CN109374252B - Compressor tandem cascade experimental device - Google Patents
Compressor tandem cascade experimental device Download PDFInfo
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- CN109374252B CN109374252B CN201811138525.6A CN201811138525A CN109374252B CN 109374252 B CN109374252 B CN 109374252B CN 201811138525 A CN201811138525 A CN 201811138525A CN 109374252 B CN109374252 B CN 109374252B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a compressor serial cascade experimental device, and belongs to the field of cascade wind tunnel experiments. The device comprises an upper grid plate 1 and a lower grid plate 2, wherein the upper grid plate 1 and the lower grid plate 2 are respectively provided with a front groove 20 and a rear groove 21 which correspond to each other, front vane sliding blocks and rear vane sliding blocks which are provided with front vane inserting grooves 22 and rear vane inserting grooves 22 are respectively arranged in the front groove 20 and the rear groove 21, the axial or circumferential positions of the sliding blocks are moved in the grooves according to the experiment requirements, and the rest space is filled with cushion blocks and fixed; the tandem blades to be tested are divided into a front row and a rear row, and the relative position relation of the front and rear blade rows of the tandem blade grid experimental piece is changed by moving the axial or circumferential position of the sliding block in the groove before the test, namely, the axial distance and the circumferential distance are adjusted. The axial spacing and the circumferential spacing of a set of tandem cascade experimental pieces can be adjusted, compared with the traditional cascade experimental pieces, the axial spacing and the circumferential spacing of the set of tandem cascade experimental pieces can be greatly reduced, the production cost, the production period, the assembly time and the storage space of the experimental pieces can be greatly saved, the development of the experimental research work of the tandem cascade is facilitated, and the control on the separation of boundary layers in the gas compressor is further realized.
Description
Technical Field
The invention relates to the field of cascade wind tunnel experiments, in particular to a tandem cascade experimental device of a gas compressor.
Background
Modern aircraft engines are precise and complex machines known as bright pearls on industrial crown, and the design of gas compressors of the aircraft engines requires high pressure ratio and high load. However, due to the existence of a strong adverse pressure gradient in a cascade channel of the high-load compressor, the suction surface of the blade and the boundary layer of the corner region are separated seriously, so that the loss of the compressor is increased, and the efficiency is reduced.
The tandem blade is a combined blade formed by two rows of blades which are close to each other. The method is a novel passive flow control technology, and can effectively control the flow separation in the compressor and improve the blade load and the efficiency of the compressor. The high-energy incoming flow is accelerated through the gap flow channel between the front blade and the rear blade and is guided to the suction surface of the rear blade, the low-energy area of the wake of the front blade is blown away, a new boundary layer can be formed again on the front edge of the rear blade, the development of boundary layer separation is prevented, the loss caused by low-energy fluid in the compressor is reduced, and the air flow turning angle and the efficiency of the compressor blade can be obviously improved.
For a tandem cascade, the axial separation is defined as the axial distance between the trailing edge of the leading blade and the leading edge of the trailing blade; the circumferential spacing is defined as the circumferential distance of the trailing edge of the leading blade from the leading edge of the trailing blade. The axial spacing and the circumferential spacing are key parameters for determining the relative positions of the front row and the rear row of the blades of the tandem blade cascade, and have decisive influence on the flow performance of the tandem blade cascade. Only the superior combination of axial spacing and circumferential spacing can the tandem cascade exhibit performance advantages over conventional cascades.
In recent years, domestic researchers have made many studies on the influence of the axial pitch and the circumferential pitch on the performance of the tandem cascade. The experimental research method is generally to design and manufacture a plurality of sets of tandem blade grids with combined axial spacing and circumferential spacing, and to perform experiments in a blade grid wind tunnel; the numerical simulation research method generally designs a plurality of sets of tandem blade cascades with combined axial spacing and circumferential spacing in a computer, and performs numerical simulation through a computational fluid dynamics method.
Wu national bracelet, Zhuang Tao nan, Guo Ben Heng, published in 1988, volume 5, 1-4, paper of International Journal of Turbo & Jet Engineers, Experimental investment of Tandem Blade Cascades With Double-Circular ARC Profiles by varying the setting angle, axial spacing and circumferential spacing to design and manufacture 24 sets of Tandem cascade experiments on which a series of wind tunnel experiments were performed to obtain their performance and flow data.
Song Asia Hui, Li Qiushui and Wuhong are published in 2008 'numerical study on influence of ultrasonic incoming flow tandem cascade rear row position on flow' of an aero-engine numerical simulation and digital design academic Commission of the Chinese aviation society, and the influence of circumferential spacing and axial spacing on the performance and the flow field of the tandem cascade under the ultrasonic incoming flow is studied through numerical simulation.
Shenchun and Tengjinfang are published in 2013, 5 th period scientific technology and engineering, and the numerical research on the influence of the axial relative position on the pneumatic performance of the tandem cascade is carried out, and numerical simulation is carried out on the tandem cascade with 5 axial intervals to investigate the influence on the overall performance and the flow field.
The influence of circumferential offset on the aerodynamic performance of the tandem cascade is published in a paper of energy saving technology in 2016 (2 nd), and the overall performance and flow field details of 5 tandem cascades with different circumferential intervals under the working conditions of a design point and a near-surge point are researched by applying computational fluid dynamics software.
It can be seen that with the development of computational fluid dynamics, researchers have made a great deal of numerical studies on the relationship between the axial spacing and the circumferential spacing and the performance of the tandem cascade, but the validity of the numerical simulation needs to be tested for verification nowadays. Cascade wind tunnel experiments remain the most reliable method for studying the above problems. Because the combination of the axial spacing and the circumferential spacing of the experiment is more, how to realize the tandem blade cascade of the combination of different axial spacing and circumferential spacing at low cost and quickly becomes a key problem faced by the experimenters.
For example, 65 cascade wind tunnel experiments are required to obtain the performance and the flow characteristics of the tandem blades under the combination of 5 axial positions and 13 circumferential positions. If the traditional cascade experimental part structure is adopted, 65 sets of cascade experimental parts need to be manufactured, the manufacturing cost is high, and a lot of inconvenience exists in management and assembly. In order to adapt to a new situation of the current tandem cascade experimental study, the traditional cascade experimental device needs to be improved.
Disclosure of Invention
In order to make up the defects of the traditional cascade experimental device, the invention provides a serial cascade experimental device of a gas compressor.
The technical scheme of the invention is as follows: a compressor tandem cascade experimental device comprises an upper grid plate 1 and a lower grid plate 2, wherein two grid plates are connected in parallel and have adjustable distance through two distance posts 13, the upper grid plate 1 is respectively provided with a front groove 20 and a rear groove 21, and the corresponding position of the lower grid plate 2 is also provided with the same front groove 20 and the same rear groove 21; the two front vane sliding blocks 3 are respectively provided with 4-8 front vane slots 22 at equal intervals along the circumferential direction and are respectively arranged in the front grooves 20 of the upper grid plate 1 and the lower grid plate 2, the two rear vane sliding blocks 4 are respectively provided with the same number of rear vane slots 23 at equal intervals along the circumferential direction and are respectively arranged in the rear grooves 21 of the upper grid plate 1 and the lower grid plate 2, the axial or circumferential positions of the sliding blocks in the grooves can be moved according to the experiment requirement, and the residual space is filled and fixed by cushion blocks; the tandem blades to be tested are divided into a front row and a rear row, two ends of the front row of blades are respectively arranged in the front blade slots 22 of the front blade sliding blocks 3, two ends of the rear row of blades are respectively arranged in the rear blade slots 23 of the rear blade sliding blocks 4, and the relative position relation of the front blade row and the rear blade row of the tandem cascade experimental piece can be changed by moving the axial positions or the circumferential positions of the sliding blocks in the slots before the experiment, namely the axial distance and the circumferential distance are adjusted.
