CN104847695A - Stage-middle air bleeding type air compressor based on micro-turbine jet engine - Google Patents
Stage-middle air bleeding type air compressor based on micro-turbine jet engine Download PDFInfo
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- CN104847695A CN104847695A CN201510240985.XA CN201510240985A CN104847695A CN 104847695 A CN104847695 A CN 104847695A CN 201510240985 A CN201510240985 A CN 201510240985A CN 104847695 A CN104847695 A CN 104847695A
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Abstract
The invention discloses a stage-middle air bleeding type air compressor based on a micro-turbine jet engine and relates to a micro-turbine jet engine structure device. The stage-middle air bleeding type air compressor based on the micro-turbine jet engine is capable of providing compressed air for an ultra-light wingtip air spraying type rotor craft. The stage-middle air bleeding type air compressor based on the micro-turbine jet engine comprises a front end cover, a diagonal flow type special centrifugal impeller, a stage-middle diffuser, a stage-post diffuser, a double-channel volute type air collecting ring and the like. The stage-middle air bleeding type air compressor uses the matched micro-turbine jet engine, the air compressor part is provided with an air bleeding structure, the compression and air bleeding functions of the air compressor are combined, and compressed air needed for an aircraft is bled from the middle part of the centrifugal impeller to push a rotor wing to rotate. The stage-middle air bleeding type air compressor based on the micro-turbine jet engine is very different from a normal micro-turbine jet engine air compressor. The stage-middle air bleeding type air compressor structure can simultaneously meet the air bleeding and engine working demands of the aircraft, the power system structure is more compact, and the weight is lighter. The stage-middle air bleeding type air compressor based on the micro-turbine jet engine better meets the power demand of the rotor craft.
Description
Technical field
This patent relates to a kind of Micro Turbine Jet Engine constructional device, and what can be surperlight type wing tip rotorjet aircraft provides pressurized air.Exactly by a Micro Turbine Jet Engine through compatibility design, bleed structure is increased at its gas compressor position, the compression of gas compressor and air-entraining function are merged, is drawn the pressurized air met required for aircraft by centrifugal impeller intermediate portion, thus promote rotor wing rotation.Air feeding type gas compressor in level, meet aircraft bleed and engine operation two aspect requirement, make power system architecture compacter, weight is lighter simultaneously.
Background technique
Be limited to the rigors of Superlight rotor craft for weight, adopt the jet-driven mode of wing tip to receive publicity, namely utilize pressurized air to produce reaction force in the wing tip ejection of rotor and promote rotor wing rotation.This just must consider a kind of compressor apparatus, can provide required pressurized air constantly.The air compressor structure form of bleed in the level that the present invention adopts, can make power system architecture compacter, and weight is lighter, meets the power demand of this rotor craft better.
Be limited to the rigors of Superlight rotor craft for weight, adopt the mode of the jet drive rotor wing rotation of wing tip to receive publicity.Owing to will utilize pressurized air at the reaction force of rotor wing tip ejection generation to promote rotor wing rotation, this just must consider a kind of air compression plant, can provide required pressurized air sustainedly and stably.Based on this requirement, this patent devises the air compressor structure form that a kind of bleed adds compression, as the element of construction of Micro Turbine Jet Engine.This gas compressor can provide the pressurized air of pressure, temperature and the traffic requirement met needed for aircraft.The gas compressor that this patent adopts, needs to carry out compatibility design to the air admission unit of Micro Turbine Jet Engine and jet nozzle, will consider that bleed can not bring large impact to the operation of motor simultaneously.This mode can make whole power system architecture compacter, and weight is lighter, more excellent performance.
Summary of the invention
Different from traditional electric drive or other power-actuated compressed air plant, this patent provides one can produce compressed-air actuated gas compressor sustainedly and stably, it carries out the element of construction of the Micro Turbine Jet Engine of overmatching design as one, pressurized air required for the jet-propelled Superlight rotor craft of wing tip can be provided, and meet the normal work of motor.Its requires as aircraft provides pressurized air compared with large discharge and elevated pressures, and can in the speed range of 50000 ~ 250000rpm stable operation.
