CN208443316U - A kind of plane cascade test device that can continuously become blade tip clearance - Google Patents
A kind of plane cascade test device that can continuously become blade tip clearance Download PDFInfo
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- CN208443316U CN208443316U CN201820898397.4U CN201820898397U CN208443316U CN 208443316 U CN208443316 U CN 208443316U CN 201820898397 U CN201820898397 U CN 201820898397U CN 208443316 U CN208443316 U CN 208443316U
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Abstract
The utility model discloses a kind of plane cascade test device that can continuously become blade tip clearance, including cascade test part, mounting rack, and mounting rack includes being provided with test surfaces, is provided with cavity in mounting rack, further includes driving device.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 replacement testpieces, can significantly shorten test period.
Description
Technical field
The utility model relates to cascade test engineering device technique fields, are that one kind can continuously become blade tip clearance specifically
Plane cascade test device.
Background technique
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 will 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.
1. blade tip clearance flowing and its be a complicated flow process with the interaction of mainstream, specifically includes that by leaf
Basin and blade back pressure difference force fluid to be leaked from leaf basin side through blade tip clearance to blade back side, form leakage vortex system and change blade and bear
Lotus distribution；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 composition 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 examination
Proved recipe method is to process the plane cascade test part of different height.The cascade test part of different height h is processed before test, when test
The plane cascade test research of different blade tip clearance δ schemes is carried out by replacing the h cascade test part of different height.
Linear motor brief introduction:
Linear motor be it is a kind of electric energy is directly changed into linear motion mechanical energy, without any intermediate conversion mechanism
Transmission 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
The specification requirement of practical 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 manufacture is at different length and shape, to guarantee to remain unchanged in the coupling in required stroke range between primary and secondary.
The method of traditional plane cascade test change 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 test
The cascade test part of h is spent, to carry out the plane cascade test research of different blade tip clearance δ schemes.Carrying out different blade tip clearances
Need to process more set plane cascade test parts when scheme experimental study, this is selecting the research work of blade tip clearance parameter
In the range of there are scale, 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.
Utility model content
The purpose of this utility model is to provide the plane cascade test device that one kind can continuously become blade tip clearance, Neng Gouyou
Effect for current plane cascade test research in carry out different blade tip clearance schemes when, cascade test part processing number of packages more cause
It is with high costs, blade tip clearance parameter cannot be obtained to the consecutive variations of plane cascade aeroperformance rule and leaf top cannot be carried out
In the change procedure of gap the problem of the transient changing process study of plane cascade aeroperformance.
The utility model is achieved through the following technical solutions:
A kind of plane cascade test device that can continuously become blade tip clearance, including multiple cascade tests arranged in parallel
Part, the mounting rack for installing multiple cascade test parts, the mounting rack include being provided with test surfaces, setting in the mounting rack
There is the cavity for installing multiple cascade test parts, further includes being connect with multiple cascade test parts and for driving multiple leaf gratings to try
Test the driving device of close/separate test surfaces of part.
Working principle: in use, the driving device that operator's control is connect with cascade test part is tested to close/separate
Face movement, since leaf grating testpieces close to test surfaces side is to immobilize at a distance from test surfaces before driving device works
, by control driving device to close/stroke far from test surfaces, so that height of the cascade test part in cavity becomes
Change；Blade tip clearance parameter can be effectively obtained to the consecutive variations of plane cascade aeroperformance rule 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 utility model only needs a set of cascade test part that test can be completed, and can effectively reduce cost.
Further, in order to preferably realize the utility model, the mounting rack include the wainscot for being provided with test surfaces,
With wainscot lower wall panels disposed in parallel and two bolts being arranged between wainscot and lower wall panels, two bolts,
Wainscot 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 the utility model, the cascade test part is close to the setting of one end of lower wall panels
There is movement 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 and drives
Dynamic device connection.
Further, in order to preferably realize the utility model, the driving device includes with movement guide rod far from leaf grating
The connection of testpieces one end and with lower wall panels maneuvering board disposed in parallel, the linear motor that is arranged between maneuvering board and lower wall panels；
The tache motorice of the 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 the utility model, the lower wall panels are additionally provided with close to the side of wainscot
For installing the first dynamic sealing guide groove of close lower wall panels one end of cascade test part, the first dynamic sealing guide groove and second are moved
Possum belly connection；The cascade test part, the first dynamic sealing guide groove and the second dynamic sealing guide groove quantity is identical and one is a pair of
It should be arranged.
Further, in order to preferably realize that the utility model, the multiple cascade test part being parallel to each other are equidistant
Setting.
A kind of test method for the plane cascade test device that can continuously become blade tip clearance, specifically includes the following steps:
Step S1: before movement, the distance of cascade test part distance from top lower wall panels test surfaces is setting linear motor
h0；
Step S2: the tache motorice of linear motor is controlled to close/movement travel S far from test surfaces, sets linear motor
Tache motorice is ﹢ S to movement travel when moving close to test surfaces, is set when linear motor tache motorice is moved to separate test surfaces
Movement travel is-S；
Step S3: it is calculated: height H=h0+S of the cascade test part when linear motor is moved to close test surfaces,
Height H=h0-S of cascade test part when linear motor is moved to separate test surfaces.
