Ram-jet and turbo-jet detonation engine

Abstract

A ram-jet and turbo-jet detonation engine includes an inlet part and a discharge part both shaped as axis-symmetrical round hollow rotating cones interconnected by a narrow middle part, having vanes, mounted on the internal surfaces of the cones, not completely overlapping a central part of a channel, and form spirals, twisted about a common central axis of the channel. The inlet cone with vanes serves as a ventilator/compressor, and the discharge cone with vanes serves as a turbine and discharge nozzle. The middle part and the discharge cone are built as one integral component. A centripetal pump supplies fuel to a mixing section. The engine includes a firing system, generating short high-voltage electrical pulses, providing for burning of combustible mixture in a detonation mode. The invention enables an independent horizontal take-off of flying apparatus and a possibility of varying/alternating the speed within a range from subsonic to hypersonic.

Claims

1. A ram-jet and turbo-jet detonation engine comprising an inlet part, including a fan and a compressor, a middle part, which includes a fuel injection device to the mixing portion, the mixing portion of the fuel and air, the burning system of the air-and-fuel mixture and combustion chamber, and the exhaust part, which comprises a turbine and exhaust nozzle, and the system of fuel ingestion, the device which provides the attachment to the outer case, and the engine control system, which is characterized by the fact that the inlet part and exhaust part are made in the form of axially symmetric round hollow rotating cones connected between each other in the narrow middle part by its narrow parts, which have blades, installed on the inner parts of the cones, that also do not block completely the central part of the channel and form the spirals, spinning around the common central axis of the channel, wherein the inlet cone fulfills the function of the fan/compressor, and the exhaust section with blades has a turbine and exhaust nozzle, wherein the middle part and exhaust section are integrated into one unified detail, the fuel injection device, which provides fuel injection into the mixing portion, is made in the form of a centripetal pump, while the burning system provides the burning of the air-and-fuel mixture in the detonation mode by creating short high-voltage impulses, wherein the rotating parts of the engine are fixed to the external part of the outer case with the use of the bearings installed on the external surfaces of the rotating parts.

2. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the flow tube of the engine is made in the form of a de Laval nozzle having the blades-spirals.

3. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the inlet cone, middle part and exhaust section are made in the form of a single integral rotating detail.

4. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the inlet cone is connected with the middle part by the reduction gear.

5. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the mixing portion and combustion chamber are made in the form of the single round cone expansion of the central channel located in front of the exhaust section having an opening to the side of the exhaust section, while the blades are located near every fuel injection nozzle, rotating every flow of the fuel in accordance with a small radius.

6. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the form, height and spacing of the blades-spirals changes along the axis of the channel.

7. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the exhaust section of adjacent portion of outer case are made as an electric generator, where the rotating exhaust section with magnets attached is used as an armature, and the function of the stator is fulfilled by the adjacent portion of the outer case which has immobile magnetic coils attached to it.

8. The ram-jet and turbo-jet detonation engine according to claim 1, wherein the inlet cone and the adjacent portion of outer case are made as the electric motor, wherein the rotating inlet cone with permanent magnets attached is used as an armature, and the function of the stator is fulfilled by the adjacent portion of the outer case which has immobile magnetic coils attached to it.

9. The ram-jet and turbo-jet detonation engine according to claim 7, wherein the power, produced by the electric generator, is used for charging of the engine itself, airborne equipment and charging of the accumulators.

10. The ram-jet and turbo-jet detonation engine according to claims 7, wherein the electronic elements (magnets, magnetic coils) which are located at the rotating parts of the engine are made by a planar method on their exterior surfaces.

11. The ram-jet and turbo-jet detonation engine according to claim 8, wherein the electronic elements (magnets, magnetic coils) which are located at the rotating parts of the engine are made by a planar method on their exterior surfaces.

Description

BRIEF DESCRIPTION OF DRAWINGS OF THE INVENTION

[0060] All elements in the drawings are shown without certain scale and proportions and are reflected in sectional views of parts of the inventive RTDE (Ram-jet and turbo-jet detonation engine), that form a single integral item.

[0061] FIG. 1Cross section along the principal plane of symmetry with unfolded blades-spirals and unfolded fuel channels of the centripetal pump: [0062] 1rotating inlet cone (fan/compressor); [0063] 2unfolded blades-spirals of the inlet cone (fan/compressor); [0064] 3rotating exhaust section (turbine/nozzle); [0065] 4unfolded blades-spirals of the exhaust section (turbine/nozzle); [0066] 5fixed part of the centripetal pump fuel storage; [0067] 6nozzles (vents) of fuel supply to the fuel storage; [0068] 7fuel channel of the centripetal pump; [0069] 8rotating part of the centripetal pump; [0070] 9conical expansion of the channelmixing area and chamber/combustion area; [0071] 10airstream/approaching flow. [0072] Cross sections: A-A, B-B, C-C, D-Dcross-sectional view perpendicular to the channel.

