CN108775850A - A kind of plane cascade test device and its test method that can continuously become blade tip clearance - Google Patents
A kind of plane cascade test device and its test method that can continuously become blade tip clearance Download PDFInfo
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- CN108775850A CN108775850A CN201810595394.8A CN201810595394A CN108775850A CN 108775850 A CN108775850 A CN 108775850A CN 201810595394 A CN201810595394 A CN 201810595394A CN 108775850 A CN108775850 A CN 108775850A
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- 238000012360 testing method Methods 0.000 title claims abstract description 164
- 238000010998 test method Methods 0.000 title claims abstract description 7
- 238000007789 sealing Methods 0.000 claims description 30
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- 238000000034 method Methods 0.000 abstract description 30
- 230000008859 change Effects 0.000 abstract description 13
- 230000001052 transient effect Effects 0.000 abstract description 9
- 238000011160 research Methods 0.000 description 16
- 230000008569 process Effects 0.000 description 15
- 238000002474 experimental method Methods 0.000 description 10
- 230000006872 improvement Effects 0.000 description 7
- 238000013461 design Methods 0.000 description 5
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- 238000010586 diagram Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 241001212149 Cathetus Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/14—Measuring arrangements characterised by the use of mechanical techniques for measuring distance or clearance between spaced objects or spaced apertures
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/003—Measuring of motor parts
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Abstract
The present invention discloses a kind of plane cascade test device and test method that can continuously become blade tip clearance, including cascade test part, mounting bracket, and mounting bracket includes being provided with test surfaces, is provided with cavity in mounting bracket, further includes driving device.Include the following steps：Step S1：The distance of cascade test part distance from top test surfaces is set as h0；Step S2：Setting linear motor tache motorice sets linear motor tache motorice to movement travel-S when being moved far from test surfaces to movement travel ﹢ S when being moved close to test surfaces；Step S3：Height H=h0+S of cascade test part when linear motor is moved to close test surfaces, height H=h0-S of the cascade test part when linear motor is moved to separate test surfaces.Effective realize continuously adjusts within the scope of the required blade tip clearance studied；It can be used in studying the Transient Aerodynamic characteristic of blade tip clearance change procedure；When studying the experimental study of blade tip clearance scheme, does not have to replace testpieces, can significantly shorten test period.
Description
Technical field
The present invention relates to cascade test engineering device technique fields, are a kind of planes that can continuously become blade tip clearance specifically
Cascade test device and its test method.
Background technology
Blade tip clearance is to arrive the distance between casing at the top of compressor or turbine cascade, is compressor and turbine cascade gas
One of the great influence parameter of dynamic performance.Blade tip clearance can lead to leaf top flow leakage, can generate serious shadow to impeller performance
It rings, such as：1. leaf top leaks so that it is logical not flow through impeller directly from blade inlet edge by interval outflow blade trailing edge for segment fluid flow
Road expansion work reduces impeller acting ability；2. blade-tip leakage flow interacts after entering mainstream channel with mainstream, blending, and
It induces a variety of flowing whirlpools to interact, change flow field structure and increases flow losses, reduces impeller engine efficiency.
Blade tip clearance flows and its is a complicated flow process with the interaction of mainstream, includes mainly：1. by leaf
Basin forces fluid to be leaked from leaf basin side to blade back side through blade tip clearance with blade back pressure difference, forms leakage vortex system and changes blade and bears
Lotus is distributed；2. the influence that blade tip and the boundary-layer of blade root flow gap；3. the relative motion between blade and casing is to leakage stream
Dynamic influence；4. tip clearance size influences, gap is bigger, and leakage flow is stronger.In order to explore and grasp blade-tip leakage flow stream
Dynamic feature and its influence to impeller performance, it usually needs the Cascade Aerodynamics of different blade tip clearance schemes are studied.
It is usually relatively easy from flowing in terms of research blade tip clearance is to the affecting laws and PHYSICAL MECHANISM of Cascade Aerodynamics
Binary plane leaf grating start with, be illustrated in figure 3 consider blade tip clearance cascade test part schematic diagram.