The axial spacing and the circumferential spacing of a set of tandem cascade experimental pieces can be adjusted, compared with the traditional cascade experimental pieces, the axial spacing and the circumferential spacing of the set of tandem cascade experimental pieces can be greatly reduced, the production cost, the production period, the assembly time and the storage space of the experimental pieces can be greatly saved, the development of the experimental research work of the tandem cascade is facilitated, and the control on the separation of boundary layers in the gas compressor is further realized.
Drawings
FIG. 1 is an overall three-dimensional view of a compressor tandem cascade experimental apparatus in example 1
FIG. 2 is an isometric view of the upper grid plate of the tandem cascade experimental apparatus of the gas compressor in example 1
FIG. 3 is a top plan view and a cross-sectional view of an upper grid plate of an experimental device for tandem cascade of compressor in example 1
FIG. 4 is an isometric view of the lower grid plate of the compressor tandem cascade experimental setup of example 1
FIG. 5 is a top view and a cross-sectional view of a lower grid plate of an experimental device for tandem cascade of compressor in example 1
FIG. 6 is an isometric view of a front vane slider of the compressor tandem cascade experimental setup of example 1
FIG. 7 is a top view of a front vane slider of the tandem cascade experimental apparatus of the compressor in embodiment 1
FIG. 8 is an isometric view of a trailing vane slide of the compressor tandem cascade experimental apparatus of example 1
FIG. 9 is a top view of a trailing blade slider of the experimental apparatus for tandem cascade of compressor in example 1
FIG. 10 is a front view of a front blade with static pressure holes on the pressure surface of the experimental device for tandem cascade of compressor in example 1
FIG. 11 is a left side view of a front blade with static pressure holes on the pressure surface of the tandem cascade experimental apparatus of the compressor in embodiment 1
FIG. 12 is a front view of a front blade with static pressure holes on the suction side of the tandem cascade experimental apparatus of the compressor in example 1
FIG. 13 is a left side view of a front blade with static pressure holes on the suction side of the tandem cascade experimental apparatus of the compressor in example 1
FIG. 14 is a front view of a trailing blade with static pressure holes on the pressure side of a tandem cascade experimental apparatus of a compressor in example 1
FIG. 15 is a left side view of a trailing blade with static pressure holes on the pressure side of a tandem cascade experimental apparatus for a compressor in example 1
FIG. 16 is a front view of a trailing blade with static pressure holes on the suction side of the experimental device for tandem cascade of compressor in example 1
FIG. 17 is a left side view of a trailing blade with static pressure holes opened on the suction side of the tandem cascade experimental apparatus of the compressor in example 1
FIG. 18 is a front view of a leading blade without static pressure measurement of the tandem cascade experimental apparatus of the compressor in example 1
FIG. 19 is a left side view of a front blade without static pressure measurement of the tandem cascade experimental apparatus of the compressor in example 1
FIG. 20 is a front view of a trailing blade without static pressure measurement of the compressor tandem cascade experimental apparatus in example 2
FIG. 21 is a left side view of a trailing blade without static pressure measurement of the compressor tandem cascade experimental apparatus in example 2
FIG. 22 is an isometric view of a forward vane spacer of the compressor tandem cascade experimental setup of example 2
FIG. 23 is an isometric view of the aft vane spacer of the compressor tandem cascade experimental set-up of example 2
FIG. 24 is a three-dimensional view of a spacer for a tandem cascade experimental apparatus of a compressor in example 2
FIG. 25 is a front view of a spacer for a tandem cascade experimental apparatus of a compressor in example 2
FIG. 26 is an overall three-dimensional view of a compressor tandem cascade experimental apparatus in example 2
FIG. 27 is an isometric view of the upper grid plate of the compressor tandem cascade experimental setup of example 2
FIG. 28 is a top plan view and a cross-sectional view of an upper grid plate of an experimental device for cascade vanes of a compressor in example 2
FIG. 29 is an isometric view of the lower grid plate of the compressor tandem cascade experimental setup of example 2
FIG. 30 is a top view and a cross-sectional view of a lower grid plate of an experimental device for tandem cascade of compressor in example 2
FIG. 31 is an overall three-dimensional view of a compressor tandem cascade experimental apparatus in example 3
FIG. 32 is an isometric view of the upper grid plate of the compressor tandem cascade experimental setup of example 3
FIG. 33 is a top plan view and a cross-sectional view of an upper grid plate of an experimental device for cascade vanes of a compressor in example 3
FIG. 34 is an isometric view of the lower grid plate of the compressor tandem cascade experimental setup of example 3
FIG. 35 is a top view and a cross-sectional view of a lower grid plate of an experimental device for cascade vanes of a compressor in example 3
In the figure: 1-upper grid plate (blade tip), 2-lower grid plate (blade root), 3-front blade slide block, 4-rear blade slide block, 5-front blade with static pressure hole on pressure surface, 6-front blade with static pressure hole on suction surface, 7-rear blade with static pressure hole on pressure surface, 8-rear blade with static pressure hole on suction surface, 9-front blade without static pressure measurement, 10-rear blade without static pressure measurement, 11-front blade cushion block, 12-rear blade cushion block, 13-distance column, 14-distance column mounting screw, 15-distance column mounting through hole, 16-static pressure tube, 17-threaded through hole for fastening screw on upstream side of front grid plate groove, 18-threaded through hole for fastening screw on two sides of rear grid plate groove, 19-threaded hole on two sides of rear grid plate groove, 20-front grid plate groove, 21-rear grid plate groove, 22-front blade slot, 23-rear blade slot, 24-static vane surface pressure hole, 25-vane cavity
Detailed Description
Example 1: the embodiment is an experimental device for tandem cascade of a gas compressor, which can adjust the axial distance and the circumferential distance of the tandem cascade.
As shown in fig. 1, the experimental apparatus for tandem cascade of compressor proposed in this embodiment includes an upper grid plate 1, a lower grid plate 2, a front vane slider 3, a rear vane slider 4, a front vane 5 with a static pressure hole on a pressure surface, a front vane 6 with a static pressure hole on a suction surface, a rear vane 7 with a static pressure hole on a pressure surface, a rear vane 8 with a static pressure hole on a suction surface, a front vane 9 without measuring static pressure, a rear vane 10 without measuring static pressure, a front vane cushion block 11, a rear vane cushion block 12, and a distance post 13. The device is integrally mirror-symmetrical up and down along the middle section of the height of the blade, and the upper grid plate 1 and the lower grid plate 2 are connected with the distance posts 13 through screws 14. One front vane slider 3 and two front vane spacers 11 are filled up and down symmetrically in front grooves 20 of the upper grid plate 1 and the lower grid plate 2, respectively (as shown in fig. 3 and 5), and are fixed by set screws mounted in the screw holes 17 as shown in fig. 3 and 5. One trailing blade slider 4 and two trailing blade spacers 12 are filled up and down symmetrically in the rear grooves 21 of the upper grid 1 and the lower grid 2, respectively (as shown in fig. 3 and 5), and are fixed by set screws mounted in the screw holes 18 as shown in fig. 3 and 5. The front blade 5 with the static pressure hole on the pressure surface, the front blade 6 with the static pressure hole on the suction surface and the four front blades 9 without measuring the static pressure are arranged between the front blade slots 22 of the two front blade sliding blocks 3; the rear blade 7 with the static pressure hole on the pressure surface, the rear blade 8 with the static pressure hole on the suction surface and the four rear blades 10 without measuring the static pressure are arranged between the rear blade slots 23 of the two rear blade sliding blocks 4.
