WO2012003706A1 - 超音速转子发动机 - Google Patents

超音速转子发动机 Download PDF

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Publication number
WO2012003706A1
WO2012003706A1 PCT/CN2011/000471 CN2011000471W WO2012003706A1 WO 2012003706 A1 WO2012003706 A1 WO 2012003706A1 CN 2011000471 W CN2011000471 W CN 2011000471W WO 2012003706 A1 WO2012003706 A1 WO 2012003706A1
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WO
WIPO (PCT)
Prior art keywords
supersonic
rotating structure
storage tank
combustion chamber
reducing agent
Prior art date
Application number
PCT/CN2011/000471
Other languages
English (en)
French (fr)
Inventor
靳北彪
Original Assignee
Jin Beibiao
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Jin Beibiao filed Critical Jin Beibiao
Publication of WO2012003706A1 publication Critical patent/WO2012003706A1/zh

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
    • F01D1/22—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially radially

Definitions

  • the present invention relates to the field of thermal energy and power, and more particularly to a supersonic rotary engine.
  • the supersonic jet channel body (such as a rocket nozzle) can be used as a thrust generating engine to convert thermal energy into supersonic gas kinetic energy with very high efficiency.
  • the supersonic jet channel body can be very High propulsion efficiency, when the supersonic jet channel body moves at a speed close to the speed of supersonic gas ejected from the supersonic jet channel, the kinetic energy of the supersonic gas can be turned into a supersonic jet channel body 100%. The sum of the kinetic energy and the energy of the supersonic jet channel body.
  • thermodynamic system is simple in structure and high in efficiency, but the supersonic injection passage body is difficult to use as an engine that outputs rotational power, because when the supersonic injection passage body rotates at a high linear speed, a large centrifugal force is generated, and now It is difficult to withstand this huge centrifugal force. If the supersonic injection passage body cannot be made to move at a high linear velocity circular motion, only a part of the kinetic energy of the gas injected from the supersonic injection passage body becomes the kinetic energy of the supersonic injection passage body and the supersonic injection passage body is externally made.
  • thermodynamic system engine
  • the supersonic jet of the supersonic jet channel body can be used to efficiently output rotational power to the outside, and an extremely simple and highly efficient engine can be manufactured. Summary of the invention
  • thermodynamic system capable of outputting rotational power with a supersonic gas injected from a supersonic injection channel body
  • the working mechanism of a thermodynamic system capable of outputting rotational power with a supersonic gas injected from a supersonic injection channel body can conclude that if the efficiency of the system is to be improved, the most important There are three ways: one is to convert the thermal energy into the supersonic gas with the highest possible efficiency; the other is to make the supersonic jet channel body (rocket nozzle, ramjet nozzle, etc.) at the highest possible line speed. Circular motion; Third, if there is no way to make the supersonic jet channel body move at a relatively high linear velocity, it is necessary to find a way to recover the kinetic energy of the high velocity gas that has left the supersonic jet channel body.
  • a supersonic rotary engine comprising a supersonic injection passage, a rotating structure and a high-pressure working medium, the supersonic injection passage being disposed on the rotating structure, a working inlet of the supersonic injection passage and the a high-pressure working medium source is connected, the jetting direction of the supersonic jet channel is generally pointed by a tangent to the rotating circumference of the rotating structure body, and the rotating structure body outputs power externally; when the supersonic rotor engine is working normally, The supersonic injection channel ejects a gas velocity greater than 2 Mach, and the static pressure of the gas jet ejected from the supersonic jet channel is equal to or less than atmospheric pressure.
  • the supersonic rotor engine further includes a passive rotating structure on which a striking transmission structure is provided, and the airflow striking by the supersonic jet channel pushes the passive rotating structure on the striking transmission structure Rotating, the passive rotating structure also outputs power to the outside.
  • the rotating structure is disposed at a periphery of the passive rotating structure
  • the passive rotating structure is disposed at a periphery of the rotating structure
  • the passive rotating structure and the rotating structure are arranged side by side.
  • a working fluid inlet of two or more of the supersonic injection passages is in communication with one of the high pressure working fluid sources.
  • the supersonic jet channel is configured as a Laval nozzle.
  • the high-pressure working fluid source is disposed on the rotating structure body or on the connecting structure of the rotating structure body or on the body of the supersonic rotor engine;
  • the high-pressure working fluid source is in communication with the supersonic jet passage via a single-channel rotary joint.
  • the striking transmission structure is configured as a flow guiding channel, and the airflow injected by the supersonic injection channel obtains additional thrust to further push the passive rotating structure body when the flow guiding channel blows out from the guiding channel The passive rotating structure rotates.
  • the high-pressure working medium source is set as a rocket combustion chamber, and the rocket combustion chamber is disposed on the rotating structure body and/or the connecting structure body of the rotating structure body, and/or the rotating structure body
  • An oxidant storage tank and a reductant storage tank are disposed on the connecting structure of the rotating structure, and the oxidant storage tank and the reducing agent storage tank are in communication with the rocket combustion chamber.
  • the high-pressure working medium source is set as a rocket combustion chamber, and the rocket combustion chamber is disposed on the rotating structure body and/or the connecting structure body of the rotating structure body, and an oxidant is disposed on the body of the supersonic rotor engine Storage tank and reducing agent storage tank;
  • the oxidant storage tank and the reductant storage tank are in communication with the rocket combustion chamber via a pre-mixer via a single-channel rotary joint, the oxidant in the oxidant storage tank and the reducing agent in the reducing agent storage tank are Burning in the rocket combustion chamber;
  • the oxidant storage tank and the reductant storage tank are in communication with the rocket combustion chamber via different passages in a two-channel rotary joint, the oxidant in the oxidant storage tank and the reducing agent in the reducing agent storage tank being The rocket combustion chamber is mixed and burned.
  • the high-pressure working medium source is set as a rocket combustion chamber, and the rocket combustion chamber is disposed on the rotating structure body and/or the connecting structure body of the rotating structure body, and an oxidant is disposed on the body of the supersonic rotor engine Storage tanks, reducing agent storage tanks and expansion agent storage tanks;
  • the oxidant storage tank, the reductant storage tank, and the expansion agent storage tank are in communication with the rocket combustion chamber via a pre-mixer via a single-channel rotary joint, the oxidant and the reducing agent in the oxidant storage tank
  • the reducing agent in the storage tank enters the rocket combustion chamber and burns;
  • the two storage tanks of the oxidant storage tank, the reducing agent storage tank and the expansion agent storage tank are connected to the rocket combustion chamber via a premixer and through one of the two-channel rotary joints, third a storage tank is communicated with the rocket combustion chamber via another passage of the two-channel rotary joint, and the oxidant in the oxidant storage tank and the reducing agent in the reducing agent storage tank enter the rocket combustion chamber and burn ;
  • the oxidant storage tank, the reductant storage tank, and the expansion agent storage tank are in communication with the rocket combustion chamber via different passages of a three-way rotary joint, the oxidant and the reducing agent in the oxidant storage tank
  • the reducing agent in the storage tank enters the rocket combustion chamber and is mixed and combusted.
  • a low speed bushing is disposed between the rotating shaft of the rotating structure and the rotating shaft support.
  • a rotating shaft of the rotating structure and a passive rotating shaft of the passive rotating structure are fitted to each other, and a stationary sleeve is disposed between the rotating shaft and the passive rotating shaft.
  • the supersonic rotor engine further includes a working fluid recovery casing, and a working fluid outlet is disposed on the working fluid recovery casing, and the supersonic injection passage and the rotating structure are disposed in the working fluid recovery casing In the structure in which the passive rotating structure is disposed, the supersonic jet passage, the rotating structure, and the passive rotating structure are disposed inside the working medium recovery casing.
  • the working medium recovery casing is configured as a condensing cooling medium recovery casing, and a condensing cooler is disposed at the condensing cooling medium recovery casing, and the condensing cooling medium recovery casing is fixedly connected to the rotating structure
  • the high-pressure working medium source is disposed on the rotating structure body, the high-pressure working medium source is set as an external combustion type high-pressure working medium generator, and a burner is disposed at the external combustion type high-pressure working substance generator The burner is heated by the external combustion type high-pressure working generator, and the working fluid outlet of the condensing cooling medium recovery casing is connected with the external combustion type high-pressure working generator, under the action of centrifugal force
  • the condensed working medium is flowed from the condensing and cooling medium recovery casing to the external combustion type high-pressure working fluid generator through the working fluid outlet, and the working medium is vaporized in the external combustion type high-pressure working substance generator A high temperature and high pressure gaseous working medium enters the supersonic jet channel.
  • the so-called supersonic jet passage of the present invention refers to all passages capable of injecting supersonic gas, that is, all injection passages that can change the thermal energy and pressure energy of the gas into the kinetic energy of the injected gas, such as a Laval nozzle, a rocket nozzle, And other shapes of passages that can jet supersonic gas, such as passages between two blades that can eject supersonic gas.
  • the rotating structure in the present invention refers to any structure that can be rotated, such as a flywheel, a rod that can be rotated, and a ring structure that can be rotated.
  • the original working medium is a high pressure entering the rocket combustion chamber.
  • the so-called turning circumference of the present invention refers to the circumference of the track formed when the rotating structure is rotated, and the circumference of the track may be the circumference of the outer track of the rotating structure, the circumference of the inner track, and the circumference of the outer track of the rotating structure and the circumference of the inner track. Any point of the track is formed by the rotation of the circumference of the track.
  • the so-called tangential line of the rotating circumference of the rotating structure body is generally pointed, including the case where the tangential line of the rotating structure body is completely accurate in the injection direction, and also includes the fact that although there is a certain degree of declination, The tangential line of the rotating circumference of the rotating structure is still the direction of the injection.