Plane cascade test is the fundamental test research project in turbomachine aerodynamic Design field, be compressor and
Most economical, most quick, the most effective technological approaches of blade profile aeroperformance is verified and checked in turbine pneumatic design.To calming the anger
In the basic research of machine and turbo blade performance, other than constantly carrying out blade design, the research of performance improvement scheduling theory,
A large amount of plane cascade test is also carried out, theoretical research is verified.It, can be to the property of leaf grating by plane cascade test
There can be deep understanding, understand aeroperformance of the blade profile under different schemes, and be the design and manufacture stockpile of new blade profile,
It is of great significance for compressor and turbine overall performance to improving.Plane cascade test equipment is mainly by air inlet section, steady
Determine the compositions such as section, jet pipe, plane cascade test part and exhaust section.
The method that traditional plane cascade test changes blade tip clearance
Different blade tip clearance schemes are being studied in the plane cascade test research process that cascade performance influences, traditional experiment side
Method is to process the plane cascade test part of different height.Process the cascade test part of different height h before experiment, when experiment passes through
The h cascade tests part of different height is replaced to carry out the plane cascade test research of different blade tip clearance δ schemes.
Linear motor brief introduction：
Linear motor be it is a kind of electric energy is directly changed into linear motion mechanical energy, without the biography of any intermediate conversion mechanism
Dynamic device.The shape of linear motor can be flat, U-type groove formula, cylinder and tubular type, which kind of construction is most suitable for seeing reality
The specification requirement of application and working environment.
The fixing end of linear motor is known as primary, and parts moving linearly is known as secondary.In practical application, by primary and secondary
Grade is manufactured into different length and shape, to ensure that the coupling in required stroke range between primary and secondary remains unchanged.
The method that traditional plane cascade test changes blade tip clearance is the plane cascade test by processing different height
Part is realized, so a blade tip clearance scheme just needs to process a set of plane cascade test part.Different height are determined before experiment
The cascade test part for spending h, to carry out the plane cascade test research of different blade tip clearance δ schemes.Carrying out different blade tip clearances
It needs to process more set plane cascade test parts when scheme experimental study, this makes the research work of blade tip clearance parameter select
In the range of there are scales, i.e. experimental study cannot obtain research range internal lobe top gap parameter property pneumatic to plane cascade
The consecutive variations rule of energy, and the transient changing process of plane cascade aeroperformance in blade tip clearance change procedure cannot be studied.
Invention content
The purpose of the present invention is to provide a kind of plane cascade test device that can continuously become blade tip clearance and its experiment sides
Method, when carrying out different blade tip clearance schemes in capable of effectively being studied for current plane cascade test, the processing of cascade test part
It is with high costs caused by number of packages is more, blade tip clearance parameter cannot not obtained to the consecutive variations rule of plane cascade aeroperformance and not
The problem of transient changing process study of plane cascade aeroperformance in blade tip clearance change procedure can be carried out.
The present invention is achieved through the following technical solutions：
A kind of plane cascade test device that can continuously become blade tip clearance, including multiple cascade test parts arranged in parallel,
Mounting bracket for installing multiple cascade test parts, the mounting bracket include being provided with test surfaces, are provided in the mounting bracket
Cavity for installing multiple cascade test parts further includes being connect with multiple cascade test parts and for driving multiple cascade tests
The driving device of close/separate test surfaces of part.
Operation principle：In use, the driving device that operating personnel's control is connect with cascade test part is tested to close/separate
Face moves, since leaf grating testpieces close to test surfaces side is to immobilize at a distance from test surfaces before driving device works
, by controlling the driving device to close/stroke far from test surfaces so that height of the cascade test part in cavity becomes
Change；It can be effectively obtained consecutive variations rule of the blade tip clearance parameter to plane cascade aeroperformance by the variation of height,
Be conducive to research of the researcher to the transient changing process of plane cascade aeroperformance in blade tip clearance change procedure simultaneously；Phase
Than the prior art, the present invention only needs a set of cascade test part that experiment can be completed, and can effectively reduce cost.
Further, in order to preferably realize the present invention, the mounting bracket include the wainscot for being provided with test surfaces, with it is upper
Siding lower wall panels disposed in parallel and two bolts being arranged between wainscot and lower wall panels, two bolts, upper walls
Plate and lower wall panels form the cavity for installing multiple cascade test parts；The lower wall panels are connect with driving device.
Further, in order to preferably realize that the present invention, the cascade test part are provided with fortune close to one end of lower wall panels
Dynamic guide rod, the lower wall panels are provided with the second dynamic sealing guide groove；The movement guide rod passes through the second dynamic sealing guide groove to be filled with driving
Set connection.