The upper grid 1 is constructed as shown in fig. 2 and 3. The upper grid plate 1 is 20mm thick and is provided with two grooves 11mm deep, and the upper grid plate can be divided into a front groove 20 and a rear groove 21 according to the axial position of the grid. As shown in fig. 1, the front groove 20 is located in the upstream direction of the wind tunnel, the front vane slider 3 is installed at a corresponding position in the groove according to the requirement of the experiment on the axial distance, and the tandem cascade front vane row is installed on the front vane slider 3. The remaining space of the front groove 20 is filled with a front vane pad 11 prefabricated according to an experimental scheme to precisely control the axial position of the front vane slider 3 and prevent air leakage. The dimensions of the front vane spacer 11 in fact determine the position of the front vane slide 3 and also the axial spacing of the tandem vane cascade. The rear groove 21 is located in the downstream direction of the front groove, the rear vane sliding blocks 4 are installed in the corresponding positions in the grooves according to the requirement of experiments on circumferential spacing, and the tandem cascade rear vane row is installed on the rear vane sliding blocks 4. The remaining space of the trailing slot 21 is filled with a trailing blade pad 12 prefabricated according to the experimental scheme to precisely control the circumferential position of the trailing blade slider 4 and prevent air leakage. Likewise, the size of the trailing blade pad 12 determines the position of the trailing blade slider 4 and also determines the circumferential spacing of the tandem cascade. The grating is completely opened in the middle area of the front and rear slots 20, 21 so that the static tube 16 of the intermediate blade shown in fig. 1 can extend beyond the grating within an adjustable range. Two threaded through holes 17 are provided upstream of the front slot 20 for receiving set screws to secure the front vane slide 3 and the front vane spacer 11. A threaded through hole 18 is provided on each of the left and right sides of the rear groove 21 for receiving a set screw to fix the trailing blade slider 4 and the trailing blade pad 12. The threaded through hole 18 has a coaxial unthreaded hole 19 on the outside, the diameter of which is slightly larger than the outer diameter of the threaded through hole 18, so as to facilitate the insertion and installation of a set screw. In order to facilitate installation in the wind tunnel test section of the cascade, the left side and the right side of the upper grid plate 1 are provided with nine installation through holes 15 for installing two distance posts 13, and the through holes 15 which do not interfere with the wind tunnel test section are selected during installation.
The structure of the lower louver 2 is shown in fig. 4 and 5. The lower grid plate 2 and the upper grid plate 1 are mirror symmetric up and down along the middle section of the blade height, and therefore are not described in detail herein. Referring to fig. 1, two distance posts 13 with a length of 100mm are respectively installed on the two sides of the upper grid plate 1 and the lower grid plate 2 through screws 14, so as to connect, fix and control the distance between the upper grid plate and the lower grid plate.
As shown in fig. 6 and 7, the front vane slider 3 is a rectangular parallelepiped, has the same height as the depth of the front groove 20, has the same circumferential dimension as the front groove 20, and forms a clearance fit. The front blade sliding block 3 is provided with 6 penetrating front blade slots 22 at equal intervals along the circumferential direction, and the cross sections of the front blade slots 22 are consistent with plugs at two ends of the front blades and form clearance fit. As shown in fig. 1, four static pressure non-measuring front vanes 9 are mounted in the two leftmost and two rightmost slots 22 by clearance fit; the front blade 5 with the static pressure hole on the pressure surface and the front blade 6 with the static pressure hole on the suction surface are arranged in the two slots 22 in the middle in a clearance fit mode, and the pressure surface of the front blade 5 with the static pressure hole on the pressure surface is opposite to the suction surface of the front blade 6 with the static pressure hole on the suction surface, so that the static pressure of the surfaces of the blades on two sides of the blade channel in the middle can be measured. The two front vane sliding blocks 3 are symmetrically arranged in the front grooves 20 of the upper grid plate 1 and the lower grid plate 2 up and down, and the installation positions are determined according to the axial distance required by experiments. The front row of blades with the height of 100mm is arranged between the two front blade sliding blocks 3 and is clamped and fixed by screws 14 arranged at two ends of two 100mm distance posts 13 after assembly.
The trailing blade slider 4 is, as shown in fig. 8 and 9, a rectangular parallelepiped, has the same height as the depth of the trailing groove 21, has the same axial dimension as the trailing groove 21, and forms a clearance fit. The rear vane slider 4 is provided with 6 rear vane slots 23 which are communicated at equal intervals along the circumferential direction, and the cross sections of the rear vane slots 23 are consistent with plugs at two ends of the rear vane and form clearance fit. As shown in fig. 1, four rear blades 10 that do not measure static pressure are mounted in the two leftmost and two rightmost slots 23 by clearance fit; the rear blade 7 with the static pressure hole on the pressure surface and the rear blade 8 with the static pressure hole on the suction surface are arranged in the two slots 23 in the middle in a clearance fit mode, and the pressure surface of the rear blade 7 with the static pressure hole on the pressure surface is opposite to the suction surface of the rear blade 8 with the static pressure hole on the suction surface, so that the static pressure of the surfaces of the blades on two sides of the blade channel in the middle can be measured. The two rear vane sliding blocks 4 are symmetrically arranged in the rear grooves 21 of the upper grid plate 1 and the lower grid plate 2 up and down, and the installation positions are determined according to the circumferential distance required by the experiment. The rear row of blades with the height of 100mm is arranged between the two rear blade sliding blocks 4 and is clamped and fixed by screws 14 arranged at the two ends of two 100mm distance posts 13 after assembly.
The front blade 5 with static pressure holes on the pressure surface is shown in fig. 10 and 11, the chord length is 34.7mm, the blade height is 100mm, the inlet geometric angle is 55 degrees, and the outlet geometric angle is 32 degrees. The partial profiles at the upper and lower ends of the blade respectively extend for 10mm to form plugs, and the plugs are inserted into the front blade slots 22 on the front blade sliding blocks 3 for fixing during assembly. And 8 static pressure holes 24 vertical to the pressure surface are uniformly formed at the blade heights of 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of the blade of 0.8mm and a static pressure pipe 16 which is inserted into the outlet end of the cavity 25 and sealed, and the surface static pressure of the blade can be measured through a pressure scanning valve.
As shown in fig. 12 and 13, the front blade 6 with static pressure holes on the suction surface has the same blade profile as the front blade 5 with static pressure holes on the pressure surface, but 8 static pressure holes 24 perpendicular to the suction surface are uniformly arranged at blade heights 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of 0.8mm and a static pressure pipe 16 inserted into the outlet end of the cavity 25 and sealed, and the static pressure on the surface of the blade can be measured through a pressure scanning valve.
