One embodiment of the present invention includes a nozzle defining a passage to receive and discharge working fluid to produce thrust. The nozzle includes the first wall structure opposite a second wall structure. The first wall structure includes a first convergent flap pivotally connected to a fir
One embodiment of the present invention includes a nozzle defining a passage to receive and discharge working fluid to produce thrust. The nozzle includes the first wall structure opposite a second wall structure. The first wall structure includes a first convergent flap pivotally connected to a first divergent flap. The second wall structure includes a second convergent flap pivotally connected to a second divergent flap. The first wall structure and the second wall structure define the throat along the passage and are reconfigurable to adjust dimensional area of the throat. One or more control valves modulate flow of the pressurized fluid into the passage through a first opening in the first wall structure and a second opening in the second wall structure approximate to the throat to change effective area of the throat by fluidic control.
대표청구항▼
What is claimed is: 1. An apparatus, comprising: a gas turbine engine including at least one compressor and at least one turbine; a nozzle defining a passage operable to receive working fluid from the turbine for discharge to produce thrust, the nozzle including a first convergent flap pivotally co
What is claimed is: 1. An apparatus, comprising: a gas turbine engine including at least one compressor and at least one turbine; a nozzle defining a passage operable to receive working fluid from the turbine for discharge to produce thrust, the nozzle including a first convergent flap pivotally connected to a first divergent flap and operable to define an adjustable throat for a convergent-divergent configuration of the nozzle along the passage; and a first conduit operable to selectively direct pressurized fluid from the compressor into a first actuation plenum, the first convergent flap being pivotally mounted to rotate in response to a controlled change in the pressurized fluid in the actuation plenum to adjust size of the throat, the first convergent flap fixed relative to a balance member such that both rotate about a common pivot axis; and wherein the balance member extends into the first actuation plenum to divide the first actuation plenum into a first chamber and a second chamber, the first conduit opens into the first chamber, and the pressurized fluid is selectively directed into the first chamber to apply force to the balance member to rotate the first convergent flap in a first direction. 2. The apparatus of claim 1, further comprising means for actuating a throat adjustment of the nozzle in response to one or more performance characteristics. 3. The apparatus of claim 1, further comprising an aircraft carrying the gas turbine engine, the nozzle and the conduit, aircraft being structure to be propelled by thrust generated by discharging the working fluid from the nozzle. 4. The apparatus of claim 1, further comprising a second conduit opening into the second chamber and the pressurized fluid is selectively directed into the second chamber to apply another force to the balance member to rotate the first convergent flap in a second direction, the second direction being opposite the first direction. 5. The apparatus of claim 4, further comprising a first stop in the first chamber and a second stop in the second chamber, the balance member being positioned between the first stop and the second stop, the balance member being structured to engage the first stop if the pressurized fluid is provided through the first conduit and the second stop if the pressurized fluid is provided through the second conduit. 6. The apparatus of claim 1, wherein the nozzle includes a second convergent flap opposite the first convergent flap and a second divergent flap opposite the first divergent flap, a second conduit operable to selectively direct the pressurized fluid from the compressor into a second actuation plenum, and the second convergent flap is pivotally mounted to rotate in response to a designated change in the pressurized fluid in the second actuation plenum to adjust the throat size of the convergent-divergent configuration. 7. The apparatus of claim 1, further comprising means for adjusting the effective size of the throat with fluidic control. 8. The apparatus of claim 1, wherein the nozzle is axisymmetric about a central axis. 9. An apparatus, comprising: a gas turbine engine including at least one compressor and at least one turbine; a nozzle defining a passage operable to receive working fluid from the turbine for discharge to produce thrust, the nozzle including a first convergent flap pivotally connected to a first divergent flap and operable to define an adjustable throat for a convergent-divergent configuration of the nozzle along the passage; a first conduit operable to selectively direct pressurized fluid from the compressor into a first actuation plenum, the first convergent flap being pivotally mounted to rotate in response to a controlled change in the pressurized fluid in the actuation plenum to adjust size of the throat; and a balance member forming a rotating wall of the first actuation plenum and structured to change the volume of the first actuation plenum when the pressurized fluid in the actuation plenum adjusts the size of the throat; and wherein the first convergent flap is fixed to the balance member, the balance member extends into the first actuation plenum to divide the first actuation plenum into a first chamber and a second chamber, the first conduit opens into the first chamber, and the pressurized fluid is selectively directed into the first chamber to apply force to the balance member to rotate the first convergent flap in a first direction. 10. The apparatus of claim 9, further comprising means for actuating a throat adjustment of the nozzle in response to one or more performance characteristics. 11. The apparatus of claim 9, further comprising an aircraft carrying the gas turbine engine, the nozzle and the conduit, aircraft being structure to be propelled by thrust generated by discharging the working fluid from the nozzle. 12. The apparatus of claim 9, further comprising a second conduit opening into the second chamber and the pressurized fluid is selectively directed into the second chamber to apply another force to the balance member to rotate the first convergent flap in a second direction, the second direction being opposite the first direction. 13. The apparatus of claim 12, further comprising a first stop in the first chamber and a second stop in the second chamber, the balance member being positioned between the first stop and the second stop, the balance member being structured to engage the first stop if the pressurized fluid is provided through the first conduit and the second stop if the pressurized fluid is provided through the second conduit. 14. The apparatus of claim 9, wherein the nozzle includes a second convergent flap opposite the first convergent flap and a second divergent flap opposite the first divergent flap, a second conduit operable to selectively direct the pressurized fluid from the compressor into a second actuation plenum, and the second convergent flap is fixed to a second balance member and is pivotally mounted to rotate in response to a designated change in the pressurized fluid in the second actuation plenum to adjust the throat size of the convergent-divergent configuration. 15. The apparatus of claim 9, further comprising means for adjusting the effective size of the throat with fluidic control. 16. The apparatus of claim 9, wherein the nozzle is axisymmetric about a central axis.
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이 특허에 인용된 특허 (18)
Sokhey Jack (Jagdish) Singh ; Crook Andrew James ; Snyder Philip Harold ; Vittal Baily R., Aircraft thrust vectoring system.
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Jourdain Grard E. A. (Saintry sur Seine FRX) Soligny Marcel R. (Chevilly Larue FRX), Nozzle for a jet engine containing an adjustable convergent-divergent portion.
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