For solving the problem, the technological scheme that this patent adopts is as follows:
Based on an air feeding type gas compressor in the level of Micro Turbine Jet Engine, to comprise in front cover, the special-shaped centrifugal impeller of diagonal flow type, level the structure such as Diffuser, Twin channel scroll casing type collector ring after Diffuser, level.Front cover is connected with engine inlets, and the special-shaped centrifugal impeller of diagonal flow type is then arranged on engine spindle; In level, Diffuser is connected with engine chamber casing front end, and after level, Diffuser is then supported in combustion box; Twin channel scroll casing type collector ring is centered around in level on Diffuser, is connected with Diffuser in level with front cover.
In level, air feeding type gas compressor is as the core cell of Micro Turbine Jet Engine, needs the needs considering bleed and engine work.Adopt the special-shaped centrifugal impeller of the diagonal flow type of enlargement discharge, arrange Diffuser and Twin channel scroll casing type collector ring in level at impeller medium position, pressurized air pressure, temperature, flow satisfied the demands is drawn.Surplus air continues by wheel compresses, enters engine chamber, ensure the continuous firing of motor by Diffuser after level.
In level, the design focal point of air feeding type gas compressor is the performance of Diffuser and Twin channel voluted type collector ring in the special-shaped impeller of diagonal flow type, level and structural design and matching relationship mutually.
Needed for aircraft, compressed-air actuated flow and pressure should determine the detailed design plan of gas compressor, and need to carry out compatibility design with other parts of Micro Turbine Jet Engine.
Under normal circumstances, receded disk impeller can reach the pressure ratio of 4.0, if be optimized design, pressure ratio can bring up to more than 6.0.The effect one adopting Diffuser in tiltedly/radial level is water conservancy diversion, two is improve air pressure further, three is aircraft bleed be separated with engine operation air, and needs to ensure that air-flow, before entering spiral case collector ring, large turnover does not occur, and reduces flow losses as far as possible.Dual-channel type spiral case collector ring and traditional single channel spiral case collector ring have a great difference, it have employed evolvent type runner design, object be comparatively uniform collection radially to surrounding flow out air, reduce pressure surge as far as possible, and obtain two strands of substantially identical air-flows of flow at symmetry direction.
Motor also needs to consider the intake duct of flow matches and the jet nozzle design for increasing turbine merit.The structure of gas compressor front cover also should adapt with intake duct simultaneously.
This patent based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, the pressurized air that pressure is 0.25 ~ 0.45 MPa, flow is 0.25 ~ 2.0 kilogram, temperature is 70 ~ 200 DEG C can be provided.
Accompanying drawing explanation
Fig. 1 is air feeding type gas compressor and the Micro Turbine Jet Engine assembly relation schematic diagram mated in the level of this patent.
Fig. 2 is air feeding type air compressor structure schematic diagram in the level of this patent.
Fig. 3 is the special-shaped centrifugal impeller of diagonal flow type that in the level of this patent, air feeding type gas compressor adopts.
Fig. 4 is Diffuser in the level that in the level of this patent, air feeding type gas compressor adopts.
Fig. 5 is Diffuser after the level that in the level of this patent, air feeding type gas compressor adopts.
Fig. 6 is the Twin channel scroll casing type collector ring that in the level of this patent, air feeding type gas compressor adopts.
Fig. 7 is the front cover that in the level of this patent, air feeding type gas compressor adopts.
In figure: 1. actuating motor, 2. actuating motor supporting frame, 3. clutch, 4. intake duct, air feeding type gas compressor unit 5. grade, 6. combustion box, 7. firing chamber, 8. main shaft, 9. nozzle ring, 10. turbine, 11. jet nozzles, 12. front covers, the special-shaped centrifugal impeller of 13. diagonal flow types, Diffuser in 14. grades, 15. Twin channel scroll casing type collector rings, Diffuser after 16. grades.