The rear blade 7 with static pressure holes on the pressure surface is shown in fig. 14 and 15, the chord length is 34.7mm, the blade height is 100mm, the inlet geometric angle is 38 degrees, and the outlet geometric angle is-8 degrees. The chord length of the rear blade is the same as that of the front blade, and the bending angle is twice of that of the front blade. The partial profiles at the upper end and the lower end of the blade respectively extend for 10 millimeters to form a plug, and the plug is inserted into a rear blade slot 23 on the rear blade sliding block 4 for fixing during assembly. 8 static pressure holes 24 vertical to the pressure surface are uniformly arranged at the blade heights of 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of the blade of 0.8mm and a static pressure pipe 16 which is inserted into the outlet end of the cavity 25 and sealed, and the surface static pressure of the blade can be measured through a pressure scanning valve.
As shown in fig. 16 and 17, the suction surface-opened static pressure hole rear blade 8 has the same blade profile as the pressure surface-opened static pressure hole rear blade 7, but 8 static pressure holes 24 perpendicular to the suction surface are uniformly opened at blade heights 10mm and 50mm from the blade root in the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of 0.8mm of the blade and a static pressure pipe 16 inserted into the outlet end of the cavity 25 and sealed, and the static pressure of the blade surface can be measured through a pressure scanning valve.
As shown in fig. 18 and 19, the front blade 9 without static pressure measurement has the same blade profile as the front blade 5 with static pressure holes on the pressure surface, but does not have the static pressure holes on the blade surface and the internal cavity.
As shown in fig. 20 and 21, the trailing blade 10 without static pressure measurement has the same blade profile as the trailing blade 7 with static pressure holes on the pressure surface, but does not have the static pressure holes on the blade surface and the internal cavity.
As shown in fig. 22, the front blade pad 11 is a rectangular parallelepiped, has the same height as the depth of the front groove 20, has the same circumferential dimension as the front groove 20, and forms a clearance fit. The remaining space for filling the front groove 20 of the upper grid plate 1 and the lower grid plate 2 after the position of the front vane slider 3 is determined is fixed by a set screw installed at the screw hole 17 at the upstream side of the front groove 20. Before the experiment, the corresponding front blade cushion block 11 is prepared according to the pre-planned axial distance. The front vane pad 11 actually serves to position, secure and reduce air leakage to the front vane slide 3.
The trailing blade pad 12 is a rectangular parallelepiped as shown in fig. 23, and has the same height as the depth of the rear groove 21 and the same axial dimension as the rear groove 21, and forms a clearance fit. The rear blade slider 4 is used for filling the residual space of the rear groove 21 of the upper grid plate 1 and the lower grid plate 2 after being positioned, and is fixed by two fastening screws arranged at the threaded holes 18 at the two sides of the rear groove 21. The corresponding trailing pad 12 is prepared according to the pre-planned circumferential spacing prior to the experiment. The trailing blade pad 12 actually serves to position, secure and reduce air leakage to the trailing blade slider 4.
The distance posts 13 are as shown in fig. 24 and 25, and have a height of 100mm, which is the same height as the blade. Both ends of the distance column 13 are provided with blind threaded holes for connecting with the screws 14. As shown in figure 1, nine mounting through holes 15 are formed in the left side and the right side of the upper grid plate 1 and the lower grid plate 2, and two distance posts 13 are mounted on the two sides of the upper grid plate 1 and the lower grid plate 2 through screws 14 respectively in a left-right mode to play a role in connecting, fixing and controlling the distance between the upper grid plate 1 and the lower grid plate 2.
The assembling process of the experimental device comprises the following steps:
the first step is as follows: the blade root ends of four front blades 9 which do not measure static pressure are respectively arranged in two slots 22 at the leftmost side and two slots at the rightmost side of one front blade sliding block 3; the blade root ends of a front blade 5 with a static pressure hole on the pressure surface and a front blade 6 with a static pressure hole on the suction surface are arranged in 2 slots 22 in the middle of the front blade sliding block 3, and the measuring surfaces of the two static pressure holes are opposite. Another front vane slider 3 is then mounted on the tip of the 6 vanes.
The second step is that: respectively installing the blade root ends of four rear blades 10 which do not measure static pressure in two slots 23 at the leftmost side and two slots at the rightmost side of one rear blade sliding block 4; the blade root ends of a rear blade 7 with a static pressure hole on the pressure surface and a rear blade 8 with a static pressure hole on the suction surface are arranged in 2 slots 23 in the middle of the rear blade sliding block 4, and the measuring surfaces of the two static pressure holes are opposite. Another trailing blade slider 4 is then mounted on the tip of the 6 blades.
The third step: the integral blade root end front blade sliding block 3 assembled in the first step is placed in a front groove 20 of a lower grid plate 2, the position of the front blade sliding block 3 is adjusted in the groove according to the axial distance planned by an experiment, one or two prefabricated front blade cushion blocks 11 are filled in the residual space, namely if the front blade sliding block 3 is arranged at one end of the front groove 20, only one front blade cushion block 11 needs to be filled at the other end, and if the front blade sliding block 3 is arranged at the middle position of the front groove 20, one front blade cushion block 11 needs to be filled at each of the two ends. Finally, the front blade cushion block 11 and the front blade sliding block 3 are fixed by installing set screws in the two threaded through holes 17 on the upstream side of the front groove 20.
The fourth step: and placing the integral blade root end trailing blade sliding block 4 assembled in the second step in a trailing groove 21 of the lower grid plate 2, adjusting the position of the trailing blade sliding block 4 in the groove according to the circumferential distance planned by the experiment, filling two prefabricated trailing blade cushion blocks 12 in the residual space, and finally installing the trailing blade cushion blocks 12 and the trailing blade sliding block 4 in threaded through holes 18 on two sides of the trailing groove 21 by using set screws to fix the trailing blade cushion blocks 12 and the trailing blade sliding block 4.
The fifth step: installing a front vane slide block 3 and a rear vane slide block 4 at the tip of a vane in a front groove 20 and a rear groove 21 of an upper grid plate 1, filling a front vane cushion block 11 which is the same as that in the third step in the symmetrical position of the front groove 20, filling two rear vane cushion blocks 12 which are the same as that in the fourth step in the symmetrical position of the rear groove 21, and finally installing two set screws in a threaded through hole 17 at the upstream side of the front groove 20 to fix the front vane cushion block 11 and the front vane slide block 3; two set screws are installed in the threaded through holes 18 on both sides of the rear groove 21 to fix the trailing blade pad 12 and the trailing blade slider 4.
And a sixth step: two ends of two distance posts 13 are respectively installed between the through holes 15 at two sides of the lower grid plate 2 and the upper grid plate 1 by screws 14. If the distance posts 13 interfere with the test section components during subsequent installation into the wind tunnel test section, another suitable location of the through holes 15 can be selected.
After the experimental device is assembled according to the preset axial distance and the preset circumferential distance, the device is installed in a cascade wind tunnel test section for experiment. After the experiment is finished, the device is disassembled, and the axial distance or the circumferential distance of the tandem blade cascades needs to be adjusted according to the next experimental scheme. At this point, the experimental device needs to be partially disassembled, adjusted and reinstalled.
