CN105927559A - Micro-miniature split turbojet driven compressor - Google Patents
Micro-miniature split turbojet driven compressor Download PDFInfo
- Publication number
- CN105927559A CN105927559A CN201510192073.XA CN201510192073A CN105927559A CN 105927559 A CN105927559 A CN 105927559A CN 201510192073 A CN201510192073 A CN 201510192073A CN 105927559 A CN105927559 A CN 105927559A
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- Prior art keywords
- compressor
- engine
- turbojet
- rear end
- micro
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a micro-miniature split turbojet driven compressor, belongs to an aircraft power plant, and can be used as a compressed air source of a power system of an ultra-light wingtip jet rotor craft. The main structure of the micro-miniature split turbojet driven compressor includes a front nut, an air inlet, a front end cover, a centrifugal impeller, a radial diffuser, a dual channel volute collector, a rear end cover, a compressor shaft, a shaft sleeve, a bearing and the like. The micro-miniature split turbojet driven compressor is connected with a modified micro turbojet engine through a coupling and driven by the turbojet engine to continuously obtain required compressed air. The core of the invention lies in that the compressor can be designed independently, an air flow channel of the compressor which supplies air to an aircraft is independent of an air flow channel of the turbojet engine, so that the operation of the engine is less subjected to interference, and the influence on the working stability of the engine is greatly reduced; and meanwhile, the adaptive modification of the engine body is also relatively simple, and the safety and reliability are therefore improved. In addition, an engine unit and a compressor unit can be replaced individually, and the repair and maintenance are substantially facilitated.
Description
Technical field
The present invention relates to a kind of microminiature aircraft power plant, can be as the dynamical system of microlight-type wing tip rotorjet aircraft
Compressed gas source.It is exactly the compressor driving this patent to describe by the Micro Turbine Jet Engine of a repacking, by compressor
Compressed air needed for aircraft rotor is provided, thus promotes rotor wing rotation.Owing to compressor is relative with turbojet engine unit only
Vertical, only it is connected with each other by shaft coupling, therefore the most split type whirlpool spray driving pressure mechanism of qi.
Background technology
It is limited to the Superlight rotor craft rigors for weight, uses wing tip jet to drive the mode of rotor wing rotation to be closed
Note.The counteracting force produced in the ejection of rotor wing tip due to compressed air to be utilized promotes rotor wing rotation, and this is necessary for considering one
Plant air compression plant, it is possible to provide required compressed air sustainedly and stably.Based on this requirement, this patent devises one
The compressor driven by the Micro Turbine Jet Engine reequiped, this compressor can provide meet pressure needed for aircraft, temperature and
The compressed air of traffic requirement.The split-type structural mode that this patent uses, can do less changing in Micro Turbine Jet Engine
Dynamic, increase a compressor unit, demand can be met.This frame mode is owing to aircraft gas is from the air-flow of compressor
Passage is separate with turbojet engine gas channel, and makes the operation of electromotor be less subject to interference, thus improves safety
And reliability.In addition engine unit can be individually replaced with compressor unit, greatly facilitates repairing and working service.
Summary of the invention
Different from traditional electric drive or other power-actuated compressor, this patent provides one can produce compression sustainedly and stably
The microminiature compressor of air, it, can be as the jet-propelled microlight-type of wing tip by a Micro Turbine Jet Engine driving through repacking
The compressed gas source of rotor craft.It requires to provide larger flow and compressed air of elevated pressures, and can be
Steady operation in the range of speeds of 50000～250000rpm.
This patent uses the mode that aircraft gas and turbojet engine gas are separated from each other, and proposes the air compressor structure of a kind of uniqueness,
And by repacking turbojet engine main shaft and nozzle, individually designed shaft coupling electromotor is connected with compressor.
For solving the problems referred to above, the technical scheme that this patent is used is as follows:
A kind of microminiature compressor, main member include front nut, air intake duct, drive end bearing bracket, receded disk impeller, radial diffuser,
Dual-channel type spiral case catcher, rear end cap, compressorshaft, axle sleeve, bearing etc..Compressorshaft by bearings in axle sleeve,
Axle sleeve is installed limit and is connected with radial diffuser.Receded disk impeller is arranged on compressorshaft, and rear end leans against in bearing on steel bushing, front
Duan Ze is compressed by front nut.Radial diffuser links together with the rear installation limit of Dual-channel type spiral case catcher, spiral case catcher
Front installation limit be then connected with the big limit of installing of drive end bearing bracket.Air intake duct rear end is then connected with the little installation limit of drive end bearing bracket.Before rear end cap
Installing limit to be connected with radial diffuser, rear end is then supported on shaft coupling.Above structure constitutes the main body of compressor.
For adapting to high speed rotating and bearing the requirement of certain axial force, compressor bearing uses ceramic ball bearing.
Dual-channel type spiral case catcher can obtain the essentially identical two strands of air-flows of flow in both sides.
For increasing the axle output work of turbojet engine, the nozzle of electromotor is carried out repacking design, has increased turbine blow down ratio.
Simultaneously in order to be connected with compressor by shaft coupling, engine spindle is done repacking design.
