Progress Report 2 November 2nd, 2006 TEAM CRUISE CONTROL

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Boundary layer with pressure gradient in flow direction.

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Presentation transcript:

Implementation of Vortex Cavities in a Turbojet Diffuser Sponsor: Williams International Progress Report 2 November 2nd, 2006 TEAM CRUISE CONTROL Michael Feldman Marvin Kong Nansi Xue

Table of Contents CFD analysis using Fluent® on regular model and shortened model Redesign of vortex cavity control

CFD Analysis CFD done on 3 different baseline models Regular length Shortened by 1 inch Shortened by 2 inches Varying degrees of flow separation for three baseline models

CFD Analysis Minimal flow separation for unmodified model

CFD Analysis Minimal flow separation for unmodified model

CFD Analysis Flow separation midway through the 1-inch shorter model

CFD Analysis Flow separation midway through the 1-inch shorter model

CFD Analysis Flow separation near inlet for the 2-inch shorter model

CFD Analysis Flow separation near inlet for the 2-inch shorter model

Vortex Cavity Re-Design Current vortex cavity is not feasible due to adverse pressure gradient Other cavity design has to be considered Higher Pressure Lower pressure Flow direction

Outside Assistance Conversation with Prof. Powell on last Friday Two Methods of Improving Boundary Layer Control Suction Blowing Diffuser Air flow Diffuser wall Flow is sucked downstream Diffuser Air flow Additional flow to impart to push boundary layer Diffuser wall

Questions?