CN103758661A - Small turbine jet engine - Google Patents
Small turbine jet engine Download PDFInfo
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- CN103758661A CN103758661A CN201410022402.1A CN201410022402A CN103758661A CN 103758661 A CN103758661 A CN 103758661A CN 201410022402 A CN201410022402 A CN 201410022402A CN 103758661 A CN103758661 A CN 103758661A
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Abstract
The invention provides a small turbine jet engine which comprises a compressor component and a combustion chamber component. The compressor component and the combustion chamber component are respectively located an air inlet end and a jet end of the small turbine jet engine. The compressor component comprises a compressor and a turbine, and the compressor and the turbine are integrally designed. By the adoption of the integral design of compressed air turbine blades, difficulty in design is reduced, and machining and assembling of a small structure are benefited; by the adoption of a reversed-flow type combustion chamber, compactness of the overall layout is benefited, dimensions in design are well controlled, and sufficient space is reserved for improving combustion efficiency; besides, the temperature of a whole shafting is effectively lowered due to outside motion of a bearing, overall system reliability is improved, service life is prolonged, requirements on bearing quality is lowered, and overall cost can be beneficially reduced.
Description
Technical field
The present invention relates to engine art, particularly, relate to a kind of miniature turbine jet engines.
Background technique
Development along with aeronautical technology, aircraft has proposed more and more higher requirement to the performance of propulsion system, turbojet engine is as a kind of main aero propulsion motor, its mechanical efficiency is high, in at present known various rotary machines, general, turbojet engine efficiency is best.And along with the variation of life style, in each different field, individualized, microminiaturization, lightweight have all become inevitable trend, jet engine of microminiature turbine also must become a popular problem.
The working principle of micro turbine engine is identical with traditional gas turbine engine, mainly parts such as minitype compressor, miniature turbine and miniature combustion chambers, consists of.Its groundwork process as shown in Figure 1, first when motor is started working, gas compressor High Rotation Speed compressing tablet does work to air, by air intake compression, air enters firing chamber through air flue, in firing chamber, from the pressurized air of gas compressor and the fuel mix that participates in reacting, burn, burning is emitted a large amount of energy firing chamber internal gas is expanded and heating, after burning, the gas of High Temperature High Pressure is finally by crossing the ejection of air outlet, firing chamber, high temperature and high pressure gas promotes turbine blade and makes its High Rotation Speed, the turbine of High Rotation Speed drives gas compressor work and exports certain moment of torsion by rotating shaft, gas sprays at a high speed in jet pipe afterwards, the gas of ejection produces repercussion active force to motor at a high speed, motor thrust output.
Particularly, Fig. 2 means the schematic diagram of the bearing of miniature turbine jet engines in Fig. 1.With reference to Fig. 2, bearing is all positioned between turbine (left side of Fig. 2) and gas compressor (right side of Fig. 2).
Yet, miniature turbine jet engines physical dimension is little, and the design of miniature turbine jet engines is not by the simple miniaturization of traditional motor, because it is one of the percentage size that has common aeroengine, its thrust weight ratio has reached the more than hundred times of common engine especially, but the working efficiency of whole motor is less than common engine, because the mechanical loss of the restricted internal gas flow of structure space is larger, because engine combustion chamber size is little, caused too combustion efficiency phenomenon on the low side, the processing of its critical component and assembling are all relatively difficult realizations.Meanwhile, because structure is less, thrust weight ratio is larger, makes the temperature of bearing higher, so bearing easily damages, working life is very short.
Summary of the invention
The present invention makes for solving the problems of the technologies described above, and its object is to provide a kind of miniature turbine jet engines.This miniature turbine jet engines overall structure is simple, is easy to processing assembling, and very large thrust can be provided simultaneously, and bearing can provide rotational power simultaneously, to drive, sends out other devices.
The invention provides a kind of miniature turbine jet engines, comprise compressor assemblies and combustion-chamber assembly, described compressor assemblies and described combustion-chamber assembly lay respectively at inlet end and the jet end of described miniature turbine jet engines, described compressor assemblies comprises gas compressor and turbine, wherein, described gas compressor and described turbine are the integrated design.
Preferably, described compressor assemblies also comprises rotor, and described gas compressor is the blade that is positioned at the air inlet side of described rotor, and described turbine is the blade that is positioned at the jet side of described rotor.
Preferably, described compressor assemblies also comprises a plurality of bearings, and described a plurality of bearings are positioned at the outside of described turbine and described gas compressor.
Preferably, described combustion-chamber assembly is reverse-flow can type combustor, and the air sucking through described gas compressor flows to described turbine after twice half-turn.
Preferably, the diameter of described miniature turbine jet engines is 5 centimetres or following.
