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.

• This report represents the work of one or more WPI undergraduate students submitted to the faculty as evidence of completion of a degree requirement. WPI routinely publishes these reports on its website without editorial or peer review.

Creator

• Stevens, Bridget L
• Thornton, Lane M
• Meyer-Lorentson, Alexander L

Publisher

• Worcester Polytechnic Institute

Identifier

• E-project-031411-141757

Advisor

• Evans, Simon

Year

• 2011

Date created

• 2011-03-14

Resource type

• Major Qualifying Project

Major

• Aerospace Engineering

Rights statement

• In Copyright