Further, in order to preferably realize the present invention, the driving device includes and movement guide rod is far from cascade test
Part one end connect and with lower wall panels maneuvering board disposed in parallel, the linear motor being arranged between maneuvering board and lower wall panels；It is described
The tache motorice of linear motor is connect with maneuvering board, and the fixing end of linear motor is connect with lower wall panels.
Further, in order to preferably realize that the present invention, the lower wall panels are additionally provided with close to the side of wainscot and are used for
The first dynamic sealing guide groove of close lower wall panels one end of cascade test part, the first dynamic sealing guide groove and the second dynamic sealing are installed
Guide groove is connected to；The cascade test part, the first dynamic sealing guide groove and the second dynamic sealing guide groove quantity it is identical and correspond set
It sets.
Further, in order to preferably realize the present invention, the multiple cascade test part spaced set being mutually parallel.
A kind of test method for the plane cascade test device that can continuously become blade tip clearance, specifically includes following steps：
Step S1：Linear motor is set before movement, the distance of cascade test part distance from top lower wall panels test surfaces is h0；
Step S2：The tache motorice of linear motor is controlled to close/movement travel S far from test surfaces, setting linear motor moves
It is ﹢ S, movement when setting linear motor tache motorice is moved to separate test surfaces to hold to movement travel when being moved close to test surfaces
Stroke is-S；
Step S3：It is calculated:Height H=h0+S of cascade test part when linear motor is moved to close test surfaces, when straight
Height H=h0-S of the line motor to cascade test part when being moved far from test surfaces.
Compared with prior art, the present invention haing the following advantages and advantageous effect：
（1）The present invention can be realized effectively to be continuously adjusted within the scope of the required blade tip clearance studied；
（2）The present invention can be used in studying the Transient Aerodynamic characteristic of blade tip clearance change procedure；
（3）The configuration of the present invention is simple, it is easy to accomplish, reduce testpieces processing charges in different blade tip clearance research process；
（4）When the present invention is used to study the experimental study of blade tip clearance scheme, do not have to replace testpieces, when can significantly shorten experiment
Between.
Description of the drawings
Fig. 1 is the elevation of experimental rig in the present invention；
Fig. 2 is the connection relationship diagram of cathetus motor and lower wall panels of the present invention；
Fig. 3 is the cascade test part schematic diagram for considering blade tip clearance；
Wherein 1- cascade tests part, 21- bolts, 22- lower wall panels, the second possum bellies of 221-, the second possum bellies of 222-, 23-
Wainscot, 231- test surfaces, 31- tache motorices, 32- fixing ends, 33- move guide plate.
Specific implementation mode
The present invention is described in further detail with reference to embodiment, embodiments of the present invention are not limited thereto.
Embodiment 1：
The present invention is achieved through the following technical solutions, as Figure 1-Figure 2, a kind of plane cascade examination that can continuously become blade tip clearance
Experiment device, including multiple cascade test parts 1 arranged in parallel, the mounting bracket for installing multiple cascade test parts 1, it is described
Mounting bracket includes being provided with test surfaces 231, and the cavity for installing multiple cascade test parts 1 is provided in the mounting bracket, also
Include connect with multiple cascade test parts 1 and for drive multiple cascade test parts 1 it is close/the driving dress far from test surfaces 231
It sets.
It should be noted that by above-mentioned improvement, in use, operating personnel control the driving being connect with cascade test part 1
Device is moved to close/separate test surfaces 231, due to working preceding leaf grating testpieces 1 close to 231 side of test surfaces in driving device
It is changeless at a distance from test surfaces 231, by controlling the driving device to close/stroke far from test surfaces 231 so that
Height of the cascade test part 1 in cavity changes；It can be effectively obtained blade tip clearance parameter pair by the variation of height
The consecutive variations rule of plane cascade aeroperformance, while being conducive to researcher to plane cascade in blade tip clearance change procedure
The research of the transient changing process of aeroperformance；Compared with prior art, the present invention only needs a set of cascade test part 1 can be completed
Experiment, effectively reduces at low cost.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 2：
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1, the mounting bracket includes being provided with survey
The wainscot 23 in examination face 231, with 23 lower wall panels 22 disposed in parallel of wainscot and setting wainscot 23 and lower wall panels 22 it
Between two bolts 21, two bolts 21, wainscot 23 and lower wall panels 22 are formed for installing multiple cascade test parts
1 cavity；The lower wall panels 22 are connect with driving device.
