CN108716434A - A kind of Automatic-boosting structure of aviation piston - Google Patents
A kind of Automatic-boosting structure of aviation piston Download PDFInfo
- Publication number
- CN108716434A CN108716434A CN201810502157.2A CN201810502157A CN108716434A CN 108716434 A CN108716434 A CN 108716434A CN 201810502157 A CN201810502157 A CN 201810502157A CN 108716434 A CN108716434 A CN 108716434A
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- China
- Prior art keywords
- fan
- propeller
- automatic
- engine
- engine shaft
- 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
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- 241000566913 Thelephora terrestris Species 0.000 claims description 2
- 230000008602 contraction Effects 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 5
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B33/00—Engines characterised by provision of pumps for charging or scavenging
- F02B33/32—Engines with pumps other than of reciprocating-piston type
- F02B33/34—Engines with pumps other than of reciprocating-piston type with rotary pumps
- F02B33/40—Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/028—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for piston engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of Automatic-boosting structure of aviation piston, including engine, pressure pipeline, duct wheel hub and the propeller being arranged on engine shaft, the fan with propeller coaxial is provided on the engine shaft；The present invention is by installing the components such as propeller fan and pressure pipeline additional, form the Automatic-boosting ability of aviation piston power, it realizes based on high and mediums flight performances such as the piston-engined unmanned planes of small-power, improve the high and medium flight time, the modes such as existing turbocharging are replaced, booster body complexity is reduced, improve engine maintenance and applicability, mitigate booster body construction weight, improves aircraft payload and cruise duration.
Description
Technical field
The present invention relates to engine arts, particularly with regard to aviation aircraft dynamical system for increasing to engine
The structure of pressure.
Background technology
The features such as aviation piston engine is low with oil consumption rate, light-weight, power bracket is wide, be widely used in it is middle-size and small-size nobody
The aviation aircrafts such as machine, trainer aircraft.For the aircraft such as high and medium unmanned plane, high and medium rarefaction of air, atmospheric density
Decline so that engine is from fully burning, engine output declines notable.Therefore, existing piston engine needs to install additional
The supercharging devices such as turbocharging could maintain high and medium engine performance.This conventional piston engine super charge mode is not
Foot place is：
It is not suitable for small-power piston engine.Due to needing engine exhaust driving turbine rotation, and then drive booster work
Make, therefore the requirement of engine exhaust amount is larger, small-power piston engine capacity is smaller, it is difficult to drive turbocharger；
Mechanism is complicated.Turbine needs to collect exhaust energy to drive booster to compress air, and turbine and booster have
Multiple blades and pipeline, and the two need to be by being driven axis connection, component is more, complicated；
Construction weight is big.Component of turbo-charger is more, and it is special to be operated in the environment such as high temperature and pressure, to materials such as blade and pipelines
Expect more demanding, weight is larger.
Invention content
The purpose of the present invention is on the basis of existing technology, proposing a kind of propeller fan Automatic-boosting mode, it is pressurized
Device is mainly made of propeller fan and pressure pipeline, provides flying power by propeller, fan and pressure pipeline are to start
Machine air inlet provides supercharging, above-mentioned to solve the problems, such as.
To achieve the goals above, the present invention adopts the following technical scheme that：
A kind of Automatic-boosting structure of aviation piston, including engine, pressure pipeline, duct wheel hub and setting are in engine shaft
On propeller, the fan with propeller coaxial is provided on the engine shaft.
In the above-mentioned technical solutions, the fan can be on same diametric plane with propeller, can not also be in same diametric plane
On.
In the above-mentioned technical solutions, for the fan with propeller when on same diametric plane, fan is integrated knot with propeller
Structure.
In the above-mentioned technical solutions, in the integral structure, it is arranged on the paddle face for the propeller being connect with engine shaft
There are several fans.
In the above-mentioned technical solutions, the fan and propeller be when on same diametric plane, fan and engine shaft it
Between or to be fixedly connected, or to be slidably connected by connector.