The utility model compared with prior art, have the following advantages that and the utility model has the advantages that
(1) it is continuously adjusted within the scope of the blade tip clearance studied needed for the utility model can be realized effectively；
(2) the utility model can be used in studying the Transient Aerodynamic characteristic of blade tip clearance change procedure；
(3) the utility model have the advantages of simple structure and easy realization, reduce in different blade tip clearance research process testpieces processing
Expense；
(4) when the utility model is used to study the experimental study of blade tip clearance scheme, does not have to replacement testpieces, can significantly contract
Short test period.
Detailed description of the invention
Fig. 1 is the elevation of the utility model；
Fig. 2 is the connection relationship diagram of linear motor and lower wall panels in the utility model；
Fig. 3 is the cascade test part schematic diagram for considering blade tip clearance；
Wherein 1- cascade test part, 21- bolt, 22- lower wall panels, the second possum belly of 221-, the second possum belly of 222-,
23- wainscot, 231- test surfaces, 31- tache motorice, 32- fixing end, 33- move guide plate.
Specific embodiment
The utility model is described in further detail below with reference to embodiment, but the embodiments of the present invention is not
It is limited to this.
Embodiment 1:
The utility model is achieved through the following technical solutions, as Figure 1-Figure 2, a kind of continuously to become the flat of blade tip clearance
Face cascade test device, including multiple cascade test parts 1 arranged in parallel, the peace for installing multiple cascade test parts 1
It shelves, the mounting rack includes being provided with test surfaces 231, is provided in the mounting rack for installing multiple cascade test parts 1
Cavity, further include connect with multiple cascade test parts 1 and for drive multiple cascade test parts 1 it is close/far from test surfaces 231
Driving device.
It should be noted that by above-mentioned improvement, in use, operator controls the driving connecting 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 fixed and invariable at a distance from test surfaces 231, by control driving device to close/stroke far from test surfaces 231, so that
Height of the cascade test part 1 in cavity changes；Blade tip clearance parameter pair can be effectively obtained 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 utility model only needs a set of cascade test part 1
Test is completed, is effectively reduced 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 rack includes setting
Have test surfaces 231 wainscot 23, with the lower wall panels 22 disposed in parallel of wainscot 23 and be arranged in wainscot 23 and lower wall panels
Two bolts 21 between 22, two bolts 21, wainscot 23 and lower wall panels 22 are formed for installing multiple leaf grating examinations
Test the cavity of part 1；The lower wall panels 22 are connect with driving device.
It should be noted that by above-mentioned improvement, the mounting rack include the wainscot 23 for being provided with test surfaces 231, with
The lower wall panels 22 disposed in parallel of wainscot 23 and two bolts 21 being arranged between wainscot 23 and lower wall panels 22, two institutes
It states bolt 21, test surfaces 231 and lower wall panels 22 and forms cavity for installing multiple cascade test parts 1；The lower wall panels 22
It is connect with driving device；Wainscot 23 is arranged in close to the side of cascade test part 1 in the test surfaces 231.
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 leans on
One end of nearly lower wall panels 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 is led
Bar passes through the second dynamic sealing guide groove 222 and connect with driving device.
It should be noted that movement guide rod, the second possum belly, the quantity of cascade test part 1 are identical by above-mentioned improvement
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 of movement 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 include with
Guide rod is moved to connect far from 1 one end of cascade test part and with the maneuvering board 33 disposed in parallel of lower wall panels 22, setting in maneuvering board 33
With the linear motor between lower wall panels 22；The tache motorice 31 of the linear motor is connect with maneuvering board 33, the fixation of linear motor
End 32 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 being 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 parallel to each other.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 include with
Lower step:
Step S1: setting linear motor before movement, 1 distance from top lower wall panels of cascade test part, 22 test surfaces 231
Distance is h0；
Step S2: the tache motorice 31 of linear motor is controlled to close/movement travel S far from test surfaces 231, sets straight line
Motor movement end 31 is ﹢ S to movement travel when moving close to test surfaces 231, and setting linear motor tache motorice 31 is surveyed to separate
Movement travel when examination face 231 moves is-S；
Step S3: it is calculated: the height H of the cascade test part 1 when linear motor is to close to the movement of test surfaces 231=
H0+S, height H=h0-S of the cascade test part 1 when linear motor is to far from the movement of test surfaces 231.
It should be noted that being ground at present in the plane cascade test for carrying out different blade tip clearance schemes by above-mentioned improvement
When studying carefully, the method generallyd use is the high plane cascade test part 1 of the different leaves of processing 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 generally requires to be carried out not according to plane cascade test result in the process on the experimental study that Cascade Aerodynamics influence
Disconnected adjusting, therefore will lead to complicated testpieces replacement when carrying out different blade tip clearance project studies, test period length and test
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 dress that can continuously become blade tip clearance
It sets, including multiple cascade test parts 1 arranged in parallel, the mounting rack for installing multiple cascade test parts 1, the installation
Frame includes being provided with test surfaces 231, and the cavity for installing multiple cascade test parts 1 is provided in the mounting rack, further includes
The driving device of close/separate test surfaces 231 of multiple cascade test parts 1 is connect and is used to drive with multiple cascade test parts 1.
