CN108263622A - A kind of dopey active cooling device - Google Patents
A kind of dopey active cooling device Download PDFInfo
- Publication number
- CN108263622A CN108263622A CN201711445364.0A CN201711445364A CN108263622A CN 108263622 A CN108263622 A CN 108263622A CN 201711445364 A CN201711445364 A CN 201711445364A CN 108263622 A CN108263622 A CN 108263622A
- Authority
- CN
- China
- Prior art keywords
- mixing tube
- ejector pipe
- dopey
- cooling device
- active cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P1/00—Air cooling
- F01P1/02—Arrangements for cooling cylinders or cylinder heads, e.g. ducting cooling-air from its pressure source to cylinders or along cylinders
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P2050/00—Applications
- F01P2050/20—Aircraft engines
Abstract
A kind of dopey active cooling device, including mixing tube and ejector pipe, the mixing tube is the cylindrical structure with connecting pin and the port of export, there is contraction section at the port of export, the connecting pin is connect with the unit for needing to radiate, the ejector pipe is L-type bend pipe, and horizontal segment is coaxially arranged at the mixing tube in the mixing tube of contraction section upstream, and vertical segment passes through the side wall of the mixing tube to be connected with aircrafts exhaust nozzle.Injection type active cooling device in the present invention installs simple, flexible structure, can be mounted in the piston engine of various configuration, improve the cooling efficiency of heat dissipation wind channel, meet the cooling requirement under dopey difference operating mode.
Description
Technical field
The present invention relates to aviation aircraft dynamical system ring control fields, are particularly suitable for using piston engine as power
Dopey environmental control system, can effectively solve the problems, such as that dopey dynamical system cools down, the environment for improving dynamical system fits
Answering property and reliability.
Background technology
At present, in the design of the dynamical system in General Aviation and unmanned plane field, generally use piston engine driving spiral
Paddle generates thrust.The cooling of piston engine cylinder head is divided into air-cooled and water cooling two ways, and two kinds of types of cooling are to pass through the external world
What air-flow punching press carried out, but flying speed is relatively low for navigation aircraft and unmanned plane, the punching press effect of air-flow is difficult full
The radiating requirements of sufficient cylinder head or radiator.
In order to meet piston-engined cooling requirement, typically design is special in nacelle outlet or radiator outlet air duct
Cooling fan carries out active cooling, engine under different operating modes required heat dissipation capacity there is also certain difference,
Therefore pumping power is also required to be controlled according to throttle while being powered to fan.
Traditional cooling fan volume is big, weight weight, ventilatory capacity is small, power consumption is big.Conventional fan can be stranded mounting design simultaneously
Difficult, increase system complexity, and it is maintainable also poor.In order to simplify the complexity of dopey dynamical system, together
The cooling efficiency of Shi Tigao dynamical systems needs to select novel active cooling method.
Invention content
Present invention solves the technical problem that it is：In order to overcome the shortcomings of existing Active Cooling, meet dopey
Cooling requirement, provides a kind of active cooling method that can be used for dopey, which is simple in structure, it is flexible for installation, can
It is good by property height, maintainability, it can be adjusted flexibly according to the installation space of engine nacelle, can be applied to the low speed of different shapes
Aircraft.
The present invention technical solution be：A kind of dopey active cooling device, including mixing tube and ejector pipe, institute
Mixing tube is stated as the cylindrical structure with connecting pin and the port of export, there is contraction section at the port of export, the connecting pin with
The unit to radiate is needed to connect, the ejector pipe is L-type bend pipe, and horizontal segment is coaxially arranged at contraction section with the mixing tube
In the mixing tube gas collecting segment of upstream, vertical segment passes through the side wall of the mixing tube to be connected with engine exhaust nozzle.
It is preferred that the connecting pin of the mixing tube is connected by the connecting flange of group section with engine-cooling system outlet.
It is preferred that the ejector pipe selects lobe ejector pipe so that the ejector pipe port of export is lobe shape.
It is preferred that the discharge area of the ejector pipe is calculated according to piston-engined extraction flow, temperature and pressure
It arrives, and obtains quantity, height, width and the inside and outside lobe Angular Dimension of lobe accordingly.
