CN111237254A - Aviation compressor blade with noise reduction function under high Reynolds number condition - Google Patents
Aviation compressor blade with noise reduction function under high Reynolds number condition Download PDFInfo
- Publication number
- CN111237254A CN111237254A CN201811447682.5A CN201811447682A CN111237254A CN 111237254 A CN111237254 A CN 111237254A CN 201811447682 A CN201811447682 A CN 201811447682A CN 111237254 A CN111237254 A CN 111237254A
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- Prior art keywords
- compressor blade
- saw teeth
- reynolds number
- blade
- triangular saw
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
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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 relates to an aviation compressor blade with a noise reduction function under the condition of high Reynolds number, which comprises a compressor blade, wherein triangular saw teeth are arranged at the tail edge of the compressor blade, a flattening area is arranged at the tail edge of the compressor blade, the flattening area is uniformly distributed above and below the triangular saw teeth, the tooth widths W of the triangular saw teeth are equal, the tooth heights H of the triangular saw teeth are equal, the areas of the two groups of flattening areas are equal, and the value of the blade height Z of the compressor blade is 120 mm. The aviation compressor blade with the noise reduction function under the high Reynolds number condition can improve the aerodynamic performance of a compressor blade airfoil, reduce wake flow loss, increase wake flow mixing, and crush and refine large vortexes concentrated at the trailing edge by using a sawtooth structure under the high Reynolds number condition, thereby effectively reducing aerodynamic noise, minimizing aerodynamic loss, and greatly improving the operation efficiency and stability of the compressor.
Description
Technical Field
The invention belongs to the technical field of aviation machinery, and particularly relates to an aviation compressor blade with a noise reduction function under the condition of high Reynolds number.
Background
The noise of the aero-engine is always a focus of people's attention, the compressor is an important component of the aero-engine, the noise of the compressor occupies an important position in the noise of the aero-engine, the influence of the structure of the trailing edge of the blade of the compressor on the noise of the compressor is great, an important method for reducing the noise of the trailing edge of the blade at present is to arrange sawteeth at the trailing edge of the blade of the compressor, namely arrange sawteeth with different shapes at the trailing edge of the blade, the method is inspired from the trailing edge of wings of natural owls and belongs to a bionic method, wherein the structure of the sawteeth at the triangular trailing edge is particularly concerned by people, and the method is applied to a great extent in the field of noise reduction of wind.
However, in the current practical situation, no matter the aircraft is in a take-off, landing or cruising state, the air flow velocity inside the engine is very high, and the aviation compressor generates great noise when in operation under the flowing state of high speed and high reynolds number, but the current research on noise reduction of the aviation compressor under the working conditions of high speed and high reynolds number is not sufficient, and effective noise reduction cannot be carried out, so that deep research needs to be carried out on noise reduction of the aviation compressor blade under the working conditions of high speed and high reynolds number.
Disclosure of Invention
The invention aims to solve the problems, and provides an aviation compressor blade with a noise reduction function under the condition of high Reynolds number, which has a simple structure and a reasonable design.
The invention realizes the purpose through the following technical scheme:
an aviation compressor blade with a noise reduction function under the condition of high Reynolds number comprises a compressor blade, wherein triangular saw teeth are arranged at the tail edge of the compressor blade, a leveling area is arranged at the tail edge of the compressor blade, the leveling area is uniformly distributed above and below the triangular saw teeth, and the compressor blade is machined by adopting an internal cutting method.
As a further optimization scheme of the invention, the tooth widths W of the triangular saw teeth of the groups are equal, the tooth heights H of the triangular saw teeth of the groups are equal, the areas of the two groups of flat areas are equal, the blade height Z of the compressor blade is 120mm, the tooth height and the tooth width of the triangular saw teeth determine the tooth crest angle epsilon of the triangular saw teeth, and H is W/2tan (epsilon/2).
As a further optimization scheme of the invention, the width W of the triangular sawtooth is 10-20 mm, and the height H of the triangular sawtooth is 5-25 mm.
As a further optimization of the present invention, the relative tooth width of the triangular saw tooth is:
W/C＝0.12
wherein C is the chord length of the reference blade of the triangular saw tooth, the value of C is 127mm, and the value of W is 15 mm.
As a further optimization scheme of the present invention, the aspect ratio of the triangular saw tooth is:
H/W＝1.2
wherein the value of H is 18 mm.