Firstly, the screws 14 at the two ends of the two distance posts 13 are dismounted, and the clamping of the blades and the front blade sliding blocks 3 and the rear blade sliding blocks 4 by the upper grid plate 1 and the lower grid plate 2 is released. Because the front blade sliding block 3 and the front blade cushion block 11 are in clearance fit with the front grooves 20 of the upper grid plate 1 and the lower grid plate 2, and the rear blade sliding block 4 and the rear blade cushion block 12 are also in clearance fit with the rear grooves 21 of the upper grid plate 1 and the lower grid plate 2, the upper grid plate 1 and the lower grid plate 2 can be detached only by unscrewing the set screws in the threaded holes 17 and the set screws in the threaded holes 18 of the upper grid plate 1 and the lower grid plate 2. And then restarting the assembly from the fourth step of the assembly process according to the axial spacing and the circumferential spacing of the next experiment.
Example 2: the embodiment is an experimental device for a serial cascade of a gas compressor, and the circumferential distance of the serial cascade can be adjusted.
As shown in fig. 26, the tandem cascade experimental apparatus for a compressor proposed in the present embodiment includes an upper grid plate 1, a lower grid plate 2, a trailing blade slider 4, a front blade 5 with a static pressure hole on a pressure surface, a front blade 6 with a static pressure hole on a suction surface, a trailing blade 7 with a static pressure hole on a pressure surface, a trailing blade 8 with a static pressure hole on a suction surface, a front blade 9 with no static pressure measurement, a trailing blade 10 with no static pressure measurement, a trailing blade pad 12, and a distance pole 13. The device is integrally mirror-symmetrical up and down along the middle section of the height of the blade, and the upper grid plate 1 and the lower grid plate 2 are connected with the distance posts 13 through screws 14. One trailing blade slider 4 and two trailing blade spacers 12 are filled up and down symmetrically in the rear grooves 21 of the upper grid 1 and the lower grid 2, respectively (as shown in fig. 28 and 30), and are fixed by set screws mounted in the screw holes 18 as shown in fig. 28 and 30. The front blade 5 with the static pressure hole on the pressure surface, the front blade 6 with the static pressure hole on the suction surface and the four front blades 9 without static pressure measurement are arranged between the front blade slots 22 of the upper grid plate 1 and the lower grid plate 2 in a clearance fit manner; the rear blade 7 with the static pressure hole on the pressure surface, the rear blade 8 with the static pressure hole on the suction surface and the four rear blades 10 without static pressure measurement are arranged between the rear blade slots 23 of the two rear blade sliding blocks 4 in a clearance fit mode.
The structure of the upper grid 1 is shown in fig. 27 and 28. The upper grid plate 1 is 20mm thick, 6 penetrating front blade slots 22 are formed in the mounting position of the front blade at equal intervals along the circumferential direction, and the cross sections of the front blade slots 22 are consistent with plugs at two ends of the front blade and form clearance fit. The upper grid 1 is provided with a rear groove 21 of 11mm depth in the rear blade mounting region. As shown in fig. 26, the rear groove 21 is located downstream of the front blade row, the trailing blade slider 4 is installed at a corresponding position in the groove according to the requirement of the circumferential spacing in the experiment, and the tandem cascade rear blade row is installed on the trailing blade slider 4. The remaining space of the trailing slot 21 is filled with a trailing blade pad 12 prefabricated according to the experimental scheme to precisely control the circumferential position of the trailing blade slider 4 and prevent air leakage. In fact, the size of the trailing blade pad 12 determines the position of the trailing blade slider 4, determining the circumferential spacing of the tandem cascade. The central region of the rear channel 21 is completely open to the grid so that the static tube 16 of the central blade, as shown in fig. 26, can extend beyond the grid within an adjustable range. A threaded through hole 18 is provided on each of the left and right sides of the rear groove 21 for receiving a set screw to fix the trailing blade slider 4 and the trailing blade pad 12. The threaded through hole 18 has a coaxial unthreaded hole 19 on the outside, the diameter of which is slightly larger than the outer diameter of the threaded through hole 18, so as to facilitate the insertion and installation of a set screw. In order to facilitate installation in the wind tunnel test section of the cascade, the left side and the right side of the upper grid plate 1 are provided with nine installation through holes 15 for installing two distance posts 13, and the through holes 15 which do not interfere with the wind tunnel test section are selected during installation.
The structure of the lower louver 2 is shown in fig. 29 and 30. The lower grid plate 2 and the upper grid plate 1 are mirror symmetric up and down along the middle section of the blade height, and therefore are not described in detail herein. As shown in the combined view of FIG. 26, two distance posts 13 with a length of 100mm are respectively arranged on the two sides of the upper grid plate 1 and the lower grid plate 2 through screws 14, and are used for connecting, fixing and controlling the distance between the upper grid plate and the lower grid plate.
The trailing blade slider 4 is, as shown in fig. 8 and 9, a rectangular parallelepiped, has the same height as the depth of the trailing groove 21, has the same axial dimension as the trailing groove 21, and forms a clearance fit. The rear vane slider 4 is provided with 6 rear vane slots 23 which are communicated at equal intervals along the circumferential direction, and the cross sections of the rear vane slots 23 are consistent with plugs at two ends of the rear vane and form clearance fit. As shown in fig. 26, four rear blades 10 that do not measure static pressure are mounted in the two leftmost and two rightmost slots 23 by clearance fit; the rear blade 7 with the static pressure hole on the pressure surface and the rear blade 8 with the static pressure hole on the suction surface are arranged in the two slots 23 in the middle in a clearance fit mode, and the pressure surface of the rear blade 7 with the static pressure hole on the pressure surface is opposite to the suction surface of the rear blade 8 with the static pressure hole on the suction surface, so that the static pressure of the surfaces of the blades on two sides of the blade channel in the middle can be measured. The two rear vane sliding blocks 4 are symmetrically arranged in the rear grooves 21 of the upper grid plate 1 and the lower grid plate 2 up and down, and the installation positions are determined according to the circumferential distance required by the experiment. The rear row of blades with the height of 100mm is arranged between the two rear blade sliding blocks 4 and is clamped and fixed by screws 14 arranged at the two ends of two 100mm distance posts 13 after assembly.
The front blade 5 with static pressure holes on the pressure surface is shown in fig. 10 and 11, the chord length is 34.7mm, the blade height is 100mm, the inlet geometric angle is 55 degrees, and the outlet geometric angle is 32 degrees. The partial profiles of the upper and lower ends of the blade extend 10mm to form plugs, and are inserted into the front blade slots 22 of the upper grid plate 1 and the lower grid plate 2 for fixing during assembly. And 8 static pressure holes 24 vertical to the pressure surface are uniformly formed at the blade heights of 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of the blade of 0.8mm and a static pressure pipe 16 which is inserted into the outlet end of the cavity 25 and sealed, and the surface static pressure of the blade can be measured through a pressure scanning valve.
As shown in fig. 12 and 13, the front blade 6 with static pressure holes on the suction surface has the same blade profile as the front blade 5 with static pressure holes on the pressure surface, but 8 static pressure holes 24 perpendicular to the suction surface are uniformly arranged at blade heights 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of 0.8mm and a static pressure pipe 16 inserted into the outlet end of the cavity 25 and sealed, and the static pressure on the surface of the blade can be measured through a pressure scanning valve.
