CN109611208A - A method of reducing ducted fan noise - Google Patents
A method of reducing ducted fan noise Download PDFInfo
- Publication number
- CN109611208A CN109611208A CN201811310442.0A CN201811310442A CN109611208A CN 109611208 A CN109611208 A CN 109611208A CN 201811310442 A CN201811310442 A CN 201811310442A CN 109611208 A CN109611208 A CN 109611208A
- Authority
- CN
- China
- Prior art keywords
- fan
- adhesive tape
- blade tip
- tip
- millimeters
- 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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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/962—Preventing, counteracting or reducing vibration or noise by means of "anti-noise"
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- 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 reducing ducted fan noise, belong to ducted fan engine noise abatement field.20 millimeters wide, high 4.5mm millimeters of annular adhesive tape is posted, and do smoothing processing before duct inner wall, the sharp position of fan at 6 millimeters for the gap between blade tip and duct inner wall.As a result, when air-flow flows through fan tip, due to fan tip and duct inner surface flow velocity difference, the vortex for being similar to " wingtip vortex " will be generated.In blade tip position, due to the arrangement of annular adhesive tape, blade tip is by the slough after being in step caused by adhesive tape, because greatly reducing blade tip linear velocity without " wingtip vortex ", to reduce eddy current crack.The present invention optimizes existing ducted fan engine under the premise of having substantially no effect on engine performance, reduces noise, is conducive to meet airworthiness requirement.
Description
Technical field
The invention belongs to ducted fan engine noise abatement field, specifically a kind of safe and reliable, satisfaction flight requires and has
There is the ducted fan engine optimization method of low-noise characteristic.
Background technique
Ducted fan engine with safety and the improved potentiality of significant performance becomes many aircraft powers because of it
Selection.Especially big Bypass Ratio Turbofan Engine is widely used in large-scale civil and military since oil consumption rate is low, noise is small
Transporter and other large-scale subsonic aircrafts, such as fuel charger, early warning plane, antisubmarine plane.
However, caused by the difference of gas flow patterns on the inside of fan wing tip and duct " wingtip vortex " can be to starting
The performance of machine has a huge impact: in flight course, will generate biggish noise and resistance.
Summary of the invention
The present invention is in view of the above-mentioned problems, by increasing adhesive tape in ducted fan flabellum front end air inlet part, with to starting
The excessive problem of noise optimizes in machine design process, specifically a kind of method for reducing ducted fan noise.
The method of the reduction ducted fan noise 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, high 4.5mm millimeters of annular adhesive tape, and do smoothing processing.As a result, when air-flow flows through fan tip, due to fan tip
With duct inner surface flow velocity difference, the vortex for being similar to " wingtip vortex " will be generated.In blade tip position, due to the cloth of annular adhesive tape
It sets, blade tip is by the slough after being in step caused by adhesive tape, because greatly reducing blade tip without " wingtip vortex "
Linear velocity, to reduce eddy current crack.
The invention has the following beneficial effects: by installing adhesive tape in fan air intake side, engine is being had substantially no effect on
Under the premise of performance, existing ducted fan engine is optimized, noise is reduced, is conducive to meet airworthiness requirement.
Detailed description of the invention
Fig. 1 is the integral layout figure of ducted fan engine of the present invention；
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 principle analysis diagram of the present invention without adhesive tape；
Fig. 4 b is the principle analysis diagram of the invention with adhesive tape；
Fig. 5 is the Duct-Burning Turbofan experiment shoot on location figure that the present invention posts annular adhesive tape；
Fig. 6 is that noise testing experimental result compares at duct left rear side 30cm of the present invention；
Fig. 7 is that noise testing experimental result compares at duct front left side 30cm of the present invention.
Specific embodiment
Technical solution of the present invention is further elaborated below with reference to examples and drawings.
The integral layout of ducted fan engine is as shown in Figure 1, include preceding blade 1, rectification cap 2, lip 3 and outer wall 4；
General ducted fan engine, can be between blade tip and duct inner wall in view of factors such as manufacturing process, blade tip deformation and vibrations
Keep certain gap, just because of there are this gap, cause high-speed rotating blade tip the gap location generate Strong shear and
Vortex finally generates high-frequency noise.