  • the tangent to the circumference of the revolution may be a tangent to the circumference of the outer track, a tangent to the circumference of the inner track, and a tangent to the circumference of the track formed by any point between the circumference of the outer track of the rotating structure and the circumference of the inner track.
  • the so-called high-pressure working medium source of the present invention refers to any system capable of providing a high-pressure gas working medium, and may be a rocket combustion chamber, a ramjet combustion chamber, a pulse combustion chamber, a high-pressure steam generator (high-pressure boiler), and the like.
  • the so-called high-pressure working fluid source in the present invention includes a high-pressure working fluid source generated in the form of external combustion, a high-pressure working fluid source generated in the form of internal combustion, and a high-pressure working fluid source generated in a mixed combustion mode, and also includes a high-pressure compressed gas source.
  • the so-called high-pressure working medium generated by the internal combustion form includes a combustion chamber and a system for supplying an oxidant and a reducing agent to the combustion chamber, and may further include a system for supplying a expanding agent to the combustion chamber, and the so-called expansion agent means not participating in the combustion chemical reaction, but
  • the working fluid which is heated or vaporized in the combustion chamber to expand the volume of the gas generated by the heat, the main function of the expansion agent is to adjust the temperature in the combustion chamber and the number of moles involved in the working medium.
  • the so-called high-pressure working fluid source produced by the external combustion mode refers to a system that generates high-temperature and high-pressure working fluid by means of external combustion.
  • the so-called high-pressure working medium produced by the co-combustion mode refers to a thermodynamic system in which all or almost all of the heat released by the combustion of the fuel is involved in the work cycle.
  • the patent relating to co-firing applied by the present inventors see the patent relating to co-firing applied by the present inventors.
  • the passive rotating structure of the present invention refers to a structure that can perform a rotational motion when receiving a high-speed gas jet ejected from the supersonic jet channel body.
  • the passive rotating structure can separately output power to the outside, and can output power to the rotating structure separately, or can be combined with the rotating structure through a reversing mechanism (such as an idler) to output power.
  • the so-called striking transmission structure in the present invention refers to a structure that can be subjected to high-speed gas striking on the passive rotating structure to rotate the passive rotating structure, and can be a leaf-like structure, a channel-like structure, etc., and the gas is in the striking transmission structure. It can flow either radially or axially.
  • the gas ejected from the supersonic jet channel The flow speed is greater than Mach 3.
  • the air velocity ejected from the supersonic jet passage is greater than 4 Mach.
  • the air velocity ejected from the supersonic jet passage is greater than 5 Mach.
  • the air velocity ejected from the supersonic jet passage is greater than 6 Mach.
  • the so-called condensing cooling medium recovery casing of the present invention refers to a working fluid recovery casing having a condensing cooling function.
  • the condensing cooler refers to a device that can cool the condensing cooling medium recovery casing.
  • the so-called burner refers to a combustion device capable of burning the heat to heat the external combustion type high-pressure working generator to vaporize the internal working medium.
  • the so-called external combustion type high-pressure working fluid generator refers to a device that heats the internal working medium by external heat to generate high-temperature and high-pressure gaseous working medium.
  • connection structure of the rotating structure in the present invention means a structure connected to the rotating structure, such as a rotating shaft, a rotating arm or a gear on a rotating structure.
  • the so-called rotating structure of the present invention directly outputs power to the rotating structure to directly output power, or indirectly through the connecting structure of the rotating structure, and the passive rotating structure is also the same.
  • the rotation direction of the rotating structure and the passive rotating structure in the present invention may be the same or different.
  • a buffer structure may be provided on a portion of the passive rotating structure that is subjected to the high-speed jet airflow striking transmission of the supersonic jet passage, and the buffer structure is designed to reduce high-speed gas.
  • the reflection acts to more efficiently transfer the kinetic energy of the high velocity gas to the passive rotating structure.
  • the so-called buffer structure of the present invention may be a multi-space structure, a rough surface structure, a mesh structure or a multi-gate structure, which enables a high-speed flying gas to stay on a surface impinging on these structures, as if two viscoelastic properties.
  • the bodies collide with each other, and the kinetic energy of the high-speed moving gas can be transmitted to the passive rotating structure more efficiently.
  • the so-called supersonic jet passage in the present invention is a supersonic jet passage because of a rotary motion.
  • the design aspect should consider the influence of centrifugal force.
  • the supersonic rotary engine disclosed in the present invention can be machined from a ceramic material.
  • the rotating structure of the present invention rotates at a high speed, so the rotating structure can be directly connected to other machines, or can be connected to a generator, or the rotating structure can be used as a rotor of a generator or a rotor of a generator. On the rotating structure.
  • the working medium recovery casing can be arranged to recover the heat and the working fluid of the supersonic injection passage exhaust gas, and at the same time, the working medium recovery casing can be evacuated to be in a low pressure or vacuum state to improve the efficiency of the engine.
  • the working fluid recovered from the working fluid recovery casing can be directly discharged, can be discharged after treatment (such as three-way catalyst, etc.), or can be re-entered into the supersonic injection channel after being heated by pressure, and can also be treated to carbon dioxide. Liquefaction is recovered.
  • the supersonic injection passage operates at a lower speed than the supersonic injection passage, so the higher the speed of the supersonic injection passage, the higher the efficiency. For this reason, the higher the rotational speed of the rotating structure in the present invention, the higher the efficiency. Since high-speed rotation produces strong centrifugal force, it is very likely that the desired speed is difficult to achieve due to limitations in the prior art and materials, so the supersonic jet channel jet (exhaust gas) still has a large kinetic energy. Therefore, a passive rotating structure is provided, and the exhaust gas injected by the supersonic injection channel of the present invention is driven against the passive rotating structure by the nearly tangential overall direction, thereby causing the passive rotating structure to rotate and output power, thereby further improving the efficiency of the engine. .
  • the principle of the invention is to use the supersonic injection channel to convert the thermal energy and pressure energy of the working medium existing in the high-pressure working medium source into the kinetic energy of the high-speed gas ejected from the supersonic injection channel with the highest possible efficiency.
  • the static pressure of the high velocity gas ejected by the supersonic jet channel is equal to the supersonic jet
  • the ambient pressure at the exit of the jet channel, the ambient pressure at the exit of the sonic jet channel can be atmospheric pressure or lower than atmospheric pressure. If it is lower than atmospheric pressure, the working fluid recovery housing must be set to recover the working fluid.
  • the vacuum is drawn so that the pressure in the working fluid recovery casing is lower than the atmospheric pressure (as if the bullet was fired from the gun, the energy in the gunpowder is converted into the kinetic energy of the bullet as efficiently as possible).
  • the supersonic jet channel body (the structure that constitutes the supersonic jet channel, such as a rocket nozzle, etc.) is subjected to a reaction force, since the supersonic jet channel is provided on the rotating structure, Therefore, the rotating structure will rotate and output power to the outside.
  • the supersonic injection passage converts the pressure energy and thermal energy of all gases into the kinetic energy of the gas and obtains the reverse thrust from the process to form the rotary motion of the rotating structure to output the power.
  • the high-speed moving gas that leaves the supersonic jet channel strikes the striking transmission structure provided on the passive rotating structure, and changes the kinetic energy of the gas into the rotational motion of the passive rotating structure and outputs the power to the external rotating body and the passive rotating structure.
  • the rotating structure and the passive rotating structure may be sealed or opened.
  • two coordinate systems can be used to observe the supersonic gas, and one is disposed on the supersonic jet channel body.
  • the coordinate system and the second is the coordinate system provided on the supersonic rotor engine body.
  • a passive rotating structure is provided to recover the kinetic energy of a gas that is still moving at a high speed in a coordinate system provided on the supersonic rotor engine body, in the process, high speed
  • the gas strikes the passive rotating structure to push the passive rotating structure to rotate and output power (as if the bullet hits the target, forcing the target to shift and work externally).
  • the relationship between the rotating structure and the passive rotating structure is completely different from the relationship between the adjacent counter-rotating blades of the conventional counter-rotating steam turbine and the gas turbine.
  • both the rotating structure and the passive rotating structure of the present invention rotate; the second is according to Newton's third law, the force received by the rotating structure in the present invention is obtained by the injection of high-pressure gas, and the structure of the passive rotating structure The rotation is obtained by the impact of high-speed gas, and the conventional steam turbine and gas turbine are obtained by the change of the pressure difference.
  • the speed of the gas ejected from the supersonic injection channel in the present invention is generally at several Mach.
  • the structure disclosed in the present invention can manufacture not only a large supersonic rotary engine but also a micro supersonic rotary engine.
  • the miniature supersonic rotary engine is much more efficient than a microturbine and has a simple structure.
  • the oxidant storage tank and the reducing agent storage tank may be rotated together with the rotating structure body, or may be rotated together with the rotating structure body to supply the oxidizing agent and the reducing agent to the high-pressure working source through the rotary joint.
  • the high-pressure working fluid source can also be set to rotate with the rotating structure or not rotate together with the rotating structure, but communicate with the supersonic jet passage through the rotary joint.
  • the oxidant, reducing agent and expansion agent can be called the original working medium.
  • the original working fluid storage tank rotates together with the rotating structure body, at least two sets of supersonic rotary engine can be set, and the supersonic rotary engine works alternately. It is also possible to add a new original working fluid; it is also possible to provide a rotary joint in this system. When the engine is rotating at a high speed, the coupling of the rotary joint is separated. When the engine is at a lower rotational speed, the coupling of the rotary joint is formed to cooperate with the supersonic jet.
