Faculty Advisor

Evans, Simon


Highly loaded compressor blades, used to increase the pressure rise through a single compressor stage, allow achievement of an overall pressure ratio with fewer stages. However, prevention of suction surface separation results in an efficiency penalty. This paper discusses the design and construction of a linear compressor cascade to evaluate the effectiveness of passively induced vortex generator jets in preventing separation on highly loaded blades. Modifications were made to an existing blade profile, and internal geometry was analyzed to minimize losses. A plenum was selected. Holes were placed upstream of the suction surface separation point and at the peak pressure point on the pressure surface. Adjustable tailboards were used to obtain periodicity through blade passages.


Worcester Polytechnic Institute

Date Accepted

March 2011


Aerospace Engineering

Project Type

Major Qualifying Project



Advisor Department

Mechanical Engineering