CN104179595B - A kind of general purpose engine directly adding hot air generation thrust - Google Patents
A kind of general purpose engine directly adding hot air generation thrust Download PDFInfo
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- CN104179595B CN104179595B CN201410398216.8A CN201410398216A CN104179595B CN 104179595 B CN104179595 B CN 104179595B CN 201410398216 A CN201410398216 A CN 201410398216A CN 104179595 B CN104179595 B CN 104179595B
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Abstract
The invention discloses a kind of general purpose engine directly adding hot air generation thrust, comprise heat source response device, heat-transfer apparatus, heat-exchange system, heat source response device is arranged on heat-transfer apparatus top, heat-transfer apparatus terminal connects heat-exchange system, the heat that motor directly utilizes heat source response device to produce, by heat-transfer apparatus, heat is passed to the intake duct of motor, and sky air flow energy is fully heated at short notice, air after being heated flows through expansion, cooling, accelerates, and discharges motor and produces thrust.Rational heat transfer and air flow design, and the empty high efficiency air flow of inflow engine is heated, after the expanding noodles via air flow channel 3 ~ 5 degree, and air Accelerating Removal and obtain thrust.Without the need to there is combustion reaction in its process, traditional combustion heat supplying pattern broken away from by motor, adopts direct heating mode, and avoid and affect combustion reaction and the factor that reduces engine efficiency, be also that the application of efficient new energy provides interface and carrier simultaneously.
Description
Technical field
The invention belongs to Aero-Space engine application field, specifically, relate to a kind of general purpose engine directly adding hot air generation thrust.
Background technique
Motor is one of core technology of aerospace flight vehicle.
Existing disclosed technical paper " Core Engine technology and the research of development of engine type spectrum " (University of Electronic Science and Technology, 2007, master's dissertation), the current situation of home and abroad aeroengine and core engine thereof, rule, Development Techniques approach is described, the feature of multianalysis Foreign Engine core engine in literary composition.At document " development of nuclear aero-engine " (cruising missile, 2009,4th phase) in, describe the external progress in nuclear aero-engine field since the forties in 20th century, discuss the scheme that the U.S. is studied in aircraft nuclear propulsion project.Disclose in Chinese patent CN1O3527319A " a kind of new work engine ", efficiently solve turboshaft engine oil consumption when the slow-speed of revolution works higher, and the defect of inefficiency.
But there is following defect in document " Core Engine technology and the research of development of engine type spectrum " and the middle motor described of patent " a kind of new work engine ": first, the heat that existing aeroengine mainly utilizes burning to produce is gas-heated, causes its combustion reaction efficiency to determine the performance of motor.The factor much causing combustion efficiency to reduce all can reduce engine/motor specific impulse, as chemical property and the proportioning of oxygenant, reducing agent itself, can oxygenant fully mix with reducing agent, combustion reaction catalyst choice and consumption, factors is difficult to precisely controlled, causes engine performance to improve further.Second, along with the appearance of some new energy, as nuclear energy, solar energy, its reaction heat production efficiency far is greater than traditional combustion reaction, if 0.1kg uranium fission production capacity and traditional 125 tons of Aviation Fuels production capacity of burning is the same, but the most primitive reaction mode of a lot of efficient new energy is not burning heat production, but directly produces heat.These new energy of the confidential use of existing aeroplane engine, just having to pass through the conversion of form of energy, greatly reducing to making efficiency.
The U.S.'s nuclear propulsion scheme introduced in document " development of nuclear aero-engine " has the following disadvantages: the first, and heat transfer system structure is too simple, and generalities, is difficult to ensure the heat high efficiency of transmission of heat source for reaction and heated air; The second, do not carry out the design of heat-exchange system, cannot ensure that gas farthest can be heated, expands, produce thrust.
Summary of the invention
In order to avoid the deficiencies in the prior art part, the present invention proposes a kind of general purpose engine directly adding hot air generation thrust, its heat utilizing thermal source directly to produce, by heat-transfer apparatus, heat is passed to the air inlet runner of motor, and air stream is fully heated at short notice, air after being heated flows through expansion, cooling, accelerates, and discharges motor and produces thrust.
