CN211230639U - Impeller rotor ramjet engine - Google Patents
Impeller rotor ramjet engine Download PDFInfo
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- CN211230639U CN211230639U CN202020077327.XU CN202020077327U CN211230639U CN 211230639 U CN211230639 U CN 211230639U CN 202020077327 U CN202020077327 U CN 202020077327U CN 211230639 U CN211230639 U CN 211230639U
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Abstract
The utility model discloses an impeller rotor ramjet belongs to rotor ramjet field, mainly comprises centrifugal fan, ramjet and axle work conversion machine etc.. The centrifugal fan provides supersonic airflow for the ramjet, the ramjet is arranged between the centrifugal fan and the shaft power converter, and the shaft power converter converts high-speed jet flow of the ramjet into shaft power for output. The application range of the ramjet is greatly expanded due to the realization of ground starting and running.
Description
Technical Field
The invention relates to the field of engines, in particular to an impeller rotor ramjet engine. The method is mainly used for automobile range extension, ships, low-speed aircrafts, power generation and the like.
Background
The aviation ramjet has the advantages of simple structure, light weight, extremely high power density, low cost, good economy in a high-speed state and the like, but is only suitable for high-speed flight scenes and cannot be used on the ground.
The gas turbine has the advantages of small volume, light weight, quick start, capability of being used on the ground and the like, belongs to a speed type, and has high rotating speed, high power density, low thermal efficiency and high noise.
Other similar prior art
Chinese patent CN110239723A discloses a circumferentially running ramjet engine: the rotary arm is provided with a ramjet engine which circularly runs around the rotary shaft like a pulled and ground donkey; the structure is simple, the weight is light, the volume is small, and the manufacturing cost is low; however, the ramjet engine rotates at a high speed and is subjected to a high centrifugal force, and therefore, the ramjet engine requires a high material strength, has a complicated oil supply and ignition system, and has many problems in air intake and exhaust.
Chinese patent CN204003154U discloses a rotary ramjet engine with a completely new structure: the zero-speed starting of the rotary punching engine is realized, the size is small, the power is high, and the power density and the cost performance are high; however, the structure is slightly complex, and the oil supply and ignition system is complex due to the fact that the ramjet (stamping wheel) rotates at high speed and is not static.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to solve the technical problem of providing the impeller ramjet which is static and does not need to rotate, has relatively simple oil supply and ignition systems, can realize ground starting and running, greatly expands the application range of the ramjet, and has the advantages of light weight, high power density, low manufacturing cost, high thermal efficiency, long service life and the like. The scheme of the invention comprises the following contents.
The impeller rotor ramjet engine mainly comprises a centrifugal fan, a ramjet engine, a shaft power converter and a starting device; the centrifugal fan provides supersonic airflow for the ramjet, the ramjet is arranged between the centrifugal fan and the shaft power converter, the airflow is accelerated by fuel, the shaft power converter converts high-speed jet flow energy of the ramjet into shaft power to be output, and the starting device can enable the impeller to rotate at high speed for starting;
the centrifugal fan comprises a centrifugal impeller and a centrifugal cylinder; the centrifugal cylinder is a round flat cylinder, an air inlet hole is arranged at the center of the flat cylinder for air inlet, the centrifugal impeller is arranged in the centrifugal cylinder, the centrifugal impeller rotates at high speed to pre-compress the inlet air and accelerate the air to supersonic speed at the outer circle of the centrifugal impeller;
the ramjet comprises a diffusion air inlet, a combustion chamber and a tail nozzle; the diffusion air inlet is communicated with an air cavity of the outer ring of the centrifugal cylinder and is aligned to the incoming flow direction of the supersonic airflow; after the incoming flow is injected into the diffusion air inlet at a high speed and is decelerated and stamped, the incoming flow enters a combustion chamber for oil mixing and combustion, fuel gas is rapidly expanded and sprayed out at a high speed at a tail nozzle, and heat energy is converted into directional kinetic energy;
the shaft work conversion machine comprises a work-doing impeller and a work-doing barrel; the acting impeller is arranged in the acting cylinder, the acting cylinder is a circular flat cylinder, an exhaust hole is formed in the center of the flat cylinder and used for exhausting air, a tail nozzle of the stamping engine is communicated with an outer ring air cavity of the acting cylinder, ultrahigh-speed air flow is sprayed into the acting cylinder along the tangential direction of an outer circle of the tail nozzle, tornado spiral air flow is formed in the cylinder, the acting impeller in the cylinder is driven by the spiral air flow to rotate, and ultrahigh-speed jet flow energy is converted into impeller shaft work and output.
