CN110844116B - Parameter-adjustable vortex generator - Google Patents
Parameter-adjustable vortex generator Download PDFInfo
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- CN110844116B CN110844116B CN201910997574.3A CN201910997574A CN110844116B CN 110844116 B CN110844116 B CN 110844116B CN 201910997574 A CN201910997574 A CN 201910997574A CN 110844116 B CN110844116 B CN 110844116B
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- 238000005096 rolling process Methods 0.000 claims abstract description 12
- 230000008602 contraction Effects 0.000 claims description 11
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 7
- 238000011160 research Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005259 measurement Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000030279 gene silencing Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005693 optoelectronics Effects 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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Abstract
The invention belongs to the technical field of helicopter model rotor tests, and relates to an adjustable parameter vortex generator. The vortex generator includes: the device comprises a tip vortex generating device, a pitching and rolling device and an attitude and vortex speed control device, wherein the tip vortex generating device and the pitching and rolling device are connected through a turbine worm mechanism, and the tip vortex generating device and the pitching and rolling device are respectively connected with the attitude and vortex speed control device through cables. The device can simulate the tip vortex of the paddle generating various vortex angles and vortex speeds.
Description
Technical Field
The invention belongs to the technical field of helicopter model rotor tests, and relates to a parameter-adjustable vortex generator.
Background
Rotor blade vortex interference noise is a typical noise generated by a helicopter rotor, and particularly in the low-speed forward flight and inclined descent state, the energy of the blade vortex interference noise accounts for 80% of the total energy of the helicopter noise. Therefore, the method is a main research field of reducing the noise of the current helicopter.
At present, the research on the rotor blade vortex interference noise at home and abroad is mainly carried out in a silencing wind tunnel, the test period is long, the test cost is very high, and the research on the blade vortex interference noise which is sufficient and pure can not be carried out due to a plurality of uncertain factors and interference factors in the test.
Disclosure of Invention
The purpose of the invention is as follows: the parameter-adjustable vortex generator can simulate the blade tip vortex generating various vortex angles and vortex speed and can be used for carrying out blade tip vortex test research on parallel blade tip vortex and various washing angles.
The technical scheme of the invention is as follows:
in a first aspect, there is provided an adjustable parameter vortex generator, comprising: the device comprises a tip vortex generating device 1, a pitching and rolling device 2 and an attitude and vortex speed control device 3, wherein the tip vortex generating device 1 and the pitching and rolling device 2 are connected through a turbine worm mechanism, and the tip vortex generating device 1 and the pitching and rolling device 2 are respectively connected with the attitude and vortex speed control device 3 through cables.
Optionally, the blade tip vortex generating device 1 includes an airfoil section 11, a working section 12, a contraction section 13, a rectification section 14, and a fan section 15, where the airfoil section 11 is sleeved with the working section 12, the working section 12 is sleeved with the contraction section 13, the contraction section 13 is sleeved with the rectification section 14, and the rectification section 14 is sleeved with the fan section 15.
Alternatively, the pitch and roll device 2 includes a pitch mechanism 21, a support mechanism 22, and a roll mechanism 23, wherein the pitch mechanism 21 and the support mechanism 22 are bolted, and the support mechanism 22 and the roll mechanism 23 are bolted.
Optionally, the airfoil section 11 has a length of 120mm, an inner diameter of 100mm, and two triangular airfoils with an aspect ratio of 1:1.73 are built in.
Alternatively, the working section 12 is 60mm in length and the outlet diameter is 100 mm.
Alternatively, the constrictor 13 has a length of 140mm, an inlet end diameter of 200mm, an outlet end diameter of 100mm, and an area constriction ratio of 1: 4.
Optionally, the flow guide section 14 is 100mm in length and 200mm in inner diameter.
Optionally, the fan section 15 is 567mm long and 300mm high, and the noise is lower than 65dBA axial fan and fan are embedded in the middle section of the fan section (15).
Optionally, the support mechanism 22 is a U-shaped bracket.
Optionally, the U-shaped bracket is made of an aluminum alloy material, and weight reduction grooves are formed in two arms of the U-shaped bracket.
The invention has the beneficial effects that: the parameter-adjustable vortex generator can simulate and generate tip vortexes of paddles with various vortex-outlet angles and vortex-outlet speeds, and can be used for performing tip vortex test research of parallel tip vortexes and various washing angles.
Drawings
FIG. 1 is a block diagram of an adjustable parameter vortex generator;
FIG. 2 is a block diagram of a tip vortex generating device;
FIG. 3 is a block diagram of a pitch and roll apparatus;
fig. 4 is a configuration diagram of the attitude and vortex speed control device.