The technical solution adopted for the present invention to solve the technical problems is: comprise heat source response device, heat-transfer apparatus, heat-exchange system,
Described heat source response device comprises fixing ball, pipeline, reaction sphere, reaction heat interface, reaction sphere and fixing ball are different, the concentric hollow spheres structure of two diameters, there is through hole at reaction sphere and fixing ball two ends, two ball through holes are connected by two Bearing score ear shape pipelines, the axial two ends of fixing ball have circular hole and reaction heat interface to be connected, and in reaction sphere, filling liquid lithium is general reaction source;
Described heat-transfer apparatus comprises connecting tube, lithium stream plate, lithium stream pipe, lithium stream plate interface, pilot flow plate, described lithium stream plate is rectangular structure, there is lithium stream plate interface at lithium stream plate two ends, on lithium stream plate, there is polylith arcuate guide stream plate at two end part, the pilot flow plate intrados at two end part is relative, symmetrical to be installed, uniform some lithium stream pipes on lithium stream plate, and described connecting tube is two L shapes pipes, connecting tube one end and lithium stream plate interface are connected, and the other end of connecting tube is connected with fixing ball by reaction heat interface;
Described heat-exchange system comprises heat exchanger, imitative aerofoil profile profile, air flow channel, the half rhombus wing, lithium stream pipe fixed hole, runner expanding noodles, uniform multi-layer air runner in described heat exchanger, vertical direction equidistantly arranges some lithium stream pipe fixed holes, lithium stream pipe fixed hole runs through multi-layer air runner, and form lattice-shaped structure with air flow channel, it is horizontal plane bottom described air flow channel, air flow channel upper surface is runner expanding noodles, there is multiple half rhombus wing every layer of air runner front end, multilayer is imitated aerofoil profile profile and is laid respectively between air flow channel layer, the top of the half rhombus wing, lithium stream plate is positioned at above heat exchanger, lithium stream pipe coordinates with lithium stream pipe fixed hole.
Described runner expanding noodles is 3 ~ 5 degree.
Beneficial effect
A kind of general purpose engine directly adding hot air generation thrust that the present invention proposes, comprise heat source response device, heat-transfer apparatus, heat-exchange system, heat source response device is arranged on heat-transfer apparatus top, heat-transfer apparatus terminal connects heat-exchange system, the heat that motor directly utilizes heat source response device to produce, by heat-transfer apparatus, heat is passed to the air inlet runner of motor, and sky air flow energy is fully heated at short notice, air after being heated flows through expansion, cooling, accelerates, and discharges motor and produces thrust.Rational heat transfer and air flow design, and the empty high efficiency air flow of inflow engine is heated, after the expanding noodles via air flow channel 3 ~ 5 degree, and air stream Accelerating Removal and obtain thrust.Without the need to there is combustion reaction in its process, traditional combustion heat supplying pattern broken away from by motor, adopts direct heating mode, and avoiding and affect combustion reaction and the factor that reduces engine efficiency, meanwhile, is also that the utilization of efficient new energy provides interface and carrier.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of general purpose engine directly adding hot air generation thrust of the present invention is described in further detail.
Fig. 1 is general purpose engine assembled shaft mapping of the present invention.
Fig. 2 is heat source response device sectional drawing of the present invention.
Fig. 3 is heat-transfer apparatus axonometric drawing of the present invention.
Fig. 4 is lithium stream plate sectional drawing of the present invention.
Fig. 5 is heat-exchange system axonometric drawing of the present invention.
Fig. 6 is heat-exchange system sectional view of the present invention.
In figure:
1. heat source response device 2. heat-transfer apparatus 3. heat-exchange system 4. is fixed ball 5. pipeline 6. reaction sphere 7. reaction heat interface 8. connecting tube 9. lithium stream plate 10. lithium stream pipe 11. lithium stream plate interface 12. pilot flow plate 13. heat exchanger 14. and is imitated the aerofoil profile profile 15. air flow channel 16. half rhombus wing 17. lithium stream pipe fixed hole 18. runner expanding noodles
Embodiment
The present embodiment is a kind of general purpose engine directly adding hot air generation thrust.
Consult Fig. 1 ~ Fig. 6, the present embodiment directly adds the general purpose engine that hot air produces thrust, is made up of heat source response device 1, heat-transfer apparatus 2 and heat-exchange system 3.Heat source response device 1 is arranged on the top of heat-transfer apparatus 2, and heat-transfer apparatus 2 terminal connects heat-exchange system 3, and meanwhile, heat-exchange system 3 flows into, flow out air stream.