In the above-mentioned technical solutions, the connector is the gear being fixed on engine shaft, and fan passes through slide teeth
Wheel is connect with engine shaft, is differed by the rotating speed of balladeur train fan and propeller.
In the above-mentioned technical solutions, fan is multistage fan, is connect with engine shaft per level-one fan, the multistage
Fan is arranged between propeller and engine shaft, and propeller is fixed on by fixed frame on engine shaft.
In the above-mentioned technical solutions, connected using activity per between level-one fan and engine shaft in the multistage fan
It connects, adjacent the two poles of the earth fan turns to different.
In the above-mentioned technical solutions, described to be turned by differential gear connection realization per between level-one fan and engine shaft
It is fast different.
In the above-mentioned technical solutions, duct wheel hub, engine are fixedly connected with pressure pipeline, are not revolved with engine shaft
Turn, in aircraft flight, air-flow flows to fan by duct wheel hub, and fan rotation does work to air-flow, and air-flow is accelerated to flow into increasing
Pressure pipeline, by the contraction of pressure pipeline, stream pressure increases and enters engine intake.
Compared with existing booster body, innovative point is embodied in this programme：
Drive the supercharging mode of turbine rotation different by engine exhaust from tradition, the present invention is rotated certainly using propeller fan
The mode of dynamic supercharging, is not only suitable for the relatively high power piston engine of medium-sized unmanned plane etc., is also applied for small drone etc.
Small-power piston engine, and conventional turbine supercharging is only applicable to piston-engined medium-sized unmanned plane of relatively high power etc.；
Different from using turbo charged piston engine, original propeller need to only be changed into propeller fan by the present invention, and be added
Piston-engined function of increasing pressure can be realized in dress pressure pipeline etc., and mechanism is simple, and complexity is low, convenient for safeguarding and reequiping；
Different from using turbo charged piston engine, the present invention increased component in piston engine is few, and mechanism letter
It is single, the working environment of high temperature and pressure, lightweight construction is not present.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
By installing the components such as propeller fan and pressure pipeline additional, the Automatic-boosting ability of aviation piston power is formed, realizes base
In high and mediums flight performances such as the piston-engined unmanned planes of small-power, the high and medium flight time is improved；
By installing the components such as propeller fan and pressure pipeline additional, the Automatic-boosting ability of aviation piston power is formed, is replaced existing
There are the modes such as turbocharging, reduce booster body complexity, improves engine maintenance and applicability；
By installing the components such as propeller fan and pressure pipeline additional, the Automatic-boosting ability of aviation piston power is formed, is replaced existing
There are the modes such as turbocharging, mitigate booster body construction weight, improves aircraft payload and cruise duration；
The propeller fan Automatic-boosting mode mechanism of aviation piston power is simple, lightweight construction, convenient for combining aircraft to carry out
Integrated design improves full machine comprehensive performance.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is the principle schematic diagram of the present invention；
Fig. 2 is the structural schematic diagram that propeller fan is placed on engine；
Fig. 3 is the structural schematic diagram of multistage fan supercharging；
Fig. 4 is the structural schematic diagram of centrifugal supercharging；
Wherein：1 is propeller；2 be pressure pipeline；3 be engine；4 be fan；5 be duct wheel hub；6 be centrifugal blades；7
It is air inlet.
Specific implementation mode
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
As shown in Fig. 1, the booster body in this programme is contained mainly by being mainly made of propeller fan and pressure pipeline
Road wheel hub, engine are fixedly connected with pressure pipeline, and engine is main power source, at work duct wheel hub and pressure pipeline
It is that the output revolving shaft with engine does not rotate.And propeller and fan are provided in the shaft of output, propeller and fan
The rotation of coaxial arrangement, propeller is mainly that aircraft provides flying power, and incoming air is mainly compressed to increasing by fan
In pressure pipe, the Automatic-boosting function to air-flow is realized.