  • the channel replenishes the original working fluid, so that the original working fluid can be replenished to the original working fluid when the engine is at a lower speed, without stopping, and there is no need to set a plurality of supersonic rotary engines, which is like an aerial refueling of the aircraft.
  • control of the original working fluid flow rate and the control of the rotary engine can be realized by the brush power supply control solenoid valve, or through the remote control solenoid valve.
  • control valve of the original working medium and/or the control valve disposed between the high-pressure working source and the supersonic injection channel can be controlled from the body by electromagnetic control to achieve the super Control of the sonic rotor engine.
  • the rotational speeds of the rotational structure of the rotating structural body and the passive rotating structural body are different, and in many structures, they may be fitted to each other, which may cause a pair of contacts.
  • a static bushing is provided between the shafts of the two mutually facing sets to reduce the relative rotational speed.
  • the so-called low speed bushing of the present invention refers to an isolating bushing having a rotational speed lower than that of the rotating structure.
  • the purpose of the present invention is to reduce the relative rotational speed difference between the bushings to form good lubrication conditions, increase life and reliability.
  • the rotation of the low-speed bushing can be driven by the rotating bushing (the bushing of the rotating structure or the bushing of the passive rotating structure), that is, the low-speed bushing is set to free, or the corresponding driving mechanism can be set on the low-speed bushing.
  • the low speed bushing rotates.
  • the so-called stationary bushing of the present invention refers to an isolating bushing in a static state, and the stationary bushing is disposed between the rotating shaft and the passive rotating shaft which are mutually set to rotate against each other, and the purpose thereof is to reduce the between the rotating shaft and the passive rotating shaft. Relative rotational speed difference to form good lubrication conditions, increasing life and reliability.
  • the so-called rotating shaft of the present invention refers to a rotating shaft connected to the rotating structure
  • the so-called passive rotating shaft refers to a rotating shaft connected to the passive rotating body
  • the so-called rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and both coupling members are provided with fluid passages, and fluid passages are provided in different coupling members. Interconnected to each other to achieve a flow of fluid from one couple to another.
  • the so-called single-channel rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and the two coupling members are provided with fluid passages, which are arranged in different coupling parts.
  • the fluid passages communicate with each other to achieve a flow of fluid from one couple to the other Pieces.
  • the so-called two-channel rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and two types of fluid passages are provided in the two coupling members, which are arranged in different pairs.
  • the same type of fluid passages of the pieces communicate with each other to realize a device in which two fluids flow from one even to the other.
  • the so-called three-channel rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and three types of fluid passages are provided in the two coupling members, which are arranged in different coupling parts.
  • the same type of fluid passages communicate with each other to realize a device in which three fluids flow from one coupling member to the other.
  • the invention has simple structure, low manufacturing cost and high reliability.
  • the present invention greatly improves the efficiency of existing engines.
  • Figure 1 is a schematic view of Embodiment 1 of the present invention.
  • Figure 1 is a schematic view of Embodiment 2 of the present invention.
  • Figure 3 is a schematic view of Embodiment 3 of the present invention.
  • Figure 4 is a schematic view of Embodiment 4 of the present invention.
  • Figure 5 is a schematic view of Embodiment 5 of the present invention.
  • Figure 6 is a schematic view of Embodiment 6 of the present invention.
  • Figure 7 is a schematic view of Embodiment 7 of the present invention.
  • Figure 8 is a schematic view of Embodiment 8 of the present invention.
  • Figure 9 is a schematic view of Embodiment 9 of the present invention.
  • Figure 10 is a schematic view of Embodiment 10 of the present invention.
  • Figure 11 is a schematic view of Embodiment 11 of the present invention
  • Figure 12 is a schematic view of Embodiment 12 of the present invention
  • Figure 13 is a schematic view of Embodiment 13 of the present invention.
  • FIG. 16 and Figure 17 are schematic views of an embodiment 15 of the present invention.
  • Figure 18 is a schematic illustration of an embodiment 16 of the present invention.
  • the supersonic rotary engine shown in FIG. 1 includes a supersonic injection passage 1, a rotating structure 2 and a high-pressure working source 3, and the supersonic injection passage 1 is disposed on the rotating structure 2, and the working fluid of the supersonic injection passage 1
  • the inlet 1001 is in communication with the high-pressure working source 3, and the jetting direction of the supersonic jet passage 1 is generally directed by a tangent to the circumference of the rotating structure 2, and the rotating structure 2 outputs power to the outside.
  • the air velocity ejected from the supersonic jet passage is greater than 2 Mach, and the static pressure of the jet ejected from the supersonic jet passage is equal to the atmospheric pressure.
  • the supersonic rotary engine shown in FIG. 2 differs from the first embodiment in that: the supersonic injection passage 1 is set as a Laval nozzle 102, and the supersonic rotary engine further includes a passive rotating structure 5 in a passive rotating structure. 5 is provided with a striking transmission structure 52. The jet airflow of the supersonic jet channel 1 drives the passive rotating structure 5 to the passive rotating structure 5 on the striking transmission structure 52, and the passive rotating structure 5 also outputs power to the outside.
  • the passive rotating structure 5 is disposed outside the rotating structure 2, and the working inlet 1001 of the two or more supersonic jet channels 1 is in communication with a high-pressure working source 3.
  • the passive rotating structure 5 is provided with a flow guiding passage 8 , and the jetting airflow of the supersonic jetting channel 1 is driven by the passive rotating structure 5 and then flows through the guiding channel 8 to obtain additional thrust to further promote passive rotation.
  • the structure 5 is rotated.
  • the air velocity ejected from the supersonic jet passage is greater than 3 Mach.
  • the supersonic rotor engine shown in FIG. 3 differs from the second embodiment in that: the rotating structure 2 is disposed at the periphery of the passive rotating structure 5, and the supersonic jet passage 1 of the passive rotating structure 5 is An air cushion cushioning structure 51 is provided at a portion of the high-speed jet stream striking, and the air cushion cushioning structure 51 reduces reflection of the high-speed jet stream.
  • the air velocity ejected from the supersonic jet channel is greater than Mach 4.
  • the supersonic rotary engine shown in FIG. 4 differs from the second embodiment in that: the high-pressure working fluid source 3 is set as a rocket combustion chamber 31, and the rocket combustion chamber 31 is disposed on the rotating structural body 2, and is passively rotated.
  • the structure 5 and the rotating structure 2 are arranged side by side. When the supersonic rotor engine is operating normally, the air velocity ejected from the supersonic jet channel is greater than Mach 5.
  • the supersonic rotary engine shown in FIG. 5 differs from the first embodiment in that: the high-pressure working fluid source 3 is disposed on the body of the supersonic rotary engine, and the high-pressure working fluid source 3 passes through the rotary joint 10 and the supersonic jet passage 1 Connected.
  • the air velocity ejected from the supersonic jet channel is greater than Mach 6.
  • the supersonic rotary engine shown in FIG. 6 differs from the first embodiment in that it further comprises a suspension bearing 6, the suspension bearing 6 suspending the rotating structure 2, and the high-pressure working source 3 is disposed on the rotating structure 2, the high voltage
  • the working fluid source 3 is in communication with the supersonic injection passage 1, and the high-pressure working fluid source 3 is set as a rocket combustion chamber 31, and the rocket combustion chamber 31 is disposed on the rotating structural body 2, and is rotated on the rotating structural body 2
  • the connecting structure of the structural body 2 is provided with an oxidizing agent storage tank 2001 and/or a reducing agent storage tank 2002, and the oxidizing agent storage tank 2001 and the reducing agent storage tank 2002 are in communication with the rocket combustion chamber 31.
  • the supersonic rotary engine shown in FIG. 7 differs from the first embodiment in that: the high-pressure working fluid source 3 is set as the rocket combustion chamber 31, and the rocket combustion chamber 31 is provided in the rotating structural body 2 and/or the rotating structural body 2.
  • an oxidant storage tank 2001 and a reducing agent storage tank 2002 are arranged on the body of the supersonic rotary engine; the oxidant storage tank 2001 and the reducing agent storage tank 2002 are burned by the premixer 2004 through the single-channel rotary joint 10 and the rocket.
  • the chamber 31 is in communication, and the oxidant in the oxidant storage tank 2001 and the reducing agent in the reducing agent storage tank 2002 are combusted in the rocket combustion chamber 31.
  • Example 8 The supersonic rotary engine shown in Fig. 8 differs from the embodiment 7 in that the oxidant storage tank 2001 and the reductant storage tank 2002 are in communication with the rocket combustion chamber 31 via different passages in the two-way rotary joint 20, the oxidant storage tank The reducing agent in the oxidant and reductant storage tank 2002 in 2001 is mixed and burned in the rocket combustion chamber 31.
  • the supersonic rotary engine shown in FIG. 9 differs from the first embodiment in that: the high-pressure working fluid source 3 is set as the rocket combustion chamber 31, and the rocket combustion chamber 31 is provided in the rotating structural body 2 and/or the rotating structural body 2.
  • an oxidant storage tank 2001, a reducing agent storage tank 2002 and an expansion agent storage tank 2003 are arranged on the body of the supersonic rotary engine; the oxidant storage tank 2001, the reducing agent storage tank 2002 and the expansion agent storage tank 2003 are premixed.
  • the device 2004 is in communication with the rocket combustion chamber 31 via a single-channel rotary joint 10, and the oxidant in the oxidant storage tank 2001 and the reducing agent in the reducing agent storage tank 2002 enter the rocket combustion chamber 31 and combust.
  • the supersonic rotary engine shown in FIG. 10 differs from the embodiment 9 in that: two types of storage tanks in the oxidant storage tank 2001, the reducing agent storage tank 2002, and the expansion agent storage tank 2003 are re-mixed by the premixer 2004.
