초록 ▼

A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid fl

A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.

대표청구항 ▼

What is claimed is: 1. 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 gene

What is claimed is: 1. 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. 2. The inlet flow control system of claim 1, wherein the at least one engine condition comprises at least one engine speed corresponding to a blade frequency. 3. The inlet flow control system of claim 1, wherein the control system adjusts the ratio of the first pressure within the first manifold and the second pressure within the second manifold to redistribute the ratio of the first injection rate and second injection rate. 4. The inlet flow control system of claim 1, wherein the at least one primary jet vortex generator and at least one secondary jet vortex generator are positioned laterally relative to one another within the engine inlet. 5. The inlet flow control system of claim 1, wherein the at least one primary jet vortex generator is positioned forward of the at least one secondary jet vortex generator. 6. The inlet flow control system of claim 1, wherein the redistribution of the ratio of the first injection rate and second injection rate alters circumferential distortion across the flow inlet. 7. The inlet flow control system of claim 1, further comprising sensors operable to sense circumferential distortion across the engine inlet, and wherein the control system is operable to: compare the sensed circumferential distortion across the engine inlet to a desired circumferential distortion across the engine inlet; and redistribute the ratio of the first injection rate and second injection rate when the sensed circumferential distortion across the engine inlet compares unfavorably to the desired circumferential distortion across the engine inlet. 8. The inlet flow control system of claim 1, wherein the at least one primary jet vortex generator and at least one secondary jet vortex generator comprise micro-jets operable to inject momentum into a near-wall boundary region. 9. The inlet flow control system of claim 8, wherein the micro-jets comprise micro fabricated mechanical structures. 10. The inlet flow control system of claim 8, wherein the micro-jets comprise synthetic pulsators. 11. An engine inlet for a gas turbine engine operable to provide improved pressure recovery and/or distortion to a compressor face, the engine inlet comprising: a ducted flow inlet 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 ducted flow inlet 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 ducted 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 ducted 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; an inlet flow control system operable to redistribute a ratio of the first injection rate and second injection rate to improve pressure recovery and/or distortion to the compressor face of an engine coupled to the engine inlet; wherein the inlet flow control system further comprises sensors operable to sense circumferential distortion across the engine inlet, and wherein the inlet flow control system is operable to: compare the sensed circumferential distortion across the engine inlet to a desired circumferential distortion across the engine inlet; redistribute a ratio of the first injection rate and second injection rate to improve pressure recovery of the inlet when at least one particular engine condition exists; and redistribute the ratio of the first injection rate and second injection rate when the sensed circumferential distortion across the engine inlet compares unfavorably to the desired circumferential distortion across the engine inlet. 12. The engine inlet of claim 11, wherein the at least one engine condition comprises at least one engine speed corresponding to a blade frequency. 13. The engine inlet of claim 11, wherein the control system adjusts the ratio of the first pressure within the first manifold and the second pressure within the second manifold to redistribute the ratio of the first injection rate and second injection rate. 14. The engine inlet of claim 11, wherein the at least one primary jet vortex generator and at least one secondary jet vortex generator are positioned laterally relative to one another within the engine inlet. 15. The engine inlet of claim 11, wherein the at least one primary jet vortex generator is positioned forward of the at least one secondary jet vortex generator. 16. The engine inlet of claim 11, wherein the redistribution of the ratio of the first injection rate and second injection rate mitigate blade vibration within a jet engine coupled to the flow inlet. 17. An engine 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 positioned rearward of and laterally with respect to the at least one primary jet vortex and 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 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 the at least one engine condition exists; wherein the at least one engine condition comprises at least one engine speed corresponding to a blade frequency; the control system adjusts the ratio of the first pressure within the first manifold and the second pressure within the second manifold to redistribute the ratio of the first injection rate and second injection rate; and wherein redistribution of the ratio of the first injection rate and second injection rate mitigate blade vibration within a jet engine coupled to the flow inlet. 18. The inlet flow control system of claim 17, wherein the redistribution of the ratio of the first injection rate and second injection rate alters circumferential distortion across the flow inlet. 19. The inlet flow control system of claim 17, wherein the sensors sense circumferential distortion across the engine inlet, and wherein the control system compares the sensed circumferential distortion across the engine inlet to a desired circumferential distortion across the engine inlet; and redistributes the ratio of the first injection rate and second injection rate when the sensed circumferential distortion across the engine inlet compares unfavorably to the desired circumferential distortion across the engine inlet. 20. The inlet flow control system of claim 17, wherein: the at least one primary jet vortex generator and at least one secondary jet vortex generator comprise micro-jets operable to inject momentum into a near-wall boundary region; and the micro-jets comprise one of micro fabricated mechanical structures and synthetic pulsators.