Patent Number: 8,585,356

Title: Control of blade tip-to-shroud leakage in a turbine engine by directed plasma flow

Abstract: An electrode (54) in the tip (31) of a turbine or compressor blade (30), and a series of electrodes (68) in a shroud (36, 64) that surrounds a rotation path (33) of the blade tip. As the blade tip reaches each shroud electrode, a controller (74) activates an electrical potential between them that generates a plasma-induced gas flow (76) directed toward the pressure side (PS) of the airfoil. The plasma creates a seal between the blade tip and the shroud, and induces a gas flow that opposes a leakage gas flow (52) from the pressure side to the suction side (SS) of the blade over the blade tip (31).

Inventors: Wiebe; David J. (Orlando, FL), Montgomery; Matthew D. (Jupiter, FL)

Assignee: Siemens Energy, Inc.

International Classification: F01D 11/20 (20060101)

Expiration Date: 1/19/12018