The device comprises a blade tip vortex generating device 1, a pitching and rolling device 2, a posture and vortex speed control device 3, an airfoil section 11, a working section 12, a contraction section 13, a rectification section 14, a fan section 15, a pitching mechanism 21, a supporting mechanism 22, a rolling mechanism 23, a standard cabinet 31, a measurement and control computer 32, a rotary table motor driver 33, a wind source motor driver 34 and a wind source motor control board 35.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
The adjustable parameter vortex generator (see figure 1) comprises three parts: a tip vortex generating device 1, a pitch and roll device 2, and an attitude and vortex speed control device 3.
(1) Blade tip vortex generating device
The tip vortex generating device 1 includes: an airfoil section 11; a working section 12; a constriction section 13; a rectifying section 14; a fan section 15.
The length of the airfoil section 11 is 120mm, the inner diameter of the airfoil section is 100mm, two triangular airfoils with the aspect ratio of 1:1.73 are arranged in the airfoil section, and the two triangular airfoils are used for generating airflow vortices;
the length of the working section 12 is 60mm, and the diameter of an outlet is 100 mm;
the length of the contraction section 13 is 140mm, the diameter of the inlet end is 200mm, the diameter of the outlet end is 100mm, and the area contraction ratio is 1: 4;
the length of the flow guide section 14 is 100mm, the inner diameter of the flow guide section is 200mm, a honeycomb device is arranged in the middle of the flow guide section, the outer diameter of the honeycomb device is 200mm, the thickness of the honeycomb device is 30mm, the honeycomb device is processed by a stainless steel sheet with the thickness of 0.5mm, and the honeycomb device is embedded in a round pipe of the flow guide section.
The length of the fan section 15 is 567mm, the height is 300mm, the middle section is embedded with a low-noise axial fan with the noise not more than 65dBA and the fan to provide an air source, and the minimum air quantity is not less than 1000 liters/minute (60 m) 3 /h)。
(2) Pitch and roll device
The pitch and roll apparatus comprises 2: a pitch mechanism 21, a support mechanism 22, and a roll mechanism 23.
The pitching mechanism 21 is formed by a stepping motor with a worm and gear mechanism rotating at a rotation angle of +/-180 degrees, and the stepping motor drives the worm and gear mechanism to rotate. The transmission ratio is 180: 1, the repeated positioning precision is 0.005 degrees, the angular speed is 15 degrees/second, and the central bearing capacity is 10 kg.
The support mechanism 22 adopts a U-shaped support for supporting the vortex generator, is made of aluminum alloy materials, and is additionally provided with weight reduction grooves in order to reduce the weight of the structure.
The rolling mechanism 23 is formed by a stepping motor with a worm and gear mechanism rotating at a rotation angle of +/-180 degrees, and the stepping motor drives the worm and gear mechanism to rotate. The transmission ratio is 360: 1, the repeated positioning precision is 0.002 degrees, the angular speed is 30 degrees/second, and the central bearing capacity is 50 kg.
(3) Attitude and vortex speed control device
The attitude and vortex speed control device 3 includes: a standard cabinet 31, a measurement and control computer 32, a turntable motor driver 33, a wind source motor driver 34 and a wind source motor control board 35.
The standard cabinet 31 adopts a 19-inch standard industrial cabinet, the width is 600mm, the depth is 600mm, and the height is 1600 mm;
the measurement and control computer 32 adopts a Hua case and a mainboard (PCA-6006LV), P4-2.4/80G/1G/52XCD and Windows XP operating system;
the turntable motor driver 33 adopts a KSG1-40A direct current voltage regulator of Kaiser electric Co., Ltd, Leqing;
the wind source motor driver 34 adopts a double-shaft stepping motor driver Y100SC (02) of Beijing Jiangyun opto-electronic technology, Inc.;
the wind source motor control board 35 is a PCI-6024E card manufactured by NI corporation for controlling the wind source motor driver and collecting signals of wind speed, pressure, etc.