In view of the starting problem of turbojet engine, also need a starting motor of connecting in compressor front end, and solid by a support
It is scheduled on compressor.
During work, being rotated together with turbojet engine by starting driven by motor compressor, when reaching certain rotating speed, electromotor is just entering
Often duty, starts motor and disengages with compressor.The energy that electromotor produces is mainly used in driving pressure mechanism of qi and produces compressed air.
The microminiature split type whirlpool spray driving pressure mechanism of qi of this patent, it is provided that pressure is 0.25～0.45 MPa, flow is
0.25～2.0 kilogram, temperature be the compressed air of 70～200 DEG C.
Accompanying drawing explanation
Fig. 1 is that the microminiature split type whirlpool spray driving pressure mechanism of qi of this patent shows with Micro Turbine Jet Engine and starting motor connected mode
It is intended to.
Fig. 2 is the sectional view of the microminiature split type whirlpool spray driving pressure mechanism of qi of this patent.
Fig. 3 is the front isometric sectional view of the microminiature split type whirlpool spray driving pressure mechanism of qi of this patent.
Fig. 4 is the rear isometric sectional view of the microminiature split type whirlpool spray driving pressure mechanism of qi of this patent.
Fig. 5 is centrifugal impeller and the radial diffuser shaft side figure of the microminiature split type whirlpool spray driving pressure mechanism of qi of this patent.
Fig. 6 is the Dual-channel type spiral case catcher shaft side figure of the microminiature split type whirlpool spray driving pressure mechanism of qi of this patent.
In figure: 1. start motor, 2. start electric machine support, 3. compressor, 4. Micro Turbine Jet Engine, 5. front nut, 6. from
Lobus cardiacus is taken turns, 7. axle sleeve, 8. compressorshaft, 9. shaft coupling, 10. rear end cap, 11. Dual-channel type spiral case catchers, 12. front ends
Lid, 13. radial diffusers, 14. air intake ducts, 15. bearings.
Detailed description of the invention
Below, in conjunction with accompanying drawing and detailed description of the invention, this patent is described further, in order to be more clearly understood that the present invention
Technical thought required for protection.
As it is shown in figure 1, be microminiature split type whirlpool spray driving pressure mechanism of qi and Micro Turbine Jet Engine and the starting motor of this patent
Connection diagram.Start motor 1, compressor 3 and electromotor 4 and use the mode of series connection, start motor and fixed by support 2
On compressor.
Fig. 2 is the main schematic diagram of structure that this patent describes compressor, compressor main member include front nut 5, air intake duct 14,
Drive end bearing bracket 12, receded disk impeller 6, radial diffuser 13, Dual-channel type spiral case catcher 11, rear end cap 10, compressorshaft 8,
Axle sleeve 7, bearing 15, shaft coupling 9 etc..Compressorshaft is by bearings in axle sleeve, and axle sleeve installs limit and radial diffuser
It is connected.Receded disk impeller is arranged on compressorshaft, and rear end leans against in bearing on steel bushing, and leading portion is then compressed by front nut.Radially
Diffuser links together with the rear installation limit of Dual-channel type spiral case catcher, the front installation limit of spiral case catcher then with drive end bearing bracket
Big limit of installing is connected.Air intake duct rear end is then connected with the little installation limit of drive end bearing bracket.Limit is installed before rear end cap be connected with radial diffuser,
Rear end is then supported on axle sleeve.
The detailed design plan of compressor should be determined and it needs to use according to flow compressed-air actuated needed for aircraft and pressure
Micro Turbine Jet Engine carry out matched design.
Under normal circumstances, receded disk impeller can reach the pressure ratio of 4.0, and if carried out optimizing design, pressure ratio can bring up to
More than 6.0.The effect one using radial diffuser is water conservancy diversion, and two is can to improve air pressure further, and air-flow is entering
There is not big turnover before entering spiral case catcher, reduce flow losses as far as possible.Dual-channel type spiral case catcher and traditional list
Passage spiral case catcher is very different, and it have employed evolvent type runner design, it is therefore an objective to more uniform collection is radially to four
The air that week flows out, reduces pressure oscillation as far as possible, and obtains, at symmetry direction, two strands of air-flows that flow is essentially identical.
In order to mate with compressor, need Micro Turbine Jet Engine carries out less amount of repacking design.Common miniature whirlpool
The Main Function of fuel-injection engine is to provide the thrust that jet-impingement produces, and improves turbine blow down ratio by repacking design nozzle,
And do not affect the unimpeded of engine air flow, as far as possible the energy that electromotor produces is converted into axle output energy.In addition in order to
Compressor connects, and has redesigned engine spindle.Repacking design about Micro Turbine Jet Engine is retouched the most in detail
State.
The operation principle of microminiature split type whirlpool spray driving pressure mechanism of qi is as follows: first by starting driven by motor compressor and the spray of miniature whirlpool
Electromotor rotates together, and when reaching certain rotating speed, electromotor enters normal operating conditions, starts motor and disengages with compressor,
Compressor is driven by engine shaft, operates with engine synchronization.When centrifugal impeller rotates, suck front air and be compressed, pressure
Contracting air is discharged via radial diffuser and Dual-channel type spiral case catcher.
