CN103590919A - High-pressure jet-propelled rotary engine - Google Patents
High-pressure jet-propelled rotary engine Download PDFInfo
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- CN103590919A CN103590919A CN201310482354.XA CN201310482354A CN103590919A CN 103590919 A CN103590919 A CN 103590919A CN 201310482354 A CN201310482354 A CN 201310482354A CN 103590919 A CN103590919 A CN 103590919A
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- rotary engine
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Abstract
The invention relates to the field of energy and power, in particular to a high-pressure jet-propelled rotary engine comprising a rotary structure, an oxidant source and a jet pipe. The rotary structure is provided with an inner combustion chamber which is communicated with a fuel source through a fuel passage. The fuel passage is provided with a fuel control valve. The fuel control valve is controlled by an intermittent supply control device which allows the fuel passage to intermittently supply fuel into the combustion chamber. A medium outlet of the oxidant source is communicated with the combustion chamber through an intake passage. A high-pressure medium outlet of the combustion chamber is communicated with the jet pipe through a jet passage. A jet direction of the jet pipe mainly points to a tangent line of a rotary periphery of the rotary engine. The jet pipe generates propelling force to propel the rotary structure to rotate and output power. The high-pressure jet-propelled rotary engine is simple in structure and can be used as an engine outputting rotary power; the highest operating temperature of the combustion chamber can be increased; the high-pressure jet-propelled rotary engine has high efficiency even when operating at low speed.
Description
Technical field
The present invention relates to energy and power engineering field, particularly a kind of high-pressure jet advances rotary engine.
Background technique
Current air breathing engine structure is more complicated, and requires motion speed fast especially, like this, is difficult in some cases use, and especially it is difficult to use as the motor of outputting rotary power.In addition, in air breathing engine, the temperature and pressure of working medium is all higher, therefore the material of motor or structural manufacturing process is had to higher requirement.Current material and structural manufacturing process have limited maximum temperature and the pressure of air breathing engine work, cause the efficiency of current air breathing engine to be difficult to further improve.For this reason, need to invent a kind of structure more simple, can improve firing chamber Maximum operating temperature, and when low cruise, particularly when low-speed rotation, also can obtain the motor of efficient propelling force, the motor that this class motor can be used as outputting rotary power uses.
Summary of the invention
In order to solve above-mentioned problems of the prior art, the technological scheme that the present invention proposes is as follows:
High-pressure jet advances rotary engine, comprise rotational structure body, oxidizer source and jet pipe, in described rotational structure body, establish firing chamber, described firing chamber is communicated with fuel source through fuel channel, on described fuel channel, fuel control valve is set, described fuel control valve is made described fuel channel control to the intermittent supply control gear of intermittent supply fuel in described firing chamber; The sender property outlet of described oxidizer source is communicated with described firing chamber through gas-entered passageway, the high-pressure working medium outlet of described firing chamber is communicated with described jet pipe through injection channel, the injection direction of described jet pipe be take described high-pressure jet and is advanced the tangent line of rotary engine revolution circumference to point to for overall, and the propelling force that described jet pipe produces promotes that described rotational structure body rotates and external outputting power.
The bearing capacity at the sender property outlet place of described oxidizer source is greater than 2MPa.
Described oxidizer source is made as compressed-air system, described compressed-air system comprises cylinder piston type gas compressor and impeller gas compressor, the pressurized gas outlet of described impeller gas compressor is communicated with the suction port of described cylinder piston type gas compressor, and the pressurized gas outlet of described cylinder piston type gas compressor is communicated with described firing chamber through described gas-entered passageway.
Described oxidizer source is made as compressed-air system, described compressed-air system comprises cylinder piston type gas compressor and impeller gas compressor, the pressurized gas outlet of described cylinder piston type gas compressor is communicated with the suction port of described impeller gas compressor, and the pressurized gas outlet of described impeller gas compressor is communicated with described firing chamber through described gas-entered passageway.
Described cylinder piston type gas compressor and/or described impeller gas compressor are made as multilevel hierarchy.