It is preferred that the quantity and arrangement of the ejector pipe are according to engine nacelle space allocation.
It is preferred that the mixing tube in the ejector pipe downstream is determined according to engine nacelle and ejector pipe distribution situation.
It is preferred that the ejector pipe and the design conditions of mixing tube are the maximum rated operating mode of engine.
The advantages of the present invention over the prior art are that：
(1) active cooling device of the invention is simple in structure, easy for installation, reliability is high, maintainability is good；
(2) active cooling device of the invention is from the direct bleed of engine exhaust port, without increasing additional power supply and control,
Avoiding increases dynamical system complexity；
(3) active cooling device of the invention can be flexible for installation according to the space allocation installation site in nacelle；
(4) the bleed effect of active cooling device of the invention changes with engine operating condition and is changed, and realizes cooling and hair
The Auto-matching of motivation working condition avoids engine supercooling and the appearance of superheat state；
(5) active cooling device of the invention can be carried effectively by designing various forms of ejector pipes, outlet mixing tube
High cooling efficiency.
Description of the drawings
Fig. 1 is active cooling device assembling schematic diagram of the present invention.
(1), (2), (3) of Fig. 2 are the structure diagrams of ejector pipe.
(1), (2) of Fig. 3 are mixing tube and ejector pipe assembling schematic diagram.
Symbol description
3. ejector pipe of radiator 1. (engine cylinder head) 2. exhaust pipe of engine of airintake wind-tunnel, 4. mixing tube.
DiInjection pipe diameter h lobe height w lobe widths θoOuter angle of flare θiIntramedullary expansion angle.
L1Mixing tube shrinks segment length, L2Mixing tube is straight segment length Dm1Mixing tube gas collecting segment diameter Dm2Mixed tube diameter
SiEjector pipe discharge area SmMixer outlet area
Specific embodiment
As shown in Figs. 1-3, dopey active cooling device of the present invention includes mixing tube 4 and ejector pipe 3, and mixing tube 4 is logical
The mounting flange for crossing group section is connect with the outlet of engine radiating unit 1, and ejector pipe 3 and the nozzle of the exhaust pipe of engine 2 connect
It connects.
Since the mixing distance of traditional ejector pipe, wall friction are lost the shortcomings of big, construction weight is heavy, shown in the present invention
Ejector pipe is lobe ejector pipe, and this structure can increase the contact area of two strands of air-flows, suitable for making for low-pressure injection system
With draught jet capacity ratio can be significantly improved at identical conditions.
According to delivery temperature, pressure and flow during engine maximum throttle state, the installation site in nacelle is considered, determine
Ejector pipe quantity to be mounted is needed, and determines the diameter D of ejector pipei；According to the design side of conventional lobe injection tube structure size
Method calculates the lobe height h, lobe width w, outer angle of flare θ of ejector pipeo, intramedullary expansion angle θi；Rule of thumb design mixing tube
Length L1And L2, mixed tube diameter Dm1And Dm2；It finally needs to determine final ejector pipe and mixing tube structure ruler by testing
It is very little.The installation of active cooling device is firstly the need of designing ejector pipe and mixing tube；It is short that active cooling device is mounted on engine
Cabin exports；Engine exhaust port is designed to ejector pipe inlet ductwork, the design of pipeline will reduce the pressure loss as possible；It will exhaust
Mouth and ejector pipe import are installed together.
The Design Rule of the present invention is as follows：
According to piston-engined extraction flow, temperature and pressure, the discharge area of ejector pipe is calculated；According to engine
Spatial position in nacelle selects the quantity and arrangement of ejector pipe, and is designed and drawn according to conventional ejector pipe computational methods
Penetrate the structure size of pipe；Suitable mixing tube is designed at ejector pipe rear.
It can be according to different nacelle spaces and motor mechanism according to the injection type active cooling device that above-mentioned rule designs
Type is flexibly installed, and the variation of draught jet capacity can meet engine different operating according to different engine throttle adjust automaticallies
Cooling requirement under state.