Has the advantages that: because of centrifugal force and other reasons, the air pressure of the inner ring and the outer ring of the acting cylinder is higher than the air pressure of the inner ring, the air pressure is reduced when the jet flow spirally advances, the air can continue to expand, the expanded air mass pushes the front air flow to accelerate, the heat energy is converted into directional kinetic energy, the accelerated air flow pushes the impeller to act and then decelerates, the kinetic energy is converted into shaft work, the air flow continuously expands to act until the end of the circle center is reached, the heat energy is fully converted into shaft work, and the speed of the spiral air flow at the position is reduced to be very low due to the fact that the linear speed of the blades close to the circle center is very low, and the kinetic energy is fully converted; the heat efficiency can be further improved by selecting proper blade shapes, blade numbers and blade arrays and controlling the rotating speed to a certain degree; in addition, the scheme has the advantages of simple and reliable structure, low noise, low manufacturing cost, high power density and the like.
The impeller rotor ramjet engine according to the above invention is characterized in that: the outer ring of the shaft work converter working cylinder is provided with an annular air passage, a tail nozzle and a fairing of the ramjet engine are arranged in the annular air passage, the periphery of the annular air passage is provided with a main working blade, the working blade is horizontally arranged on a wheel disc of a working impeller, can bear high-temperature high-speed airflow impact and converts most of ultrahigh-speed jet flow energy into impeller shaft work for output; the long edge of the horizontal installation refers to the connection of the blade and the impeller disc, and the connection is reliable and the endurance is large.
Has the advantages that: the working vanes around the circular air passage directly face the tail nozzle of the stamping engine and need to bear extremely high impact force and temperature rise, the manufacturing cost is high, and the vanes at other parts are opposite, so the manufacturing cost can be reduced by separate arrangement, in addition, because the main working vanes of the scheme adopt horizontal installation and other reasons, the requirements on material strength, manufacturing process and the like are greatly reduced, the manufacturing cost is further reduced, the rotating speed is improved, the reliability is improved, and the service life is prolonged; the scheme also has the advantages of more compact structure and higher conversion efficiency.
The impeller rotor ramjet engine according to the above invention is characterized in that: the outer ring of the centrifugal cylinder of the centrifugal fan is provided with an annular air passage, a diffusion air inlet of the ramjet is arranged in the annular air passage, scavenging blades are arranged on the periphery of the annular air passage, and the scavenging blades are fixed on a wheel disc of the centrifugal impeller and can sweep airflow into the diffusion air inlet of the ramjet so as to maintain the flow speed of supersonic airflow in the annular air passage.
Has the advantages that: the scheme can ensure that supersonic airflow is more stable, the stamping effect is better, the starting is easy, and the structure is more compact.
The ramjet engine of the invention, claim 2, is characterized in that: the working impeller has a higher rotating speed than the centrifugal impeller, so that the linear speed of the main working blade is higher, the relative speed of the main working blade and the ultrahigh-speed jet flow is reduced, and the airflow impact and the temperature rise on the main working blade are reduced.
Has the advantages that: the scheme can further reduce the manufacturing and mounting cost of the main working blade and prolong the service life of the main working blade; the selection of a suitable rotation speed ratio also enables a higher thermal efficiency.
The ramjet engine of the invention, claim 2, is characterized in that: the diameter of the working impeller is larger than that of the centrifugal impeller, so that the linear speed of the main working blade is higher, the relative speed of the main working blade and the ultra-high-speed jet flow is reduced, and the airflow impact and the temperature rise borne by the main working blade are reduced.
Has the advantages that: the scheme can further reduce the manufacturing and mounting cost of the main acting blade, and is beneficial to improving the reliability and prolonging the service life; the selection of a suitable diameter ratio also enables a higher thermal efficiency.
6 the impeller rotor ramjet engine according to the above invention, the scheme is characterized in that: the working impeller also comprises an auxiliary working impeller which is arranged opposite to the working impeller, high-speed jet flow advances between the two impellers along the direction of a spiral path and a circle center exhaust hole, impeller blades on two sides of the high-speed jet flow are repeatedly pushed along the path, and jet flow energy can be more fully converted into impeller shaft work to be output.
