CN110530595A - A kind of plane cascade test platform test section inlet system of the adjustable angle of attack - Google Patents
A kind of plane cascade test platform test section inlet system of the adjustable angle of attack Download PDFInfo
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- CN110530595A CN110530595A CN201910652577.3A CN201910652577A CN110530595A CN 110530595 A CN110530595 A CN 110530595A CN 201910652577 A CN201910652577 A CN 201910652577A CN 110530595 A CN110530595 A CN 110530595A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention provides a kind of plane cascade test platform test section inlet systems of adjustable angle of attack, to there is the turbine test platform for becoming angle of attack demand to provide a kind of individually change angle of attack scheme of implementation and simple structure.Inlet system is made of prepass, intermediate channel and rear channel, is mainly constituted by rectifying four section components of leaf grating in front stretching plate, intermediate plate, rear expansion plate and channel.Respectively there is rectification leaf grating at one in three channels, can be rotated between front stretching plate and rear expansion plate and intermediate plate by axis connection, intermediate plate is moved up and down by displacement mechanism drive, changes rear channel and axial angle, to change the test section inlet air flow angle of attack.When adjusting the angle of attack, the angle of attack is increased or reduced, and antero-posterior pathway is elongated or shortened by expansion plate, and inlet system axis projection is apart from constant.Straightener(stator) blade uses NACA blade profile, and through over commutation leaf grating, the channel exit uniformity after meets test section import requirement to channel interior air-flow, is computed, inlet system pitot loss is within 5%.
Description
Technical field
The invention belongs to aero-engine cascade test platform technical fields, are related to a kind of subsonic speed plane cascade test platform,
Especially a kind of test section inlet system that can be used for adjusting the subsonic speed plane cascade test platform leaf grating angle of attack.
Background technique
Plane cascade test platform is the important device for measuring blade aerodynamic performance and air film cooling performance, is tried at present in leaf grating
In testing, multiple operating points of leaf grating can nearly all be measured, Main change parameter includes free stream Mach number and the leaf grating angle of attack
Deng.It is wherein directed to the angle of attack variation of leaf grating, the mode that the testing stand of mainstream is all made of the rotation of leaf grating clutch disk at present is adjusted
Section, but structure is complicated for the regulative mode of this type, and each blade in leaf grating is also changed while changing the angle of attack
Thus the relative position of leading edge line position and tailgate and exit passageway can generate more uncontrollable factor.In this regard, being asked for this
Topic, we devise a kind of plane cascade test platform test section inlet system of adjustable angle of attack, are suitable for suitable Mach number
And range of angles of attack, the inlet system do not change the flow field type face in test section, can the separately adjustable angle of attack, structure simple possible.
Summary of the invention
Goal of the invention: angle of attack tune is adjusted by the way of the rotation of leaf grating clutch disk for the testing stand of current mainstream
Various drawbacks possessed by saving, we design a kind of plane cascade test platform test section import of simply adjustable angle of attack of structure
System, be allowed to be suitable for suitable Mach number and range of angles of attack, the separately adjustable angle of attack of the inlet system, do not change test section other
Uncorrelated factor.
To achieve the above object, present invention employs following technical solutions:
A kind of plane cascade test platform test section inlet system of the adjustable angle of attack, the system by front stretching plate, intermediate plate,
Expansion plate respectively constitutes prepass, intermediate channel and rear channel afterwards, respectively there is rectification leaf grating at one in three channels；Front stretching plate and
The outer end of expansion plate is fixed afterwards, and inner end and intermediate plate are rotatablely connected by axis, and intermediate plate is moved up and down by displacement mechanism drive, is made
Channel and axial angle change afterwards, to change the test section inlet air flow angle of attack.
Further, the inlet system application conditions are cascade test platform test section inflow Mach number no more than 0.8, and
The positive and negative angle of attack variation of cascade test is between -35 °~35 °.
Further, the front stretching plate and rear expansion plate are made of multi-section retractable nested plates, by between nested plates
The flexible change for adapting to length of nesting；And the front-rear position of the intermediate plate is constant, front stretching plate, intermediate plate and rear expansion plate
Axis projection length do not change with moving up and down for intermediate plate.Intake channel does not almost stress, so conduit wall is very thin,
3mm can meet intensity requirement, then every grade of sleeve wall thickness bring aisle spare changes relative to entire aisle spare ratio very
It is small, it can be neglected.In addition, channel velocity is subsonic speed, aerodynamic loss caused by transition shoulder is minimum between channel level, stream field
Influence also very little.So in practical applications, nested structure can be used.
