CN106837840A - A kind of fan-shaped cascade experiment system for stator blade aeroperformance research in Non-uniform Currents - Google Patents
A kind of fan-shaped cascade experiment system for stator blade aeroperformance research in Non-uniform Currents Download PDFInfo
- Publication number
- CN106837840A CN106837840A CN201710047017.6A CN201710047017A CN106837840A CN 106837840 A CN106837840 A CN 106837840A CN 201710047017 A CN201710047017 A CN 201710047017A CN 106837840 A CN106837840 A CN 106837840A
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- China
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- stator
- stator blade
- fan
- top grating
- shaped cascade
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Abstract
The present invention provides a kind of fan-shaped cascade experiment system for stator blade aeroperformance research in Non-uniform Currents, it is characterised in that including：Converging portion；Fan-shaped CASCADE EXPERIMENT section, including measurement apparatus between stator top grating, stator lower grid plate, adjustable vane, left and right suction chamber, stator blade top grating, stator blade lower grid plate, slip stator blade and level；Suction system, including flowmeter, choke valve, water circulating type vacuum pump, threephase asynchronous and frequency-variable controller, the suction flow of frequency-variable controller and throttle valve adjustment water circulating type vacuum pump, and water circulating type vacuum pump is connected with left and right suction chamber by pipeline；Experiment test and data collecting system, the import of outlet and fan-shaped CASCADE EXPERIMENT section with converging portion are connected, for the measurement to parameter preset.The present invention realizes lower cost and shirtsleeve operation by building fan-shaped cascade experiment system by the cooperation of each several part, so that each performance parameters are measured and analyzed in obtaining Non-uniform Currents, it is that follow-up study lays the foundation.
Description
Technical field
It is capable of achieving under the conditions of distortion the present invention relates to one kind, is studied for compressor stator aeroperformance in Non-uniform Currents
Fan-shaped cascade experiment system.
Background technology
Gas turbine is as a kind of advanced power set with its remarkable performance in aviation, naval vessel, generating, oil
The departments such as work, natural gas transportation and railway transportation are used widely.Produced as the Major Strategic of national defense industry and national economy
Product, its correlation technique is the core technology of 21 century dynamical system, directly affect a national defence for country, the energy, safety and
Competition in the industry ability.Compressor is the core component of gas turbine, and its service behaviour under different operating modes has to overall performance
And directly affect, be always the emphasis of domestic and foreign scholars research.In recent years, in order to meet aircraft flight height, flying speed, with
And the demand of high-performance mobility, compressor inlet flow field becomes to become increasingly complex, often occurs significantly to flow in compressor
Field distortion.It is because compressor blade design belongs to high-tech category, although there is theoretical calculation method but main still by various
Experiment could obtain desired result,
Therefore, in order to further influence of the research inlet distortion to stator blade runner interior flow field, it is necessary to be directed to distortion
The stator blade runner of fluid influence carries out experiment measurement, but whole level experiment difficulty is big, high cost, and data are difficult measurement.And receive
The stator blade runner of distortion fluid influence is presented obvious heterogeneity, and the flow regime of each runner is differed, and also increases reality
The difficulty of test amount.Therefore, fan-shaped CASCADE EXPERIMENT part of the design with adjustable vane, it is ensured that stator blade inlet air conditions are with it in level
Unanimously, the influence of distortion condition is counted again, while also to ensure enough measurable flow road quantity, such experiment and DATA REASONING
Method is very necessary.
The content of the invention
According to technical problem set forth above, and provide a kind of fan for stator blade aeroperformance research in Non-uniform Currents
Shape cascade experiment system.It is of the invention main by the fan-shaped CASCADE EXPERIMENT section of converging portion cooperation, suction system and experiment test system
And data collecting system, so as to have an experiment, difficulty is small, low cost, simple to operate, and can carry out different free stream Mach numbers, difference
The advantage of the experiment under the conditions of flow angle, pitches and change moving-stator blade the relative circumferential position etc..