  • One of the passage rotary joints 20 is in communication with the rocket combustion chamber 31, and the third storage tank is connected to the rocket combustion chamber 31 via the other of the two-way rotary joints 20.
  • the oxidant and reducing agent are stored in the oxidant storage tank 2001.
  • the reducing agent in the canister 2002 enters the rocket combustion chamber 31 and burns.
  • the supersonic rotary engine shown in FIG. 11 differs from the embodiment 9 in that the oxidant storage tank 2001, the reducing agent storage tank 2002, and the expansion agent storage tank 2003 pass through different passages of the three-way rotary joint 30 and the rocket combustion chamber. 31 is connected, the oxidant in the oxidant storage tank 2001 and the reducing agent in the reducing agent storage tank 2002 enter the rocket combustion chamber 31 and are mixed and burned.
  • the supersonic rotary engine shown in Fig. 12 differs from the first embodiment in that a low speed bushing 203 is provided between the rotary shaft 200 of the rotary structural body 2 and the rotary shaft support 201.
  • the supersonic rotor engine shown in FIG. 13 differs from the first embodiment in that: the rotating shaft 200 of the rotating structural body 2 and the passive rotating shaft 500 of the passive rotating structural body 5 are set to each other, A stationary bushing 204 is disposed between the rotating shaft 200 and the passive rotating shaft 500.
  • the supersonic rotary engine shown in FIG. 14 or FIG. 15 differs from the first embodiment in that: the supersonic rotary engine further includes a working fluid recovery casing 4, and a working medium guide is disposed on the working fluid recovery casing 4.
  • the outlet 401, the supersonic injection passage 1 and the rotating structure 2 are disposed inside the working fluid recovery casing 4, and the static pressure of the airflow ejected from the supersonic injection passage is less than atmospheric pressure.
  • the supersonic injection passage 1, the rotating structure 2, and the passive rotating structure 5 are disposed inside the working medium recovery casing 4.
  • the supersonic rotary engine shown in FIG. 16 or FIG. 17 differs from the second embodiment in that: the supersonic rotary engine further includes a working fluid recovery casing 4, and a working medium is disposed on the working fluid recovery casing 4.
  • the outlet 401, the supersonic injection passage 1, the rotating structure 2 and the passive rotating structure 5 are disposed inside the working fluid recovery casing 4, and the working fluid recovery casing 4 is set as a condensing and cooling worker
  • the recovery casing 440 is provided with a condensing cooler 4401 at the condensing cooling medium recovery casing 440.
  • the condensing cooling medium recovery casing 440 is fixedly connected to the rotating structure 2, and the high-pressure working source 3 is disposed on the rotating structure 2.
  • the high-pressure working medium source 3 is set as an external combustion type high-pressure working medium generator 3331, and the external combustion type high-pressure working medium generator 3331 is provided with a burner 3332, and the burner 3332 is heated by the external combustion type high-pressure working medium 3331, and the condensing and cooling worker
  • the working fluid outlet 401 of the recovery casing 440 is in communication with the external combustion type high-pressure working generator 3331, and the condensed working medium is discharged from the condensing and cooling medium recovery casing 440 through the working fluid outlet 401 by the centrifugal force.
  • Combustion Pressure working fluid generator 3331, the external combustion type high-pressure working fluid generator 3331 working fluid is vaporized into high temperature and high pressure gaseous working channel 1 into the supersonic jet.
  • the supersonic rotary engine shown in FIG. 18 differs from the embodiment 15 in that a condensing cooler 4401 is provided at the working fluid recovery casing 4, and is disposed at the working fluid outlet 401 of the working fluid recovery casing 4.
  • Compressed gas structure 4000, high-pressure working medium source 3 is set as external combustion type high-pressure working medium generator 3331
  • burner 3332 is installed in external combustion type high-pressure working medium generator 3331