Above-mentioned embodiment is only the preferred embodiment of the present invention, it is impossible to limit protection scope of the present invention, this area with this
The change of any unsubstantiality made on the basis of the present invention of technical staff and replacement to belong to the present invention required for protection
Scope.
Claims (4)
1. microminiature split type whirlpool spray driving pressure mechanism of qi, it is characterised in that: main member includes front nut, air intake duct, front
End cap, receded disk impeller, radial diffuser, Dual-channel type spiral case catcher, rear end cap, compressorshaft, axle sleeve, bearing etc..
2. spray driving pressure mechanism of qi in microminiature split type whirlpool as claimed in claim 1, it is characterised in that: compressorshaft passes through bearing
Being supported in axle sleeve, axle sleeve is installed limit and is connected with radial diffuser.Receded disk impeller is arranged on compressorshaft, and rear end leans against axle
Holding on interior steel bushing, leading portion is then compressed by front nut.Radial diffuser is connected to one with the rear installation limit of Dual-channel type spiral case catcher
Rising, the front installation limit of spiral case catcher is then connected with the big limit of installing of drive end bearing bracket.Air intake duct rear end then with the little installation limit of drive end bearing bracket
It is connected.Installing limit before rear end cap to be connected with radial diffuser, rear end is then supported on shaft coupling.
3. spray driving pressure mechanism of qi in microminiature split type whirlpool as claimed in claim 1, it is characterised in that: compressor independently sets
Meter, the gas channel of compressor is separate with turbojet engine gas channel.
4. spray driving pressure mechanism of qi in microminiature split type whirlpool as claimed in claim 1, it is characterised in that: the custom-designed dual pathways
Formula spiral case catcher can obtain the essentially identical two strands of air-flows of flow in both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510192073.XA CN105927559A (en) | 2015-04-22 | 2015-04-22 | Micro-miniature split turbojet driven compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510192073.XA CN105927559A (en) | 2015-04-22 | 2015-04-22 | Micro-miniature split turbojet driven compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105927559A true CN105927559A (en) | 2016-09-07 |
Family
ID=56839907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510192073.XA Pending CN105927559A (en) | 2015-04-22 | 2015-04-22 | Micro-miniature split turbojet driven compressor |
Country Status (1)
| Country | Link |
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| CN (1) | CN105927559A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109595078A (en) * | 2018-12-27 | 2019-04-09 | 中国人民解放军总参谋部第六十研究所 | A kind of water injection structure for turbojet engine |
| CN109944871A (en) * | 2019-01-30 | 2019-06-28 | 西安交通大学 | A kind of hydrodynamic radial bearing and centrifugal pump |
| CN116221150A (en) * | 2023-04-12 | 2023-06-06 | 西安嘉盛智造科技有限公司 | A centrifugal compressor for bleed air |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1116280A (en) * | 1994-03-18 | 1996-02-07 | 株式会社日立制作所 | centrifugal compressor |
| CN1864042A (en) * | 2003-11-06 | 2006-11-15 | 埃克森美孚上游研究公司 | Method for efficient nonsynchronous lng production |
| CN201461531U (en) * | 2009-07-03 | 2010-05-12 | 黄敏 | Mixed flow type compressor impeller of turbocharger |
| US20110138816A1 (en) * | 2008-11-12 | 2011-06-16 | Kazuhiro Takeda | Driving device and an operation method of a 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 |
-
2015
- 2015-04-22 CN CN201510192073.XA patent/CN105927559A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1116280A (en) * | 1994-03-18 | 1996-02-07 | 株式会社日立制作所 | centrifugal compressor |
| CN1864042A (en) * | 2003-11-06 | 2006-11-15 | 埃克森美孚上游研究公司 | Method for efficient nonsynchronous lng production |
| US20110138816A1 (en) * | 2008-11-12 | 2011-06-16 | Kazuhiro Takeda | Driving device and an operation method of a compressor |
| CN201461531U (en) * | 2009-07-03 | 2010-05-12 | 黄敏 | Mixed flow type compressor impeller of turbocharger |
| 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 (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109595078A (en) * | 2018-12-27 | 2019-04-09 | 中国人民解放军总参谋部第六十研究所 | A kind of water injection structure for turbojet engine |
| CN109944871A (en) * | 2019-01-30 | 2019-06-28 | 西安交通大学 | A kind of hydrodynamic radial bearing and centrifugal pump |
| CN109944871B (en) * | 2019-01-30 | 2020-06-23 | 西安交通大学 | Hydraulic dynamic pressure radial bearing and centrifugal pump |
| CN116221150A (en) * | 2023-04-12 | 2023-06-06 | 西安嘉盛智造科技有限公司 | A centrifugal compressor for bleed air |
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| DD01 | Delivery of document by public notice |
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| DD01 | Delivery of document by public notice |
Addressee: Zhang Xinyu Document name: Notification that Application Deemed to be Withdrawn |
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| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160907 |
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| WD01 | Invention patent application deemed withdrawn after publication |