The mounting rack includes the wainscot 23 for being provided with test surfaces 231 and the lower wall panels 22 disposed in parallel of wainscot 23
And two bolts 21 between wainscot 23 and lower wall panels 22 are set, 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
Nut cooperation is fixed by wainscot 23 and lower wall panels 22.
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 passes through the second dynamic sealing guide groove 222 and connect with driving device.
Second possum belly is 3mm ~ 12mm along the depth for moving guide rod length direction.
The driving device includes connecting with movement guide rod far from 1 one end of cascade test part 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 and fortune of the linear motor
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
The diameter of bar is 2 ~ 10mm.The lower wall panels 22 are along the depth and second with a thickness of the first possum belly for moving guide rod length direction
The summation of possum belly depth.
The multiple 1 spaced set of cascade test part being parallel to each other.
The linear motor is provided with the linear encoder of ± 1 μm of control precision, and linear motor and linear encoder are
The prior art is not belonging to the improvement of the utility model, does not repeat this its internal structure；
It should be noted that the utility model can effectively be directed to current plane cascade test by above-mentioned improvement
When carrying out different blade tip clearance schemes in research, cascade test part 1 is with high costs caused by processing number of packages mostly, cannot obtain leaf top
Gap parameter is to the consecutive variations rule of plane cascade aeroperformance and cannot carry out plane cascade in blade tip clearance change procedure
The problem of transient changing process study of aeroperformance.
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 the preferred embodiment of the utility model, not does limit in any form to the utility model
System, any simple modification made by the above technical examples according to the technical essence of the present invention, equivalent variations, each falls within
Within the protection scope of the utility model.
Claims (6)
1. one kind can continuously become the plane cascade test device of blade tip clearance, including multiple cascade test parts arranged in parallel
(1), for installing the mounting rack of multiple cascade test parts (1), the mounting rack includes being provided with test surfaces (231), the peace
The cavity for installing multiple cascade test parts (1) is provided in shelving, it is characterised in that: further include and multiple cascade test parts
(1) connect and for drive multiple cascade test parts (1) it is close/far from test surfaces (231) driving device.
2. the plane cascade test device that one kind according to claim 1 can continuously become blade tip clearance, it is characterised in that: institute
State mounting rack include be provided with test surfaces (231) wainscot (23), with wainscot (23) lower wall panels disposed in parallel (22) with
And two bolts (21) between wainscot (23) and lower wall panels (22) are set, two bolts (21), wainscot (23),
And lower wall panels (22) form the cavity for installing multiple cascade test parts (1)；The lower wall panels (22) and driving device connect
It connects.
3. the plane cascade test device that one kind according to claim 2 can continuously become blade tip clearance, it is characterised in that: institute
It states cascade test part (1) and the one end of lower wall panels (22) is provided with movement guide rod, it is dynamic that the lower wall panels (22) are provided with second
Possum belly (222)；The movement guide rod passes through the second dynamic sealing guide groove (222) and connect with driving device.
4. the plane cascade test device that one kind according to claim 3 can continuously become blade tip clearance, it is characterised in that: institute
State driving device include with movement guide rod connect far from cascade test part (1) one end and with lower wall panels (22) movement disposed in parallel
Plate (33), the linear motor being arranged between maneuvering board (33) and lower wall panels (22)；The tache motorice (31) of the linear motor with
Maneuvering board (33) connection, the fixing end (32) of linear motor are connect with lower wall panels (22).
5. the plane cascade test device that one kind according to claim 4 can continuously become blade tip clearance, it is characterised in that: institute
It states lower wall panels (22) and is additionally provided with close lower wall panels (22) for installing cascade test part (1) close to the side of wainscot (23)
The first dynamic sealing guide groove of one end, the first dynamic sealing guide groove are connected to the second dynamic sealing guide groove (222)；The cascade test
Part (1), the first dynamic sealing guide groove and second dynamic sealing guide groove (222) quantity are identical and be arranged in a one-to-one correspondence.
6. one kind according to claim 1-5 can continuously become the plane cascade test device of blade tip clearance, special
Sign is: the multiple cascade test part (1) spaced set being parallel to each other.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201820898397.4U CN208443316U (en) | 2018-06-11 | 2018-06-11 | A kind of plane cascade test device that can continuously become blade tip clearance |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201820898397.4U CN208443316U (en) | 2018-06-11 | 2018-06-11 | A kind of plane cascade test device that can continuously become blade tip clearance |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108775850A (en) * | 2018-06-11 | 2018-11-09 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of plane cascade test device and its test method that can continuously become blade tip clearance |
| 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 |
-
2018
- 2018-06-11 CN CN201820898397.4U patent/CN208443316U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108775850A (en) * | 2018-06-11 | 2018-11-09 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of plane cascade test device and its test method that can continuously become blade tip clearance |
| CN108775850B (en) * | 2018-06-11 | 2024-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Planar blade cascade test device capable of continuously changing blade top gap and test method thereof |
| 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 |
| 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 |
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