Has the advantages that: the energy conversion is more sufficient, the thermal efficiency is improved, and the size of the engine is reduced and the power density is improved.
The impeller rotor ramjet engine according to the above invention is characterized in that: the working impeller comprises working blades and an impeller disc, and the working blades are horizontally arranged on the impeller disc; the long sides of the blades of the horizontally-arranged fingers are connected with the impeller disc, so that the connection is reliable and the endurance is high.
Has the advantages that: the number of blades can be reduced, and the installation is firm, the reliability is high, and the cost is low.
8 the impeller rotor ramjet engine according to the above invention, the scheme is characterized in that: the system also comprises a tail gas temperature detector and a control unit; the tail gas temperature detector can effectively detect the temperature of the tail gas of the engine, and the control unit can adjust the load according to the detected temperature of the tail gas and control the rotating speed of the impeller rotor of the engine at an economic rotating speed so as to obtain higher thermal efficiency; the economic rotating speed refers to the rotating speed of the corresponding impeller rotor when the temperature rise of tail gas is small, and at the moment, the thermal efficiency is high.
The principle is that because the air-fuel ratio is relatively fixed, the energy increment of the gas in unit weight in the airflow is relatively fixed, the higher the thermal efficiency is, the smaller the residual energy increment of the tail gas in unit weight is, because the flow velocity of the tail gas is very small, the energy of the tail gas is mainly heat energy, and the heat energy of the gas in unit weight is in direct proportion to the temperature thereof, the smaller the temperature rise of the tail gas is, namely the thermal efficiency is inversely related to the temperature rise of the tail gas, so that the lower the temperature rise of the tail gas can obtain higher thermal efficiency.
Has the advantages that: the scheme for improving the thermal efficiency is provided, the thermal efficiency of the engine can be greatly improved, and energy conservation and emission reduction are realized.
The invention has the advantages of
The invention has simple and reliable structure, small volume, large power density, high thermal efficiency, low noise, low manufacturing cost, long service life and quiet use. Can be suitable for various fuels, including green energy sources such as hydrogen, natural gas and the like.
In accordance with the present invention, the following detailed description is presented with reference to the accompanying drawings in order to provide a more complete understanding of the invention and other features and advantages.
Drawings
FIG. 1 is a schematic sectional view of an engine according to an embodiment;
FIG. 2 is a schematic view of a centrifugal impeller in an embodiment;
FIG. 3 is a top view of an embodiment of a ramjet engine;
FIG. 4 is a schematic diagram of a working impeller in an embodiment
In the figure: 1. a centrifugal fan; 11. an air inlet; 12. a centrifugal blade; 13. a basin-shaped impeller plate; 14. a scavenging vane; 15. an impeller plate; 16. a centrifugal cylinder; 2. a ramjet engine; 21. a diffusion air inlet; 22. a combustion chamber; 23. a tail spout; 24. a diffuser inlet cowling; 25. a jet nozzle fairing; 3. a shaft work converter; 31. a basin-shaped impeller plate; 32. a main working blade; 33. a working vane; 34. a secondary working blade; 35. an impeller plate; 36. an exhaust port; 37. an acting cylinder.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings.
Examples
The embodiment provides a preferred impeller ramjet engine technical scheme, which is mainly suitable for automobile range extension, ships, low-speed aircrafts and power generation, and is specifically as follows.
As shown in fig. 1, the engine mainly comprises a centrifugal fan (1), a ramjet engine (2), a shaft power converter (3) and the like; the centrifugal fan (1) provides supersonic airflow for the ramjet (2), the ramjet (2) is arranged between the centrifugal fan (1) and the shaft power converter (3), and the shaft power converter (3) converts high-speed jet flow of the ramjet (2) into shaft power to be output.
As shown in fig. 1 and fig. 2, the centrifugal impeller is composed of a basin-shaped impeller disc (13), centrifugal blades (12), scavenging blades (14) and a sub-impeller disc (15), an annular air passage is formed between the centrifugal blades (12) and the scavenging blades (14), and a diffusion air inlet (21) of the ramjet (2) and a fairing (24) thereof are arranged in the annular air passage; the centrifugal impeller rotates at a high speed, air enters the centrifugal cylinder (16) from the air inlet (11), is accelerated and pre-compressed by the centrifugal impeller, and forms supersonic airflow in the annular air passage, so that conditions are created for normal operation of the ramjet engine (2).