[0073] Cross Sectionsview along the channel:

[0074] FIG. 2 depicts cross-sectional view of the rotating inlet cone (fan/compressor) A-A: [0075] 11rotation direction of RTDE's parts; [0076] 12rotation direction of air flow in the central channel.

[0077] FIG. 3 depicts a cross-sectional view of a rotating middle part extended up to the centripetal pumpB-B.

[0078] FIG. 4 depicts a cross-sectional view of the centripetal pump with unfolded fuel channelsC-C: 13rotation direction of rotating fuel-air mixture jets.

[0079] FIG. 5 depicts a cross-sectional view of the rotating exhaust section (turbine/nozzle) D-D: 14the direction of rotation of the rotating jets of the combustion products.

THE PREFERRED EMBODIMENTS OF THE INVENTION.

[0080] The Simplest Embodiment (FIG. 1).

[0081] All the rotating elements during the production are integrated into a single integrated detail, the inner blades of which, having a helix form, are screwed in one direction (clock-wise or counter clock-wise), while changing by its form, height and spacing, extending from the beginning of the inlet cone and to the end of the exhaust section.

[0082] The blades have minimal height in the narrow middle section of the channel (possibly, the height can be zerothe absence of the blades in the portion of the maximum conversion of the channel).

[0083] An inlet cone (fan/compressor) 1 (FIG. 1) with blades-spirals is configured to:

[0084] a) at subsonic velocity of the FA, [0085] provide the rotation of the input (countercurrent) airstream 10 (FIG. 1) in the center of the channel in the direction 12 (FIG. 2) by rotating the cone 1 in the direction 11, wherein the air pressed by the centrifugal force to the inner perimeter of the inlet cone, thus, increasing the pressure near the blades 2; [0086] accelerate the wall air flow along the channel and discharge the air in the mixing portion, and, furthermore, in the combustion chamber, while functioning as a fan and a compressor; [0087] provide the near-sonic velocity of the airflow in a conversion (narrowing part) of the channel;

[0088] b) at supersonic velocity of the FA: [0089] drag the vertex of the compression shock's cone, which is formed in the front edge of the air inlet, inside the channel, providing more even (laminar) air movement in the inlet.

[0090] The front edges of the spiral blades of the inlet cone 2 (FIG. 1.) must have cutoffs of outer angles, so that at a low supersonic velocity the conical compression shock, which starts at the front edge of the air inlet and is directed inside the channel, does not touch them.

[0091] At the subsonic motion of the approach flow/airstream 10 (FIG. 1.) along the narrowing inlet cone 1 (FIG. 1), the velocity in the channel gradually increases, and, subsequently, the tilt angle of the blades towards the axis of the engine (channel) must decrease while the helix pitch (the spiral's step) increases. Thus, the helix pitch must be maximum in the narrowest middle portion of the central channel (FIG. 3), while the spiral must be stretched to the limit, and the height of the spiral blades must be minimal/(close to zero).

[0092] A fuel injection device (centripetal pump) 8 (FIG. 1) is configured to inject the fuel from an immovable part of the fuel system, associated with the FA's body, to a rotating annular mixing part.

[0093] The rotating part of the centripetal fuel injection pump 8, having the fuel delivery ducts 7, is rigidly connected (i.e. constitutes a single integral unit) with the turbine 3 (FIG. 1), while the immovable round external part of the pump body 5, which simultaneously acts as a fuel storage unit, is rigidly connected to the immovable outer casing of the engine.

[0094] The immovable round external part of the pump 5 (fuel storage unit) is a U-shaped rotating object (or V-shaped or alike), having an open portion facing the axis of rotation.

[0095] The fuel is injected into the fuel storage unit by the apertures (ducts) 6 situated sidewise, located at some distance from the inner bottom of the U-profile from several (opposite) sides of this body 5.

[0096] During the spinning of the rotating inner part of the pump, the injected fuel, which is dragged (captured) by the rotation, is depressed by the centrifugal force to the inner immovable U-shaped bottom (of the profile) of the fuel storage unit forming an even layer.

[0097] The length of a duct between the inner bottom of the fuel storage unit and the apertures for fuel injection into it must exceed the distance between the bottom of the fuel storage unit and the rotating part of the pump.

[0098] The amount of the injected fuel must be such that, during the rotation of the central (rotating) part of the pump, the level of fuel reached (immersed) the inputs of the fuel channels of the inner rotating part of the centripetal pump, but also did not reach (did not fill) the apertures for fuel injection. This mode is designed to inject the liquid fuel into the combustion chamber.

[0099] The fuel is injected by the inlets of the fuel channels, facing in the same direction as the direction of the rotation of the central part of the centripetal pump, and is injected to the section mixing fuel and air, located along the perimeter (around) of the narrow part of the central channel of the engine.

