Active bleed for airfoils
AssigneeLockheed Martin Corporation
InventorsDan Baruzzini, Neal David Domel, Jeffrey G. Hakes, Daniel N. Miller
Life of this patent
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Abstract
An airfoil active bleed system and related method. A housing includes an induction wall, an exhaust wall having one or more exhaust ports, and a chamber between the induction and exhaust walls. Zero-net-mass-flux actuators are located in the chamber and configured and positioned to collectively induct fluid through the induction wall and selectively exhaust fluid through the exhaust port(s).
Claims18
An airfoil active boundary layer control system, comprising:
- a housing including an induction wall having a gas permeable surface, an exhaust wall having at least one exhaust port, and a chamber disposed between and at least partially defined by the induction and exhaust walls;
- and
- at least one zero-net-mass-flux actuator in the chamber including an actuator orifice in fluid communication with the gas permeable surface of the induction wall and the at least one exhaust port, the actuator orifice being aligned with the at least one exhaust port.
An active boundary layer control for an airfoil, comprising:
- a housing including an induction wall having a gas permeable surface, an exhaust wall having one or more exhaust ports, and a chamber between the induction and exhaust walls;
- a plurality of zero-net-mass-flux actuators located in the chamber and configured and positioned to at least augment bleed through the airfoil by collectively inducting fluid through the gas permeable surface of the induction wall and selectively exhausting fluid through the one or more exhaust ports;
- and
- a plurality of actuator orifices carried by respective actuators of the plurality of zero-net-mass-flux-actuators, the plurality of actuator orifices being positioned and aligned to entrain into a respective one of the one or more exhaust ports at least some air that does not pass through the plurality of actuator orifices.
A method of actively controlling a boundary layer of fluid flowing over an airfoil suction surface, comprising:
- inducting at least some of the fluid through a portion of the airfoil suction surface, into a chamber under the airfoil suction surface, and into an actuator orifice of a zero-net-mass-flux actuator located in the chamber;
- and
- exhausting fluid out of the zero-net-mass-flux actuator through the actuator orifice thereof, through a chamber exhaust port located in an exhaust wall that is aligned with the actuator orifice, and out of the chamber exhaust port to an interior of the airfoil.
Dependencies are inferred from the claim text.