According to said method, miniature turbine jet engines of the present invention, owing to having used integrated compressor turbine blade design, has reduced the difficulty of design, and is conducive to the processing assembling of microstructure.And owing to having adopted reverse-flow can type combustor, contribute to the compact type of integral layout, controlled well the size of design, and reserved sufficient space to improve combustion efficiency.In addition, outer the moving of bearing reduced the temperature that whole axle is effectively, improved entire system reliability and working life, reduced the requirement to bearing quality, contributes to reduce holistic cost.
Accompanying drawing explanation
Fig. 1 means the schematic diagram of miniature turbine jet engines described in the prior art.
Fig. 2 means the schematic diagram of the bearing of miniature turbine jet engines described in the prior art.
Fig. 3 means the sectional view of miniature turbine jet engines of the present invention.
Fig. 4 means the perspective view of miniature turbine jet engines of the present invention.
Fig. 5 a, Fig. 5 b mean the structural representation of miniature turbine jet engines rotor of the present invention.
Fig. 6 is the structural representation that the inlet flange that miniature turbine jet of the present invention starts is shown.
Fig. 7 is the structural representation that the shell of miniature turbine jet engines of the present invention is shown.
Fig. 8 is the air flow process schematic diagram that miniature turbine jet engines combustion-chamber assembly of the present invention is shown.
Fig. 9 is the structural representation that miniature turbine jet engines combustion-chamber assembly exocoel of the present invention is shown.
Figure 10 is the structural representation that miniature turbine jet engines combustion-chamber assembly inner chamber of the present invention is shown.
Figure 11 is the structural representation that miniature turbine jet engines combustion-chamber assembly end cap of the present invention is shown.
Embodiment
The embodiment of miniature turbine jet engines of the present invention is described below with reference to the accompanying drawings.Those of ordinary skill in the art can recognize, without departing from the spirit and scope of the present invention in the situation that, can to described embodiment, revise by various mode.Therefore, accompanying drawing is illustrative with being described in essence, rather than for limiting the protection domain of claim.In addition, in this manual, accompanying drawing draws not in scale, and identical reference character represents same or analogous part.
Fig. 3 means the sectional view of miniature turbine jet engines of the present invention.Fig. 4 means the perspective view of miniature turbine jet engines of the present invention.As shown in Figure 3, Figure 4, the jet end that left side is miniature turbine jet engines, right side is inlet end.Miniature turbine jet engines of the present invention comprises compressor assemblies 100 and combustion-chamber assembly 200.Compressor assemblies 100 comprises inlet flange 110, nut 120, main shaft 130, bearing 140, sleeve 150, air guide flange 160 and rotor 170.Described combustion-chamber assembly 200 comprises: shell 210, exocoel 220, end cap 230, combustion gas mouth 240, inner chamber 250, spark plug 260 and stator 270.
In the present invention, gas compressor and turbine are integrated, play both effects simultaneously.
Particularly, Fig. 5 a, Fig. 5 b mean the structural representation of miniature turbine jet engines rotor 170 of the present invention, as shown in Fig. 5 a, Fig. 5 b, rotor 170 both sides are equipped with blade, the blade 171 that is positioned at air inlet side (being compressor assemblies side) plays the effect of air intake, is called gas compressor, for ambient air is sucked, the blade 172 that is positioned at the side of giving vent to anger (being combustion-chamber assembly side) drives main shaft 130 rotations because the pressurized gas that burnt impact, be called turbine.
And, referring again to Fig. 3, Fig. 4, due to gas compressor and turbine are integrated, two bearings 140 are all positioned at turbine 172 and gas compressor 171 right sides after integrated, also be positioned at combustion-chamber assembly 200 right sides, be positioned at the outside of combustion-chamber assembly 200, turbine 172, gas compressor 171, realized the outer of bearing 140 and moved.
Particularly, as shown in Figure 6, inlet flange 110 is provided with inlet hole 111, central through bore 112, through hole 113 and positioning ring 114(and sees Fig. 3).Central through bore 112 is for bearing 140 is installed, and is provided with one section of internal thread, for attaching nut 120 at the right-hand member of central through bore 112.Described main shaft 130 is multidiameter shaft, and axle 131 places that coordinate with stator 270 of main shaft 130 are provided with outside thread, and for connecting rotor 170, the shaft shoulder 132 is for rotor 170 axially locating.The shaft shoulder 133, the shaft shoulder 134 are respectively used to the axially locating of two bearing 140 inner rings.Axle 135 diameters of main shaft 130 are less than the central through bore diameter of nut 120.Between two bearings 140, be provided with sleeve 150, in Fig. 3, bearing 140 outer rings in left side lean against on the positioning ring 114 of inlet flange 110, sleeve 150 compresses the outer ring of left side bearing 140, right side bearing 140 outer ring clamp sleeves 150, nut 120 is provided with central through bore and outside thread, nut 120 is threaded connection with inlet flange 110 fixing, compresses the outer ring of bearing 140.Described air guide flange 160, between inlet flange 110 and shell 210, is bolted.Air guide flange 160 inside are smooth curved surface, reduce intake resistance.Air guide flange 160 is provided with central through bore, and through-hole diameter is greater than main shaft, for air inlet.Described rotor 170 is positioned at axle 131 places of main shaft 130, and the central through bore place of rotor 170 is provided with internal thread, for being connected and fixed with main shaft 130.Rotor 170 outsides are along being circumferentially with many half slots 173, and half slot is equivalent to motive sealing, prevents that gas is from the narrow and small gap leakage between stator 270 and rotor 170.