  • burner 3332 is heated by external combustion type high-pressure working medium generator 3331.
  • the working fluid outlet 401 of the working fluid recovery casing 4 is connected to the external combustion type high-pressure working generator 3331 via the compressed air structure 4000, and the working medium in the external combustion type high-pressure working generator 3331 is set to helium, in the external combustion type.
  • the helium gas in the high-pressure working medium generator 3331 is heated into a high-temperature high-pressure helium gas, and the high-temperature high-pressure helium gas is sprayed through the supersonic jet channel 1 and the passive rotating structure 5 is rotated into a working medium to recover the working medium.
  • the casing 4 is cooled and pressurized by the compressed air structure 4000 in the working medium recovery casing 4, and then enters the external combustion type high-pressure working generator 3331 to enter the next cycle; the so-called gas pressure structure is set A blade pressurization structure on the rotating structure 2 or on the passive rotating structure 5.

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Abstract

一种超音速转子发动机，包括超音速喷射通道（1）、旋转结构体（2）和高压工质源（3）。超音速喷射通道（1）设置在旋转结构体（2）上。超音速喷射通道（1）的工质入口（1001）与高压工质源（3）连通。超音速喷射通道（1）以旋转结构体（2）回转圆周的切线方向为喷射方向。旋转结构体（2）对外输出动力。该发动机结构简单、制造成本较低且可靠性高，并显著地提高了效率。

Description

超音速转子发动机
技术领域 本发明涉及热能与动力领域， 尤其是一种超音速转子发动机。
背景技术
无论是活塞式还是透平式发动机， 其结构均相对复杂， 效率也不高。 而超 音速喷射通道体（如火箭喷管等）作为产生推力的发动机， 可以以非常高的效 率将热能转换成超音速气体的动能， 只要超音速喷射通道体的运动速度足够高 就可以获得非常高的推进效率， 当超音速喷射通道体的运动速度接近从超音速 喷射通道体内喷出的超音速气体的运动速度时， 就可以百分之百的把超音速气 体的动能全部变成超音速喷射通道体的动能和超音速喷射通道体对外所做的 功这两部分能量之和。 这种热动力系统结构简单、 效率高， 但是超音速喷射通 道体很难作为输出旋转动力的发动机使用， 因为当超音速喷射通道体作高线速 度旋转运动吋， 会产生巨大的离心力， 而现有材^ t很难承受这一巨大离心力。 如果不能使超音速喷射通道体作高线速度圆周运动，就会导致超音速喷射通道 体喷射出来的气体的动能中只有一部分变为超音速喷射通道体的动能和超音 速喷射通道体对外所做的功， 而另外一部分甚至是大部分仍作为气体的动能存 在于气体中， 最终这部分气体动能不对外作功， 而白白浪费掉。 因此， 由超音 速喷射获得反冲力， 再由反冲力对外作功的动力系统效率都较低。
如果能够发明一种新型热动力系统 （发动机）， 可以利用超音速喷射通道 体的超音速喷射对外高效输出旋转动力， 就可以制造出结构极其简单、 效率非 常高的发动机。 发明内容
详细分析， 以由超音速喷射通道体所喷射的超音速气体获得反作用力的能 够输出旋转动力的热动力系统的工作机理可以得出这样的结论： 如果要想提高 这一系统的效率， 最重要的途径有三个： 一是以尽可能高的效率将热能转换成 超音速气体的动能；二是使超音速喷射通道体（火箭喷管、冲压发动机喷管等） 以尽可能高的线速度作圆周运动； 三是如果没有办法使超音速喷射通道体以相 当高的线速度作圆周运动，就必须找到一种可以回收已经离开超音速喷射通道 体的高速气体的动能的方法。
为了实现上述目的， 本发明提出的技术方案如下：
一种超音速转子发动机，包括超音速喷射通道、旋转结构体和高压工质源， 所述超音速喷射通道设置在所述旋转结构体上， 所述超音速喷射通道的工质入 口与所述高压工质源连通， 所述超音速喷射通道的喷射方向以所述旋转结构体 迴转圆周的切线为总体指向， 所述旋转结构体对外输出动力； 所述超音速转子 发动机正常工作时， 自所述超音速喷射通道喷射出来的气流速度大于 2马赫， 自所述超音速喷射通道喷射出来的气流的静压等于或小于大气压强。
所述超音速转子发动机还包括被动旋转结构体，在所述被动旋转结构体上 设打击传动结构，所述超音速喷射通道喷射的气流打击在所述打击传动结构上 推动所述被动旋转结构体转动， 所述被动旋转结构体也对外输出动力。
所述旋转结构体设置在所述被动旋转结构体的外围；
或所述被动旋转结构体设置在所述旋转结构体的外围；
或所述被动旋转结构体和所述旋转结构体并列设置。
两个或多个所述超音速喷射通道的工质入口与一个所述高压工质源连通。 所述超音速喷射通道设为拉瓦尔喷管。
所述高压工质源设置在所述旋转结构体上或设置在所述旋转结构体的连 接结构体上或设置在所述超音速转子发动机的机体上；
在所述高压工质源设置在所述超音速转子发动机的机体上的结构中， 所述 高压工质源经单通道旋转接头与所述超音速喷射通道连通。 所述打击传动结构设为导流通道，所述超音速喷射通道喷射的气流对所述 导流通道打击传动后自所述导流通道流出时所述被动旋转结构体获得额外推 力进一步推动所述被动旋转结构体旋转。
所述高压工质源设为火箭燃烧室，所述火箭燃烧室设在所述旋转结构体和 /或所述旋转结构体的连接结构体上，在所述旋转结构体上和 /或所述旋转结构 体的连接结构体上设氧化剂储罐和还原剂储罐，所述氧化剂储罐和所述还原剂 储罐与所述火箭燃烧室连通。
所述高压工质源设为火箭燃烧室，所述火箭燃烧室设在所述旋转结构体和 /或所述旋转结构体的连接结构体上， 在所述超音速转子发动机的机体上设氧 化剂储罐和还原剂储罐；
所述氧化剂储罐和所述还原剂储罐经预混器再经单通道旋转接头与所述 火箭燃烧室连通，所述氧化剂储罐中的氧化剂和所述还原剂储罐中的还原剂在 所述火箭燃烧室中燃烧；
或所述氧化剂储罐和所述还原剂储罐经双通道旋转接头中的不同通道与 所述火箭燃烧室连通，所述氧化剂储罐中的氧化剂和所述还原剂储罐中的还原 剂在所述火箭燃烧室中混合后燃烧。
所述高压工质源设为火箭燃烧室，所述火箭燃烧室设在所述旋转结构体和 /或所述旋转结构体的连接结构体上， 在所述超音速转子发动机的机体上设氧 化剂储罐、 还原剂储罐和膨胀剂储罐；
所述氧化剂储罐、所述还原剂储罐和所述膨胀剂储罐经预混器再经单通道 旋转接头与所述火箭燃烧室连通，所述氧化剂储罐中的氧化剂和所述还原剂储 罐中的还原剂进入所述火箭燃烧室后燃烧;
或所述氧化剂储罐、所述还原剂储罐和所述膨胀剂储罐中的两种储罐经预 混器再经双通道旋转接头中的一个通道与所述火箭燃烧室连通， 第三种储罐经 所述双通道旋转接头中的另一个通道与所述火箭燃烧室连通， 所述氧化剂储罐 中的氧化剂和所述还原剂储罐中的还原剂进入所述火箭燃烧室后燃烧；
或所述氧化剂储罐、所述还原剂储罐和所述膨胀剂储罐经三通道旋转接头 的不同通道与所述火箭燃烧室连通，所述氧化剂储罐中的氧化剂和所述还原剂 储罐中的还原剂进入所述火箭燃烧室后混合燃烧。
在所述旋转结构体的旋转轴和旋转轴支座之间设低速轴套。
在所述旋转结构体的旋转轴和所述被动旋转结构体的被动旋转轴相互套 装设置， 在所述旋转轴和所述被动旋转轴之间设静止轴套。
所述超音速转子发动机还包括工质回收壳体，在所述工质回收壳体上设工 质导出口， 所述超音速喷射通道和所述旋转结构体设置在所述工质回收壳体的 内部； 在设置所述被动旋转结构体的结构中， 所述超音速喷射通道、 所述旋转 结构体和所述被动旋转结构体设置在所述工质回收壳体的内部。
所述工质回收壳体设为冷凝冷却工质回收壳体，在所述冷凝冷却工质回收 壳体处设冷凝冷却器， 所述冷凝冷却工质回收壳体与所述旋转结构体固连， 所 述高压工质源设在所述旋转结构体上， 所述高压工质源设为外燃式高压工质发 生器， 在所述外燃式高压工质发生器处设燃烧器， 所述燃烧器对所述外燃式高 压工质发生器加热， 所述冷凝冷却工质回收壳体的所述工质导出口与所述外燃 式高压工质发生器连通， 在离心力的作用下被冷凝的工质由所述冷凝冷却工质 回收壳体经所述工质导出口流向所述外燃式高压工质发生器， 工质在所述外燃 式高压工质发生器被汽化成高温高压气态工质进入所述超音速喷射通道。
本发明所谓的超音速喷射通道是指一切可以喷射超音速气体的通道， 即一 切可以将气体的热能和压力能变成喷射气体的动能的喷射通道， 如拉瓦尔喷 管、 火箭的喷管， 以及其他形状的可以喷射超音速气体的通道， 如可以喷射超 音速气体的两叶片之间的通道等。
本发明中的旋转结构体是指一切可以作旋转运动的结构体， 如飞轮、 可以 作旋转运动的杆以及可以作旋转运动的环形结构体等。