According to engine characteristics, delivery temperature, pressure and flow are different under different throttles, therefore draught jet capacity ratio
It is also different.The cooling requirement of usual dopey is maximum in take-off climb section, and engine is in full load condition at this time,
And the relatively low radiating condition of flying speed of aircraft is the most severe；But exhaust exit temperature and pressure in Engine full load
Highest, therefore to needing that maximum throttle operating mode is selected to ensure injection at this time as design point when ejector pipe and mixing tube design
The draught jet capacity ratio of pipe be it is highest, it is also most apparent to the gain effect of cooling system.And start under engine other operating modes
Machine extraction flow and pressure are relatively low, and radiating requirements are also relatively small, therefore use injection type Active Cooling System, according to engine
Different working conditions can voluntarily adjust draught jet capacity ratio, change the cooling effect of engine under different conditions.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (7)
1. a kind of dopey active cooling device, it is characterised in that：Including mixing tube and ejector pipe, the mixing tube be with
Connecting pin and the cylindrical structure of the port of export have contraction section, the connecting pin and the unit for needing to radiate at the port of export
Connection, the ejector pipe are L-type bend pipe, and horizontal segment is coaxially arranged at the mixing tube collection of contraction section upstream with the mixing tube
In gas section, vertical segment passes through the side wall of the mixing tube to be connected with engine exhaust nozzle.
2. a kind of dopey active cooling device according to claim 1, it is characterised in that：The company of the mixing tube
End is connect to connect with engine-cooling system outlet by the connecting flange of group section.
3. a kind of dopey active cooling device according to claim 2, it is characterised in that：The ejector pipe is selected
Lobe ejector pipe so that the ejector pipe port of export is lobe shape.
4. a kind of dopey active cooling device according to claim 3, it is characterised in that：The ejector pipe goes out
Open area is calculated according to piston-engined extraction flow, temperature and pressure, and obtain accordingly the quantity of lobe, height,
Width and inside and outside lobe Angular Dimension.
5. a kind of dopey active cooling device according to claim 1, it is characterised in that：The number of the ejector pipe
Amount and arrangement are according to engine nacelle space allocation.
6. a kind of dopey active cooling device according to claim 1, it is characterised in that：The ejector pipe downstream
Mixing tube determined according to engine nacelle and ejector pipe distribution situation.
7. a kind of dopey active cooling device according to claim 1, it is characterised in that：The ejector pipe and mixed
The design conditions for closing pipe are the maximum rated operating mode of engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711445364.0A CN108263622A (en) | 2017-12-27 | 2017-12-27 | A kind of dopey active cooling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711445364.0A CN108263622A (en) | 2017-12-27 | 2017-12-27 | A kind of dopey active cooling device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108263622A true CN108263622A (en) | 2018-07-10 |
Family
ID=62772805
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711445364.0A Pending CN108263622A (en) | 2017-12-27 | 2017-12-27 | A kind of dopey active cooling device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108263622A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2042893U (en) * | 1989-01-24 | 1989-08-16 | 北京理工大学 | Resonant air-intake and exhaust-injection system |
| CN102673793A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Exhaust ejector system of airplane auxiliary power unit |
| CN104648674A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Low-resistance fan-aided ejecting air feeding device |
| CN205381408U (en) * | 2016-02-18 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Ejector device |
| CN107416214A (en) * | 2017-06-29 | 2017-12-01 | 南京航空航天大学 | A kind of perflation ventilation structure for aircraft secondary power systems |
-
2017
- 2017-12-27 CN CN201711445364.0A patent/CN108263622A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2042893U (en) * | 1989-01-24 | 1989-08-16 | 北京理工大学 | Resonant air-intake and exhaust-injection system |
| CN102673793A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Exhaust ejector system of airplane auxiliary power unit |
| CN104648674A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Low-resistance fan-aided ejecting air feeding device |
| CN205381408U (en) * | 2016-02-18 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Ejector device |
| CN107416214A (en) * | 2017-06-29 | 2017-12-01 | 南京航空航天大学 | A kind of perflation ventilation structure for aircraft secondary power systems |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20180710 |