Shell 210 is connected with air guide flange 160, inlet flange 110 use bolts, and shell 210 provides airtight space for Micro Turbine Jet Engine, simultaneously for fixedly end cap 230 is installed.Fig. 7 is the structural representation that the shell of miniature turbine jet engines of the present invention is shown.As shown in Figure 7, shell 210 inside are provided with a plurality of bar shaped boss 211, and boss 211 is for fixed stator 270 is installed, and guarantee to leave the gap for mistake gas between stator 270 and shell 210.Between the boss 211 of stator 270 and shell 210, be interference fit, without relative movement.Stator 270 is coaxial with rotor 170, is positioned at rotor 170 outsides, and stator 270 carries out axially locating by inner chamber 250 and air guide flange 160.Stator 270 is provided with blade 271 near inlet end one side, the bending direction of blade 271 is contrary with the bending direction of the blade 171 of rotor 170, sheet 271 distributes along even circumferential, for the air that blade 171 is sucked, guides in the space between shell 210 and exocoel 220.Stator 270 is provided with blade 272 near combustion-chamber assembly one side, and the bending direction of blade 272 is contrary with the bending direction of the blade 172 of rotor 170, and sheet 272 distributes along even circumferential, for the high temperature and high pressure gas in combustion-chamber assembly is guided to blade 172.
In the present invention, the combustion-chamber assembly of miniature turbine jet engines belongs to reverse-flow can type combustor, and the air sucking through described gas compressor flows to described turbine after twice half-turn.Fig. 8 is the air flow process schematic diagram that miniature turbine jet engines combustion-chamber assembly of the present invention is shown.As shown in Figure 8, the air flow process flowing out from gas compressor represents with overstriking black line, through four times 90 degree, turns, and after twice half-turn, flows to turbine.
Particularly, Fig. 9 is the structural representation that miniature turbine jet engines combustion-chamber assembly exocoel of the present invention is shown.It is inner and coaxial with housing 210 that exocoel 220 is positioned at housing 210, and exocoel 220 carries out axially locating by stator 270 and inner chamber 250, and Fig. 5 (sees a) in the shaft shoulder 273 places that in Fig. 3, the low order end of exocoel 220 is pressed in stator 270.At exocoel 220, near exhaust end place, be provided with the aperture 221 that many rows distribute along even circumferential, the air that gas compressor sucks from the external world enters combustion-chamber assembly by aperture 221.End cap 230 is positioned at exhaust end, by bolt and inner chamber 250, shell 210, is fixed together, and as shown in figure 11, establishes central through bore 231, tapped hole 232,233 and through hole 234 on end cap 230.Central through bore 231 is for exhaust, and tapped hole 232 is for fixing spark plug 260, and tapped hole 233 is for fixing combustion gas mouth 240.
Figure 10 is the structural representation that miniature turbine jet engines combustion-chamber assembly inner chamber of the present invention is shown.It is inner and coaxial with housing 210 that described inner chamber 250 is positioned at housing 210, and inner chamber 250 is provided with fuel gas hole 251, through hole 252, breast door 253 and central through bore 254.Inner chamber 250 is fixed together by bolt and shell 210, end cap 230, has realized axially locating and circumferential location.Inner chamber 250 contoured surfaces are smooth surface, can reduce the resistance that the high temperature and high pressure gas that forms after gas fuel burning runs into.The high temperature and high pressure gas forming in combustion-chamber assembly sprays from central through bore 254 after turbine.The ignition tip of spark plug 260 extend into combustion-chamber assembly inside by breast door 253, ignited flammable gas, and fuel gas hole 251 is that combustion gas enters the passage of combustion-chamber assembly from combustion gas mouth 240.
