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):

Report Date:

2007-03-01

Pagination or Media Count:

73.0

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.

Subject Categories:

  • Aircraft
  • Hydraulic and Pneumatic Equipment
  • Machinery and Tools

Distribution Statement:

APPROVED FOR PUBLIC RELEASE