The rear blade 7 with static pressure holes on the pressure surface is shown in fig. 14 and 15, the chord length is 34.7mm, the blade height is 100mm, the inlet geometric angle is 38 degrees, and the outlet geometric angle is-8 degrees. The chord length of the rear blade is the same as that of the front blade, and the bending angle is twice of that of the front blade. The partial profiles at the upper end and the lower end of the blade respectively extend for 10mm to form a plug, and the plug is inserted into the blade slot 23 on the rear blade sliding block 4 for fixing during assembly. 8 static pressure holes 24 vertical to the pressure surface are uniformly arranged at the blade heights of 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of the blade of 0.8mm and a static pressure pipe 16 which is inserted into the outlet end of the cavity 25 and sealed, and the surface static pressure of the blade can be measured through a pressure scanning valve.
As shown in fig. 16 and 17, the suction surface-opened static pressure hole rear blade 8 has the same blade profile as the pressure surface-opened static pressure hole rear blade 7, but 8 static pressure holes 24 perpendicular to the suction surface are uniformly opened at blade heights 10mm and 50mm from the blade root in the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of 0.8mm of the blade and a static pressure pipe 16 inserted into the outlet end of the cavity 25 and sealed, and the static pressure of the blade surface can be measured through a pressure scanning valve.
As shown in fig. 18 and 19, the front blade 9 without static pressure measurement has the same blade profile as the front blade 5 with static pressure holes on the pressure surface, but does not have the static pressure holes on the blade surface and the internal cavity.
As shown in fig. 20 and 21, the trailing blade 10 without static pressure measurement has the same blade profile as the trailing blade 7 with static pressure holes on the pressure surface, but does not have the static pressure holes on the blade surface and the internal cavity.
The trailing blade pad 12 is a rectangular parallelepiped as shown in fig. 23, and has the same height as the depth of the rear groove 21 and the same axial dimension as the rear groove 21, and forms a clearance fit. The rear blade slider 4 is used for filling the residual space of the rear groove 21 of the upper grid plate 1 and the lower grid plate 2 after being positioned, and is fixed by two fastening screws arranged at the threaded holes 18 at the two sides of the rear groove 21. The corresponding trailing pad 12 is prepared according to the pre-planned circumferential spacing prior to the experiment. The trailing blade pad 12 actually serves to position, secure and reduce air leakage to the trailing blade slider 4.
The distance posts 13 are as shown in fig. 24 and 25, and have a height of 100mm, which is the same height as the blade. Both ends of the distance column 13 are provided with blind threaded holes for connecting with the screws 14. As shown in FIG. 26, nine mounting through holes 15 are formed on the left side and the right side of the upper grid plate 1 and the lower grid plate 2, and two distance posts 13 are respectively mounted on the left side and the right side of the upper grid plate 1 and the lower grid plate 2 through screws 14, so that the functions of connecting, fixing and controlling the distance between the upper grid plate 1 and the lower grid plate 2 are achieved.
The assembling process of the experimental device comprises the following steps:
the first step is as follows: the blade root ends of four front blades 9 which do not measure static pressure are respectively arranged in two slots 22 at the leftmost side and two slots at the rightmost side of the lower grid plate 2; the blade root ends of a front blade 5 with a static pressure hole on the pressure surface and a front blade 6 with a static pressure hole on the suction surface are arranged in 2 slots 22 in the middle of the lower grid plate 2, and the measuring surfaces of the two static pressure holes are opposite.
The second step is that: respectively installing the blade root ends of four rear blades 10 which do not measure static pressure in two slots 23 at the leftmost side and two slots at the rightmost side of one rear blade sliding block 4; the blade root ends of a rear blade 7 with a static pressure hole on the pressure surface and a rear blade 8 with a static pressure hole on the suction surface are arranged in 2 slots 23 in the middle of the rear blade sliding block 4, and the measuring surfaces of the two static pressure holes are opposite. Another trailing blade slider 4 is then mounted on the tip of the 6 blades.
The third step: and placing the integral blade root end trailing blade sliding block 4 assembled in the second step in a trailing groove 21 of the lower grid plate 2, adjusting the position of the trailing blade sliding block 4 in the groove according to the circumferential distance planned by the experiment, filling two prefabricated trailing blade cushion blocks 12 in the residual space, and finally installing the trailing blade cushion blocks 12 and the trailing blade sliding block 4 in threaded through holes 18 on two sides of the trailing groove 21 by using set screws to fix the trailing blade cushion blocks 12 and the trailing blade sliding block 4.
The fourth step: moving the whole assembled before, installing the circumferential sliding blocks 4 of the blade tips and the rear blade tips of the front blades 5, 6 and 9 in the front blade slot 22 and the rear slot 21 of the upper grid plate 1, filling the two rear blade cushion blocks 12 same as the third step in the symmetrical positions of the rear slot 21, and finally installing two set screws in the threaded through holes 18 at the two sides of the rear slot 21 to fix the rear blade cushion blocks 12 and the rear blade sliding blocks 4.
The fifth step: two ends of two distance posts 13 are respectively installed between the through holes 15 at two sides of the lower grid plate 2 and the upper grid plate 1 by screws 14. If the distance posts 13 interfere with the test section components during subsequent installation into the wind tunnel test section, another suitable location of the through holes 15 can be selected.
After the experimental device is assembled according to the preset circumferential distance, the device is installed in a cascade wind tunnel test section for experiment. After the experiment is finished, the device is disassembled, and the circumferential distance of the tandem blade cascades needs to be adjusted according to the next experimental scheme. At this point, the experimental device needs to be partially disassembled, adjusted and reinstalled.
Firstly, the screws 14 at the two ends of the two distance posts 13 are detached, and the clamping of the upper grid plate 1 and the lower grid plate 2 on the blade and the rear vane sliding block 4 is released. Because the rear blade sliding block 4 and the rear blade cushion block 12 are in clearance fit with the rear grooves 21 of the upper grid plate 1 and the lower grid plate 2, the upper grid plate 1 and the lower grid plate 2 can be detached from the two ends of the rear blade sliding block 4 only by unscrewing the set screws in the threaded holes 18 of the upper grid plate 1 and the lower grid plate 2. Assembly is then resumed from the third step of the assembly process at the circumferential spacing of the next experiment.
Example 3: the embodiment is an experimental device for a serial cascade of a gas compressor, and the axial distance of the serial cascade can be adjusted.
As shown in fig. 1, the tandem cascade experimental apparatus for a compressor proposed in the embodiment of the present invention includes an upper grid plate 1, a lower grid plate 2, a front vane slider 3, a front vane 5 with a static pressure hole on a pressure surface, a front vane 6 with a static pressure hole on a suction surface, a rear vane 7 with a static pressure hole on a pressure surface, a rear vane 8 with a static pressure hole on a suction surface, a front vane 9 without measuring static pressure, a rear vane 10 without measuring static pressure, a front vane cushion block 11, and a distance pole 13. The device is integrally mirror-symmetrical up and down along the middle section of the height of the blade, and the upper grid plate 1 and the lower grid plate 2 are connected with the distance posts 13 through screws 14. One front vane slider 3 and two front vane spacers 11 are filled up and down symmetrically in front grooves 20 of the upper grid plate 1 and the lower grid plate 2, respectively (as shown in fig. 3 and 5), and are fixed by set screws mounted in the screw holes 17 as shown in fig. 3 and 5. The front blade 5 with the static pressure hole on the pressure surface, the front blade 6 with the static pressure hole on the suction surface and the four front blades 9 without measuring the static pressure are arranged between the front blade slots 22 of the two front blade sliding blocks 3; the rear blade 7 with the static pressure hole on the pressure surface, the rear blade 8 with the static pressure hole on the suction surface and the four rear blades 10 without measuring the static pressure are arranged between the rear blade slots 23 of the upper grid plate 1 and the lower grid plate 2.