Further, scalable nested plates are not more than four sections, and each section of contact size is not less than 20cm.
Further, three sections of axis projection length ratios of the front stretching plate, intermediate plate and rear expansion plate are 3:1:3.
Further, rear passage length be not less than 1 meter, rear channel outlet sectional position be located at rectification leaf grating costa on or
Position in costa slightly rearward 1cm, channel outlet flow angle is the test leaf grating angle of attack after guarantee.Herein, rear passage length refers to
Physical length, rather than projected length.
Further, the rectification leaf grating is made of four blades, and blade is NACA blade profile, and rectification leaf grating established angle is always
It is consistent with the place channel airflow angle of current.
Further, the pitch d of the rectification leaf grating is the ratio of channel height h and number of blade n, and leaf chord length L is 2 times
Pitch d.
Beneficial effects of the present invention: the present invention provides a kind of plane cascade test platform test section import system of adjustable angle of attack
System, be allowed to be suitable for suitable Mach number and range of angles of attack, the separately adjustable angle of attack of the inlet system, do not change test section other not
Correlative factor avoids generating other uncontrollable factors, while the program has many advantages, such as structure is simple, easy to implement.
Detailed description of the invention
Fig. 1 be the leaf grating angle of attack Zi -30 ° to 30 ° variations when channel variation schematic diagram.
Fig. 2 is inlet system structural schematic diagram.
Fig. 3 is that -30 ° of angle of attack lower inlet system centre section Mach number cloud atlas of leaf grating and streamline are superimposed schematic diagram.
Wherein: 1- front stretching plate, 2- intermediate plate, expansion plate after 3-, 4- prepass, 5- intermediate channel, channel after 6-, 7- go out
Mouth section, 8- rectify leaf grating, and 9- tests leaf grating.
Specific embodiment
Specific embodiments of the present invention are further described below in conjunction with attached drawing.In the following description for
It explains purpose and not restrictive, elaborates detail, to help to be fully understood by the present invention.However, to art technology
It will be apparent that the present invention can also be practiced in the other embodiments departing from these details for personnel.
It should be noted that only showing in the accompanying drawings in order to avoid having obscured the present invention because of unnecessary details
Gone out with closely related device structure and/or processing step according to the solution of the present invention, and be omitted with relationship of the present invention not
Big other details.
It is leaf grating in Fig. 1 the invention discloses a kind of plane cascade test platform test section inlet system of adjustable angle of attack
When the angle of attack is Zi -30 ° to 30 ° variations channel change schematic diagram, wherein (a), (b), (c) be respectively the leaf grating angle of attack be -30 °, 0 °,
Channel at 30 ° changes schematic diagram；Fig. 2 inlet system structural schematic diagram, Fig. 3 cut for -30 ° of angle of attack lower inlet system centres of leaf grating
Face Mach number cloud atlas and streamline are superimposed schematic diagram.
The plane cascade test platform test section inlet system of the adjustable test leaf grating angle of attack is logical by prepass 4, centre
Road 5 and rear channel 6 form, mainly by rectifying 8 four section components of leaf grating in front stretching plate 1, intermediate plate 2, rear expansion plate 3 and channel
It constitutes.Respectively there is rectification leaf grating at one in three channels, can be turned between front stretching plate and rear expansion plate and intermediate plate by axis connection
Dynamic, intermediate plate is moved up and down by displacement mechanism drive, changes rear channel and axial angle, to change test section inlet air flow
The angle of attack.
Further, the plane cascade test platform test section inlet system shown to Fig. 3 carries out numerical simulation, realizes examination
Test the inlet conditions of a section Ma=0.45, -30 ° of angles of attack.
Further, the change in direction can occur, in three channel entrances due to air-flow in order to avoid airflow direction changes
Become bring segregation phenomenon, the rectification leaf grating of NACA blade profile is installed respectively in three channels leading edge section, pitch d is channel height
The ratio of h and number of blade n, leaf chord length L are 2 times of pitch d.
Further, since the inlet system connects upstream passageway and downstream tests section, continuously become the angle of attack in test leaf grating
In the process, upstream passageway outlet is constant with downstream tests section entrance location, therefore the axis of front stretching plate, intermediate plate and rear expansion plate
Do not change to projected length with moving up and down for intermediate plate, and front stretching plate and rear expansion plate are by multi-section retractable nested plates
Composition can pass through the flexible change for adapting to length of the nesting between nested plates.
