Patent ID: 8840451

Claim:
An aircraft cabin pressure control system outflow valve, comprising: a frame configured to be mounted on an aircraft, and having an inner surface that defines a flow passage through the frame; a valve element disposed within the flow passage and rotationally coupled to the frame, the valve element adapted to receive an actuator output drive torque and configured, in response thereto, to rotate between a closed position and a plurality of open positions; and a vortex generator structure coupled to the valve element and rotatable therewith, the vortex generator structure comprising: a plurality of first vortex generators, the first vortex generators spaced apart from each other and configured to generate first vortices when the valve element is in an open position and fluid flows through the flow passage, and a plurality of second vortex generators formed in each of the first vortex generators and spaced apart from each other, the second vortex generators each configured to generate second vortices, which are smaller than the first vortices, when the valve element is in an open position and fluid flows through the flow passage.