Accession Number : ADA466059


Title :   Tip Clearance Control Using Plasma Actuators


Descriptive Note : Final technical rept. 1 Jan 2004-31 Dec 2006


Corporate Author : NOTRE DAME UNIV IN DEPT OF AEROSPACE AND MECHANICAL ENGINEERING


Personal Author(s) : Morris, Scott C ; Corke, Thomas C


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a466059.pdf


Report Date : Mar 2007


Pagination or Media Count : 73


Abstract : This report documents experimental results from a series of experiments using active flow control to improve the performance and efficiency of turbine tip clearance flows. The flow control was based on plasma actuators. Two experimental facilities were used as part of this research project. The first was a low-speed, large-scale turbine cascade using Pak-B turbine blades. The second was a smaller scale, high-speed cascade with low aspect ratio. The active flow control was design to act as a plasma squealer. Specifically, the plasma force was oriented perpendicular to the camber line in order to resist the leakage flow through the tip gap. Both steady and unsteady forcing was used as a method for manipulating natural jet-like instabilities that existed as the leakage flow separated in the tip gap. The results have indicated that the unsteady plasma forcing was as effective as the passive squealer geometry in reducing the losses that occurred in the wake of the blade tip.


Descriptors :   *TURBINE BLADES , *ACTUATORS , *TURBOMACHINERY , PLASMAS(PHYSICS) , LOW VELOCITY , CAMBER , BLADE TIPS , ASPECT RATIO , TURBINES , WAKE , RESEARCH FACILITIES


Subject Categories : Aircraft
      Hydraulic and Pneumatic Equipment
      Machinery and Tools


Distribution Statement : APPROVED FOR PUBLIC RELEASE