[0100] The direct-flow combustion chamber may require more combustible gas fuel at the hypersonic (supersonic) velocity of the FA.

[0101] In order to inject the gas fuel (vapor) into the combustion chamber, the amount of the fuel, injected into the fuel storage unit, is adjusted in such manner that the inlets of the fuel channels of the rotating part of the pump (during its rotation) would not reach the level of the liquid fuel, which is depressed by the centrifugal force to the bottom of the fuel storage unit (that would be located above it), and the fuel channels would receive only vapor of the fuel.

[0102] The electrical heating elements, which regulate/increase the temperature of the fuel in the fuel storage unit, are attached to the body of the resting fuel storage unit on the exterior side in order to provide intensive evaporation of the fuel, increase of the temperature and pressure of the fuel vapor in the fuel storage unit, or, if necessary, inject the hot liquid fuel into the combustion chamber.

[0103] The mixing portion of fuel with air 9 (FIG. 1.) is designed to create a combustible fuel-air mixture by creating along the perimeter (around) of the central part of the flow of the rotating airflows (resembling the rotating roller in the roller bearing, but consisting of gas jets)section C-C (FIG. 4).

[0104] The form of the blades on this portion is made in such a way, that the streams twirl at a small radius 13.

[0105] The velocity of the fuel stream in the fuel channels of the centripetal pump and, subsequently, the velocity of outflow of fuel in the central channel will be subsonic.

[0106] The combustion chamber (portion) with detonation burning (combustion) 9 (FIG. 1) is configured for impulse detonation, burning the combustion mixture, while its surface acts as a reflective surface during the detonation burning.

[0107] The blades-spirals on this portion are located so that that one of their sides is approximated to one rotating stream so (every blade is associated with its own stream) that the pressure of the flow during the detonation burning on this (own) blade is greater than on the more distant blade from the other side of the flow.

[0108] The direction (the angle of location) of the reflective surfaces of the blades is made so that, during the detonation burning, the reflected wave is directed along the channel of the spiral.

[0109] Thus, the tangential component of the pressure on the reflecting surface during the detonation burning rotates the exhaust section (nozzle), and the component of the pressure creates the exhaust thrust.

[0110] The mode of impulse high-voltage burning is chosen on the basis of durability and possibility of oxygen-hydrocarbon mixture burning.

[0111] The pulse ratio and the periodicity of the high-voltage impulses of the detonation burning of the burning mixture are chosen so that with them the stream of the burning mixture, while rotating, could pass from the beginning to the end of the cone extension of the rotating channel after the mixing portion (mixing portionchamber/combustion portion).

[0112] The frequency of the burning impulses which depends on the velocity of rotation of the burning chamber and the amount of blades-spirals will be high. This will provide for high and constant average engine thrust.

[0113] The blades-spirals will have a gap between the mixing portion and the chamber/burning portion.

[0114] The exhaust section (nozzle/turbine) 3 (FIG. 1.) is configured to: [0115] create the engine thrust by forming the supersonic reactive jet flow; and [0116] provide the rotation of the nozzle with the use of tangential component of the pressure of the flow.

[0117] The rotating and extending flows 14 (FIG. 5.) after burning on the perimeter around the central flow 12 provide linear pressure on the blades 4, as in the combustion chamber, while providing additional tangential force which rotates the nozzle 3 in the direction 11.

[0118] The engine thrust and the rotation of the nozzle are provided by the accumulated linear and tangential forces inside the cone-like combustion chamber (during the detonation burning) and in the output cone (during the supersonic exit of the jet flow).

[0119] The inlet cone is made in the form of an electric motor so that it could be swirled with the use of vehicle-borne batteries or an external source (during the start).

[0120] The exhaust section is made in the form of an electrical generator so that it could provide burning of the air-fuel mixture, charging of magnetic bearings (if provided), charging of vehicle-borne batteries and vehicle-borne equipment of the FA.

[0121] The rotation of the inlet cone during the flight is provided by rotation of the exhaust conical section (nozzle/turbine), which is rigidly connected to the inlet cone.

[0122] The electrical elements (magnets, magnetic coil), located on the rotating parts of the engine, are made by planar technology on their external surfaces in order to minimize their thickness and weight.

[0123] The bearings (frictionless or magnetic), which are located at the external surfaces of the rotating parts, are used as devices that provide for mounting the rotating parts of the engine on the immovable outer case.

INDUSTRIAL APPLICABILITY

[0124] The straight-flow turbo-jet engine is configured as the engine of military/civilian apparatus which has horizontal takeoff/landing and long flight with the possibility to change/mix the velocity between subsonic and hypersonic velocity.

[0125] Apart from that, the straight-flow turbo-jet engine can be used as an independent stationary/mobile electric generator or a pump configured to pump air at a high-velocity (for example, in wind tunnels).