The vortex generator provided by the embodiment of the invention has a better technical effect.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (4)
1. An adjustable parameter vortex generator, comprising: the device comprises a blade tip vortex generating device (1), a pitching and rolling device (2) and a posture and vortex speed control device (3), wherein the blade tip vortex generating device (1) and the pitching and rolling device (2) are connected through a turbine worm mechanism, the blade tip vortex generating device (1) and the pitching and rolling device (2) are respectively connected with the posture and vortex speed control device (3) through cables, the blade tip vortex generating device (1) comprises an airfoil section (11), a working section (12), a contraction section (13), a rectifying section (14) and a fan section (15), wherein the airfoil section (11) and the working section (12) are sleeved, the working section (12) and the contraction section (13) are sleeved, the contraction section (13) and the rectifying section (14) are sleeved, the rectifying section (14) and the fan section (15) are sleeved, the length of the airfoil section (11) is 120mm, the inner diameter is 100mm, and two built-in triangular airfoils with the aspect ratio of 1:1.73 are arranged, the length of the fan section (15) is 567mm, the height is 300mm, the middle section of the fan section (15) is embedded with an axial flow fan and a fan, the noise is lower than 65dBA, the length of the working section (12) is 60mm, and the diameter of an outlet is 100 mm; the length of the contraction section (13) is 140mm, the diameter of the inlet end is 200mm, the diameter of the outlet end is 100mm, and the area contraction ratio is 1: 4; the length of the rectifying section (14) is 100mm, and the inner diameter is 200 mm.
2. The vortex generator according to claim 1, wherein the pitch and roll device (2) comprises a pitch mechanism (21), a support mechanism (22) and a roll mechanism (23), wherein the pitch mechanism (21) and the support mechanism (22) are bolted and the support mechanism (22) and the roll mechanism (23) are bolted.
3. The vortex generator according to claim 2, wherein the support means (22) is a U-shaped bracket.
4. The vortex generator according to claim 3, wherein the material of the U-shaped bracket is an aluminum alloy material, and weight-reducing grooves are provided on both arms of the U-shaped bracket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910997574.3A CN110844116B (en) | 2019-10-18 | 2019-10-18 | Parameter-adjustable vortex generator |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910997574.3A CN110844116B (en) | 2019-10-18 | 2019-10-18 | Parameter-adjustable vortex generator |
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| CN110844116A CN110844116A (en) | 2020-02-28 |
| CN110844116B true CN110844116B (en) | 2022-09-30 |
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Citations (2)
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| CN108100300A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of whirlpool generating means for whole elimination room paddle-vortex interaction experiment |
| CN207946209U (en) * | 2018-02-05 | 2018-10-09 | 百林机电科技（苏州）有限公司 | A kind of low-speed jet device |
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| JPH07286935A (en) * | 1994-04-19 | 1995-10-31 | Nippon Kagaku Kogyo Kk | Low Noise Axial Blower in Circulating Wind Tunnel Equipment |
| CN2372230Y (en) * | 1998-07-17 | 2000-04-05 | 申振华 | Blade of high-lift helicopter rotor |
| US7100875B2 (en) * | 2004-02-20 | 2006-09-05 | The Boeing Company | Apparatus and method for the control of trailing wake flows |
| US20170137116A1 (en) * | 2009-07-10 | 2017-05-18 | Peter Ireland | Efficiency improvements for flow control body and system shocks |
| US9909425B2 (en) * | 2011-10-31 | 2018-03-06 | Pratt & Whitney Canada Corporation | Blade for a gas turbine engine |
| FR3003032B1 (en) * | 2013-03-07 | 2015-04-03 | Turbomeca | METHOD AND SYSTEM FOR CONTROLLING THE HEALTH OF AN AIRCRAFT TURBOMACHINE |
| CN204606209U (en) * | 2015-04-20 | 2015-09-02 | 中国直升机设计研究所 | A kind of low noise blade tip |
| CN105092204A (en) * | 2015-07-24 | 2015-11-25 | 南京航空航天大学 | Apparatus used for helicopter rotor blade-vortex interference noise experiment |
| CN105181289A (en) * | 2015-09-14 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Fairing for empennage wind tunnel testing |
| CN105923155B (en) * | 2016-06-08 | 2018-11-23 | 南京航空航天大学 | A kind of low noise blade for rotor craft |
| CN106919749B (en) * | 2017-02-24 | 2020-03-10 | 湖北工业大学 | Low-noise wind turbine blade design method and low-noise wind turbine blade |
| CN108317101A (en) * | 2018-03-27 | 2018-07-24 | 广东顺威精密塑料股份有限公司 | A kind of tab construction of cross flow fan |
| CN109747818B (en) * | 2018-12-30 | 2021-09-03 | 南京航空航天大学 | Helicopter rotor wing aerodynamic interference control method based on blade tip mass jet |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100300A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of whirlpool generating means for whole elimination room paddle-vortex interaction experiment |
| CN207946209U (en) * | 2018-02-05 | 2018-10-09 | 百林机电科技（苏州）有限公司 | A kind of low-speed jet device |
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