The upper grid 1 is constructed as shown in fig. 2 and 3. The upper grid plate 1 is 20mm thick and is provided with a front groove 20 with the depth of 11 mm. As shown in fig. 1, the front groove 20 is located in the upstream direction of the wind tunnel, the front vane slider 3 is installed at a corresponding position in the groove according to the requirement of the experiment on the axial distance, and the tandem cascade front vane row is installed on the front vane slider 3. The remaining space of the front groove 20 is filled with a front vane pad 11 prefabricated according to an experimental scheme to precisely control the axial position of the front vane slider 3 and prevent air leakage. The dimensions of the front vane spacer 11 in fact determine the position of the front vane slide 3 and also the axial spacing of the tandem vane cascade. The grating is completely opened in the middle area of the front slot 20 so that the static tube 16 of the intermediate blade shown in fig. 1 can extend beyond the grating within an adjustable range. Two threaded through holes 17 are provided upstream of the front slot 20 for receiving set screws to secure the front vane slide 3 and the front vane spacer 11. In order to facilitate installation in the wind tunnel test section of the cascade, the left side and the right side of the upper grid plate 1 are provided with nine installation through holes 15 for installing two distance posts 13, and the through holes 15 which do not interfere with the wind tunnel test section are selected during installation.
The structure of the lower louver 2 is shown in fig. 4 and 5. The lower grid plate 2 and the upper grid plate 1 are mirror symmetric up and down along the middle section of the blade height, and therefore are not described in detail herein. Referring to fig. 1, two distance posts 13 with a length of 100mm are respectively installed on the two sides of the upper grid plate 1 and the lower grid plate 2 through screws 14, so as to connect, fix and control the distance between the upper grid plate and the lower grid plate.
As shown in fig. 6 and 7, the front vane slider 3 is a rectangular parallelepiped, has the same height as the depth of the front groove 20, has the same circumferential dimension as the front groove 20, and forms a clearance fit. The front blade sliding block 3 is provided with 6 penetrating front blade slots 22 at equal intervals along the circumferential direction, and the cross sections of the front blade slots 22 are consistent with plugs at two ends of the front blades and form clearance fit. As shown in fig. 1, four static pressure non-measuring front vanes 9 are mounted in the two leftmost and two rightmost slots 22 by clearance fit; the front blade 5 with the static pressure hole on the pressure surface and the front blade 6 with the static pressure hole on the suction surface are arranged in the two slots 22 in the middle in a clearance fit mode, and the pressure surface of the front blade 5 with the static pressure hole on the pressure surface is opposite to the suction surface of the front blade 6 with the static pressure hole on the suction surface, so that the static pressure of the surfaces of the blades on two sides of the blade channel in the middle can be measured. The two front vane sliding blocks 3 are symmetrically arranged in the front grooves 20 of the upper grid plate 1 and the lower grid plate 2 up and down, and the installation positions are determined according to the axial distance required by experiments. The front row of blades with the height of 100mm is arranged between the two front blade sliding blocks 3 and is clamped and fixed by screws 14 arranged at two ends of two 100mm distance posts 13 after assembly.
The front blade 5 with static pressure holes on the pressure surface is shown in fig. 10 and 11, the chord length is 34.7mm, the blade height is 100mm, the inlet geometric angle is 55 degrees, and the outlet geometric angle is 32 degrees. The partial profiles at the upper and lower ends of the blade respectively extend for 10mm to form plugs, and the plugs are inserted into the front blade slots 22 on the front blade sliding blocks 3 for fixing during assembly. And 8 static pressure holes 24 vertical to the pressure surface are uniformly formed at the blade heights of 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of the blade of 0.8mm and a static pressure pipe 16 which is inserted into the outlet end of the cavity 25 and sealed, and the surface static pressure of the blade can be measured through a pressure scanning valve.
As shown in fig. 12 and 13, the front blade 6 with static pressure holes on the suction surface has the same blade profile as the front blade 5 with static pressure holes on the pressure surface, but 8 static pressure holes 24 perpendicular to the suction surface are uniformly arranged at blade heights 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of 0.8mm and a static pressure pipe 16 inserted into the outlet end of the cavity 25 and sealed, and the static pressure on the surface of the blade can be measured through a pressure scanning valve.
The rear blade 7 with static pressure holes on the pressure surface is shown in fig. 14 and 15, the chord length is 34.7mm, the blade height is 100mm, the inlet geometric angle is 38 degrees, and the outlet geometric angle is-8 degrees. The chord length of the rear blade is the same as that of the front blade, and the bending angle is twice of that of the front blade. The partial profiles of the upper and lower ends of the blade extend 10mm to form plugs, and are inserted into the rear blade slots 23 of the upper grid plate 1 and the lower grid plate 2 for fixing during assembly. 8 static pressure holes 24 vertical to the pressure surface are uniformly arranged at the blade heights of 10mm and 50mm away from the blade root along the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of the blade of 0.8mm and a static pressure pipe 16 which is inserted into the outlet end of the cavity 25 and sealed, and the surface static pressure of the blade can be measured through a pressure scanning valve.
As shown in fig. 16 and 17, the suction surface-opened static pressure hole rear blade 8 has the same blade profile as the pressure surface-opened static pressure hole rear blade 7, but 8 static pressure holes 24 perpendicular to the suction surface are uniformly opened at blade heights 10mm and 50mm from the blade root in the chord length direction, the diameter of each static pressure hole is 0.4mm, the static pressure holes are led out to the outside through a cavity 25 with the inner diameter of 0.8mm of the blade and a static pressure pipe 16 inserted into the outlet end of the cavity 25 and sealed, and the static pressure of the blade surface can be measured through a pressure scanning valve.
As shown in fig. 18 and 19, the front blade 9 without static pressure measurement has the same blade profile as the front blade 5 with static pressure holes on the pressure surface, but does not have the static pressure holes on the blade surface and the internal cavity.
As shown in fig. 20 and 21, the trailing blade 10 without static pressure measurement has the same blade profile as the trailing blade 7 with static pressure holes on the pressure surface, but does not have the static pressure holes on the blade surface and the internal cavity.
As shown in fig. 22, the front blade pad 11 is a rectangular parallelepiped, has the same height as the depth of the front groove 20, has the same circumferential dimension as the front groove 20, and forms a clearance fit. The remaining space for filling the front groove 20 of the upper grid plate 1 and the lower grid plate 2 after the position of the front vane slider 3 is determined is fixed by a set screw installed at the screw hole 17 at the upstream side of the front groove 20. Before the experiment, the corresponding front blade cushion block 11 is prepared according to the pre-planned axial distance. The front vane pad 11 actually serves to position, secure and reduce air leakage to the front vane slide 3.