It should be noted that by above-mentioned improvement, the mounting bracket include the wainscot 23 for being provided with test surfaces 231, with
23 lower wall panels 22 disposed in parallel of wainscot and two bolts 21 being arranged between wainscot 23 and lower wall panels 22, two institutes
State the cavity of bolt 21, test surfaces 231 and the formation of lower wall panels 22 for installing multiple cascade test parts 1；The lower wall panels 22
It is connect with driving device；The test surfaces 231 are arranged in wainscot 23 close to the side of cascade test part 1.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 3：
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Fig. 2, the cascade test part 1 is under
One end of siding 22 is provided with movement guide rod, and the lower wall panels 22 are provided with the second dynamic sealing guide groove 222；The movement guide rod is worn
The second dynamic sealing guide groove 222 is crossed to connect with driving device.
It should be noted that by above-mentioned improvement, movement guide rod, the second possum belly, the quantity of cascade test part 1 are identical
And it is arranged in a one-to-one correspondence.In use, multiple cascade test parts 1 are led by being adjacent to the movement of 22 side of lower wall panels connection respectively
Bar and driving device connection realize that gap of the cascade test part 1 between 23 side of wainscot and wainscot 23 changes；
By the second dynamic sealing guide groove 222, effectively the direction of motion for moving guide rod is limited.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 4：
The present embodiment advanced optimizes on the basis of the above embodiments, as shown in Figure 1, the driving device includes and movement
Guide rod far from 1 one end of cascade test part connect and with 22 maneuvering board 33 disposed in parallel of lower wall panels, setting maneuvering board 33 under
Linear motor between siding 22；The tache motorice 31 of the linear motor is connect with maneuvering board 33, the fixing end 32 of linear motor
It is connect with lower wall panels 22.
The one end of the telemechanical guide rod far from cascade test part 1 is fixedly connected with maneuvering board 33, the tache motorice of linear motor
31 are threadedly coupled with maneuvering board 33, and the fixing end 32 of linear motor is fixedly connected by connecting bolt with lower wall panels 22.
The lower wall panels 22 are additionally provided with the close lower wall panels for installing cascade test part 1 close to the side of wainscot 23
The first dynamic sealing guide groove 221 of 22 one end, the first dynamic sealing guide groove 221 are connected to the second dynamic sealing guide groove 222；The leaf
Grid testpieces 1, the first dynamic sealing guide groove 221 and 222 quantity of the second dynamic sealing guide groove are identical and be arranged in a one-to-one correspondence.
First dynamic sealing guide groove 221 is set so that is more clear earth's surface for height of the cascade test part 1 in cavity
Show.
The multiple 1 spaced set of cascade test part being mutually parallel.Spaced set avoids spacing unequal to rear
Phase research impacts.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 5：
As shown in Figure 1, a kind of test method for the plane cascade test device that can continuously become blade tip clearance, specifically includes following step
Suddenly：
Step S1：Linear motor is set before movement, the distance of 1 distance from top lower wall panels of cascade test part, 22 test surfaces 231
For h0；
Step S2：The tache motorice 31 of linear motor is controlled to close/movement travel S far from test surfaces 231, sets linear motor
Tache motorice 31 is ﹢ S to movement travel when being moved close to test surfaces 231, and setting linear motor tache motorice 31 is to far from test surfaces
Movement travel when 231 movement is-S；
Step S3：It is calculated:Height H=h0+S of cascade test part 1 when linear motor is to close to the movement of test surfaces 231,
Height H=h0-S of cascade test part 1 when linear motor is to far from the movement of test surfaces 231.
It should be noted that by above-mentioned improvement, ground at present in the plane cascade test for carrying out different blade tip clearance schemes
When studying carefully, the method for generally use is to process the high plane cascade test part 1 of different leaves to realize, a blade tip clearance scheme just needs
A set of plane cascade test part 1 is processed, and the blade tip clearance studied cannot continuously adjust during the test.But in Ye Ding
Gap parameter during the experimental study that Cascade Aerodynamics influence on generally requiring to be carried out not according to plane cascade test result
Disconnected adjusting, therefore testpieces replaces that complicated, test period is long and experiment when can cause to carry out different blade tip clearance project studies
The extremely high problem of part processing charges；It is unable to get research range internal lobe top gap parameter in the prior art to plane leaf simultaneously
The consecutive variations rule of grid aeroperformance and the transient state change that plane cascade aeroperformance in blade tip clearance change procedure cannot be studied
Change process.