本发明中当所述高压工质源设为火箭燃烧室吋，原工质是高压进入所述火 箭燃烧室的。
本发明所谓的迴转圆周指旋转结构体作旋转运动时所形成的轨迹圆周， 此 轨迹圆周可以是旋转结构体的外围轨迹圆周、 内侧轨迹圆周以及旋转结构体外 围轨迹圆周和内侧轨迹圆周之间的任何点作旋转运动所形成的轨迹圆周。 本发明所谓的以旋转结构体迴转圆周的切线为总体指向， 既包括以旋转结 构体迴转圆周的切线为完全精确的喷射指向的情况，也包括虽然存在一定程度 上的偏角但大体上仍然以旋转结构体迴转圆周的切线为喷射指向的情况。所述 迴转圆周的切线可以是外围轨迹圆周的切线、 内侧轨迹圆周的切线以及旋转结 构体外围轨迹圆周和内侧轨迹圆周之间的任何点作旋转运动所形成的轨迹圆 周的切线。
本发明所谓的高压工质源是指一切可以提供高压气体工质的系统，可以是 火箭燃烧室、冲压发动机燃烧室、脉冲燃烧室、高压水蒸气发生器（高压锅炉） 等。 本发明中所谓的高压工质源包括外燃形式产生的高压工质源、 内燃形式产 生的高压工质源和混燃形式产生的高压工质源， 也包括高压压縮气体源。 所谓 的内燃形式产生的高压工质源包括燃烧室以及向燃烧室提供氧化剂、还原剂的 系统， 还可以包括向燃烧室提供膨胀剂的系统， 所谓的膨胀剂是指不参与燃烧 化学反应， 但在燃烧室内受热气化或受热产生气体体积膨胀的工质， 膨胀剂的 主要作用是调节燃烧室内的温度和参与作功工质的摩尔数。所谓的外燃形式产 生的高压工质源是指利用外燃方式产生高温高压工质的系统。所谓的混燃形式 产生的高压工质源是指将燃料燃烧所释放的热量全部或近乎全部都参与作功 循环的热动力系统， 详见本发明人申请的有关混燃的专利。
本发明所谓的被动旋转结构体是指在接受从所述超音速喷射通道体喷射 出来的高速气体打击时可以作旋转运动的结构体。被动旋转结构体可以单独对 外输出动力， 可以与旋转结构体分别对外输出动力， 也可以与旋转结构体经换 向机构（如惰轮等）合并后对外输出动力。 本发明中所谓的打击传动结构是指 设在被动旋转结构体上的可以接受高速气体打击，使被动旋转结构体发生转动 的结构， 可以是叶状结构、 通道状结构等， 气体在打击传动结构处可以径向流 动， 也可以轴向流动。
所述超音速转子发动机正常工作时， 自所述超音速喷射通道喷射出来的气 流速度大于 3马赫。
所述超音速转子发动机正常工作时， 自所述超音速喷射通道喷射出来的气 流速度大于 4马赫。
所述超音速转子发动机正常工作时， 自所述超音速喷射通道喷射出来的气 流速度大于 5马赫。
所述超音速转子发动机正常工作时， 自所述超音速喷射通道喷射出来的气 流速度大于 6马赫。
本发明所谓的冷凝冷却工质回收壳体是指具有冷凝冷却功能的工质回收 壳体。 所谓冷凝冷却器是指可以对冷凝冷却工质回收壳体进行冷却的装置。 所 谓的燃烧器是指能够燃烧放热对所述外燃式高压工质发生器进行加热，使其内 部工质气化的燃烧装置。所谓外燃式高压工质发生器是指由外部受热加热内部 工质使其产生高温高压气态工质的装置。
本发明中所谓的旋转结构体的连接结构体是指与旋转结构体相连接的结 构体， 如旋转轴、 旋转臂或旋转结构体上的齿轮等结构。 本发明所谓的旋转结 构体对外输出动力指旋转结构体直接对外输出动力，或经旋转结构体的连接结 构体间接对外输出动力， 被动旋转结构体亦然。 本发明中的旋转结构体和被动 旋转结构体的旋转方向可以相同， 也可以不同。
为了提高高速气体对被动旋转结构体的打击传动效率，可以在被动旋转结 构体的受超音速喷射通道的高速喷射气流打击传动的部位上设缓冲结构， 所述 缓冲结构的目的是为了减少高速气体的反射作用， 以便更有效的将高速气体的 动能传递给被动旋转结构体。
本发明所谓的缓冲结构可以是多空结构、 粗糙表面结构、 筛网结构或多栅 结构，这些结构能够使高速飞来的气体在撞击具有这些结构的表面时发生停留 作用， 犹如两个粘弹性体相互撞击， 可以更高效地将高速运动气体的动能传给 被动旋转结构体。
本发明中所谓的超音速喷射通道由于作旋转运动， 所以在超音速喷射通道 的设计方面要考虑离心力的影响。
本发明所公开的超音速转子发动机可以用陶瓷材料加工。
本发明中， 由于超音速喷射通道设置在旋转结构体上， 当超音速喷射通道 喷射吋获得反推力， 而旋转结构体就可以获得扭矩从而旋转， 旋转结构体对外 输出动力。 一般说来， 本发明的旋转结构体作高速旋转， 所以旋转结构体可以 直接与其他机械连接， 也可以和发电机相连， 也可以将旋转结构体作为发电机 的转子使用或者发电机的转子设置在旋转结构体上。
本发明中工质回收壳体的设置可以回收超音速喷射通道尾气的热量和工 质， 同时可以通过对工质回收壳体抽气使其处于低压或真空状态， 以提高发动 机的效率。由工质回收壳体回收来的工质可以直接排放，可以经处理后排放（如 三元催化剂等）， 也可以经加压加热后重新进入超音速喷射通道， 还可以经处 理将其中的二氧化碳液化加以回收。
一般情况下， 超音速喷射通道的运行速度低于超音速喷射通道的喷射速 度， 所以超音速喷射通道的运动速度越高， 效率越高。 为此， 本发明中旋转结 构体的转速越高， 效率也越高。 由于高速旋转会产生强大的离心力， 很有可能 由于现有技术和材料的限制， 很难达到希望的转速， 所以超音速喷射通道喷射 物 （尾气）仍然具有很大的动能。 因此， 设置了被动旋转结构体， 将本发明中 超音速喷射通道喷射的尾气以近乎切线的总体指向对被动旋转结构体打击传 动，进而使被动旋转结构体产生旋转对外输出动力，进一步提高发动机的效率。
本发明的原理是利用超音速喷射通道一次性将存在于高压工质源内的工 质所具有的热能和压力能以尽可能高的效率转换成从超音速喷射通道中喷出 的高速气体的动能， 所述超音速喷射通道喷出的高速气体的静压等于超音速喷 射通道出口处的环境压强，所谓超音速喷射通道出口处的环境压强可以是大气 压强， 也可以低于大气压强， 如果低于大气压强， 必须设置工质回收壳体， 将 工质回收壳体抽成真空， 使工质回收壳体内的压强低于大气压强（犹如子弹从 枪膛中射出一样， 尽可能高效地将火药中的能量转换为子弹的动能）。 在这一 转换过程中， 依据牛顿第三定律， 超音速喷射通道体（构成超音速喷射通道的 结构体， 如火箭喷管等） 受到反作用力， 由于超音速喷射通道设在旋转结构体 上， 所以旋转结构体将发生旋转并可对外输出动力。 这与燃气轮机或蒸汽轮机 的第一级的工作原理不同， 因为在燃气轮机和蒸汽轮机中不可能在第一级就把 工质中的热能和压力能变成没有静压或静压很低的高速气体的动能，在燃气轮 机和蒸汽轮机中是通过多级的形式将工质的能量转换成动力。 在蒸汽轮机中， 虽然也有喷管， 但喷管都是固定在机体上的， 而且喷管相邻的动静叶之间或相 邻的对转动叶之间均存在相当高的静压， 因此， 相邻的动静叶之间和对转动叶 之间需要尽可能小的间隙以减少叶顶泄漏等能量损失。而本发明所公开的超音 速转子发动机则不同，超音速喷射通道将所有气体的压力能和热能转换成气体 的动能并从此过程中获得反向推力形成旋转结构体的旋转运动进而对外输出 动力， 离开超音速喷射通道的高速运动气体打击在设在被动旋转结构体上的打 击传动结构， 将气体的动能变成被动旋转结构体的旋转运动并对外输出动力， 在旋转结构体和被动旋转结构体之间不存在或只存在很小的静压， 因此避免了 在蒸汽轮机和燃气轮机中广泛存在的并严重影响效率的叶顶漏气问题。在本发 明所公开的超音速转子发动机中旋转结构体和被动旋转结构体之间可以密封 设置， 也可以开放设置。
本发明中可用两个坐标系观察超音速气体， 一是设在超音速喷射通道体上 的坐标系， 二是设在所述超音速转子发动机机体上的坐标系。 在本发明中为了 进一步提高系统的效率， 设置了被动旋转结构体以对在设在所述超音速转子发 动机机体上的坐标系中仍高速运动的气体的动能进行回收， 在这个过程中， 高 速气体对被动旋转结构体打击推动被动旋转结构体转动对外输出动力（犹如子 弹打击到靶上， 迫使靶发生位移， 对外作功）。 由此可见， 超音速喷射通道和 设置在被动旋转结构体上接受打击的打击传动结构之间不存在静压联系， 也不 存在相互作用 （相当于枪体和靶之间的关系， 虽然枪体受子弹反射的作用获得 推力， 靶也在子弹的作用下获得推力， 但枪体和靶之间不村在相互作用）； 同 理， 旋转结构体和被动旋转结构体之间没有静压联系， 也不存在相互作用； 而 是超音速喷射通道体与高速气体在分离界面处（犹如枪口处） 的相互作用， 以 及被动旋转结构体和高速气体在接受高速气体打击传动处的相互作用。由此不 难看出，旋转结构体和被动旋转结构体之间的相互关系与传统对转蒸汽轮机和 燃气轮机的相邻对转叶之间的关系是完全不同的。一是本发明的旋转结构体与 被动旋转结构体均发生旋转； 二是按照牛顿第三定律， 本发明中旋转结构体所 受的力是由于高压气体的喷射而得到的，被动旋转结构体的旋转是受到高速气 体的冲击而得到的， 而传统的汽轮机和燃气轮机是靠压差的变化而得到的； 三 是本发明中自超音速喷射通道喷射出来的气体的速度一般说来要在数马赫以 上，这就使超音速喷射通道内的能量全部或绝大部分变成了高速运动的气体的 动能， 从而使旋转结构体发生旋转。 由于超音速喷射通道的运动速度低于其喷 射速度， 所述高速运动的气体仍然具有相当的能量， 使这些气体撞击到被动旋 转结构体上可以对高速运动气体的动能进行回收。在旋转结构体和被动旋转结 构体之间只考虑高速运动气体的动能作用， 而不存在或只存在很小的静压作 用； 四是本发明中的旋转结构体和被动旋转结构体不存在压比的关联， 而在汽 轮机和燃气轮机中则不然。且旋转结构体和被动旋转结构体之间的空间内不存 在静压作用， 因此可以设为开放式， 而在汽轮机和燃气轮机中则不然。
由于旋转结构体和被动旋转结构体之间不存在相互作用， 所以本发明所公 开的系统中不存在通道顶（即所谓叶顶）漏气问题。 本发明中所公开的结构不 仅可以制造大型超音速转子发动机， 也可以制造微型超音速转子发动机。 微型 超音速转子发动机的效率远高于微型透平机， 而且结构简单。
本发明中氧化剂储罐和还原剂储罐可以与旋转结构体一同作旋转运动， 也 可以不与旋转结构体一同作旋转运动而是通过旋转接头给高压工质源补给氧 化剂和还原剂。 同理， 高压工质源也可以设为与旋转结构体一同作旋转运动或 不与旋转结构体一同作旋转运动而是通过旋转接头与超音速喷射通道连通。
