Dr. Parviz Merati

Third Advisor

Dr. Iskender Sahin

Access Setting

Masters Thesis-Open Access

Abstract

Computational simulations have been performed to study the effects of unsteady rotor wakes on the total pressure losses and the boundary layer characteristics in a compressor cascade. In the numerical simulations, transitional and turbulent flow conditions were modeled at design and off-design inlet flow angles, and for varying rotor wake widths and wake velocity deficits.

First, simulations were performed in the absence of rotor wakes at the inlet of the EGV (Exit Guide Vane) cascade. Second, simulations were performed for different wake width and wake velocity deficit values at the inlet of the EGV cascade. The majority of the numerical simulations in which a rotor wake was specified indicated that the total pressure losses increase as the rotor wake width and wake velocity deficit increase. F low turning, in general, decreased as the wake depth and wake velocity deficit were increased. For the design simulations, the skin friction was found to decrease as the wake width was increased. In addition, some of the design flow simulations predicted a decrease in the skin friction as the wake velocity deficit was increased. For several of the off-design flow simulations, the skin friction decreased as the wake width was increased. The results from these simulations provide a data base that can be used for improving compressor cascade performance.

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