The technological means that the present invention is used is as follows：
A kind of fan-shaped cascade experiment system for stator blade aeroperformance research in Non-uniform Currents, it is characterised in that bag
Include：
Converging portion, the cylinder with the fan-shaped flow area for meeting Vickers curve shape；
Fan-shaped CASCADE EXPERIMENT section, including on stator top grating, stator lower grid plate, adjustable vane, left and right suction chamber, stator blade
Measurement apparatus between screen, stator blade lower grid plate, slip stator blade and level；
Coordinate displacement mechanism fixed seat is arranged on the stator top grating；The adjustable vane is fixed up and down by stator
Block is arranged between the stator top grating and the stator lower grid plate；Stator adjusts locating piece and the adjustable vane upper end
Stator rotary shaft connects and composes stator regulation detent mechanism；
Left side suction plate, left side suction chamber baffle plate, right side suction side plate and right side suction chamber baffle plate are fixed on the stator
The two ends of top grating and the stator lower grid plate constitute the left and right suction chamber；
Connected using slideway between the slip stator blade and the stator blade top grating and the stator blade lower grid plate；PIV forms
Sprue is embedded in the sealing that the stator blade top grating constitutes the stator blade top grating；When PIV experiment is carried out, PIV forms sliding block peace
In the slideway of the stator blade top grating；Slideway is measured between level to be arranged on the stator blade top grating, sprue is measured between level embedding
Enter the stator blade top grating and constitute sealing；When measuring between carry out level, sprue is measured between removing the level, and will be measured between level and slide
Block is measured on slideway between being arranged on the level and constitutes measurement apparatus between the level；
Suction system, including flowmeter, choke valve, water circulating type vacuum pump, threephase asynchronous and frequency-variable controller,
The suction flow of the frequency-variable controller and water circulating type vacuum pump described in the throttle valve adjustment, and by pipeline by the water
Circulating vavuum pump is connected with the left and right suction chamber；
Experiment test and data collecting system, the outlet with the converging portion and the fan by each data acquisition device
The import of shape CASCADE EXPERIMENT section is connected, and the pressure signal that will be obtained is converted into electric signal, is transferred to computer and is processed, and completes
Collection and treatment to default experiment parameter.
Further, the outlet size of the converging portion is matched completely with the entrance of the fan-shaped CASCADE EXPERIMENT section,
And total pressure probe mounting hole and wall static pressure hole are set in the outlet port region of the converging portion.
Further, the suction system is used and arranges that suction seam is by convection into interior flow field and carries out in left and right side suction plate
Suction, the left side suction plate and the right side suction plate be fixed on the upper and lower screen of stator by Positioning screw, and with it is described
Left side suction chamber baffle plate and the right side suction chamber baffle plate set up sealing suction chamber respectively, on the left side suction plate and the right side
SS is opened in the suction plate of side to be attached with the water circulating type vacuum pump, completes suction.
Further, coordinate displacement mechanism fixed seat is connected by bolt with the ring flange of the fan-shaped CASCADE EXPERIMENT section
Connect, the change according to leaf grating outlet measurement section changes coordinate displacement mechanism in ring flange circumferential position.
Further, the joint face of the stator top grating, the stator lower grid plate and the upper and lower fixed block of the stator is equal
Using spherical design, the adjustable vane adjusts locating piece and adjusts angle by the stator, and by upper end set screw and institute
The positioning spiro pit stated on stator top grating is fixed, and the adjustable vane after packing ring and lower end nut are to positioning is carried out
It is fixed.
Further, the slip stator blade is integrally machined shaping using blade and upper lower flow channel, quiet with described by slip teeth
Leaf top grating and the stator blade lower grid plate are connected.
Further, when inter-stage parameter measurement is carried out, the outlet section of the upper and lower screen of stator passes through between flange and level
Measurement extension connection；When static cascade experiment is carried out, the outlet section of the upper and lower screen of stator passes through flange and the stator blade
The entrance of upper and lower screen is connected.
Further, the outlet section of the stator blade top grating is additionally provided with the radial pressure gradient of different height by flange
Baffle plate, i.e. 30% leaf baffle plate high and 50% leaf baffle plate high.