氧化剂、 还原剂和膨胀剂都可以称为原工质， 当原工质储罐与旋转结构体 一同作旋转运动时， 可以设置至少两套超音速转子发动机， 超音速转子发动机 交替工作， 停车时补充新的原工质； 也可以在这个系统中设置旋转接头， 发动 机处于高速旋转时， 旋转接头的偶件发生分离； 而发动机处于较低转速时， 旋 转接头的偶件形成配合给超音速喷射通道补给原工质，这样就可以在发动机处 于较低转速时对原工质储罐补给原工质， 而不必停车， 也不必设置多套超音速 转子发动机， 这种形式犹如飞机的空中加油。
在原工质储罐与旋转结构体一同作旋转运动的结构中，对原工质流量的控 制以及对所述转子发动机的控制， 可以通过电刷供电控制电磁阀来实现， 也可 以通过遥控电磁阀来控制，还可以通过电磁控制方式从机体上控制原工质控制 阀和 /或设在所述高压工质源和超音速喷射通道之间的控制阀以实现对所述超 音速转子发动机的控制。
在本发明中所公开的超音速转子发动机中， 一般说来， 旋转结构体和被动 旋转结构体的转速的旋转方向不同， 而且在很多结构中可能会相互套装， 这样 就会造成相接触的对转面之间的转速差过大造成润滑困难磨损过快的问题， 为 降低这一转速差，本发明中在两个相互对转套装的轴之间设静止轴套以减少相 对转速。
本发明所谓的低速轴套是指转速低于所述旋转结构体转速的隔离轴套， 其 目的是减少轴套之间的相对转速差， 以形成良好的润滑条件， 增加寿命和可靠 性。 低速轴套的转动可以靠转动轴套（旋转结构体的轴套或被动旋转结构体的 轴套） 带动， 即低速轴套设为自由式， 也可以在低速轴套上设相应驱动机构， 使低速轴套发生转动。
本发明所谓的静止轴套是指处于静止状态的隔离轴套，静止轴套设置在相 互套装相互对转的旋转轴和被动旋转轴之间，其目的是降低旋转轴和被动旋转 轴之间的相对转速差， 以形成良好的润滑条件， 增加寿命和可靠性。
本发明所谓的旋转轴是指与旋转结构体相连的转动轴，所谓的被动旋转轴 是指与被动旋转体相连的旋转轴。
本发明所谓的旋转接头是指两个相互配合的偶件， 其中一个偶件的转速与 另一个偶件的转速不同， 两个偶件内均设有流体通道， 设置在不同偶件的流体 通道之间相互连通， 以实现流体由一个偶件流向另一个偶件的器件。
本发明所谓的单通道旋转接头是指两个相互配合的偶件， 其中一个偶件的 转速与另一个偶件的转速不同， 两个偶件内均设有流体通道， 设置在不同偶件 的流体通道之间相互连通， 以实现一种流体由一个偶件流向另一个偶件的器 件。
本发明所谓的双通道旋转接头是指两个相互配合的偶件， 其中一个偶件的 转速与另一个偶件的转速不同， 两个偶件内均设有两类流体通道， 设置在不同 偶件的同类流体通道之间相互连通， 以实现两种流体分别由一个偶 流向另一 个偶件的器件。
本发明所谓的三通道旋转接头是指两个相互配合的偶件， 其中一个偶件的 转速与另一个偶件的转速不同， 两个偶件内均设有三类流体通道， 设置在不同 偶件的同类流体通道之间相互连通， 以实现三种流体分别由一个偶件流向另一 个偶件的器件。
本发明的有益效果如下：
1、 本发明结构简单， 制造成本低， 可靠性高。
2、 本发明大幅度提高了现有发动机的效率。
附图说明
图 1为本发明的实施例 1的示意图；
图 1为本发明的实施例 2的示意图；
图 3为本发明的实施例 3的示意图；
图 4为本发明的实施例 4的示意图；
图 5为本发明的实施例 5的示意图；
图 6为本发明的实施例 6的示意图；
图 7为本发明的实施例 7的示意图；
图 8为本发明的实施例 8的示意图；
图 9为本发明的实施例 9的示意图；
图 1 0为本发明的实施例 10的示意图；
图 1 1为本发明的实施例 1 1的示意图； 图 1 2为本发明的实施例 12的示意图；
图 1 3为本发明的实施例 13的示意图；
图 14和图 1 5为本发明的实施例 14的示意图；
图 1 6和图 1 7为本发明的实施例 15的示意图；
图 18为本发明的实施例 1 6的示意图。
具体实施方式 实施例 1
如图 1 所示的超音速转子发动机， 包括超音速喷射通道 1、 旋转结构体 2 和高压工质源 3， 超音速喷射通道 1设置在旋转结构体 2上， 超音速喷射通道 1的工质入口 1001与高压工质源 3连通，超音速喷射通道 1的喷射方向以旋转 结构体 2迴转圆周的切线为总体指向， 旋转结构体 2对外输出动力。 超音速转 子发动机正常工作时，自所述超音速喷射通道喷射出来的气流速度大于 2马赫， 自所述超音速喷射通道喷射出来的气流的静压等于大气压强。
实施例 2
如图 2所示的超音速转子发动机， 其与实施例 1的区别在于： 超音速喷射 通道 1设为拉瓦尔喷管 102， 超音速转子发动机还包括被动旋转结构体 5， 在 被动旋转结构体 5上设打击传动结构 52，超音速喷射通道 1的喷射气流在打击 传动结构 52上对被动旋转结构体 5打击传动推动被动旋转结构体 5转动， 被 动旋转结构体 5也对外输出动力。被动旋转结构体 5设置在旋转结构体 2的外 围， 两个或多个超音速喷射通道 1的工质入口 1001与一个高压工质源 3连通。 被动旋转结构体 5设有导流通道 8， 超音速喷射通道 1的喷射气流对所述被动 旋转结构体 5打击传动后经导流通道 8流出时被动旋转结构体 5获得额外推力 进一步推动被动旋转结构体 5旋转。 超音速转子发动机正常工作时， 自所述超 音速喷射通道喷射出来的气流速度大于 3马赫。
实施例 3
如图 3所示的超音速转子发动机， 其与实施例 2的区别在于： 旋转结构体 2设置在被动旋转结构体 5的外围， 被动旋转结构体 5的受超音速喷射通道 1 的高速喷射气流打击的部位上设气垫缓冲结构 51， 气垫缓冲结构 51减少高速 喷射气流的反射。 超音速转子发动机正常工作时， 自所述超音速喷射通道喷射 出来的气流速度大于 4马赫。
实施例 4
如图 4所示的超音速转子发动机， 其与实施例 2的区别在于： 高压工质源 3设为火箭燃烧室 31， 所述火箭燃烧室 31设在所述旋转结构体 2上， 被动旋 转结构体 5和旋转结构体 2并列设置。 超音速转子发动机正常工作时， 自所述 超音速喷射通道喷射出来的气流速度大于 5马赫。
实施例 5
如图 5所示的超音速转子发动机， 其与实施例 1的区别在于： 高压工质源 3设置在超音速转子发动机的机体上，高压工质源 3经旋转接头 10与超音速喷 射通道 1连通。超音速转子发动机正常工作时, 自所述超音速喷射通道喷射出 来的气流速度大于 6马赫。
实施例 6
如图 6所示的超音速转子发动机， 其与实施例 1的区别在于： 还包括悬浮 轴承 6， 悬浮轴承 6将旋转结构体 2悬浮， 高压工质源 3设置在旋转结构体 2 上，高压工质源 3与超音速喷射通道 1连通，高压工质源 3设为火箭燃烧室 31， 所述火箭燃烧室 31设在所述旋转结构体 2上，在旋转结构体 2上和 /或旋转结 构体 2的连接结构体上设氧化剂储罐 2001和 /或还原剂储罐 2002，氧化剂储罐 2001和还原剂储罐 2002与火箭燃烧室 31连通。
实施例 7
如图 7所示的超音速转子发动机， 其与实施例 1的区别在于： 高压工质源 3设为火箭燃烧室 31， 火箭燃烧室 31设在旋转结构体 2和 /或旋转结构体 2的 连接结构体上， 在超音速转子发动机的机体上设氧化剂储罐 2001 和还原剂储 罐 2002 ; 氧化剂储罐 2001和还原剂储罐 2002经预混器 2004再经单通道旋转 接头 10与火箭燃烧室 31连通，氧化剂储罐 2001中的氧化剂和还原剂储罐 2002 中的还原剂在火箭燃烧室 31 中燃烧。
实施例 8 如图 8所示的超音速转子发动机， 其与实施例 7的区别在于： 氧化剂储罐 2001和还原剂储罐 2002经双通道旋转接头 20中的不同通道与火箭燃烧室 31 连通，氧化剂储罐 2001 中的氧化剂和还原剂储罐 2002中的还原剂在火箭燃烧 室 31中混合后燃烧。
实施例 9
如图 9所示的超音速转子发动机， 其与实施例 1的区别在于： 高压工质源 3设为火箭燃烧室 31， 火箭燃烧室 31设在旋转结构体 2和 /或旋转结构体 2的 连接结构体上，在超音速转子发动机的机体上设氧化剂储罐 2001、还原剂储罐 2002和膨胀剂储罐 2003 ; 氧化剂储罐 2001、 还原剂储罐 2002和膨胀剂储罐 2003经预混器 2004再经单通道旋转接头 10与火箭燃烧室 31连通， 氧化剂储 罐 2001中的氧化剂和还原剂储罐 2002中的还原剂进入火箭燃烧室 31后燃烧。
实施例 10
如图 10所示的超音速转子发动机， 其与实施例 9的区别在于： 氧化剂储 罐 2001、 还原剂储罐 2002和膨胀剂储罐 2003中的两种储罐经预混器 2004再 经双通道旋转接头 20中的一个通道与火箭燃烧室 31连通， 第三种储罐经双通 道旋转接头 20中的另一个通道与火箭燃烧室 31连逋， 氧化剂储罐 2001 中的 氧化剂和还原剂储罐 2002中的还原剂进入火箭燃烧室 31后燃烧。
实施例 1 1
如图 1 1所示的超音速转子发动机， 其与实施例 9的区别在于： 氧化剂储 罐 2001、 还原剂储罐 2002和膨胀剂储罐 2003经三通道旋转接头 30的不同通 道与火箭燃烧室 31连通， 氧化剂储罐 2001 中的氧化剂和还原剂储罐 2002中 的还原剂进入火箭燃烧室 31后混合燃烧。
实施例 12
如图 12所示的超音速转子发动机， 其与实施例 1 的区别在于： 在旋转结 构体 2的旋转轴 200和旋转轴支座 201之间设低速轴套 203。
实施例 13
如图 13所示的超音速转子发动机， 其与实施例 1 的区别在于： 在旋转结 构体 2的旋转轴 200和被动旋转结构体 5的被动旋转轴 500相互套装设置，在 旋转轴 200和被动旋转轴 500之间设静止轴套 204。
实施例 14
如图 14或图 15所示的超音速转子发动机， 其与实施例 1的区别在于： 超 音速转子发动机还包括工质回收壳体 4， 在所述工质回收壳体 4上设工质导出 口 401， 所述超音速喷射通道 1和所述旋转结构体 2设置在所述工质回收壳体 4的内部， 自所述超音速喷射通道喷射出来的气流的静压小于大气压强。
此外， 在设置所述被动旋转结构体 5的结构中， 所述超音速喷射通道 1、 所述旋转结构体 2和所述被动旋转结构体 5设置在所述工质回收壳体 4的内部。