As shown in fig. 1 and fig. 3, the ramjet (2) mainly comprises a diffusion air inlet (21), a combustion chamber (22) and a tail nozzle (23), and is obliquely arranged between the centrifugal fan (1) and the shaft power converter (3); after being decelerated and stamped, the supersonic incoming flow high-speed injection diffusion air inlet (21) enters a combustion chamber (22) for oil mixing and combustion, fuel gas is rapidly expanded and ejected at high speed at a tail nozzle (23), and heat energy is converted into directional kinetic energy; the super-high speed jet flow forms tornado spiral airflow in the acting cylinder (37), the spiral airflow drives the acting impeller in the cylinder to rotate, and jet flow energy is converted into impeller shaft work to be output.
As shown in fig. 1 and 4, the working impeller is composed of a basin-shaped impeller disc (31), main working blades (32) and working blades (33), wherein the main working blades (32) are horizontally arranged on the wheel disc (31) of the working impeller and can bear high-speed airflow impact; the working impeller also comprises an auxiliary working impeller, the impeller consists of an auxiliary impeller disc (35) and an auxiliary impeller (34), and works synchronously with the working impeller, the quantity and the array mode of the auxiliary working blades (34) and the working blades (33) are the same, but the angles are staggered, so that jet flow can swing left and right while advancing along a spiral track, thus airflow can be smooth, and the energy conversion effect is increased; an annular air passage is formed between the main working blade (32) and the working blade (33), and a tail nozzle (23) and a fairing (25) of the ramjet engine are arranged in the annular air passage; the ultra-high speed jet flow firstly pushes a main working blade (32) to work, and most of the jet flow energy is converted into shaft work to be output; the high-speed airflow continues to spirally advance to push the working blades (33) and the auxiliary working blades (34) at the two sides to work until the working direction is close to the circle center; the tail gas is finally discharged from the exhaust port (36), and the work cycle is finished.
Has the advantages that: because of centrifugal force and other reasons, the air pressure of the inner and outer rings of the acting cylinder (37) is higher than that of the inner ring, the air pressure is reduced when jet flow spirally advances, the air can continue to expand, the expanded air mass pushes the front air flow to accelerate, heat energy is converted into directional kinetic energy, the accelerated air flow pushes the impeller to do work and then decelerates, the kinetic energy is converted into shaft work, the air flow continuously expands to do work until the end of the air flow approaches the center of a circle, the heat energy is fully converted into the shaft work, and the speed of the spiral air flow at the position can also be reduced to be very low due to the low linear velocity of the blades close to the center of a circle, and the jet flow kinetic energy; the heat efficiency can be further improved by selecting proper blade shapes, blade numbers and blade arrays and controlling the rotating speed to a certain degree; in addition, the scheme has the advantages of simple and reliable structure, low noise, low manufacturing cost, high power density and the like.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the spirit and scope of the invention. The present invention is not to be limited by the specific embodiments disclosed herein, and other embodiments that fall within the scope of the claims of the present application are intended to be within the scope of the present invention.
Claims (8)
1. An impeller rotor ramjet engine, characterized in that: the system comprises a centrifugal fan, a ramjet engine, a shaft power converter and a starting device; the centrifugal fan provides supersonic airflow for the ramjet, the ramjet is arranged between the centrifugal fan and the shaft power converter, the airflow is accelerated by fuel, the shaft power converter converts high-speed jet flow energy of the ramjet into shaft power to be output, and the starting device can enable the impeller to rotate at high speed for starting;
the centrifugal fan comprises a centrifugal impeller and a centrifugal cylinder; the centrifugal cylinder is a round flat cylinder, an air inlet hole is arranged at the center of the flat cylinder for air inlet, the centrifugal impeller is arranged in the centrifugal cylinder, the centrifugal impeller rotates at high speed to pre-compress the inlet air and accelerate the air to supersonic speed at the outer circle of the centrifugal impeller;
the ramjet comprises a diffusion air inlet, a combustion chamber and a tail nozzle; the diffusion air inlet is communicated with an air cavity of the outer ring of the centrifugal cylinder and is aligned to the incoming flow direction of the supersonic airflow; after the incoming flow is injected into the diffusion air inlet at a high speed and is decelerated and stamped, the incoming flow enters a combustion chamber for oil mixing and combustion, fuel gas is rapidly expanded and sprayed out at a high speed at a tail nozzle, and heat energy is converted into directional kinetic energy;
the shaft work conversion machine comprises a work-doing impeller and a work-doing barrel; the acting impeller is arranged in the acting cylinder, the acting cylinder is a circular flat cylinder, an exhaust hole is formed in the center of the flat cylinder and used for exhausting air, a tail nozzle of the stamping engine is communicated with an outer ring air cavity of the acting cylinder, ultrahigh-speed air flow is sprayed into the acting cylinder along the tangential direction of an outer circle of the tail nozzle, tornado spiral air flow is formed in the cylinder, the acting impeller in the cylinder is driven by the spiral air flow to rotate, and ultrahigh-speed jet flow energy is converted into impeller shaft work and output.