On described gas-entered passageway, establish and other put cooling channel, described gas-entered passageway is put cooling channel and is communicated with described injection channel through described side, puts on cooling channel, establish cooling control valve on described side.
Described high-pressure jet advances rotary engine also to comprise rotary inertia body, and described rotary inertia body is directly connected with described rotational structure body or described rotary inertia body is connected with described rotational structure body through gear.
Described jet pipe is made as more than two, and described jet pipe advances on rotary engine revolution circumference and is evenly arranged at described high-pressure jet.
Principle of the present invention is: oxygenant and the fuel High Temperature High Pressure working medium producing of burning in described firing chamber sprays from described jet pipe through described injection channel, thereby promotes described rotational structure body to rotate and obtain rotating power.By described intermittent supply control gear, control described fuel control valve, realize the intermittent supply of fuel, when temperature, pressure is too high in described firing chamber, can stop or reducing the feed of fuel, by the oxygenant that continues to enter, absorb the heat in described firing chamber, thereby reach the object of controlling temperature and pressure in described firing chamber.
In the present invention, the bearing capacity at the sender property outlet place of described oxidizer source is greater than 2 MPa, 3MPa, 4MPa, 5MPa, 6MPa, 7MPa, 8MPa, 9MPa, 10MPa, 11MPa, 12MPa, 13MPa, 14MPa, 15MPa, 16MPa, 17MPa, 18MPa, 19MPa, 20MPa, 21MPa, 22MPa, 23MPa, 24MPa, 25MPa, 26MPa, 27MPa, 28MPa, 29MPa or is greater than 30MPa.
In the present invention, working pressure and its bearing capacity at the sender property outlet place of described oxidizer source match, and the maximum service pressure at the sender property outlet place of described oxidizer source reaches its bearing capacity.
In the present invention, so-called " intermittent supply of fuel " refers to that fuel is not continual and steady feed, but fluctuation-type feed (amount of fuel charge changes) or fuel stop feed a period of time in feed after a period of time, the Changing Pattern of fuel charge amount or the duration of fuel charge can be by actual conditions adjustment with the duration that stops feed.
In the present invention, described intermittent supply control gear can be controlled described fuel control valve and work with timing feed mode, intermittent supply mode or long pause feed mode, described timing feed mode refers to the feed mode of spraying by time relationship, described intermittent supply mode refers to the feed mode of intermittent injection, and described long pause feed mode refers to that the dwell time is greater than the feed mode of discharge time.
In the present invention, because oil spout is discrete, therefore, when oil spout, motor is in superhigh temperature state work (so-called superhigh temperature refers to the temperature that temperature can bear higher than conventional engines), when oil spout stops, the temperature of working medium declines, described firing chamber and combustion gas turbine are carried out cooling, thereby improve the average operating temperature of motor, final realization raised the efficiency.
In the present invention, described fuel control valve can optionally adopt common control valve, its keying is controlled by described intermittent supply control gear, and described intermittent supply control gear can optionally adopt machine control unit of the prior art or electric control device etc., and all can realize the device of intermittently controlling.
In the present invention, formed track circumference when so-called " revolution circumference " refers to described rotational structure body and for example, rotate with the structure (described jet pipe) of described rotational structure body motion.
In the present invention, so-called " tangent line that turns round circumference of take is overall and points to ", both the tangent line that had comprised turning round circumference sprays situation about pointing to for completely accurate, although also comprise that it is to spray situation about pointing to that the drift angle existing to a certain extent still be take the tangent line of revolution circumference substantially.
In the present invention, the oxygenant in described oxidizer source refers to the material that can react with fuel generation combustion chemistry, can be pressurized air, liquid oxygen or liquefied air etc.
In the present invention, should, according to the known technology in energy and power engineering field, in necessary place, necessary parts, unit or system be set.
Beneficial effect of the present invention is as follows:
The present invention is simple in structure, and the motor that can be used as outputting rotary power uses, and can improve firing chamber Maximum operating temperature, and also have greater efficiency when low cruise simultaneously.