Embodiment
Below, by reference to the accompanying drawings and embodiment, this patent is described further, more clearly to understand this patent technical thought required for protection.
As shown in Figure 1, be air feeding type gas compressor in the level of this patent and the Micro Turbine Jet Engine assembly relation mated.Dotted line frame in figure shown in 5 is air feeding type gas compressor unit in level, and remaining part is Micro Turbine Jet Engine main structure and the cell cube of coupling.
Fig. 2 shows the main structure of air feeding type gas compressor in level.To comprise in front cover 12, the special-shaped centrifugal impeller 13 of diagonal flow type, level after Diffuser 14, Twin channel scroll casing type collector ring 15 and level the spare parts such as Diffuser 16.Front cover 12 is connected with engine inlets 4, and the special-shaped centrifugal impeller 13 of diagonal flow type is then arranged on engine spindle 8; In level, Diffuser 14 is connected with engine chamber casing 6 front end, and after level, Diffuser 16 is then supported in combustion box 6; Twin channel scroll casing type collector ring 15 is centered around in level on Diffuser 14, is connected with Diffuser in level 14 with front cover 16.
Fig. 3 ~ Fig. 7 then to respectively illustrate in the special-shaped centrifugal impeller of diagonal flow type, level structural type and the major character of the spare parts such as Diffuser, Twin channel scroll casing type collector ring and front cover after Diffuser, level.
Compatibility design about Micro Turbine Jet Engine is not described in detail in this patent.
In level, the working principle of air feeding type gas compressor is as follows: in level, air feeding type gas compressor is as the core cell of Micro Turbine Jet Engine, when motor reaches normal working, gas compressor is separated the pressurized air meeting flow and pressure needs and is drawn out to aircraft through Twin channel voluted type collector ring 15 to both sides by Diffuser in level 14, residual gas stream continues to be compressed, enter firing chamber 7 by Diffuser after level 16 and participate in burning, to maintain the normal work of micro turbine engine.
Above-mentioned mode of execution is only the preferred implementation of this patent; can not limit the protection domain of this patent with this, change and the replacement of any unsubstantiality that those skilled in the art does on the basis of this patent all belong to this patent scope required for protection.
Claims (7)
1. one kind based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: by a Micro Turbine Jet Engine through compatibility design, bleed structure is increased at its gas compressor position, the compression of gas compressor and air-entraining function are merged, is drawn the pressurized air met required for aircraft by centrifugal impeller intermediate portion.
2. as claimed in claim 1 based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: to comprise in front cover, the special-shaped centrifugal impeller of diagonal flow type, level the main structure such as Diffuser, Twin channel scroll casing type collector ring after Diffuser, level.
3. as claimed in claim 1 based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: front cover is connected with engine inlets, the special-shaped centrifugal impeller of diagonal flow type is then arranged on engine spindle; In level, Diffuser is connected with engine chamber casing front end, and after level, Diffuser is then supported in combustion box; Twin channel scroll casing type collector ring is centered around in level on Diffuser, is connected with Diffuser in level with front cover.
4. as claimed in claim 2 based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: adopt the special-shaped centrifugal impeller of the diagonal flow type of enlargement discharge, arrange Diffuser and Twin channel scroll casing type collector ring in level at impeller medium position, pressurized air pressure, temperature, flow satisfied the demands is drawn.Surplus air continues by wheel compresses, enters engine chamber, ensure the continuous firing of motor by Diffuser after level.
5. as claimed in claim 2 based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: the design focal point of gas compressor is the performance of Diffuser and Twin channel voluted type collector ring in the special-shaped impeller of diagonal flow type, level and structural design and matching relationship mutually.
6. as claimed in claim 2 based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: the intake duct, jet nozzle etc. of gas compressor needs and Micro Turbine Jet Engine carry out compatibility design.