Further, experiment test and data collecting system, including total pressure probe, wall static pressure air feeders, five hole gas
Dynamic probe, five points three hole rake probes, 12 hole stagnation pressure rakes, wall static pressure air feeders, particle image velocimeter, coordinate bit
Telephone-moving structure, pressure scanning valve and remote computer；The total pressure probe is arranged on converging portion outlet and the fan-shaped leaf grating
Experimental section import, gos deep into the central area in region to be measured；Five hole air feeders and the 12 hole stagnation pressure rake are arranged on
The outlet port of the fan-shaped CASCADE EXPERIMENT section；The pressure scanning valve is made up of multiple pressure scanning modules, is internally integrated
Pressure sensor and A/D converters, after experiencing pressure signal, by processing direct output digit signals to remote computer.
Further, the five points three hole rake probe is arranged between the adjustable vane and the slip stator blade, is surveyed
Stagnation pressure, static pressure and the Mach number of stator exit flow are measured, in real time by the aerodynamic parameter measured by the five points three hole rake probe
By the regulation to source of the gas, the Mach Number Never To Be Exceeded for measuring the five points three hole probe reaches desired value, and then beginning stator blade goes out
The measurement of mouth parameter.
The present invention has advantages below：
The present invention is used for the fan-shaped cascade experiment system of stator blade aeroperformance research in Non-uniform Currents by building, each
Partial mutual cooperation with relatively low cost and shirtsleeve operation can obtain in Non-uniform Currents different free stream Mach numbers and attack
Leaf grating interior flow field structure and aeroperformance under corner condition, be enter from now on compressor flow field characteristic analysis under the conditions of line distortion,
Performance optimizes and blade aerodynamic shape-designing is accumulated experience, and is also the anti-distortion capability study of later compressor and the development of level experiment
Lay the foundation, with important theory significance and application value realistic.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description does simply to introduce, it should be apparent that, drawings in the following description are this hairs
Some bright embodiments, for those of ordinary skill in the art, without having to pay creative labor, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is the structural representation of sector cascade experiment system of the invention.
Fig. 2 is the structured flowchart of suction system of the present invention.
Fig. 3 is the structural representation of sector CASCADE EXPERIMENT section of the invention.
Fig. 4 is the structural representation of adjustable vane of the present invention.
Fig. 5 is the structural representation that the present invention slides stator blade.
Fig. 6 is the structural representation of particle image speed-measuring system of the present invention.
In figure：1st, converging portion；2nd, fan-shaped CASCADE EXPERIMENT section；3rd, experiment test and data collecting system；4th, coordinate bit telephone-moving
Structure fixed seat；5th, stator top grating；6th, stator regulation locating piece；7th, total pressure probe seat；8th, stator lower grid plate；9th, adjustable vane；
10th, extension is measured between level；11st, left side suction plate；12nd, left side suction chamber baffle plate；13rd, PIV forms sprue；14th, PIV forms are slided
Block；15th, right side suction side plate；16th, stator blade top grating；17th, sliding block is measured between level；18th, sprue is measured between level；19th, measured between level
Slideway；20th, right side tailgate；21st, stator blade lower grid plate；22nd, right side suction chamber baffle plate；23rd, stator blade is slided；24th, left side tailgate；25、
30% leaf baffle plate high；26th, 50% leaf baffle plate high；27th, stator rotary shaft；28th, the upper and lower fixed block of stator；29th, packing ring；30th, laser
Generator；31st, CCD camera；32nd, cantilever slides stator blade.