Heat source response device 1 comprises fixing ball 4, pipeline 5, reaction sphere 6, reaction heat interface 7, reaction sphere 6 and fixing ball 4 are different, the concentric hollow spheres structure of two diameters, there is through hole at reaction sphere 6 and fixing ball 4 two ends, reaction sphere 6 is connected by two Bearing score ear shape pipelines 5 with the two through hole of fixing ball 4, two pipelines 5 input reaction raw materials and output-response waste material respectively, the fixing axial two ends of ball 4 have circular hole to be fixedly connected with reaction heat interface 7, and in reaction sphere 6, filling liquid lithium is general reaction source.
Heat-transfer apparatus 2 is made up of connecting tube 8, lithium stream plate 9, lithium stream pipe 10, lithium stream plate interface 11, pilot flow plate 12, lithium stream plate 9 is rectangular structure, there is lithium stream plate interface 11 at lithium stream plate 9 two ends, on lithium stream plate 9, there is polylith arcuate guide stream plate 12 at two end part, pilot flow plate 12 intrados at two end part is relative, pilot flow plate 12 symmetry is installed, and lithium stream plate 9 is evenly equipped with some lithium stream pipes 10; Connecting tube 8 is two L shape pipes, and connecting tube 8 one end is fixedly connected with lithium stream plate interface 11, and the other end of connecting tube 8 is connected with the circular hole of fixing ball 4 by reaction heat interface 7.When engine operation, high temp. lithium liquid flows out from reaction sphere 6, and flow into lithium stream plate 9 via connecting tube 8 interface, spread by pilot flow plate 12, lithium liquid flows to the lithium stream pipe 10 of arrangement, upper and lower two-way flow in lithium stream pipe 10.Lithium liquid converges outflow lithium stream plate 9 by pilot flow plate 12 in outlet port, again flows back in the reaction sphere 6 of heat source response device 1, thus form the circulation of lithium liquid through connecting tube 8.In the cyclic process of lithium liquid, be delivered to endlessly by reaction heat in lithium stream pipe 10, ensure that exothermic reaction continues to carry out, heat flows to cool air stream endlessly.
Heat-exchange system 3 comprises heat exchanger 13, imitative aerofoil profile profile 14, air flow channel 15, the half rhombus wing 16, lithium stream pipe fixed hole 17, runner expanding noodles 18, uniform multi-layer air runner 15 in heat exchanger 13, vertical direction equidistantly arranges some lithium stream pipe fixed holes 17, lithium stream pipe fixed hole 17 runs through multi-layer air runner 15, and lithium stream pipe fixed hole 17 and air flow channel 15 form lattice-shaped structure.It is horizontal plane bottom air flow channel 15, air flow channel 15 upper surface is runner expanding noodles 18, every layer of air runner 15 front end is provided with multiple half rhombus wing 16, multilayer imitates that aerofoil profile profile 14 is separately fixed between air flow channel layer, the top of the half rhombus wing 16, lithium stream plate 9 is fixedly mounted on above heat exchanger 13, lithium stream pipe 10 coordinates with lithium stream pipe fixed hole 17, and lithium stream pipe 10 inserts heat exchanger 13 along lithium stream pipe fixed hole 17 and runs through multi-layer air runner 15.Air flows through air flow channel 15 and flows into after in heat-exchange system, carries out surface heating by air flow channel 15, heats by centered by lithium stream pipe 10.
In the present embodiment, runner expanding noodles 18 is 3 ~ 5 degree; When aircraft is with supersonic flight, the air stream complete expansion that air flow channel 15 is heated.After air stream flows into air flow channel 15, heated by lithium stream pipe 10; Due to the existence of runner expanding noodles 18, the power in high temperature and high pressure gas acting thrust, lift direction on expanding noodles, can fully expand when flowing through expanding noodles with Airflow, thus cooling, accelerates, and the gas after acceleration is discharged thus produced thrust.
The present embodiment is tested certain h type engine h scale model and measures, and major character dimensional parameters is as following table:
Wherein, reaction sphere, connecting tube, lithium stream plate adopt carbofrax material; The material selection cast iron of remaining part.
Heat source response device is exposed in atmosphere, placing burning reaction source in reaction sphere, filling liquid lithium in heat-transfer apparatus.Through test, reaction temperature is 1000 degrees Celsius, and connecting tube top temperature is 997 degrees Celsius, connecting tube terminal temperature is 956.2 degrees Celsius, lithium stream plate central area temperature is 892.4 degrees Celsius, and the mean temperature of lithium stream pipe is 856.9 degrees Celsius, and heat transfer efficiency is 86%.
