An engine is described that derives its propulsive energy from the flash expansion of liquid nitrogen from a liquid form to a gaseous form. The gaseous nitrogen is forced to escape from the rear of a casing of the engine, thereby providing a propulsive force to the casing. The escaping gaseous nitro
An engine is described that derives its propulsive energy from the flash expansion of liquid nitrogen from a liquid form to a gaseous form. The gaseous nitrogen is forced to escape from the rear of a casing of the engine, thereby providing a propulsive force to the casing. The escaping gaseous nitrogen, mixed with air, is harnessed to rotate a first fan that in turn rotates a second fan that draws air into the front of the engine. The warmer air flowing through the engine is utilized to regulate the temperature of the engine, and to facilitate the evaporation of the nitrogen propellant, thereby creating a steady state condition that may last as long as the supply of liquid nitrogen.
대표청구항▼
1. An engine for providing motion comprising: a casing with a forward terminal end and a rearward terminal end, the casing having a hollow interior defined by a bore that has an axis of symmetry, the bore extending continuously along the axis from the forward end to the rearward end, the bore includ
1. An engine for providing motion comprising: a casing with a forward terminal end and a rearward terminal end, the casing having a hollow interior defined by a bore that has an axis of symmetry, the bore extending continuously along the axis from the forward end to the rearward end, the bore including a flow constriction at a location between the forward end and the rearward end;a center body positioned within the bore and sized such that the bore is not completely obstructed at any point between the forward end and the rearward end, the center body including a forward hub, a middle hub, and a rearward hub, the middle hub being flanked by the forward hub and the rearward hub, wherein the forward hub and the rearward hub are connected to each other by a rod extending rotationally freely through the middle hub whereby the forward hub and the rearward hub are configured to rotate in unison while the middle hub remains rotationally stationary;a forward fan attached to the forward hub;a rearward fan attached to the rearward hub, wherein the rearward fan is configured to drive the forward fan, and the forward fan is configured to draw air from outside the casing into the bore, the forward fan, rearward fan, and bore being configured in relation to each other such that air drawn into the casing is propelled through the bore in a continuous stream from the forward end to the rearward end;a plurality of support elements, each support element being connected to the casing at a first portion of the support element, and to the middle hub at a second portion of the support element, the support elements being collectively configured to support the middle hub in relation to the casing;at least one delivery tube extending from a first location outside the casing to a second location in the bore of the casing, the delivery tube being configured to deliver liquid nitrogen from the first location to the second location. 2. The engine of claim 1, wherein the at least one delivery tube comprises a hollow bore extending within one of the support elements. 3. The engine of claim 2, wherein the bore extending within one of the support elements connects to a bore extending within the middle hub. 4. The engine of claim 3, wherein the bore extending within the middle hub opens onto an external surface of the middle hub. 5. The engine of claim 1, wherein each support element is connected to the casing at the first portion of the support element through a first rotationally movable bearing, and is connected to the middle element at the second portion of the support element through a second rotationally movable bearing, whereby the center body is movable along the axis of the bore while being supported by the support elements. 6. The engine of claim 1, wherein the flow constriction in the bore includes the center body positioned to partially obstruct a portion of the bore. 7. The engine of claim 6, wherein the bore has an internal diameter, and the flow constriction includes a narrowing of the internal diameter. 8. The engine of claim 1 wherein the forward fan is configured to drive air perpendicularly across a diameter of the fan. 9. The engine of claim 1, wherein the forward fan is configured to drive air parallel with a diameter of the fan. 10. A method of providing propulsive power comprising: providing an engine casing having a bore extending from a forward terminal end of the casing to a rearward terminal end of the casing;forcing air in a continuous stream through the bore from the forward end to emerge from the bore at the rearward end;injecting liquid nitrogen into the bore at the same time that air is being forced through the bore;evaporating the liquid nitrogen into gaseous form in the presence of the air;expelling the gaseous nitrogen, mixed with air, from the rearward end of the casing thereby providing a forwardly propulsive force to the casing. 11. The method of claim 10, wherein forcing air through the bore includes rotating a first fan inside the bore using, as a rotational propellant, the nitrogen mixed with air being expelled from the casing, and thereby rotating a second fan connected to the first fan so that the second fan draws air into the casing. 12. The method of claim 10, wherein forcing air through the bore includes forcing the air past a constriction in the bore, thereby accelerating the air in the vicinity of the constriction. 13. The method of claim 12, wherein forcing air past a constriction includes forcing the air past a reduction in an internal diameter of the bore. 14. The method of claim 12, wherein forcing air past a constriction includes forcing the air around an aerodynamically shaped element located within the bore. 15. The method of claim 12, wherein injecting liquid nitrogen into the bore includes injecting the liquid nitrogen to a location in the bore that coincides with the location of the constriction in the bore. 16. The method of claim 10, further including electively changing the size of the constriction in the bore. 17. The method of claim 16, wherein changing the size of the constriction in the bore includes moving an aerodynamically shaped object along the axis of the bore.
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Holl Raymond (Farnham EN), Aircraft gas turbine engine turbine blade cooling.
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