Specific embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
As shown in Fig. 1, Fig. 6, a kind of fan-shaped cascade experiment system for stator blade aeroperformance research in Non-uniform Currents,
Including：
Converging portion 1, the converging portion 1 is located at after wind-tunnel cylinder, is bolted, with meeting Vickers curve shape
Fan-shaped flow area cylinder (" smaller part cylinder " i.e. with sector crosssection), by circular flow area of the prior art
Be converted to sector.The outlet size of the converging portion 1 is matched completely with the entrance of fan-shaped CASCADE EXPERIMENT section 2；
As shown in figure 3, fan-shaped CASCADE EXPERIMENT section 2, including stator top grating 5, stator lower grid plate 8, adjustable vane 9, left and right
Measurement apparatus between suction chamber, stator blade top grating 16, stator blade lower grid plate 21, slip stator blade 23 and level；
Coordinate displacement mechanism fixed seat 4 is connected by bolt with the ring flange of the fan-shaped CASCADE EXPERIMENT section 2, that is, be arranged on
On the stator top grating 5, the change according to leaf grating outlet measurement section changes coordinate displacement mechanism in ring flange circumferential position.
As shown in figure 4, the adjustable vane 9 is arranged on the stator top grating 5 and institute by the upper and lower fixed block 28 of stator
State between stator lower grid plate 8, the connection of the stator top grating 5, the stator lower grid plate 8 and the upper and lower fixed block 28 of the stator
Face uses the screen inner side of spherical design, the upper and lower screen of stator to be set using sphere with the joint face of the upper and lower fixed block 28 of stator
Meter；Stator adjusts locating piece 6 and connects and composes stator regulation detent mechanism with the stator rotary shaft 27 of the upper end of the adjustable vane 9；
The adjustable vane 9 adjusts locating piece 6 and adjusts angle by the stator, and by upper end set screw and the stator top grating
Positioning spiro pit on 5 is fixed can carry out accurate adjustment, and described adjustable after packing ring 29 and lower end nut are to positioning is led
Leaf 9 is fixed, and packing ring 29 can facilitate the installation of adjustable vane 9, position and fixed.Five are set on the stator lower grid plate 8
Three hole probe mounting grooves of point.
Left side suction plate 11, left side suction chamber baffle plate 12, right side suction side plate 15 and right side suction chamber baffle plate 22 are by fixed
Position screw is fixed on the stator top grating 5 and the two ends of the stator lower grid plate 8 constitute the left and right suction chamber；
When inter-stage parameter measurement is carried out, the outlet section of the upper and lower screen of stator passes through to measure extension between flange and level
Section 10 is connected；When static cascade experiment is carried out, the outlet section of the upper and lower screen of stator is upper and lower with the stator blade by flange
The entrance of screen is connected.
As shown in figure 5, the slip stator blade 23 is integrally machined shaping, the slip stator blade 23 using blade and upper lower flow channel
It is connected with slideway using slip teeth between the stator blade top grating 16 and the stator blade lower grid plate 21, thus it is possible to vary slide stator blade 23
Circumferential relative position inside leaf grating, while pitches experiment can also be carried out, i.e., by increasing cunning between sliding blade
Block changes cascade solidity, and two neighboring slip stator blade 23 closely adjacent can form a complete runner；The stator blade screen 16
On be provided with PIV measurement window structure and level between measurement apparatus, and the stator blade top grating 16 outlet section pass through flange
It is provided with the radial pressure gradient baffle plate of different height, the i.e. 30% leaf leaf of baffle plate 25 and 50% baffle plate 26 high high.Under the stator blade
Screen 21 is connected by bolt with the stator lower grid plate 8, is provided with slip stator blade slideway and screwed hole.Left side tailgate 24 and right side
Tailgate 20 is connected with the stator blade top grating 16 and the stator blade lower grid plate 21 by screwed hole.
The PIV measurements window structure is made up of optical glass, PIV forms sprue 13 and PIV forms sliding block 14, optics glass
Glass is embedded on the PIV forms sliding block 14, and the arrangement for sliding stator blade 32 by PIV forms sliding block 14 and cantilever can be measured not
With circumferential position leaf grating internal speed field structure, PIV forms sprue 13 is embedded in the stator blade top grating 16 and constitutes the stator blade
The sealing of top grating 16；When PIV experiment is carried out, PIV forms sliding block 14 is arranged in the slideway of the stator blade top grating 16,
PIV forms sprue 13 is closely connected with the stator blade top grating 16 by screw and realizes top grating when PIV experiment is not carried out
Sealing；
Slideway 19 is measured between level to be arranged on the stator blade top grating 16, sprue 18 is measured between level and is embedded in grid on the stator blade
Plate 16 constitutes sealing；When measuring between carry out level, sprue 18 is measured between removing the level, and be arranged on sliding block 17 is measured between level
Measured between the level on slideway 19 and constitute measurement apparatus between the level；Five hole air feeders can go deep into leaf through measurement sliding block 17
Measured inside grid, and measure sliding block 17 can be measured between level according to measurement request slide into it is circumferentially moved in 19.