In implementation process, fan can be arranged on same diametric plane with propeller, can also be arranged as supercharging device
On different diametric planes, but it is exactly fan and propeller must be on the coaxially connected output revolving shaft to engine to have a bit.Work as wind
Fan when on same diametric plane, may be used fan and be wholely set with propeller, that is, propeller and shaft are connect with propeller
The blade of several fans is provided on tactile paddle face, when propeller is during rotation, fan blade follows propeller one
Rotation is played, to realize the function of increasing pressure to air-flow.When fan and propeller are on same diametric plane, rotating speed and steering are all
It is consistent.
But propeller can also be on different diametric planes from fan, that is to say, that along engine output revolving shaft
Direction, fan can be arranged in the left side or right side of propeller, and the connection between fan and shaft, which may be used, to be fixedly connected
Or flexible connection can also be used.It is fixedly connected and exactly fan blade is fixed in shaft, and be flexibly connected and then pass through
Differential gear is connected in shaft.The rotating speed of fan and steering are consistent with propeller if being fixedly connected, and are flexibly connected
If the rotating speed of fan and propeller then differ, and it is also inconsistent according to the steering that the installation direction of gear both makes.
Schematic diagram in Fig. 1 is the preposition situation of propeller fan, but is needed in many cases, by propeller and wind
Fan carries out postposition, as shown in Fig. 2, realizing supercharging by changing intake method.
Structure in Fig. 1 and Fig. 2 applies in general to the aircraft of small drone etc, uses single stage fan and is increased
Pressure.And Fig. 3 is a kind of expanded application of this programme, is suitable for large-scale aircraft, therefore in order to increase compression efficiency use it is more
The fan of grade.Because using multistage fan, thus the rotating speed of adjacent fans and steering be cannot be identical, and to realize this
One purpose, existing gear structure, which may be used, to be realized easily；Because multistage fan is different from single stage fan, therefore will
Propeller be by a fixed frame be mounted on engine shaft on, and fan then be mounted on fixed frame in so that fan and
Propeller is on same diametric plane as possible, or fan is made to be symmetricly set on the both sides of propeller.
Fig. 4 is the structure of centrifugal fan supercharging, is suitable for low-speed operations device, and above-mentioned is all tube-axial fan supercharging
Suitable for the aircraft of high-speed flight, supercharging principle is consistent.
The invention is not limited in specific implementation modes above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (10)
1. a kind of Automatic-boosting structure of aviation piston, including engine, pressure pipeline, duct wheel hub and setting turn in engine
Propeller on axis, it is characterised in that the fan with propeller coaxial is provided on the engine shaft.
2. a kind of Automatic-boosting structure of aviation piston according to claim 1, it is characterised in that the fan and spiral
Paddle can be on same diametric plane, can not also be on same diametric plane.
3. a kind of Automatic-boosting structure of aviation piston according to claim 2, it is characterised in that the fan and spiral
When on same diametric plane, fan is structure as a whole paddle with propeller.
4. a kind of Automatic-boosting structure of aviation piston according to claim 3, it is characterised in that in the integral structure,
It is provided with several fans on the paddle face for the propeller being connect with engine shaft.
5. a kind of Automatic-boosting structure of aviation piston according to claim 2, it is characterised in that the fan and spiral
Paddle is not when on same diametric plane, between fan and engine shaft or to be fixedly connected, or to be slidably connected by connector.
6. a kind of Automatic-boosting structure of aviation piston according to claim 5, it is characterised in that the connector is solid
The gear being scheduled on engine shaft, fan are connect by balladeur train with engine shaft, and balladeur train fan and spiral shell are passed through
The rotating speed of rotation paddle differs.
7. a kind of Automatic-boosting structure of aviation piston according to claim 1, it is characterised in that fan is multistage fan,
It is connect with engine shaft per level-one fan, the multistage fan is arranged between propeller and engine shaft, propeller
It is fixed on engine shaft by fixed frame.
8. a kind of Automatic-boosting structure of aviation piston according to claim 1, it is characterised in that in the multistage fan
Per, using being flexibly connected, adjacent the two poles of the earth fan turns to different between level-one fan and engine shaft.
9. a kind of Automatic-boosting structure of aviation piston according to claim 8, it is characterised in that described per level-one fan
It is connected by differential gear between engine shaft and realizes that rotating speed is different.