7. as claimed in claim 1 based on air feeding type gas compressor in the level of Micro Turbine Jet Engine, it is characterized in that: the structure characteristic of Diffuser, involute Twin channel scroll casing type collector ring etc. after Diffuser, level in the special-shaped centrifugal impeller of diagonal flow type of employing, level.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510240985.XA CN104847695A (en) | 2015-05-13 | 2015-05-13 | Stage-middle air bleeding type air compressor based on micro-turbine jet engine |
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| CN201510240985.XA CN104847695A (en) | 2015-05-13 | 2015-05-13 | Stage-middle air bleeding type air compressor based on micro-turbine jet engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021217792A1 (en) * | 2020-04-30 | 2021-11-04 | 西安增材制造国家研究院有限公司 | Combustion assembly structure of turbojet engine |
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| CN203098039U (en) * | 2012-12-20 | 2013-07-31 | 无锡康明斯涡轮增压技术有限公司 | Two-stage turbocharger applicable to heavy-duty diesel engine |
| CN103438026A (en) * | 2013-09-09 | 2013-12-11 | 中国航空动力机械研究所 | Centrifugal air compressor with intermediate-stage air entrainment function |
| CN203743074U (en) * | 2013-12-30 | 2014-07-30 | 汉美综合科技（常州）有限公司 | Adjustable diffuser gas compressor |
| CN203756611U (en) * | 2014-04-14 | 2014-08-06 | 大连交通大学 | Diffuser pre-tightening structure suitable for pressurizer |
| CN103967649A (en) * | 2013-01-24 | 2014-08-06 | 李吉光 | Turbojet engine |
| CN104088702A (en) * | 2014-07-01 | 2014-10-08 | 北京航空航天大学 | Compact micro gas turbine |
| CN104343734A (en) * | 2014-09-05 | 2015-02-11 | 北京动力机械研究所 | Centrifugal compressor |
| CN204200674U (en) * | 2014-06-27 | 2015-03-11 | 哈尔滨工程大学 | The centrifugal-flow compressor casing bleed recirculation structure of variable geometry |
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
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2015
- 2015-05-13 CN CN201510240985.XA patent/CN104847695A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1889816A (en) * | 1930-10-30 | 1932-12-06 | White S Marine Engineering Com | Distributor |
| CN201025157Y (en) * | 2007-02-12 | 2008-02-20 | 深圳市康铖机械设备有限公司 | Micro turbine jet engine |
| CN203098039U (en) * | 2012-12-20 | 2013-07-31 | 无锡康明斯涡轮增压技术有限公司 | Two-stage turbocharger applicable to heavy-duty diesel engine |
| CN103967649A (en) * | 2013-01-24 | 2014-08-06 | 李吉光 | Turbojet engine |
| CN103438026A (en) * | 2013-09-09 | 2013-12-11 | 中国航空动力机械研究所 | Centrifugal air compressor with intermediate-stage air entrainment function |
| CN203743074U (en) * | 2013-12-30 | 2014-07-30 | 汉美综合科技（常州）有限公司 | Adjustable diffuser gas compressor |
| CN203756611U (en) * | 2014-04-14 | 2014-08-06 | 大连交通大学 | Diffuser pre-tightening structure suitable for pressurizer |
| CN204200674U (en) * | 2014-06-27 | 2015-03-11 | 哈尔滨工程大学 | The centrifugal-flow compressor casing bleed recirculation structure of variable geometry |
| CN104088702A (en) * | 2014-07-01 | 2014-10-08 | 北京航空航天大学 | Compact micro gas turbine |
| CN104343734A (en) * | 2014-09-05 | 2015-02-11 | 北京动力机械研究所 | Centrifugal compressor |
| CN104500268A (en) * | 2014-12-12 | 2015-04-08 | 常州环能涡轮动力股份有限公司 | Micro turbine jet engine with two-sided centrifugal pressure roller |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021217792A1 (en) * | 2020-04-30 | 2021-11-04 | 西安增材制造国家研究院有限公司 | Combustion assembly structure of turbojet engine |
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