The invention has the beneficial effects that:
1) the triangular saw teeth are arranged on one side edge of the blade of the air compressor, the aerodynamic performance of the blade airfoil of the air compressor can be improved by the arrangement of the triangular saw teeth, the wake flow loss is reduced, the wake flow mixing is increased, and the large vortex concentrated at the tail edge can be crushed and refined by the saw tooth structure under the condition of high Reynolds number, so that the aerodynamic noise is effectively reduced, the aerodynamic loss is minimized, and the operation efficiency and the operation stability of the air compressor are greatly improved;
2) the invention has simple structure, reasonable design and convenient realization.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a mating view of triangular serrations of the present invention with compressor blades;
FIG. 3 is a graph of the relationship between the total pressure loss coefficient and the sawtooth structure of the present invention.
Fig. 4 is a graph of the relationship of the sawtooth structure of the present invention to sound pressure level.
FIG. 5 is a diagram showing the distribution of vortex core structure when H/W is 0 according to the present invention.
FIG. 6 is a graph showing the distribution of vortex core structure when H/W is 1.2 according to the present invention.
In the figure: 1 compressor blade, 2 triangular saw teeth and 3 flat areas.
Detailed Description
The present application will now be described in further detail with reference to the drawings, it should be noted that the following detailed description is given for illustrative purposes only and is not to be construed as limiting the scope of the present application, as those skilled in the art will be able to make numerous insubstantial modifications and adaptations to the present application based on the above disclosure.
Example 1
As shown in fig. 1 and 2, an aviation compressor blade with a noise reduction function under a high reynolds number condition comprises a compressor blade 1, triangular saw teeth 2 are arranged at the tail edge of the compressor blade 1, a leveling region 3 is arranged at the tail edge of the compressor blade 1, the leveling regions 3 are uniformly distributed above and below the triangular saw teeth 2, the tooth widths W of the triangular saw teeth 2 are equal, the tooth heights H of the triangular saw teeth 2 are equal, the areas of the two leveling regions 3 are equal, the value of the blade height Z of the compressor blade 1 is 120mm, the tooth width W of the triangular saw teeth 2 is 10-20 mm, the tooth height H of the triangular saw teeth 2 is 5-25 mm, and the relative tooth widths of the triangular saw teeth 2 are as follows:
W/C＝0.12
wherein C is the chord length of the reference blade of the triangular saw tooth 2, the value of C is 127mm, the value of W is 15mm,
aspect ratio of the triangular serration 2:
H/W＝1.2
wherein the value of H is 18 mm.
As shown in fig. 3 to 6, when the reference blade chord length C is 127mm, the blade height Z is 120mm, the tooth height H is 18mm, and the tooth width W is 15mm, a serrated trailing edge blade with H/W of 1.2 is obtained by an inscribed method, and in various airfoil profiles, H/W is 1.The total pressure loss coefficient is minimum when 2 hours, the aerodynamic performance loss is reduced to the minimum while the noise reduction effect is achieved, aiming at the condition that the Ma is equal to U/U and is equal to 0.3 of the compressor, the fluid is defined as air, and the air density rho is 1.23kg/m3Kinematic viscosity u 1.46 × 10-5m/s, main flow speed U is 102m/s, Reynolds number Re is 8.87 multiplied by 105Under the operating mode, according to Powell's whirlpool sound theory, there is the whirlpool in the flow field to have pneumatic sound source, and the reduction of single tone spike noise is because the broken result of the whirlpool of blade spanwise direction, becomes the miniaturity whirlpool by the large-scale whirlpool, and the reduction of vorticity is favorable to reducing the noise, quotes the Q rule as the judgement basis of whirlpool, promptly: q1/2 (| | Ω | | non-woven hair)2-||E||2) Wherein omega is the vorticity tensor, E is the strain rate tensor, carry out the data verification that obtains after the emulation according to emulation software, the noise reduction effect that the compressor obtained this moment is best, compare in former wing, when adopting tooth aspect ratio H/W1.2, tooth height H18 mm, tooth width W15 mm's sawtooth, can improve the aerodynamic performance of compressor blade airfoil, reduce wake flow loss, increase wake flow blending, and can utilize the sawtooth structure to concentrate on the broken and refining of the big vortex of trailing edge department under the high reynolds number condition, thereby effectively reduced aerodynamic noise, let aerodynamic loss minimum simultaneously, make the efficiency and the stability of compressor operation improve greatly.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention.
Claims (5)
1. An aviation compressor blade with function of making an uproar falls under high reynolds number condition, including compressor blade (1), its characterized in that: triangular saw teeth (2) are arranged at the tail edge of the compressor blade (1), a leveling area (3) is arranged at the tail edge of the compressor blade (1), and the leveling area (3) is uniformly distributed above and below the triangular saw teeth (2).