As shown in Fig. 2 suction system, including flowmeter, choke valve, water circulating type vacuum pump, threephase asynchronous and
Frequency-variable controller, the threephase asynchronous drives water circulating type vacuum pump to set up vacuum, the frequency-variable controller and described
The suction flow of water circulating type vacuum pump described in throttle valve adjustment, and by pipeline by the water circulating type vacuum pump and the left side
Right suction chamber is connected, by choke valve and the further control and suck amount of flowmeter；The suction system is used and taken out in left and right side
The intensive suction seam of suction disc arrangement is by convection into interior flow field and is aspirated, and the left side suction plate 11 and the right side suction plate 15 are logical
Positioning screw is crossed to be fixed on the upper and lower screen of stator, and with the left side suction chamber baffle plate 12 and the right side suction chamber baffle plate
22 set up sealing suction chamber respectively, open SS in the left side suction plate 11 and the right side suction plate 15 and are followed with the water
Ring vacuum pumps are attached, and complete suction.
Experiment test and data collecting system 3, with the outlet of the converging portion 1 and entering for the fan-shaped CASCADE EXPERIMENT section 2
Mouth is connected, for the measurement to parameter preset；Including total pressure probe, wall static pressure air feeders, five hole air feeders, five points three
Hole rake probe, 12 hole stagnation pressure rakes, wall static pressure air feeders, particle image velocimeter, coordinate displacement mechanism, pressure are swept
Retouch valve and remote computer, the pressure scanning valve is made up of multiple pressure scanning modules, be internally integrated pressure sensor and
A/D converters, after experiencing pressure signal, by processing direct output digit signals to remote computer.
In the outlet port region of converging portion 1 and the arrangement arrangement total pressure probe of stator top grating 5 seat 7, (i.e. total pressure probe is installed
The setting in hole), and the wall static pressure hole in stator top grating 5 close near trailing edge, the total pressure probe gos deep into region to be measured
Central area measures nozzle ring and comes to flow stagnation pressure by air feeders, using wall static pressure hole measurement stator outlet wall static pressure.
The five points three hole rake probe is arranged between the adjustable vane 9 and the slip stator blade 23, measures stator
The stagnation pressure of exit flow, static pressure and Mach number, in real time by the aerodynamic parameter measured by the five points three hole rake probe by right
The regulation of source of the gas, the Mach Number Never To Be Exceeded for measuring the five points three hole probe reaches desired value, and then starts stator blade outlet parameter
Measurement.
Five hole air feeders and the 12 hole stagnation pressure rake are arranged on the outlet position of the fan-shaped CASCADE EXPERIMENT section 2
Put；A slit is opened up on stator blade top grating 16, facilitates five-hole probe to go deep into inside leaf grating, coordinate displacement mechanism passes through coordinate
Displacement mechanism fixed seat 4 is arranged on the flange of stator top grating 5, and programming Driving Stepping Motor by remote computer controls five holes
Probe measurement stator blade exit flow field parameter.The pressure signal that air feeders and five-hole probe are perceived is delivered to pressure by pneumatic hose
Power scan module carries out data acquisition, by after A/D conversions, output digit signals to remote computer complete aerodynamic parameter and survey
Amount.