Compared to existing, the design can be conducive to researcher for cascade test part 1 close to surveying using linear motor
231 side gap parameter of examination face is to the consecutive variations rule of plane cascade aeroperformance and cannot carry out blade tip clearance change procedure
The problem of transient changing process study of middle plane cascade aeroperformance.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
Embodiment 6：
The present embodiment most preferred embodiment, as Figure 1-Figure 2, a kind of plane cascade test device that can continuously become blade tip clearance,
Including multiple cascade test parts 1 arranged in parallel, the mounting bracket for installing multiple cascade test parts 1, the mounting bracket
Including being provided with test surfaces 231, the cavity for installing multiple cascade test parts 1 is provided in the mounting bracket, further include with
The connection of multiple cascade test parts 1 and for drive multiple cascade test parts 1 it is close/driving device far from test surfaces 231.
The mounting bracket includes the wainscot 23 for being provided with test surfaces 231 and 23 lower wall panels 22 disposed in parallel of wainscot
And two bolts 21 being arranged between wainscot 23 and lower wall panels 22, two bolts 21, wainscot 23 and lower wall
Plate 22 forms the cavity for installing multiple cascade test parts 1；The lower wall panels 22 are connect with driving device.Two bolts 21 with
Wainscot 23 and lower wall panels 22 are fixed in nut cooperation.
The cascade test part 1 is provided with movement guide rod close to one end of lower wall panels 22, and the lower wall panels 22 are provided with
Two dynamic sealing guide grooves 222；The movement guide rod is connect across the second dynamic sealing guide groove 222 with driving device.
Second possum belly is 3mm ~ 12mm along the depth of guide rod length direction is moved.
The driving device includes connecting far from 1 one end of cascade test part with movement guide rod and being arranged in parallel with lower wall panels 22
Maneuvering board 33, the linear motor that is arranged between maneuvering board 33 and lower wall panels 22；The tache motorice 31 of the linear motor and fortune
Movable plate 33 connects, and the fixing end 32 of linear motor is connect with lower wall panels 22.
The lower wall panels 22 are additionally provided with the close lower wall panels for installing cascade test part 1 close to the side of wainscot 23
The first dynamic sealing guide groove 221 of 22 one end, the first dynamic sealing guide groove 221 are connected to the second dynamic sealing guide groove 222；The leaf
Grid testpieces 1, the first dynamic sealing guide groove 221 and 222 quantity of the second dynamic sealing guide groove are identical and be arranged in a one-to-one correspondence.
First dynamic sealing guide groove 221 is 2mm ~ 15mm along the depth for the length direction for moving guide rod length direction.The movement is led
A diameter of 2 ~ 10mm of bar.The lower wall panels 22 are the depth and second of the first possum belly along the thickness of guide rod length direction is moved
The summation of possum belly depth.
The multiple 1 spaced set of cascade test part being mutually parallel.
The linear motor is provided with the linear encoder of ± 1 μm of control accuracy, and linear motor and linear encoder are
The prior art is not belonging to the improvement of the present invention, does not repeat this its internal structure；
It should be noted that by above-mentioned improvement, the present invention can effectively be directed in the research of current plane cascade test and open
When opening up different blade tip clearance schemes, cascade test part 1 is with high costs caused by processing number of packages mostly, cannot obtain blade tip clearance parameter
To the consecutive variations rule of plane cascade aeroperformance and plane cascade aeroperformance in blade tip clearance change procedure cannot be carried out
Transient changing process study the problem of.
The other parts of the present embodiment are same as the previously described embodiments, and so it will not be repeated.
The above is only presently preferred embodiments of the present invention, not does limitation in any form to the present invention, it is every according to
According to the technical spirit of the present invention to any simple modification, equivalent variations made by above example, the protection of the present invention is each fallen within
Within the scope of.