2. The impeller-rotor ramjet engine as set forth in claim 1, wherein: the outer ring of the shaft work converter working cylinder is provided with an annular air passage, a tail nozzle and a fairing of the ramjet engine are arranged in the annular air passage, the periphery of the annular air passage is provided with a main working blade, the working blade is horizontally arranged on a wheel disc of a working impeller, can bear high-temperature high-speed airflow impact and converts most of ultrahigh-speed jet flow energy into impeller shaft work for output; the long edge of the horizontal installation refers to the connection of the blade and the impeller disc, and the connection is reliable and the endurance is large.
3. The impeller-rotor ramjet engine according to claim 1 or 2, characterized in that: the outer ring of the centrifugal cylinder of the centrifugal fan is provided with an annular air passage, a diffusion air inlet of the ramjet is arranged in the annular air passage, scavenging blades are arranged on the periphery of the annular air passage, and the scavenging blades are fixed on a wheel disc of the centrifugal impeller and can sweep airflow into the diffusion air inlet of the ramjet so as to maintain the flow speed of supersonic airflow in the annular air passage.
4. The impeller-rotor ramjet engine as set forth in claim 2, wherein: the rotating speed of the working impeller is higher than that of the centrifugal impeller, so that the linear speed of the main working blade is higher, the relative speed of the main working blade and the ultrahigh-speed jet flow is reduced, and the impact of air flow on the main working blade is reduced.
5. The impeller-rotor ramjet engine as set forth in claim 2, wherein: the diameter of the working impeller is larger than that of the centrifugal impeller, so that the linear speed of the main working blade is higher, the relative speed of the main working blade and the ultrahigh-speed jet flow is reduced, and the impact of air flow on the main working blade is reduced.
6. The impeller-rotor ramjet engine according to any one of claims 1, 2, 4, 5, wherein: the working impeller also comprises an auxiliary working impeller which is arranged opposite to the working impeller, high-speed jet flow advances between the two impellers along the direction of a spiral path and a circle center exhaust hole, impeller blades on two sides of the high-speed jet flow are repeatedly pushed along the path, and jet flow energy can be more fully converted into impeller shaft work to be output.
7. The impeller-rotor ramjet engine according to any one of claims 1, 2, 4, 5, wherein: the working impeller comprises working blades and an impeller disc, and the working blades are horizontally arranged on the impeller disc; the long edge of the horizontal installation refers to the connection of the blade and the impeller disc, and the connection is reliable and the endurance is large.
8. The impeller-rotor ramjet engine according to any one of claims 1, 2, 4, 5, wherein: the system also comprises a tail gas temperature detector and a control unit; the tail gas temperature detector can effectively detect the temperature of the tail gas of the engine, and the control unit can adjust the load according to the detected temperature of the tail gas and control the rotating speed of the impeller rotor of the engine at an economic rotating speed; the economic rotating speed refers to the rotating speed of the corresponding impeller rotor when the temperature of the tail gas is lower, and the thermal efficiency is higher at the moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020077327.XU CN211230639U (en) | 2020-01-15 | 2020-01-15 | Impeller rotor ramjet engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020077327.XU CN211230639U (en) | 2020-01-15 | 2020-01-15 | Impeller rotor ramjet engine |
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| Publication Number | Publication Date |
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| CN211230639U true CN211230639U (en) | 2020-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020077327.XU Active CN211230639U (en) | 2020-01-15 | 2020-01-15 | Impeller rotor ramjet engine |
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| CN (1) | CN211230639U (en) |
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- 2020-01-15 CN CN202020077327.XU patent/CN211230639U/en active Active
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