2. The aviation compressor blade with noise reduction function under high Reynolds number conditions of claim 1, wherein: the tooth widths W of the triangular saw teeth (2) are equal, the tooth heights H of the triangular saw teeth (2) are equal, the areas of the two groups of leveling areas (3) are equal, and the value of the blade height Z of the compressor blade (1) is 120 mm.
3. The aviation compressor blade with noise reduction function under high Reynolds number conditions of claim 2, wherein: the range of the tooth width W of the triangular saw teeth (2) is 10-20 mm, and the range of the tooth height H of the triangular saw teeth (2) is 5-25 mm.
4. An aviation compressor blade with noise reduction function under high Reynolds number conditions according to claim 3, wherein: the relative tooth width of the triangular saw teeth (2):
W/C＝0.12
wherein C is the reference blade chord length of the triangular saw teeth (2), the value of C is 127mm, and the value of W is 15 mm.
5. The aviation compressor blade with noise reduction function under high Reynolds number conditions of claim 4, wherein: the tooth aspect ratio of the triangular sawtooth (2) is as follows:
H/W＝1.2
wherein the value of H is 18 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811447682.5A CN111237254A (en) | 2018-11-29 | 2018-11-29 | Aviation compressor blade with noise reduction function under high Reynolds number condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811447682.5A CN111237254A (en) | 2018-11-29 | 2018-11-29 | Aviation compressor blade with noise reduction function under high Reynolds number condition |
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| Publication Number | Publication Date |
|---|---|
| CN111237254A true CN111237254A (en) | 2020-06-05 |
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| CN201811447682.5A Pending CN111237254A (en) | 2018-11-29 | 2018-11-29 | Aviation compressor blade with noise reduction function under high Reynolds number condition |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113793587A (en) * | 2021-11-16 | 2021-12-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Noise reduction method based on vortex array |
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| CN104948396A (en) * | 2015-07-22 | 2015-09-30 | 代元军 | Wind turbine blade adopting serrated blade tip tail edge structure and wind turbine |
| CN105484946A (en) * | 2015-11-23 | 2016-04-13 | 北京金风科创风电设备有限公司 | Blade, blade sawtooth tail edge and manufacturing method thereof |
| CN106089569A (en) * | 2016-07-20 | 2016-11-09 | 湘潭大学 | A kind of Miniature Wind Turbine Blades aerofoil profile being applicable to low reynolds number flow |
| CN206707918U (en) * | 2017-02-10 | 2017-12-05 | 中国电力工程顾问集团华北电力设计院有限公司 | Waveform trailing edge blade and H type vertical-shaft aerogenerators |
| CN207212709U (en) * | 2017-09-11 | 2018-04-10 | 加丁（天津）科技有限公司 | A kind of low-noise centrifugal fan, air cleaning unit provided with sawtooth trailing edge blade |
| CN108386383A (en) * | 2018-02-24 | 2018-08-10 | 西安交通大学 | A kind of intersection bionic blade and preparation method thereof of combination Scad section's fish bodies and pinion |
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2018
- 2018-11-29 CN CN201811447682.5A patent/CN111237254A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104948396A (en) * | 2015-07-22 | 2015-09-30 | 代元军 | Wind turbine blade adopting serrated blade tip tail edge structure and wind turbine |
| CN105484946A (en) * | 2015-11-23 | 2016-04-13 | 北京金风科创风电设备有限公司 | Blade, blade sawtooth tail edge and manufacturing method thereof |
| CN106089569A (en) * | 2016-07-20 | 2016-11-09 | 湘潭大学 | A kind of Miniature Wind Turbine Blades aerofoil profile being applicable to low reynolds number flow |
| CN206707918U (en) * | 2017-02-10 | 2017-12-05 | 中国电力工程顾问集团华北电力设计院有限公司 | Waveform trailing edge blade and H type vertical-shaft aerogenerators |
| CN207212709U (en) * | 2017-09-11 | 2018-04-10 | 加丁（天津）科技有限公司 | A kind of low-noise centrifugal fan, air cleaning unit provided with sawtooth trailing edge blade |
| CN108386383A (en) * | 2018-02-24 | 2018-08-10 | 西安交通大学 | A kind of intersection bionic blade and preparation method thereof of combination Scad section's fish bodies and pinion |
Non-Patent Citations (1)
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| 武威: "锯齿尾缘叶片的气动性能研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113793587A (en) * | 2021-11-16 | 2021-12-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Noise reduction method based on vortex array |
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Application publication date: 20200605 |