The distance posts 13 are as shown in fig. 24 and 25, and have a height of 100mm, which is the same height as the blade. Both ends of the distance column 13 are provided with blind threaded holes for connecting with the screws 14. As shown in figure 1, nine mounting through holes 15 are formed in the left side and the right side of the upper grid plate 1 and the lower grid plate 2, and two distance posts 13 are mounted on the two sides of the upper grid plate 1 and the lower grid plate 2 through screws 14 respectively in a left-right mode to play a role in connecting, fixing and controlling the distance between the upper grid plate 1 and the lower grid plate 2.
The assembling process of the experimental device comprises the following steps:
the first step is as follows: the blade root ends of four front blades 9 which do not measure static pressure are respectively arranged in two slots 22 at the leftmost side and two slots at the rightmost side of one front blade sliding block 3; the blade root ends of a front blade 5 with a static pressure hole on the pressure surface and a front blade 6 with a static pressure hole on the suction surface are arranged in 2 slots 22 in the middle of the front blade sliding block 3, and the measuring surfaces of the two static pressure holes are opposite. Another front vane slider 3 is then mounted on the tip of the 6 vanes.
The second step is that: the blade root ends of four rear blades 10 which do not measure static pressure are respectively arranged in two slots 23 at the leftmost side and two slots at the rightmost side of the lower grid plate 2; the blade root ends of the rear blade 7 with the static pressure holes on the pressure surface and the rear blade 8 with the static pressure holes on the suction surface are arranged in the middle 2 slots 23 of the lower grid plate 2, and the measuring surfaces of the two static pressure holes are opposite.
The third step: the integral blade root end front blade sliding block 3 assembled in the first step is placed in a front groove 20 of a lower grid plate 2, the position of the front blade sliding block 3 is adjusted in the groove according to the axial distance planned by an experiment, one or two prefabricated front blade cushion blocks 11 are filled in the residual space, namely if the front blade sliding block 3 is arranged at one end of the front groove 20, only one front blade cushion block 11 needs to be filled at the other end, and if the front blade sliding block 3 is arranged at the middle position of the front groove 20, one front blade cushion block 11 needs to be filled at each of the two ends. Finally, the front blade cushion block 11 and the front blade sliding block 3 are fixed by installing set screws in the two threaded through holes 17 on the upstream side of the front groove 20.
The fourth step: moving the whole assembled before, installing the blade root ends of the front blade sliding block 3 and the rear blades 7, 8 and 10 at the blade root ends into the front groove 20 and the rear blade slot 23 of the upper grid plate 1, filling two rear blade cushion blocks 12 which are the same as the third step at the symmetrical positions of the front groove 20, and finally installing two set screws into the threaded through holes 18 in the front side of the front groove 20 to fix the front blade cushion blocks 11 and the front blade sliding block 3.
The fifth step: two ends of two distance posts 13 are respectively installed between the through holes 15 at two sides of the lower grid plate 2 and the upper grid plate 1 by screws 14. If the distance posts 13 interfere with the test section components during subsequent installation into the wind tunnel test section, another suitable location of the through holes 15 can be selected.
After the experimental device is assembled according to the preset axial distance, the device is installed in a cascade wind tunnel test section for experiment. After the experiment is finished, the device is disassembled, and the axial distance of the tandem blade cascade needs to be adjusted according to the next experimental scheme. At this point, the experimental device needs to be partially disassembled, adjusted and reinstalled.
Firstly, the screws 14 at the two ends of the two distance posts 13 are detached, and the clamping of the blades by the upper grid plate 1 and the lower grid plate 2 with the front blade sliding block 3 and the rear blades 7, 8 and 10 is released. Because the front blade sliding block 3 and the front blade cushion block 11 are in clearance fit with the front grooves 20 of the upper grid plate 1 and the lower grid plate 2, the upper grid plate 1 and the lower grid plate 2 can be detached from the two ends of the front blade sliding block 3 only by unscrewing the set screws in the threaded holes 17 of the upper grid plate 1 and the lower grid plate 2. Assembly is then resumed from the third step of the assembly process according to the axial spacing of the next experiment.
Claims (3)
1. The experimental device for the tandem cascade of the air compressor is characterized by comprising an upper grid plate (1) and a lower grid plate (2), wherein the two grid plates are connected in parallel and at an adjustable interval, a front groove (20) and a rear groove (21) are respectively formed in the upper grid plate (1), and the same front groove (20) and the same rear groove (21) are also formed in the corresponding positions of the lower grid plate (2); the two front vane sliding blocks (3) are respectively provided with a plurality of front vane slots (22) at equal intervals along the circumferential direction and are respectively arranged in the front grooves (20) of the upper grid plate (1) and the lower grid plate (2), the two rear vane sliding blocks (4) are respectively provided with a same number of rear vane slots (23) at equal intervals along the circumferential direction and are respectively arranged in the rear grooves (21) of the upper grid plate (1) and the lower grid plate (2), the axial or circumferential positions of the sliding blocks in the grooves are moved, and the residual space is filled and fixed by cushion blocks; the tandem blades to be tested are divided into a front row and a rear row, two ends of the front row of blades are respectively arranged in a front blade slot (22) of a front blade sliding block (3), two ends of the rear row of blades are respectively arranged in a rear blade slot (23) of a rear blade sliding block (4), the relative position relation of the front blade row and the rear blade row of the tandem blade grid experimental piece is changed through the axial position or the circumferential position of the sliding blocks in the slots before the test, and the axial distance or the circumferential distance can be adjusted.
2. The compressor tandem cascade experimental device as claimed in claim 1, wherein the upper cascade plate (1) and the lower cascade plate (2) are connected in parallel and with adjustable distance through two distance posts (13).
3. The compressor tandem cascade experimental device as claimed in claim 1, wherein the number of the front blade slots (22) is 4-8.
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| CN112881026B (en) * | 2019-11-13 | 2022-11-15 | 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 |
| CN113865838B (en) * | 2020-06-12 | 2023-08-11 | 中国航发商用航空发动机有限责任公司 | Reverse thrust blade cascade test system and test reverse thrust blade cascade thereof |
| CN112985743B (en) * | 2021-02-25 | 2023-03-24 | 西北工业大学 | Plane cascade experimental device capable of independently adjusting installation angle |
| CN113418716B (en) * | 2021-06-05 | 2024-05-31 | 西北工业大学 | Blade cascade experimental device with adjustable blade top gap |
| CN114623101B (en) * | 2022-03-10 | 2023-06-09 | 北京航空航天大学 | Serial blade with variable circumferential position |
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| CN101059131B (en) * | 2007-05-25 | 2010-06-23 | 哈尔滨工业大学 | Blowing or sucking type air compressor cascade experiment system |
| CN100491950C (en) * | 2007-06-11 | 2009-05-27 | 哈尔滨工业大学 | Air compressor louver experiment device with adjustable additional blades based on relative motion concept |
| CN102287389A (en) * | 2011-07-07 | 2011-12-21 | 西北工业大学 | Experimental apparatus of compressor grate |
| CN202333203U (en) * | 2011-11-16 | 2012-07-11 | 河海大学常州校区 | Patch board with adjustable gap |
| CN103953579B (en) * | 2014-04-24 | 2016-08-31 | 成都中科航空发动机有限公司 | A kind of compressor rotor blade with top jag and method for designing |
| CN107152419B (en) * | 2017-07-24 | 2019-07-02 | 北京航空航天大学 | A kind of big bending angle compressor stator blade of root series connection multistage blade profile |
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| CN109374252A (en) | 2019-02-22 |
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