KING ABDULLAH UNIVERSITY OF SCIENCE AND TECHNOLOGY
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12
초록▼
A detonation engine can detonate a mixture of fuel and oxidizer within a cylindrical detonation region to produce work. The detonation engine can have a first and a second inlet having ends fluidly connected from tanks to the detonation engine. The first and second inlets can be aligned along a comm
A detonation engine can detonate a mixture of fuel and oxidizer within a cylindrical detonation region to produce work. The detonation engine can have a first and a second inlet having ends fluidly connected from tanks to the detonation engine. The first and second inlets can be aligned along a common axis. The inlets can be connected to nozzles and a separator can be positioned between the nozzles and along the common axis.
대표청구항▼
1. A method for detonating a mixture of fuel and oxidizer, the method comprising: introducing an oxidizer to a detonation engine through a first inlet;introducing a fuel to the detonation engine through a second inlet, wherein the first and second inlets are collinear with a common axis;accelerating
1. A method for detonating a mixture of fuel and oxidizer, the method comprising: introducing an oxidizer to a detonation engine through a first inlet;introducing a fuel to the detonation engine through a second inlet, wherein the first and second inlets are collinear with a common axis;accelerating the oxidizer through a first nozzle;accelerating the fuel through a second nozzle;directing the oxidizer against a first side of a separator and radially outward from the common axis;directing the fuel against a second side of the separator, the second side being opposite the first side, and radially outward from the common axis;detonating the mixture of the fuel and the oxidizer at a distance from the common axis, within a cylindrical detonation region, to produce combustion products; andpassing the combustion products over a turbine to rotate the turbine,wherein the turbine is mounted with first and second bearings attached to the first and second inlets, respectively. 2. The method of claim 1, wherein the first inlet has a first end fluidly connected to a first tank and a second end fluidly connected to the detonation engine. 3. The method of claim 2, wherein the second inlet has a first end fluidly connected to a second tank and a second end fluidly connected to the detonation engine. 4. The method of claim 1 or 3, wherein accelerating the oxidizer through the first nozzle produces supersonic flow, and wherein accelerating the fuel through the second nozzle produces supersonic flow. 5. The method of claim 4, further comprising: expanding the combustion products resulting from detonating the mixture through the turbine to produce work. 6. The method of claim 1, further comprising: providing obstacles to inhibit expansion of the combustion products. 7. The method of claim 1, further comprising: stabilizing detonation of the mixture in the detonation engine. 8. The method of claim 7, wherein obstacles are configured in the detonation engine to achieve stabilization of the detonation. 9. The method of claim 1, further comprising: stabilizing a detonation of the engine to obtain a resultant standing detonation wave by delivering the oxidizer and the fuel to the detonation region with a speed equal to a speed of the resultant standing detonation wave. 10. A method for detonating a mixture of fuel and oxidizer, the method comprising: introducing an oxidizer to a detonation engine through a first inlet that is rotatably attached to a first bearing;introducing a fuel to the detonation engine through a second inlet that is rotatably attached to a second bearing, wherein the first and second inlets are collinear with a common axis;accelerating the oxidizer through a first nozzle;accelerating the fuel through a second nozzle;directing the oxidizer against a first side of a separator and radially outward from the common axis;directing the fuel against a second side of the separator, the second side being opposite the first side, and radially outward from the common axis;detonating the mixture of the fuel and the oxidizer at a distance from the common axis within a cylindrical detonation region, to produce combustion products; andpassing the combustion products over a turbine to rotate the turbine,wherein the turbine is attached to the first and second bearings. 11. The method of claim 10, wherein accelerating the oxidizer through the first nozzle produces supersonic flow, and wherein accelerating the fuel through the second nozzle produces supersonic flow. 12. The method of claim 11, further comprising: expanding the combustion products resulting from detonating the mixture through the turbine to produce work. 13. The method of claim 10, further comprising: providing obstacles to inhibit expansion of the combustion products, wherein the obstacles are configured in the detonation engine to achieve stabilization of the detonation. 14. The method of claim 10, further comprising: stabilizing a detonation of the engine to obtain a resultant standing detonation wave by delivering the oxidizer and the fuel to the detonation region with a speed equal to a speed of the resultant standing detonation wave. 15. A method for detonating a mixture of fuel and oxidizer, the method comprising: introducing an oxidizer to a detonation engine through a first inlet;introducing a fuel to the detonation engine through a second inlet, wherein the first and second inlets are collinear with a common axis;accelerating the oxidizer through a first nozzle;accelerating the fuel through a second nozzle;directing the oxidizer against a first side of a separator and radially outward from the common axis;directing the fuel against a second side of the separator, the second side being opposite the first side, and radially outward from the common axis; anddetonating the mixture of the fuel and the oxidizer at a distance from the common axis, within a cylindrical detonation region, to produce a standing detonation wave.
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이 특허에 인용된 특허 (12)
Cowan ; Sr. Howard H. (3315 N. Godfrey #36 Midland TX 79707), Air cooled rotary combustion engine.
Lee Ching-Pang (Cincinnati OH) Venkataramani Kattalaicheri S. (Westchester OH) Lahti Daniel J. (Cincinnati OH) Lee Vincent H. (Jupiter FL), Hypersonic scramjet engine fuel injector.
Tew, David E.; Anderson, Torger J.; Guile, Roy N.; Sobel, David R.; Twelves, Jr., Wendell V.; Jones, Gary D., Pulse detonation engine having an aerodynamic valve.
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