Claims (7)
1. a kind of plane cascade test device that can continuously become blade tip clearance, including multiple cascade test parts arranged in parallel
（1）, for installing multiple cascade test parts（1）Mounting bracket, the mounting bracket include be provided with test surfaces（231）, the peace
It is provided in shelving for installing multiple cascade test parts（1）Cavity, it is characterised in that：Further include and multiple cascade test parts
（1）It connects and for driving multiple cascade test parts（1）Close/far from test surfaces（231）Driving device.
2. a kind of plane cascade test device that can continuously become blade tip clearance according to claim 1, it is characterised in that：Institute
It includes being provided with test surfaces to state mounting bracket（231）Wainscot（23）With wainscot（23）Lower wall panels disposed in parallel（22）With
And it is arranged in wainscot（23）With lower wall panels（22）Between two bolts（21）, two bolts（21）, wainscot（23）,
And lower wall panels（22）It is formed for installing multiple cascade test parts（1）Cavity；The lower wall panels（22）Connect with driving device
It connects.
3. a kind of plane cascade test device that can continuously become blade tip clearance according to claim 2, it is characterised in that：Institute
State cascade test part（1）Close to lower wall panels（22）One end be provided with movement guide rod, the lower wall panels（22）It is dynamic to be provided with second
Possum belly（222）；The movement guide rod passes through the second dynamic sealing guide groove（222）It is connect with driving device.
4. a kind of plane cascade test device that can continuously become blade tip clearance according to claim 3, it is characterised in that：Institute
Driving device is stated to include and move guide rod far from cascade test part（1）One end connects and and lower wall panels（22）Movement disposed in parallel
Plate（33）, be arranged in maneuvering board（33）With lower wall panels（22）Between linear motor；The tache motorice of the linear motor（31）With
Maneuvering board（33）Connection, the fixing end of linear motor（32）With lower wall panels（22）Connection.
5. a kind of plane cascade test device that can continuously become blade tip clearance according to claim 4, it is characterised in that：Institute
State lower wall panels（22）Close to wainscot（23）Side be additionally provided with for installing cascade test part（1）Close lower wall panels（22）
The first dynamic sealing guide groove of one end, the first dynamic sealing guide groove and the second dynamic sealing guide groove（222）Connection；The cascade test
Part（1）, the first dynamic sealing guide groove and the second dynamic sealing guide groove（222）Quantity is identical and is arranged in a one-to-one correspondence.
6. special according to a kind of plane cascade test device that can continuously become blade tip clearance of claim 1-5 any one of them
Sign is：The multiple cascade test part being mutually parallel（1）Spaced set.
7. a kind of test method of plane cascade test device that can continuously become blade tip clearance according to claim 6,
It is characterized in that：Specifically include following steps：
Step S1：Linear motor is set before movement, cascade test part（1）Distance from top lower wall panels（22）Test surfaces（231）
Distance be h0；
Step S2：Control the tache motorice of linear motor（31）To close/separate test surfaces（231）Movement travel S, set straight line
Motor movement end（31）To close to test surfaces（231）Movement travel when movement is ﹢ S, sets linear motor tache motorice（31）To
Far from test surfaces（231）Movement travel when movement is-S；
Step S3：It is calculated:When linear motor is to close to test surfaces（231）Cascade test part when movement（1）Height H=
H0+S, when linear motor is to far from test surfaces（231）Cascade test part when movement（1）Height H=h0-S.
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| CN201810595394.8A CN108775850B (en) | 2018-06-11 | 2018-06-11 | Planar blade cascade test device capable of continuously changing blade top gap and test method thereof |
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| CN201810595394.8A CN108775850B (en) | 2018-06-11 | 2018-06-11 | Planar blade cascade test device capable of continuously changing blade top gap and test method thereof |
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| CN108775850B CN108775850B (en) | 2024-01-19 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111579197A (en) * | 2020-03-25 | 2020-08-25 | 西北工业大学 | Gap-variable plane blade cascade gap adjustment experimental device and method |
| CN112729751A (en) * | 2020-12-30 | 2021-04-30 | 哈尔滨工业大学 | Test bed |
| CN112881026A (en) * | 2019-11-13 | 2021-06-01 | 中国航发商用航空发动机有限责任公司 | Back-thrust blade cascade for blade density adjustable test |
| 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 |
| CN113418716A (en) * | 2021-06-05 | 2021-09-21 | 西北工业大学 | Blade cascade experimental device with adjustable blade top clearance |
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