Accompanying drawing explanation
Fig. 1 is the structural representation of the embodiment of the present invention 1;
Fig. 2 is the structural representation of the embodiment of the present invention 1 medium-pressure air compressor system;
Fig. 3 is the structural representation of the embodiment of the present invention 2 medium-pressure air compressor systems;
Fig. 4 is the structural representation of the embodiment of the present invention 3;
Fig. 5 is the structural representation of the embodiment of the present invention 4;
Fig. 6 is the structural representation that the present invention includes the compressed-air system of multistage described cylinder piston type gas compressor;
Fig. 7 is the structural representation that the present invention includes the compressed-air system of multistage described impeller gas compressor,
In figure:
1 rotational structure body, 2 oxidizer sources, 3 jet pipes, 4 firing chambers, 5 fuel source, 6 rotary inertia bodies, 10 fuel control valves, 11 fuel channels, 12 intermittent supply control gear, 21 gas-entered passageways, 22 cylinder piston type gas compressors, 23 impeller gas compressors, 24 other cooling channel, 25 cooling control valves, 31 injection channels put.
Embodiment
High-pressure jet as shown in Figure 1 advances rotary engine, comprise rotational structure body 1, oxidizer source 2 and jet pipe 3, in described rotational structure body 1, establish firing chamber 4, described firing chamber 4 is communicated with fuel source 5 through fuel channel 11, on described fuel channel 11, fuel control valve 10 is set, described fuel control valve 10 is made described fuel channel 11 control to the intermittent supply control gear 12 of the interior intermittent supply fuel in described firing chamber 4; The sender property outlet of described oxidizer source 2 is communicated with described firing chamber 4 through gas-entered passageway 21, the high-pressure working medium outlet of described firing chamber 4 is communicated with described jet pipe 3 through injection channel 31, the injection direction of described jet pipe 3 be take described high-pressure jet and is advanced the tangent line of rotary engine revolution circumference to point to for overall, and the propelling force that described jet pipe 3 produces promotes described rotational structure body 1 and rotates and external outputting power.
In the present embodiment, described jet pipe magnitude setting is two, and these two described jet pipes 3 are evenly arranged on described rotary engine revolution circumference.
In the present embodiment, the bearing capacity that the sender property outlet place of described oxidizer source is optionally set is greater than 2MPa.And the working pressure of described oxidizer source and the bearing capacity in its outlet port are matched.
In the present embodiment, described oxidizer source 2 can optionally adopt the pre-stored storage tank that has oxygenant, the pre-stored storage tank that has pressurized air, liquid oxygen or liquefied air for example, and the bearing capacity at the sender property outlet place of described storage tank is greater than 2MPa.
In the present embodiment, described oxidizer source 2 is also optionally made as compressed-air system as shown in Figure 2, described compressed-air system comprises cylinder piston type gas compressor 22 and impeller gas compressor 23, the pressurized gas outlet of described impeller gas compressor 23 is communicated with the suction port of described cylinder piston type gas compressor 22, the pressurized gas outlet of described cylinder piston type gas compressor 22 is communicated with described firing chamber 4 through described gas-entered passageway 21, and the bearing capacity in the pressurized gas outlet port of described cylinder piston type gas compressor 22 is greater than 2MPa.
High-pressure jet described in the present embodiment advances rotary engine, and itself and embodiment's 1 difference is:
Described oxidizer source 2 changes the compressed-air system being made as shown in Figure 3, described compressed-air system comprises cylinder piston type gas compressor 22 and impeller gas compressor 23, the pressurized gas outlet of described cylinder piston type gas compressor 22 is communicated with the suction port of described impeller gas compressor 23, and the pressurized gas outlet of described impeller gas compressor 23 is communicated with described firing chamber 4 through described gas-entered passageway 21.The bearing capacity of the pressurized gas outlet of described impeller gas compressor 23 is greater than 5MPa.
Optionally, as shown in Figure 6 and Figure 7, the described cylinder piston type gas compressor 22 in above-described embodiment 1 and embodiment 2 is made as to multilevel hierarchy or described impeller gas compressor 23 is made as to multilevel hierarchy.
Selectively, described cylinder piston type gas compressor and described impeller gas compressor are all made as to multilevel hierarchy.