实施例 15
如图 16或图 1 7所示的超音速转子发动机， 其与实施例 2的区别在于： 超 音速转子发动机还包括工质回收壳体 4， 在所述工质回收壳体 4上设工质导出 口 401， 所述超音速喷射通道 1、 所述旋转结构体 2和所述被动旋转结构体 5 设置在所述工质回收壳体 4的内部，工质回收壳体 4设为冷凝冷却工质回收壳 体 440， 在冷凝冷却工质回收壳体 440处设冷凝冷却器 4401， 冷凝冷却工质回 收壳体 440与旋转结构体 2固连， 高压工质源 3设在旋转结构体 2上， 高压工 质源 3设为外燃式高压工质发生器 3331， 在外燃式高压工质发生器 3331处设 燃烧器 3332 ,燃烧器 3332对外燃式高压工质发生器 3331加热，冷凝冷却工质 回收壳体 440的工质导出口 401 与外燃式高压工质发生器 3331连通， 在离心 力的作用下被冷凝的工质由冷凝冷却工质回收壳体 440经工质导出口 401流向 外燃式高压工质发生器 3331 , 工质在外燃式高压工质发生器 3331被汽化成高 温高压气态工质进入超音速喷射通道 1。
实施例 15
如图 18所示的超音速转子发动机， 其与实施例 1 5的区别在于： 在工质回 收壳体 4处设冷凝冷却器 4401，在工质回收壳体 4的工质导出口 401处设压气 结构 4000， 高压工质源 3设为外燃式高压工质发生器 3331， 在外燃式高压工 质发生器 3331处设燃烧器 3332， 燃烧器 3332对外燃式高压工质发生器 3331 加热， 工质回收壳体 4的工质导出口 401经压气结构 4000与外燃式高压工质 发生器 3331连通， 外燃式高压工质发生器 3331 内的工质设为氦气， 在外燃式 高压工质发生器 3331 内氦气被加热成高温高压氦气， 高温高压氦气通过超音 速喷射通道 1喷射作功并通过打击传动的形式使被动旋转结构体 5旋转作功后 进入工质回收壳体 4， 在工质回收壳体 4 内被降温冷却后的氦气经压气结构 4000压縮增压后再进入外燃式高压工质发生器 3331， 进入下一个循环； 所谓 压气结构是设在旋转结构体 2上或设在被动旋转结构体 5上的叶片增压结构。
显然， 本发明不限于以上实施例， 还可以有许多变形。 本领域的普通技术 人员， 能从本发明公开的内容直接导出或联想到的所有变形， 均应认为是本发 明的保护范围。

Claims

权 利 要 求
1、 一种超音速转子发动机， 包括超音速喷射通道 （1)、 旋转结构体 （2) 和高压工质源 （3)， 其特征在于： 所述超音速喷射通道 （1) 设置在所述旋转 结构体 （2) 上， 所述超音速喷射通道 （1) 的工质入口 （1001) 与所述高压工 质源 （3) 连通， 所述超音速喷射通道（1) 的喷射方向以所述旋转结构体 （2) 迴转圆周的切线为总体指向， 所述旋转结构体 （2) 对外输出动力； 所述超音 速转子发动机正常工作时， 自所述超音速喷射通道 （1) 喷射出来的气流速度 大于 2马赫， 自所述超音速喷射通道 （1) 喷射出来的气流的静压等于或小于 大气压强。
2、 根据权利要求 1 所述超音速转子发动机， 其特征在于： 所述超音速转 子发动机还包括被动旋转结构体 （5)， 在所述被动旋转结构体 （5) 上设打击 传动结构（52)， 所述超音速喷射通道（1) 喷射的气流打击在所述打击传动结 构 （52) 上推动所述被动旋转结构体（5) 转动， 所述被动旋转结构体 （5)也 对外输出动力。
3、 根据权利要求 2所述超音速转子发动机， 其特征在于： 所述旋转结构 体 （2) 设置在所述被动旋转结构体 （5) 的外围；
或所述被动旋转结构体 （5) 设置在所述旋转结构体 （2) 的外围； 或所述被动旋转结构体 （5) 和所述旋转结构体 （2) 并列设置。
4、 根据权利要求 1 所述超音速转子发动机， 其特征在于： 两个或多个所 述超音速喷射通道（1)的工质入口 （1001)与一个所述高压工质源（3)连通。
5、 根据权利要求 1 所述超音速转子发动机， 其特征在于： 所述超音速喷 射通道 （1) 设为拉瓦尔喷管 （102)。
6、 根据权利要求 1 所述超音速转子发动机， 其特征在于： 所述高压工质 源 （3) 设置在所述旋转结构体 （2) 上或设置在所述旋转结构体 （2) 的连接 结构体上或设置在所述超音速转子发动机的机体上；
在所述高压工质源（3)设置在所述超音速转子发动机的机体上的结构中， 所述高压工质源 （3) 经单通道旋转接头 （10) 与所述超音速喷射通道 （1) 连 通。
7、 根据权利要求 2所述超音速转子发动机， 其特征在于： 所述打击传动 结构 （52) 设为导流通道 （8)， 所述超音速喷射通道 （1) 喷射的气流对所述 导流通道（8)打击传动后自所述导流通道（8)流出时所述被动旋转结构体（5) 获得额外推力进一步推动所述被动旋转结构体 （5) 旋转。
8、 根据权利要求 1 所述超音速转子发动机， 其特征在于： 所述高压工质 源（3)设为火箭燃烧室（31)， 所述火箭燃烧室（31)设在所述旋转结构体（2) 和 /或所述旋转结构体（2) 的连接结构体上， 在所述旋转结构体（2) 上和 /或 所述旋转结构体 （2) 的连接结构体上设氧化剂储罐 （2001 ) 和还原剂储罐
(2002), 所述氧化剂储罐 （2001) 和所述还原剂储罐 （2002) 与所述火箭燃 烧室 （31) 连通。
9、 根据权利要求 1 所述超音速转子发动机， 其特征在于： 所述高压工质 源（3)设为火箭燃烧室（31)， 所述火箭燃烧室（31)设在所述旋转结构体（2) 和 /或所述旋转结构体（2) 的连接结构体上， 在所述超音速转子发动机的机体 上设氧化剂储罐 （2001) 和还原剂储罐 （2002);
所述氧化剂储罐（2001) 和所述还原剂储罐（2002) 经预混器 （2004)再 经单通道旋转接头（10)与所述火箭燃烧室（31 )连通，所述氧化剂储罐（2001 ) 中的氧化剂和所述还原剂储罐（2002) 中的还原剂在所述火箭燃烧室 （31) 中 燃烧；
或所述氧化剂储罐（2001)和所述还原剂储罐（2002)经双通道旋转接头 (20) 中的不同通道与所述火箭燃烧室 （31) 连通， 所述氧化剂储罐 （2001) 中的氧化剂和所述还原剂储罐（2002) 中的还原剂在所述火箭燃烧室 （31) 中 混合后燃烧。
10、 根据权利要求 1所述超音速转子发动机， 其特征在于： 所述高压工质 源（3)设为火箭燃烧室（31 )， 所述火箭燃烧室（31 )设在所述旋转结构体（2) 和 /或所述旋转结构体（2) 的连接结构体上， 在所述超音速转子发动机的机体 上设氧化剂储罐 （2001)、 还原剂储罐 （2002) 和膨胀剂储罐 （2003);
所述氧化剂储罐（2001)、所述还原剂储罐（2002)和所述膨胀剂储罐（2003) 经预混器 （2004) 再经单通道旋转接头 （10) 与所述火箭燃烧室 （31) 连通， 所述氧化剂储罐（2001 ) 中的氧化剂和所述还原剂储罐（2002) 中的还原剂进 入所述火箭燃烧室 （3Ό 后燃烧；
或所述氧化剂储罐 （2001 )、 所述还原剂储罐 （2002 ) 和所述膨胀剂储罐 (2003) 中的两种储罐经预混器 （2004)再经双通道旋转接头 （20) 中的一个 通道与所述火箭燃烧室 （31 ) 连通， 第三种储罐经所述双通道旋转接头 （20) 中的另一个通道与所述火箭燃烧室 （31 ) 连通， 所述氧化剂储罐（2001 ) 中的 氧化剂和所述还原剂储罐（2002) 中的还原剂进入所述火箭燃烧室（31 )后燃 烧；
或所述氧化剂储罐 （2001 )、 所述还原剂储罐 （2002 ) 和所述膨胀剂储罐 (2003) 经三通道旋转接头 （30) 的不同通道与所述火箭燃烧室 （31 ) 连通， 所述氧化剂储罐（2001 ) 中的氧化剂和所述还原剂储罐（2002) 中的还原剂进 入所述火箭燃烧室 （31 ) 后混合燃烧。
11、 根据权利要求 1所述超音速转子发动机， 其特征在于： 在所述旋转结 构体 (2) 的旋转轴 (200) 和旋转轴支座 (201 ) 之间设低速轴套 (203)。
12、 根据权利要求 2所述超音速转子发动机， 其特征在于： 在所述旋转结 构体 （2) 的旋转轴 （200) 和所述被动旋转结构体 （5) 的被动旋转轴 （500) 相互套装设置， 在所述旋转轴 （200)和所述被动旋转轴 （500)之间设静止轴 套 （204)。
13、 根据权利要求 1至 12任意之一所述超音速转子发动机， 其特征在于： 所述超音速转子发动机还包括工质回收壳体 （4)， 在所述工质回收壳体 （4) 上设工质导出口 （401 )， 所述超音速喷射通道 （1 )和所述旋转结构体（2)设 置在所述工质回收壳体（4) 的内部； 在设置所述被动旋转结构体 （5) 的结构 中， 所述超音速喷射通道 （1 )、 所述旋转结构体 （2) 和所述被动旋转结构体
(5) 设置在所述工质回收壳体 （4) 的内部。
14、 根据权利要求 13所述超音速转子发动机， 其特征在于： 所述工质回 收壳体 （4) 设为冷凝冷却工质回收壳体 （440)， 在所述冷凝冷却工质回收壳 体 （440) 处设冷凝冷却器 （4401 )， 所述冷凝冷却工质回收壳体 （440) 与所 述旋转结构体 （2) 固连， 所述高压工质源 （3) 设在所述旋转结构体 （2) 上， 所述高压工质源 （3)设为外燃式高压工质发生器（3331)， 在所述外燃式高压 工质发生器 （3331 ) 处设燃烧器 （3332)， 所述燃烧器 （3332) 对所述外燃式 高压工质发生器 （3331 ) 加热， 所述冷凝冷却工质回收壳体 （440) 的所述工 质导出口 （401) 与所述外燃式高压工质发生器 （3331 ) 连通， 在离心力的作 用下被冷凝的工质由所述冷凝冷却工质回收壳体 （440) 经所述工质导出口 (401)流向所述外燃式高压工质发生器 （3331)， 工质在所述外燃式高压工质 发生器 （3331 ) 被汽化成高温高压气态工质进入所述超音速喷射通道 （1)。
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