CN109630313A - A method of improving ducted fan engine pulling force - Google Patents
A method of improving ducted fan engine pulling force Download PDFInfo
- Publication number
- CN109630313A CN109630313A CN201811315625.1A CN201811315625A CN109630313A CN 109630313 A CN109630313 A CN 109630313A CN 201811315625 A CN201811315625 A CN 201811315625A CN 109630313 A CN109630313 A CN 109630313A
- Authority
- CN
- China
- Prior art keywords
- blade tip
- pulling force
- adhesive tape
- ducted fan
- increase
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000002390 adhesive tape Substances 0.000 claims abstract description 25
- 241000883990 Flabellum Species 0.000 claims description 2
- 238000009499 grossing Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 7
- 230000015556 catabolic process Effects 0.000 abstract description 2
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VIKNJXKGJWUCNN-XGXHKTLJSA-N norethisterone Chemical compound O=C1CC[C@@H]2[C@H]3CC[C@](C)([C@](CC4)(O)C#C)[C@@H]4[C@@H]3CCC2=C1 VIKNJXKGJWUCNN-XGXHKTLJSA-N 0.000 description 1
- 235000009566 rice Nutrition 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of methods for improving ducted fan engine pulling force, belong to ducted fan engine optimization and improve pulling force field.20 millimeters wide, the annular adhesive tape of high 4.5mm is posted before duct inner wall, the sharp position of fan at 6 millimeters for the gap between blade tip and duct inner wall.Due to the presence in blade tip gap, cause to generate stronger vortex at blade tip, to reduce blade tip pulling force and increase induced drag, to increase torque；Due to the arrangement of annular adhesive tape, blade tip is in the slough after step caused by adhesive tape, it is thus eliminated that blade tip is vortexed, to increase blade tip pulling force and reduce induced drag.Present invention significantly reduces the aerial drainage effect of blade tip and blade tip vortices breakdown is reduced, to achieve the effect that reduce torque, improve pulling force.Lift improves after joint strip, and as the engine speed increases, pulling force improvement effect becomes apparent.
Description
Technical field
The invention belongs to ducted fan engine optimizations to improve pulling force field, be related to it is a kind of safe and reliable, meet flight and want
The method asked and ducted fan engine pulling force can be significantly improved.
Background technique
Ducted fan is because become many Power System of Flight Vehicle with safety and the improved potentiality of significant performance
Selection.Especially big Bypass Ratio Turbofan Engine is widely used in large-scale civil and military fortune since oil consumption rate is low, noise is small
Defeated machine and other large-scale subsonic aircrafts, such as fuel charger, early warning plane, antisubmarine plane.
It is restricted due to being limited to the factors such as production, processing and assembly technology and blade tip deformation, general ducted fan blade tip
Can all there be certain gap amount between duct inner wall.Presence just because of this gap leads to fan when rotating at high speed
Stronger shearing and blade tip aerial drainage effect can be generated between on the inside of wing tip and duct, to reduce blade tip pulling force and increase torsion
Square.
Summary of the invention
The present invention in view of the above-mentioned problems, there is certain thickness adhesive tape by the installation of duct inner wall before blade tip, compared with
Under the premise of the influence engine performance of low degree, the pulling force of blade tip is improved, torque is reduced；Specifically a kind of raising duct
The method of Duct-Burning Turbofan pulling force.
The method of the raising ducted fan engine pulling force specifically:
For the gap between blade tip and duct inner wall, before duct inner wall, the sharp position of fan at 6 millimeters, wide 20 milli is posted
Rice, the annular adhesive tape of high 4.5mm.Due to the presence in blade tip gap, cause to generate stronger vortex at blade tip, to reduce blade tip
Pulling force simultaneously increases induced drag, to increase torque；Due to the arrangement of annular adhesive tape, after blade tip is in step caused by adhesive tape
Slough, it is thus eliminated that blade tip be vortexed, to increase blade tip pulling force and reduce induced drag.
The invention has the following beneficial effects:
1) a kind of, method for improving ducted fan engine pulling force, significantly reduces the aerial drainage effect of blade tip and reduces
Blade tip vortices breakdown, to achieve the effect that reduce torque, improve pulling force.