10. according to a kind of Automatic-boosting structure of any aviation pistons of claim 1-9, it is characterised in that duct wheel
Hub, engine are fixedly connected with pressure pipeline, are not rotated with engine shaft, and in aircraft flight, air-flow passes through duct wheel
Hub flows to fan, and fan rotation does work to air-flow, accelerates air-flow to flow into pressure pipeline, pass through the contraction of pressure pipeline, air-flow pressure
Power increases and enters engine intake.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810502157.2A CN108716434A (en) | 2018-05-23 | 2018-05-23 | A kind of Automatic-boosting structure of aviation piston |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810502157.2A CN108716434A (en) | 2018-05-23 | 2018-05-23 | A kind of Automatic-boosting structure of aviation piston |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108716434A true CN108716434A (en) | 2018-10-30 |
Family
ID=63900354
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810502157.2A Pending CN108716434A (en) | 2018-05-23 | 2018-05-23 | A kind of Automatic-boosting structure of aviation piston |
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| Country | Link |
|---|---|
| CN (1) | CN108716434A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117141756A (en) * | 2023-11-01 | 2023-12-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Small-size many ducts unmanned aerial vehicle of quick deployment |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6209311B1 (en) * | 1998-04-13 | 2001-04-03 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
| US20140223884A1 (en) * | 2009-09-09 | 2014-08-14 | The Boeing Company | Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan |
| US20160245161A1 (en) * | 2015-02-20 | 2016-08-25 | Pratt & Whitney Canada Corp. | Compound engine assembly with modulated flow |
| CN205770144U (en) * | 2016-05-27 | 2016-12-07 | 中国科学院光电研究院 | A kind of dynamical system of rotor craft |
| CN107010230A (en) * | 2015-10-26 | 2017-08-04 | 通用电气公司 | For the method and system avoided across engine debris |
| CN107161349A (en) * | 2016-03-07 | 2017-09-15 | 通用电气公司 | Propulsion system for aircraft |
| CN206645025U (en) * | 2017-03-01 | 2017-11-17 | 广东合即得能源科技有限公司 | A kind of jet-propelled unmanned aerial vehicle of single rotor |
| CN107816384A (en) * | 2017-10-11 | 2018-03-20 | 中国航发南方工业有限公司 | Aviation hybrid power system and its unmanned plane based on radial-piston motor |
-
2018
- 2018-05-23 CN CN201810502157.2A patent/CN108716434A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6209311B1 (en) * | 1998-04-13 | 2001-04-03 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
| US20140223884A1 (en) * | 2009-09-09 | 2014-08-14 | The Boeing Company | Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan |
| US20160245161A1 (en) * | 2015-02-20 | 2016-08-25 | Pratt & Whitney Canada Corp. | Compound engine assembly with modulated flow |
| CN107010230A (en) * | 2015-10-26 | 2017-08-04 | 通用电气公司 | For the method and system avoided across engine debris |
| CN107161349A (en) * | 2016-03-07 | 2017-09-15 | 通用电气公司 | Propulsion system for aircraft |
| CN205770144U (en) * | 2016-05-27 | 2016-12-07 | 中国科学院光电研究院 | A kind of dynamical system of rotor craft |
| CN206645025U (en) * | 2017-03-01 | 2017-11-17 | 广东合即得能源科技有限公司 | A kind of jet-propelled unmanned aerial vehicle of single rotor |
| CN107816384A (en) * | 2017-10-11 | 2018-03-20 | 中国航发南方工业有限公司 | Aviation hybrid power system and its unmanned plane based on radial-piston motor |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117141756A (en) * | 2023-11-01 | 2023-12-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Small-size many ducts unmanned aerial vehicle of quick deployment |
| CN117141756B (en) * | 2023-11-01 | 2024-01-23 | 中国空气动力研究与发展中心计算空气动力研究所 | Small-size many ducts unmanned aerial vehicle of quick deployment |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181030 |
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| RJ01 | Rejection of invention patent application after publication |