Patent ID: 7617670

Claim:
An inlet flow control system for a gas turbine engine operable to improve pressure recovery and/or distortion within a flow inlet, the inlet flow control system comprising: a duct operable to receive a primary fluid flow; a first manifold; at least one primary jet vortex generator located proximate to an inner surface of the duct wherein the at least one primary jet vortex generator injects fluid received from the first pressure manifold at a first injection rate into a boundary layer of the primary fluid flow within the flow inlet; a second manifold; at least one secondary jet vortex generator located proximate to the inner surface of the duct wherein the at least one secondary jet vortex generator injects fluid received from the second manifold at a second injection rate into a boundary layer of the primary fluid flow within the flow inlet, and wherein the fluid injected at the first injection rate and second injection rate are operable to induce secondary flow structure(s) within the boundary layer; a control system operable to redistribute a ratio of the first injection rate and second injection rate to improve pressure recovery and/or distortion of the flow inlet; sensors arrayed and extending between the at least one primary jet vortex generator and the at least one secondary jet vortex generator, the sensors being operable to sense at least one engine condition, and wherein the control system redistributes the ratio of the first injection rate and second injection rate to improve pressure recovery of the inlet when at least one engine condition exists; and a redistribution of the ratio of the first injection rate and second injection rate mitigate blade vibration within the gas turbine engine.