Further, nested plates number is not more than four sections, and to guarantee air-tightness, minimal-contact size can not mistake between each nested plates
Small, according to current machining accuracy and operating experience, which can guarantee air-tightness not less than 20cm.
Further, outlet flow parameter is uniform, direction is consistent in order to make, and rear passage length is not less than 1 meter.In reality
In the application of border, in order to which channel outlet flow angle is the leaf grating angle of attack after guaranteeing, then after channel outlet sectional position should be located at test leaf
Position in 1cm on grid costa or after costa.
Embodiment
It is rear logical in -30 ° of angle of attack lower inlet system centre section Mach number cloud atlas of Fig. 3 leaf grating and streamline superposition schematic diagram
Road near exit air-flow streamline, which is parallel to channel, realizes -30 ° of airflow direction, and outlet Mach number uniformity is
0.442, and 0.45 deviation 1.8% of demand Mach number, it is furthermore computed, air-flow is by the system loss within 5%.To sum up institute
It states, the present invention meets the needs of test section inflow Mach number 0.45, -30 ° of angle of attack operating condition.
The above is only a preferred embodiment of the present invention, it should be pointed out that for those skilled in the art
Various improvements and modifications may be made without departing from the principle of the present invention, for example by rectifying leaf grating in rear channel
Afterwards plus grid further increases the angle of attack and range of Mach numbers expansion that airflow homogeneity applies the present invention, these are improved and profit
Decorations also should be regarded as protection scope of the present invention.
Claims (8)
1. a kind of plane cascade test platform test section inlet system of adjustable angle of attack, it is characterised in that: the system is by front stretching
Plate, intermediate plate, rear expansion plate respectively constitute prepass, intermediate channel and rear channel, respectively there is rectification leaf grating at one in three channels；
The outer end of front stretching plate and rear expansion plate is fixed, and inner end and intermediate plate are rotatablely connected by axis, and intermediate plate is driven by displacement mechanism
It moves up and down, changes rear channel and axial angle, to change the test section inlet air flow angle of attack.
2. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 1, it is characterised in that:
The inlet system application conditions are that cascade test platform test section inflow Mach number is not more than 0.8, and the positive negative angle of attack of cascade test
Variation is between -35 °~35 °.
3. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 1, it is characterised in that:
The front stretching plate and rear expansion plate are made of multi-section retractable nested plates, adapt to length by the way that the nesting between nested plates is flexible
Change；And the front-rear position of the intermediate plate is constant, the axis projection length of front stretching plate, intermediate plate and rear expansion plate not with
Moving up and down for intermediate plate and change.
4. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 3, it is characterised in that:
Scalable nested plates are not more than four sections, and each section of contact size is not less than 20cm.
5. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 3, it is characterised in that:
Three sections of axis projection length ratios of the front stretching plate, intermediate plate and rear expansion plate are 3:1:3.
6. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 1, it is characterised in that:
Passage length is not less than 1 meter afterwards, and rear channel outlet sectional position is located on rectification leaf grating costa or in costa slightly rearward 1cm
Position, channel outlet flow angle is the test leaf grating angle of attack after guarantee.
7. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 1, it is characterised in that:
The rectification leaf grating is made of four blades, blade be NACA blade profile, rectification leaf grating established angle always with place channel airflow stream
It is consistent to angle.
8. the plane cascade test platform test section inlet system of the adjustable angle of attack according to claim 7, it is characterised in that:
The pitch d of the rectification leaf grating is the ratio of channel height h and number of blade n, and leaf chord length L is 2 times of pitch d.
