Type of Document Master's Thesis Author Eddy, Grant Lee URN etd-09272001-173833 Title Study of Steady-State Wake Characteristics of Variable Angle Wedges Degree Master of Science Department Mechanical Engineering Advisory Committee
Advisor Name Title King, Peter S. Committee Chair Dancey, Clinton L. Committee Member O'Brien, Walter F. Jr. Committee Member Keywords
- Gas Turbine Engine Testing
- Inlet Distortion
Date of Defense 2001-09-21 Availability unrestricted AbstractCurrent methods of creating inlet total pressure distortion for testing in gas turbine engines are only able to simulate steady-state distortion patterns. With modern military aircraft it is becoming necessary to examine the effects of transient inlet distortion on engines. One alternative being evaluated is a splitting airfoil that is essentially a wedge that can be set at different opening angles. An array of such devices would be placed in front of the engine for testing that would be capable of creating steady-state distortion patterns as well as transient distortion patterns by changing the opening angle of the airfoils.
The work here analyzes the steady-state wake characteristics of some of the splitting airfoil concepts. Single-wedge tests were conducted with various opening angles in an attempt to classify the various aspects found in the wake pattern. It was found that the wake has completely different characteristics with larger opening angles. In addition, several different combinations of wedges were also examined to see if single wedge analysis could be applied to arrays of wedges. Analysis was done on combinations of wedges aligned vertically as well as combinations that were done horizontally. It was found that single wedge characteristics change considerably when different wake patterns interact with each other
Filename Size Approximate Download Time (Hours:Minutes:Seconds)
28.8 Modem 56K Modem ISDN (64 Kb) ISDN (128 Kb) Higher-speed Access Eddy1.pdf 2.97 Mb 00:13:45 00:07:04 00:06:11 00:03:05 00:00:15
If you have questions or technical problems, please Contact DLA.