BACKGROUND

1. Field of the Invention

The present invention relates generally to flow separation control over an airfoil, compressor blade, turbine blade, and the like. More specifically, the present invention is related to a system and method to control flow separation utilizing a method of injecting fluid and/or gas into a separated boundary layer to reduce, if not eliminate, the boundary layer separation near the trailing edge of the airfoil during flight.

2. Description of Related Art

Airfoils are well known in the art and are effective means to manipulated gas and/or fluid within an airstream. In one embodiment, the airfoil could be utilized to create lift for an aircraft, as depicted inFIGS. 1 and 2.FIG. 1depicts a simplified cross-sectional side view of an airfoil101traveling through an airstream103that passes over a top surface105and bottom surface107of airfoil101. It should be appreciated that the airfoil101could represent a wing of an aircraft. However, the same features are found in compressor blades, turbine blades, and the like.

One of the problems commonly associated with airfoil101is the limited use during different flight regimes. For example,FIG. 2depicts a common problem associated with airfoil101during flight; specifically, flow separation201can occur near the trailing edge of the airfoil101during different flight regimes. It should be understood that flow separation201greatly reduces the efficiency of the airfoil, which in turn could result in catastrophic failure.

Accordingly, although great strides have been made in the area of airfoils, compressor blades, and/or turbine blades, many shortcomings remain.