2) a kind of, method for improving ducted fan engine pulling force, the experimental results showed that lift improves after joint strip, and with
The raising of engine speed, pulling force improvement effect become apparent.
Detailed description of the invention
Fig. 1 is the integral layout figure of ducted fan engine of the present invention；Fig. 1 a is the front view of ducted fan engine；Figure
1b is the outer wall figure of ducted fan engine；
Fig. 2 is the three-dimensional detail figure of ducted fan engine of the present invention；
Fig. 3 is the cross-sectional view of the Duct-Burning Turbofan with adhesive tape and the fan point detailed view of fan of the invention；
Fig. 4 a is lift principle analysis diagram of the present invention without adhesive tape；
Fig. 4 b is that lift of the present invention with adhesive tape improves principle analysis diagram；
Fig. 5 is the Duct-Burning Turbofan experiment shoot on location figure that the present invention posts annular adhesive tape；
Fig. 6 is the Comparative result schematic diagram that the present invention has ringless-type adhesive tape to duct tensile test.
Specific embodiment
Technical solution of the present invention is further elaborated below with reference to examples and drawings.
As illustrated in figs. 1A and ib, including preceding blade 1 rectifies cap 2 to the integral layout of ducted fan engine, lip 3 with
And outer wall 4；As shown in Fig. 2, the present invention disposes two rows of three flabellum paddles 5 on propeller hub, to increase engine inhaled air volume and speed
Degree.Adhesive tape 6 is disposed in the front side of preceding blade simultaneously, as shown in figure 5, before the fan point position of specially duct inner wall at 6 millimeters, cloth
It sets and posts 20 millimeters wide, the annular adhesive tape of high 4.5mm, and do smoothing processing；Above-mentioned parameter be after different tests compare most
It determines eventually, by improving existing ducted fan engine, achievees the purpose that promote pulling force.
Due to the presence of blade tip gap 3mm, cause to generate stronger vortex at blade tip, to reduce blade tip pulling force and increase
Induced drag, to increase torque；Due to the arrangement of annular adhesive tape, blade tip is in the slough after step caused by adhesive tape,
It is thus eliminated that blade tip is vortexed, to increase blade tip pulling force and reduce induced drag.Main purpose is so that aircraft
Duct lift improves in starting and flight course, and secondary objective is the stability enhanced in flight course.
As shown in figure 3, its middle and upper part larger area is propeller hub cross-sectional profile, You Lianggen rod piece is fixed on inside duct,
Figure middle and lower part is the aerofoil profile of duct, which is enough to provide the requirements during aircraft takeoff and cruise.
Annular adhesive tape, which is sticked, by the duct to Duct-Burning Turbofan and does not paste annular adhesive tape compares, the blade tip stream of no adhesive tape
It moves as shown in fig. 4 a, due to the presence in blade tip gap, causes to generate at blade tip by strong vortex, to reduce blade tip pulling force
And increase induced drag, to increase torque.The blade tip flowing for posting annular adhesive tape is as shown in Figure 4 b, since blade tip is in adhesive tape
Slough after generated step, thus greatly it is smaller even be eliminated blade tip vortex, to increase blade tip pulling force and subtract
Small induced drag.
There is ringless-type adhesive tape by duct inner wall, test comparison is carried out to duct pulling force, as a result as shown in fig. 6, abscissa
For power/kw, ordinate is pulling force/kg.Duct pulling force after obviously finding joint strip in figure gets a promotion, and pulling force is promoted maximum
Value is 2kg or so.When power increases, pulling force promotion is become apparent.By the experiment, reasonability of the invention is demonstrated.
Claims (2)
1. a kind of method for improving ducted fan engine pulling force, which is characterized in that specifically:
20 millimeters wide, height is posted before duct inner wall, the sharp position of fan at 6 millimeters for the gap between blade tip and duct inner wall
The annular adhesive tape of 4.5mm, and do smoothing processing；Due to the presence in blade tip gap, cause to generate stronger vortex at blade tip, thus
It reduces blade tip pulling force and increases induced drag, to increase torque；Due to the arrangement of annular adhesive tape, blade tip is in produced by adhesive tape
Step after slough, it is thus eliminated that blade tip be vortexed, to increase blade tip pulling force and reduce induced drag.