High-pressure jet as shown in Figure 4 advances rotary engine, it is on embodiment 1 basis, on described gas-entered passageway 21, set up the other cooling channel 24 of putting, described gas-entered passageway 21 is put cooling channel 24 and is communicated with described injection channel 31 through described side, put on cooling channel 24, establish cooling control valve 25 on described side.
Open after described cooling control valve 25, Partial shrinkage gas will directly not spray from described jet pipe 3 by described firing chamber 4 after described injection channel 31, and described injection channel 31 and described jet pipe 3 are had to certain cooling action.
In the present invention, all mode of executions all can, with reference to the present embodiment, be established described side and be put cooling channel 24 and relational structure thereof on described gas-entered passageway 21.
Embodiment 4
High-pressure jet as shown in Figure 5 advances rotary engine, and it sets up rotary inertia body 6 on embodiment 1 basis, and described rotary inertia body 6 is directly connected with described rotational structure body 1.
Storage area energy when described firing chamber 4 fuel combustion of described rotary inertia body 6 in described high-pressure jet propelling rotary engine are worked, when stopping or reducing the fuel charge to described firing chamber 4, energy can be returned to described rotational structure body 1, thereby the rotating speed of described rotational structure body 1 can not occurred significantly changing because of the variation of fuel charge in described firing chamber 4.
Optionally, described rotary inertia body 6 can also for example, be connected with described rotational structure body 1 through gear (gear shift).
In addition, on described rotary engine revolution circumference, three jet pipes 3 have been evenly arranged in the present embodiment.According to the actual requirements, can be chosen on the revolution circumference of described rotary engine three the above jet pipes 3 are evenly set.
In the present invention, all mode of executions all can be set up described rotary inertia body 6 with reference to the present embodiment.
Can be optionally, the described high-pressure jet in all mode of executions in the present invention advances the appropriate location of rotary engine that cooling system is set.
When all of the embodiments of the present invention is specifically implemented, all optionally the bearing capacity at the sender property outlet place of described oxidizer source is greater than to 2MPa, 3MPa, 4MPa, 5MPa, 6MPa, 7MPa, 8MPa, 9MPa, 10MPa, 11MPa, 12MPa, 13MPa, 14MPa, 15MPa, 16MPa, 17MPa, 18MPa, 19MPa, 20MPa, 21MPa, 22MPa, 23MPa, 24MPa, 25MPa, 26MPa, 27MPa, 28MPa, 29MPa or is greater than 30MPa.
In all of the embodiments of the present invention, described jet pipe 3 all advances on rotary engine revolution circumference and is evenly arranged at described high-pressure jet, as the mode of execution that can convert, described jet pipe 3 can advance non-homogeneous layout on rotary engine revolution circumference at described high-pressure jet, does not affect the realization of the object of the invention.
Obviously, the invention is not restricted to above embodiment, according to the known technology of related domain and technological scheme disclosed in this invention, can derive or association goes out many flexible programs, all these flexible programs, also should think protection scope of the present invention.
Claims (8)
1. a high-pressure jet advances rotary engine, comprise rotational structure body (1), oxidizer source (2) and jet pipe (3), it is characterized in that: in described rotational structure body (1), establish firing chamber (4), described firing chamber (4) is communicated with fuel source (5) through fuel channel (11), fuel control valve (10) is set on described fuel channel (11), and described fuel control valve (10) is made described fuel channel (11) control to the intermittent supply control gear (12) of the interior intermittent supply fuel in described firing chamber (4); The sender property outlet of described oxidizer source (2) is communicated with described firing chamber (4) through gas-entered passageway (21), the high-pressure working medium outlet of described firing chamber (4) is communicated with described jet pipe (3) through injection channel (31), the injection direction of described jet pipe (3) be take described high-pressure jet and is advanced the tangent line of rotary engine revolution circumference to point to for overall, and the propelling force that described jet pipe (3) produces promotes that described rotational structure body (1) rotates and external outputting power.
2. high-pressure jet advances rotary engine as claimed in claim 1, it is characterized in that: the bearing capacity at the sender property outlet place of described oxidizer source (2) is greater than 2MPa.