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| CN201910652577.3A CN110530595A (en) | 2019-07-19 | 2019-07-19 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
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| CN201910652577.3A CN110530595A (en) | 2019-07-19 | 2019-07-19 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112683943A (en) * | 2020-12-01 | 2021-04-20 | 西安交通大学 | Turbine experimental apparatus with adjustable pitch |
| CN112747929A (en) * | 2020-11-30 | 2021-05-04 | 南京航空航天大学 | Flow channel adjusting mechanism of cascade test bed for expanding adjusting range of cascade attack angle |
| CN113029574A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Length-adjustable planar cascade test section wallboard |
| CN113029575A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Height-adjustable plane cascade test section |
| CN113029576A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Method for jointly adjusting spray pipe and test section in plane cascade subsonic test device |
| CN114658678A (en) * | 2022-02-21 | 2022-06-24 | 南京航空航天大学 | Tongue plate structure of plane cascade test bed of gas compressor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089545A (en) * | 2011-10-31 | 2013-05-08 | 朱凯瑜 | Closed wind power generating equipment |
| CN104019959A (en) * | 2014-05-30 | 2014-09-03 | 西南交通大学 | Variable attack angel apparatus for wind tunnel test of aircraft engine model |
| CN104595245A (en) * | 2015-01-04 | 2015-05-06 | 南京航空航天大学 | Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof |
| CN104712455A (en) * | 2013-12-12 | 2015-06-17 | 中航商用航空发动机有限责任公司 | Reverse thrust device of fanjet and reverse thrust blade grid applied to reverse thrust device |
| CN107725482A (en) * | 2016-08-10 | 2018-02-23 | 上海电气燃气轮机有限公司 | Improve the sectional-regulated exit guide blade and its governor motion of compressor off design performance |
| CN108253219A (en) * | 2017-12-15 | 2018-07-06 | 中国航空工业集团公司成都飞机设计研究所 | A kind of adjustable hatchcover testing stand air inlet section of airflow direction |
| CN109540453A (en) * | 2018-11-26 | 2019-03-29 | 吉林大学 | A kind of wind tunnel test rack of dimensional airfoil |
-
2019
- 2019-07-19 CN CN201910652577.3A patent/CN110530595A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089545A (en) * | 2011-10-31 | 2013-05-08 | 朱凯瑜 | Closed wind power generating equipment |
| CN104712455A (en) * | 2013-12-12 | 2015-06-17 | 中航商用航空发动机有限责任公司 | Reverse thrust device of fanjet and reverse thrust blade grid applied to reverse thrust device |
| CN104019959A (en) * | 2014-05-30 | 2014-09-03 | 西南交通大学 | Variable attack angel apparatus for wind tunnel test of aircraft engine model |
| CN104595245A (en) * | 2015-01-04 | 2015-05-06 | 南京航空航天大学 | Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof |
| CN107725482A (en) * | 2016-08-10 | 2018-02-23 | 上海电气燃气轮机有限公司 | Improve the sectional-regulated exit guide blade and its governor motion of compressor off design performance |
| CN108253219A (en) * | 2017-12-15 | 2018-07-06 | 中国航空工业集团公司成都飞机设计研究所 | A kind of adjustable hatchcover testing stand air inlet section of airflow direction |
| CN109540453A (en) * | 2018-11-26 | 2019-03-29 | 吉林大学 | A kind of wind tunnel test rack of dimensional airfoil |
Non-Patent Citations (1)
| Title |
|---|
| 蒲永彬: "一体化二元变几何进气道设计及气动性能研究", 《中国优秀硕士学位论文全文数据库 基础科学辑》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112747929A (en) * | 2020-11-30 | 2021-05-04 | 南京航空航天大学 | Flow channel adjusting mechanism of cascade test bed for expanding adjusting range of cascade attack angle |
| CN112683943A (en) * | 2020-12-01 | 2021-04-20 | 西安交通大学 | Turbine experimental apparatus with adjustable pitch |
| CN112683943B (en) * | 2020-12-01 | 2021-11-16 | 西安交通大学 | Turbine experimental apparatus with adjustable pitch |
| CN113029574A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Length-adjustable planar cascade test section wallboard |
| CN113029575A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Height-adjustable plane cascade test section |
| CN113029576A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Method for jointly adjusting spray pipe and test section in plane cascade subsonic test device |
| CN113029575B (en) * | 2021-03-23 | 2022-04-26 | 中国空气动力研究与发展中心空天技术研究所 | Height-adjustable plane cascade test section |
| CN113029574B (en) * | 2021-03-23 | 2022-06-24 | 中国空气动力研究与发展中心空天技术研究所 | Length-adjustable planar cascade test section wallboard |
| CN114658678A (en) * | 2022-02-21 | 2022-06-24 | 南京航空航天大学 | Tongue plate structure of plane cascade test bed of gas compressor |
| CN114658678B (en) * | 2022-02-21 | 2022-12-06 | 南京航空航天大学 | Tongue plate structure of plane cascade test bed of gas compressor |
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