Particle image velocimeter is made up of laser generator 30, CCD camera 31 and particle generator, and particle generator is being received
Hold back in the cylinder of section front and spread trace particle, laser generator 30 and CCD camera 31 are by synchronizer control, PIV form sliding blocks
Optical glass is inlayed on 14, facilitates projection and the cameras capture scattered light signal of laser, obtain leaf grating internal speed vector field.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
Pipe has been described in detail with reference to foregoing embodiments to the present invention, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, or which part or all technical characteristic are entered
Row equivalent；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (10)
1. it is a kind of in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system, it is characterised in that including：
Converging portion (1), the cylinder with the fan-shaped flow area for meeting Vickers curve shape；
Fan-shaped CASCADE EXPERIMENT section (2), including stator top grating (5), stator lower grid plate (8), adjustable vane (9), left and right suction chamber
Room, stator blade top grating (16), stator blade lower grid plate (21), slip stator blade (23) measurement apparatus and between level；
Coordinate displacement mechanism fixed seat (4) is on the stator top grating (5)；The adjustable vane (9) is by stator
Lower fixed block (28) is between the stator top grating (5) and the stator lower grid plate (8)；Stator adjusts locating piece (6)
Stator regulation detent mechanism is connected and composed with the stator rotary shaft (27) of the adjustable vane (9) upper end；
Side plate (15) and right side suction chamber baffle plate (22) are aspirated admittedly in left side suction plate (11), left side suction chamber baffle plate (12), right side
The two ends for being scheduled on the stator top grating (5) and the stator lower grid plate (8) constitute the left and right suction chamber；
Slip stator blade (23) is connected between the stator blade top grating (16) and the stator blade lower grid plate (21) using slideway；
PIV forms sprue (13) the insertion stator blade top grating (16) constitutes the sealing of the stator blade top grating (16)；Carrying out PIV realities
When testing, PIV forms sliding block (14) are in the slideway of the stator blade top grating (16)；Slideway (19) is measured between level installed in institute
State on stator blade top grating (16), sprue (18) the insertion stator blade top grating (16) is measured between level and constitutes sealing；Between level is carried out
During measurement, sprue (18) is measured between removing the level, and slideway is measured installed between the level by sliding block (17) is measured between level
(19) measurement apparatus between the level are constituted on；
Suction system, including flowmeter, choke valve, water circulating type vacuum pump, threephase asynchronous and frequency-variable controller, it is described
The suction flow of frequency-variable controller and water circulating type vacuum pump described in the throttle valve adjustment, and by pipeline by the water circulation
Formula vavuum pump is connected with the left and right suction chamber；
Experiment test and data collecting system (3), by the outlet of each data acquisition device and the converging portion (1) and described
The import of fan-shaped CASCADE EXPERIMENT section (2) is connected, and the pressure signal that will be obtained is converted into electric signal, is transferred at computer
Reason, completes the collection and treatment to default experiment parameter.
2. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, the outlet size of the converging portion (1) is matched completely with the entrance of fan-shaped CASCADE EXPERIMENT section (2),
And total pressure probe mounting hole and wall static pressure hole are set in the outlet port region of the converging portion (1).
3. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, the suction system is used arranges that suction seam is by convection into interior flow field and is aspirated in left and right side suction plate, institute
State left side suction plate (11) and the right side suction plate (15) be fixed on the upper and lower screen of stator by Positioning screw, and with institute
State left side suction chamber baffle plate (12) and the right side suction chamber baffle plate (22) sets up sealing suction chamber respectively, in left side suction
SS is opened on plate (11) and the right side suction plate (15) to be attached with the water circulating type vacuum pump, complete suction.
4. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, coordinate displacement mechanism fixed seat (4) is connected by bolt with the ring flange of fan-shaped CASCADE EXPERIMENT section (2)
Connect, the change according to leaf grating outlet measurement section changes coordinate displacement mechanism in ring flange circumferential position.
5. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, the connection of the stator top grating (5), the stator lower grid plate (8) and the upper and lower fixed block of the stator (28)
Face uses spherical design, and the adjustable vane (9) adjusts locating piece (6) and adjusts angle by the stator, and is determined by upper end
Position screw is fixed with the positioning spiro pit on the stator top grating (5), and after packing ring (29) and lower end nut are to positioning
The adjustable vane (9) be fixed.
6. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, slip stator blade (23) is integrally machined shaping using blade and upper lower flow channel, by slip teeth and the stator blade
Top grating (16) and the stator blade lower grid plate (21) are connected.
7. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, when inter-stage parameter measurement is carried out, the outlet section of the upper and lower screen of stator passes through measurement between flange and level and prolongs
Section (10) connection long；When static cascade experiment is carried out, the outlet section of the upper and lower screen of stator passes through flange and the stator blade
The entrance of upper and lower screen is connected.
8. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, the outlet section of the stator blade top grating (16) is kept off by the radial pressure gradient that flange is additionally provided with different height
Plate, i.e. 30% leaf baffle plate high (25) and 50% leaf baffle plate high (26).
9. it is according to claim 1 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, experiment test and data collecting system (3), including total pressure probe, wall static pressure air feeders, the pneumatic spy in five holes
Pin, five points three hole rake probes, 12 hole stagnation pressure rakes, wall static pressure air feeders, particle image velocimeter, coordinate bit telephone-moving
Structure, pressure scanning valve and remote computer；The total pressure probe is arranged on the converging portion (1) outlet and the fan-shaped leaf grating reality
Section (2) import is tested, gos deep into the central area in region to be measured；Five hole air feeders and the 12 hole stagnation pressure rake are arranged on
The outlet port of fan-shaped CASCADE EXPERIMENT section (2)；The pressure scanning valve is made up of multiple pressure scanning modules, is internally integrated
Pressure sensor and A/D converters, after experiencing pressure signal, by processing direct output digit signals to remote computer.
10. it is according to claim 9 in Non-uniform Currents stator blade aeroperformance research fan-shaped cascade experiment system,
Characterized in that, the five points three hole rake probe is arranged between the adjustable vane (9) and slip stator blade (23), survey
Stagnation pressure, static pressure and the Mach number of stator exit flow are measured, in real time by the aerodynamic parameter measured by the five points three hole rake probe
By the regulation to source of the gas, the Mach Number Never To Be Exceeded for measuring the five points three hole probe reaches desired value, and then beginning stator blade goes out
The measurement of mouth parameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710047017.6A CN106837840B (en) | 2017-01-22 | 2017-01-22 | It is a kind of to be used for the fan-shaped cascade experiment system that stator blade aeroperformance is studied in Non-uniform Currents |
Applications Claiming Priority (1)
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| CN108931363A (en) * | 2018-07-05 | 2018-12-04 | 西安交通大学 | A kind of plane and D remote sensing tele-experimentation device |
| CN108953232A (en) * | 2018-07-20 | 2018-12-07 | 大连海事大学 | A kind of non-axisymmetric distribution stator blade axial-flow compressor |
| CN110907118A (en) * | 2019-12-12 | 2020-03-24 | 西北工业大学 | Plane blade grid experimental device with variable installation angle and experimental method |
| CN113883098A (en) * | 2021-09-10 | 2022-01-04 | 中国民航大学 | Stator blade distortion-resistant axial flow compressor and stator blade distortion-resistant method of axial flow compressor |
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| CN108953232A (en) * | 2018-07-20 | 2018-12-07 | 大连海事大学 | A kind of non-axisymmetric distribution stator blade axial-flow compressor |
| CN110907118A (en) * | 2019-12-12 | 2020-03-24 | 西北工业大学 | Plane blade grid experimental device with variable installation angle and experimental method |
| CN113883098A (en) * | 2021-09-10 | 2022-01-04 | 中国民航大学 | Stator blade distortion-resistant axial flow compressor and stator blade distortion-resistant method of axial flow compressor |
| CN114370422A (en) * | 2021-12-27 | 2022-04-19 | 哈尔滨工业大学 | Coordinate frame for collecting fan-shaped blade grid inlet flow field and using method thereof |
| CN114370422B (en) * | 2021-12-27 | 2024-04-05 | 哈尔滨工业大学 | Coordinate frame for collecting fan-shaped blade grid inlet flow field and using method thereof |
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