Heat exchanger inlet air flow rate degree is 1Ma, and temperature is 26.9 degrees Celsius, and air density is 1.225kg/m
3, through the heating of lithium stream pipe array, the air flow velocity of heat exchanger outlet is 2.85Ma, and temperature is 142.6 degrees Celsius, and the conversion efficiency of heat energy and kinetic energy is 89%.The gross thrust of whole power plant is 5000N, and efficiency value is 77%.General purpose engine of the present invention directly can use the heat of heat source response device, and the air stream flowing through heat exchanger is fully heated at short notice, through the effect of expanding noodles, produces great thrust while high-temperature gas cooling, Accelerating Removal.
Claims (2)
1. one kind directly adds the general purpose engine that hot air produces thrust, comprise heat source response device, heat-transfer apparatus, heat-exchange system, heat source response device is arranged on heat-transfer apparatus top, heat-transfer apparatus terminal connects heat-exchange system, the heat that motor directly utilizes heat source response device to produce, by heat-transfer apparatus, heat is passed to the air inlet runner of motor, it is characterized in that:
Described heat source response device comprises fixing ball, pipeline, reaction sphere, reaction heat interface, reaction sphere and fixing ball are different, the concentric hollow spheres structure of two diameters, there is through hole at reaction sphere and fixing ball two ends, two ball through holes are connected by two Bearing score ear shape pipelines, the axial two ends of fixing ball have circular hole and reaction heat interface to be connected, and in reaction sphere, filling liquid lithium is general reaction source;
Described heat-transfer apparatus comprises connecting tube, lithium stream plate, lithium stream pipe, lithium stream plate interface, pilot flow plate, described lithium stream plate is rectangular structure, there is lithium stream plate interface at lithium stream plate two ends, on lithium stream plate, there is polylith arcuate guide stream plate at two end part, the pilot flow plate intrados at two end part is relative, symmetrical to be installed, uniform some lithium stream pipes on lithium stream plate, and described connecting tube is two L shapes pipes, connecting tube one end and lithium stream plate interface are connected, and the other end of connecting tube is connected with fixing ball by reaction heat interface;
Described heat-exchange system comprises heat exchanger, imitative aerofoil profile profile, air flow channel, the half rhombus wing, lithium stream pipe fixed hole, runner expanding noodles, uniform multi-layer air runner in described heat exchanger, vertical direction equidistantly arranges some lithium stream pipe fixed holes, lithium stream pipe fixed hole runs through multi-layer air runner, and form lattice-shaped structure with air flow channel, it is horizontal plane bottom described air flow channel, air flow channel upper surface is runner expanding noodles, there is multiple half rhombus wing every layer of air runner front end, multilayer is imitated aerofoil profile profile and is laid respectively between air flow channel layer, the top of the half rhombus wing, lithium stream plate is positioned at above heat exchanger, lithium stream pipe coordinates with lithium stream pipe fixed hole.
2. the general purpose engine directly adding hot air generation thrust according to claim 1, is characterized in that: described runner expanding noodles is 3 ~ 5 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410398216.8A CN104179595B (en) | 2014-08-13 | 2014-08-13 | A kind of general purpose engine directly adding hot air generation thrust |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410398216.8A CN104179595B (en) | 2014-08-13 | 2014-08-13 | A kind of general purpose engine directly adding hot air generation thrust |
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| CN104179595A CN104179595A (en) | 2014-12-03 |
| CN104179595B true CN104179595B (en) | 2016-03-02 |
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| CN201410398216.8A Expired - Fee Related CN104179595B (en) | 2014-08-13 | 2014-08-13 | A kind of general purpose engine directly adding hot air generation thrust |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5048288A (en) * | 1988-12-20 | 1991-09-17 | United Technologies Corporation | Combined turbine stator cooling and turbine tip clearance control |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN102383969A (en) * | 2010-08-30 | 2012-03-21 | 张柏海 | Kinetic energy pressure type jet engine |
-
2014
- 2014-08-13 CN CN201410398216.8A patent/CN104179595B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5048288A (en) * | 1988-12-20 | 1991-09-17 | United Technologies Corporation | Combined turbine stator cooling and turbine tip clearance control |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN102383969A (en) * | 2010-08-30 | 2012-03-21 | 张柏海 | Kinetic energy pressure type jet engine |
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| CN104179595A (en) | 2014-12-03 |
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Granted publication date: 20160302 Termination date: 20160813 |