As shown in Fig. 2, the present invention disposes three leaf paddles 5 on propeller hub, to increase engine inhaled air volume and speed.Such as figure
Shown in 5, while before duct inner wall, the sharp position of fan at 6 millimeters, arrangement posts 20 millimeters wide, the annular adhesive tape of high 4.5mm, and
Do smoothing processing.Blade tip gap 3mm, so that when air-flow flows through fan tip, due to fan tip and duct inner surface flow velocity
Difference will generate the vortex for being similar to " wingtip vortex ".In blade tip position, due to the arrangement of annular adhesive tape, blade tip will be in adhesive tape
In slough after generated step, because greatly reducing blade tip linear velocity without " wingtip vortex ", to reduce
Eddy current crack.
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, no adhesive tape air flowing
As shown in fig. 4 a, when air-flow flows through fan tip, due to fan tip and duct inner surface flow velocity difference, generation is similar to
The vortex of " wingtip vortex ".Therefore, no matter biggish noise will be all generated during taking off or cruising.Post annular adhesive tape
Air flow schematic diagram is as shown in Figure 4 b, and in blade tip position, due to the placement of adhesive tape, blade tip will be in step caused by adhesive tape
In slough afterwards, because without " wingtip vortex " in Fig. 4 a, to reduce eddy current crack.
There is ringless-type adhesive tape by duct inner wall, test comparison is carried out to noise at duct left rear side 30cm, as a result such as Fig. 6
Shown, abscissa is power/kw, and ordinate is noise intensity/dBA.It is found from figure, under equal-wattage, making an uproar after joint strip
The more non-joint strip of sound intensity degree is substantially reduced.This effect is especially apparent in low-power, and difference maximum is up to 30 decibels.
There is ringless-type adhesive tape by duct inner wall, test comparison is carried out to noise at duct front left side 30cm, such as Fig. 7 institute
Show, lower than the noise decibel value of non-joint strip after duct joint strip under Same Efficieney, human ear can be clearly felt that patch when actual test
Duct sound after item is softer, and noise can be relatively much lower after duct joint strip when low speed.
The present invention demonstrates this method for the applicability of ducted fan engine noise reduction.
Claims (2)
1. a kind of method for reducing ducted fan noise, 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
4.5mm millimeters of annular adhesive tape, and do smoothing processing；As a result, when air-flow flows through fan tip, due to fan tip and duct
Inner surface flow velocity difference will generate the vortex for being similar to " wingtip vortex "；In blade tip position, due to the arrangement of annular adhesive tape, blade tip
It will be in the slough after step caused by adhesive tape, because greatly reducing blade tip linear velocity without " wingtip vortex ",
To reduce eddy current crack.
2. a kind of method for reducing ducted fan noise as described in claim 1, which is characterized in that be also arranged three on propeller hub
Leaf paddle, to increase engine inhaled air volume and speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811310442.0A CN109611208A (en) | 2018-11-06 | 2018-11-06 | A method of reducing ducted fan noise |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811310442.0A CN109611208A (en) | 2018-11-06 | 2018-11-06 | A method of reducing ducted fan noise |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109611208A true CN109611208A (en) | 2019-04-12 |
Family
ID=66002033
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811310442.0A Pending CN109611208A (en) | 2018-11-06 | 2018-11-06 | A method of reducing ducted fan noise |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109611208A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109630313A (en) * | 2018-11-06 | 2019-04-16 | 武汉卓尔无人机制造有限公司 | A method of improving ducted fan engine pulling force |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN109630313A (en) * | 2018-11-06 | 2019-04-16 | 武汉卓尔无人机制造有限公司 | A method of improving ducted fan engine pulling force |
-
2018
- 2018-11-06 CN CN201811310442.0A patent/CN109611208A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN109630313A (en) * | 2018-11-06 | 2019-04-16 | 武汉卓尔无人机制造有限公司 | A method of improving ducted fan engine pulling force |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109630313A (en) * | 2018-11-06 | 2019-04-16 | 武汉卓尔无人机制造有限公司 | A method of improving ducted fan engine pulling force |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190412 |