2. a kind of method for improving ducted fan engine pulling force as described in claim 1, which is characterized in that in unmanned plane
Two rows of three flabellum paddles are also arranged on propeller hub, to increase engine inhaled air volume and speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811315625.1A CN109630313B (en) | 2018-11-06 | 2018-11-06 | Method for improving tension of ducted fan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811315625.1A CN109630313B (en) | 2018-11-06 | 2018-11-06 | Method for improving tension of ducted fan engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109630313A true CN109630313A (en) | 2019-04-16 |
| CN109630313B CN109630313B (en) | 2021-04-02 |
Family
ID=66067381
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811315625.1A Expired - Fee Related CN109630313B (en) | 2018-11-06 | 2018-11-06 | Method for improving tension of ducted fan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109630313B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109611208A (en) * | 2018-11-06 | 2019-04-12 | 武汉卓尔无人机制造有限公司 | A method of reducing ducted fan noise |
| CN114233515A (en) * | 2021-12-16 | 2022-03-25 | 浙江云途飞行器技术有限公司 | Fan engine with noise reduction function |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100148515A1 (en) * | 2007-11-02 | 2010-06-17 | Mary Geddry | Direct Current Brushless Machine and Wind Turbine System |
| CN201606315U (en) * | 2009-11-20 | 2010-10-13 | 深圳市蓝岱科技有限公司 | Blade-tip clearance vortex flow restraining structure of ducted fan |
| CN101973391A (en) * | 2010-10-15 | 2011-02-16 | 北京理工大学 | Lip and spread angle variable efficient duct |
| CN102745328A (en) * | 2012-07-13 | 2012-10-24 | 北京理工大学 | Bypass with tip eddy-current confinement effect |
| CN105966601A (en) * | 2016-06-14 | 2016-09-28 | 西北工业大学 | Ducted fan lip inflatable air bag and flow separation control method thereof |
| CN107284652A (en) * | 2017-06-21 | 2017-10-24 | 张家港致盈电子技术有限公司 | Integrated culvert type propeller |
| CN109611208A (en) * | 2018-11-06 | 2019-04-12 | 武汉卓尔无人机制造有限公司 | A method of reducing ducted fan noise |
-
2018
- 2018-11-06 CN CN201811315625.1A patent/CN109630313B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100148515A1 (en) * | 2007-11-02 | 2010-06-17 | Mary Geddry | Direct Current Brushless Machine and Wind Turbine System |
| CN201606315U (en) * | 2009-11-20 | 2010-10-13 | 深圳市蓝岱科技有限公司 | Blade-tip clearance vortex flow restraining structure of ducted fan |
| CN101973391A (en) * | 2010-10-15 | 2011-02-16 | 北京理工大学 | Lip and spread angle variable efficient duct |
| CN102745328A (en) * | 2012-07-13 | 2012-10-24 | 北京理工大学 | Bypass with tip eddy-current confinement effect |
| CN105966601A (en) * | 2016-06-14 | 2016-09-28 | 西北工业大学 | Ducted fan lip inflatable air bag and flow separation control method thereof |
| CN107284652A (en) * | 2017-06-21 | 2017-10-24 | 张家港致盈电子技术有限公司 | Integrated culvert type propeller |
| CN109611208A (en) * | 2018-11-06 | 2019-04-12 | 武汉卓尔无人机制造有限公司 | A method of reducing ducted fan noise |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109611208A (en) * | 2018-11-06 | 2019-04-12 | 武汉卓尔无人机制造有限公司 | A method of reducing ducted fan noise |
| CN114233515A (en) * | 2021-12-16 | 2022-03-25 | 浙江云途飞行器技术有限公司 | Fan engine with noise reduction function |
| CN114233515B (en) * | 2021-12-16 | 2023-10-03 | 浙江云途飞行器技术有限公司 | Fan engine with noise reduction function |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109630313B (en) | 2021-04-02 |
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Granted publication date: 20210402 |