Particularly, the working principle of the miniature turbine jet engines the present invention relates to is as follows, first by high-pressure air source, facing to the inlet hole 111 of inlet flange 110, blow, start rotor 170, rotor 170 rotations, compressor blade 171 sucks ambient air through inlet hole 111, and air is through air guide flange 160 central through bores, through blade 171 and rotor blade 271, enter the space between housing 210 and exocoel 220 again, the through hole 221 through exocoel 220 enters combustion-chamber assembly again.Meanwhile, inflammable gas enters the space between end cap 230 and inner chamber 250 from combustion gas mouth 240, then enters combustion-chamber assembly by the aperture 251 on inner chamber 250, and inflammable gas mixes with air.Simultaneously, spark plug 260 igniting, inflammable gas in combustion-chamber assembly is lighted, gas fuel burning forms high temperature and high pressure gas and promotes turbine blade 172, drive stator 170 High Rotation Speeds, stator 170 rotations are constantly by air intake combustion-chamber assembly, and high temperature and high pressure gas, from 254 ejections of lumen centers through hole, forms powerful Driving force simultaneously.
Preferably, the diameter of miniature turbine jet engines of the present invention is 5 centimetres or following.
According to said method, miniature turbine jet engines of the present invention, owing to having used integrated compressor turbine blade design, has reduced the difficulty of design, and is conducive to the processing assembling of microstructure.Owing to having adopted reverse-flow can type combustor, contribute to the compact type of integral layout simultaneously, controlled well the size of design, and reserved sufficient space to improve combustion efficiency.In addition, outer the moving of bearing reduced the temperature that whole axle is effectively, improved entire system reliability and working life, reduced the requirement to bearing quality.Contribute to reduce holistic cost.
It will be appreciated by those skilled in the art that the miniature turbine jet engines relating to for foregoing invention, can also on the basis that does not depart from content of the present invention, make various improvement and combination.Therefore, protection scope of the present invention should be determined by the content of appending claims.
Claims (5)
1. a miniature turbine jet engines, comprise compressor assemblies and combustion-chamber assembly, described compressor assemblies and described combustion-chamber assembly lay respectively at inlet end and the jet end of described miniature turbine jet engines, and described compressor assemblies comprises gas compressor and turbine
Wherein, described gas compressor and described turbine are the integrated design.
2. miniature turbine jet engines according to claim 1, wherein, described compressor assemblies also comprises rotor, and described gas compressor is the blade that is positioned at the air inlet side of described rotor, and described turbine is the blade that is positioned at the jet side of described rotor.
3. miniature turbine jet engines according to claim 1 and 2, wherein, described compressor assemblies also comprises a plurality of bearings, described a plurality of bearings are positioned at the outside of described turbine and described gas compressor.
4. miniature turbine jet engines according to claim 1 and 2, wherein, described combustion-chamber assembly is reverse-flow can type combustor, the air sucking through described gas compressor flows to described turbine after twice half-turn.
5. miniature turbine jet engines according to claim 1, wherein, the diameter of described miniature turbine jet engines is 5 centimetres or following.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410022402.1A CN103758661B (en) | 2014-01-17 | 2014-01-17 | Miniature turbine jet engines |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410022402.1A CN103758661B (en) | 2014-01-17 | 2014-01-17 | Miniature turbine jet engines |
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| CN103758661A true CN103758661A (en) | 2014-04-30 |
| CN103758661B CN103758661B (en) | 2016-08-17 |
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| CN201410022402.1A Active CN103758661B (en) | 2014-01-17 | 2014-01-17 | Miniature turbine jet engines |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040118101A1 (en) * | 2002-12-23 | 2004-06-24 | Dewis David W. | Recuperator configuration |
| KR101141144B1 (en) * | 2011-11-30 | 2012-05-04 | 국방과학연구소 | Micro turbine engine with generator |
| US20120210728A1 (en) * | 2011-02-18 | 2012-08-23 | Dynamo Micropower Corporation | Fluid Flow Devices with Vertically Simple Geometry and Methods of Making the Same |
| CN202628278U (en) * | 2012-06-15 | 2012-12-26 | 北京中陆航星机械动力科技有限公司 | Miniature turbojet engine starting system |
-
2014
- 2014-01-17 CN CN201410022402.1A patent/CN103758661B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040118101A1 (en) * | 2002-12-23 | 2004-06-24 | Dewis David W. | Recuperator configuration |
| US20120210728A1 (en) * | 2011-02-18 | 2012-08-23 | Dynamo Micropower Corporation | Fluid Flow Devices with Vertically Simple Geometry and Methods of Making the Same |
| KR101141144B1 (en) * | 2011-11-30 | 2012-05-04 | 국방과학연구소 | Micro turbine engine with generator |
| CN202628278U (en) * | 2012-06-15 | 2012-12-26 | 北京中陆航星机械动力科技有限公司 | Miniature turbojet engine starting system |
Non-Patent Citations (1)
| Title |
|---|
| H.-C.LIU等: ""Fabrication of Ceramic Components for Micro Gas Engines"", 《CERAMIC ENGINEERING AND SCIENCE PROCEEDINGS》, vol. 23, no. 4, 1 January 2002 (2002-01-01), pages 43 - 50 * |
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| CN103758661B (en) | 2016-08-17 |
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