3. high-pressure jet advances rotary engine as claimed in claim 1, it is characterized in that: described oxidizer source (2) is made as compressed-air system, described compressed-air system comprises cylinder piston type gas compressor (22) and impeller gas compressor (23), the pressurized gas outlet of described impeller gas compressor (23) is communicated with the suction port of described cylinder piston type gas compressor (22), and the pressurized gas outlet of described cylinder piston type gas compressor (22) is communicated with described firing chamber (4) through described gas-entered passageway (21).
4. high-pressure jet advances rotary engine as claimed in claim 1, it is characterized in that: described oxidizer source (2) is made as compressed-air system, described compressed-air system comprises cylinder piston type gas compressor (22) and impeller gas compressor (23), the pressurized gas outlet of described cylinder piston type gas compressor (22) is communicated with the suction port of described impeller gas compressor (23), and the pressurized gas outlet of described impeller gas compressor (23) is communicated with described firing chamber (4) through described gas-entered passageway (21).
5. as described in claim 3 or 4, high-pressure jet advances rotary engine, it is characterized in that: described cylinder piston type gas compressor (22) and/or described impeller gas compressor (23) are made as multilevel hierarchy.
6. as described in any one in claim 1 to 4, high-pressure jet advances rotary engine, it is characterized in that: on described gas-entered passageway (21), establish the other cooling channel (24) of putting, described gas-entered passageway (21) is put cooling channel (24) and is communicated with described injection channel (31) through described side, put on cooling channel (24), establish cooling control valve (25) on described side.
7. as described in any one in claim 1 to 4, high-pressure jet advances rotary engine, it is characterized in that: described high-pressure jet advances rotary engine also to comprise rotary inertia body (6), and described rotary inertia body (6) is directly connected with described rotational structure body (1) or described rotary inertia body (6) is connected with described rotational structure body (1) through gear.
8. as described in any one in claim 1 to 4, high-pressure jet advances rotary engine, it is characterized in that: described jet pipe (3) is made as more than two, and described jet pipe (3) advances on rotary engine revolution circumference and is evenly arranged at described high-pressure jet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310482354.XA CN103590919A (en) | 2012-10-22 | 2013-10-15 | High-pressure jet-propelled rotary engine |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210404730 | 2012-10-22 | ||
| CN201210404730.9 | 2012-10-22 | ||
| CN201310482354.XA CN103590919A (en) | 2012-10-22 | 2013-10-15 | High-pressure jet-propelled rotary engine |
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| CN103590919A true CN103590919A (en) | 2014-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310482354.XA Pending CN103590919A (en) | 2012-10-22 | 2013-10-15 | High-pressure jet-propelled rotary engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104879238A (en) * | 2014-02-27 | 2015-09-02 | 南京美雪动力科技有限公司 | Multi-mode pulse detonation engine |
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| US20030140614A1 (en) * | 2002-01-29 | 2003-07-31 | Nearhoof Charles F. | Fuel injection control system for a turbine engine |
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| CN101988426A (en) * | 2010-10-22 | 2011-03-23 | 靳北彪 | Turbine composite gas compression system |
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- 2013-10-15 CN CN201310482354.XA patent/CN103590919A/en active Pending
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| US5282356A (en) * | 1993-01-07 | 1994-02-01 | Abell Irwin R | Flywheel engine |
| US5408824A (en) * | 1993-12-15 | 1995-04-25 | Schlote; Andrew | Rotary heat engine |
| CN1354322A (en) * | 2000-11-17 | 2002-06-19 | 祝长宇 | Jet rotary engine |
| US20030140614A1 (en) * | 2002-01-29 | 2003-07-31 | Nearhoof Charles F. | Fuel injection control system for a turbine engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104879238A (en) * | 2014-02-27 | 2015-09-02 | 南京美雪动力科技有限公司 | Multi-mode pulse detonation engine |
| CN104879238B (en) * | 2014-02-27 | 2017-04-05 | 南京美雪动力科技有限公司 | Multi-mode pulse-knocking engine |
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Application publication date: 20140219 |