CN113252279A - Pneumatic test simulation device for impeller machinery - Google Patents
Pneumatic test simulation device for impeller machinery Download PDFInfo
- Publication number
- CN113252279A CN113252279A CN202110723275.8A CN202110723275A CN113252279A CN 113252279 A CN113252279 A CN 113252279A CN 202110723275 A CN202110723275 A CN 202110723275A CN 113252279 A CN113252279 A CN 113252279A
- Authority
- CN
- China
- Prior art keywords
- assembly
- chain
- simulation device
- simulation
- air outlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 61
- 238000012360 testing method Methods 0.000 title claims abstract description 54
- 230000007246 mechanism Effects 0.000 claims abstract description 59
- 230000005540 biological transmission Effects 0.000 claims description 20
- 238000003756 stirring Methods 0.000 claims description 16
- 239000012530 fluid Substances 0.000 claims description 12
- 238000004891 communication Methods 0.000 claims description 5
- 230000004308 accommodation Effects 0.000 claims 2
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 22
- 238000006243 chemical reaction Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 238000005381 potential energy Methods 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a pneumatic test simulation device for impeller machinery, and relates to the technical field of pneumatic tests. The device includes movable vane simulation subassembly, quiet leaf subassembly and air-out subassembly. The movable vane simulation assembly comprises a rotating mechanism and a wake generation mechanism, wherein the wake generation mechanism is arranged on the rotating mechanism and can rotate along with the rotating mechanism so as to enable the airflow to turn in the circumferential direction. The fixed blade assembly comprises a plurality of fixed blades arranged at intervals, gaps are formed between every two adjacent fixed blades, and the fixed blade assembly is communicated with the air outlet assembly through the gaps. This pneumatic experimental analogue means of impeller machinery can be through setting up movable vane simulation subassembly simulation movable vane, and its simple slewing mechanism and wake take place the mechanism and can make the air current take place circumference turn, have simulated the workflow of movable vane, have reduced experimental cost and the degree of difficulty, and this structural design is reasonable, and the practicality is strong.
Description
Technical Field
The invention relates to the technical field of pneumatic tests, in particular to a simulation device for a pneumatic test of an impeller machine.
Background
The impeller machine is a power machine which takes continuous rotating blades as a body and enables energy to be converted between fluid working media and shaft power. It can be divided into axial flow, radial flow, mixed flow, combined type, etc. according to the moving direction of the fluid. Generally, axial flow has high efficiency, large flow rate, but low pressure ratio (expansion ratio); radial efficiency, flow rate is slightly lower, but pressure ratio (expansion ratio is large). It belongs to power machinery under the disciplines of power engineering and engineering thermophysics, and two secondary disciplines of fluid machinery. The application is wide, including air compressors, turbines, rotors and the like in military aircrafts and ship engines; a marine propeller thruster; a water pump, a fan, a steam turbine, a wind turbine and a water turbine in the power generation system; turbine compressors and expanders used in the refrigeration industry; compressors, fans and the like in the chemical industry. Turbomachinery is often one of the most critical, most important components in these industries.
The existing impeller mechanical pneumatic test needs to provide a real movable impeller to perform test simulation, but the movable impeller structure is complex, the test cost and the test difficulty are large, and the simulation is not facilitated to be performed.
The inventor finds in research that at least the following disadvantages exist in the prior related art:
the test cost and the test difficulty are high.
Disclosure of Invention
The invention aims to provide a pneumatic test simulation device for impeller machinery, which can simulate an impeller by arranging an impeller simulation assembly, can enable airflow to turn circumferentially by a simple rotating mechanism and a wake generation mechanism, simulate the working process of the impeller, reduce the cost and difficulty of the test, and has reasonable structural design and strong practicability.
The embodiment of the invention is realized by the following steps:
the embodiment of the application provides a pneumatic test simulation device of impeller machinery, and it includes movable vane simulation subassembly, quiet leaf subassembly and air-out subassembly. The movable vane simulation assembly comprises a rotating mechanism and a trail generating mechanism, wherein the trail generating mechanism is arranged on the rotating mechanism and can rotate along with the rotating mechanism so as to enable the airflow to turn in the circumferential direction. The stator blade assembly comprises a plurality of stator blades arranged at intervals, gaps are formed between every two adjacent stator blades, and the stator blade assembly is communicated with the air outlet assembly through the gaps.
This pneumatic experimental analogue means of impeller machinery can be through setting up movable vane simulation subassembly simulation movable vane, and its simple slewing mechanism and wake take place the mechanism and can make the air current take place circumference turn, have simulated the workflow of movable vane, have reduced experimental cost and the degree of difficulty, and this structural design is reasonable, and the practicality is strong.
In some embodiments of the present invention, the rotating mechanism includes a driving sprocket, a driven sprocket, and a chain, the chain is wound around the driving sprocket, a contact surface between the driving sprocket and the chain is a sliding surface capable of sliding relative to each other, and a contact surface between the driven sprocket and the chain is a sliding surface capable of sliding relative to each other.
The chain transmission is engaged transmission taking a chain as a middle flexible part, and has the advantages of no elastic sliding, high friction coefficient, compact structure, small shaft pressing force and capability of working in severe environments such as high temperature and humidity compared with belt transmission; compared with gear transmission, the gear transmission has the advantages of suitability for remote transmission, low manufacturing cost and low installation precision, and the gear transmission is adopted, so that the structure is compact, the pressure shaft force is small, the cost is low, and the rotating working state of the moving blade can be simulated easily.
In some embodiments of the present invention, the chain includes a pin shaft and a link plate, the pin shaft is disposed through the link plate, the wake generation mechanism and the pin shaft are connected to each other, and an extending direction of the wake generation mechanism is perpendicular to a transmission direction of the chain.
The extending direction of the tail generating mechanism and the transmission direction of the chain are always kept perpendicular, so that the contact surface of the tail generating mechanism and gas can be enlarged, the circumferential turning of the gas flow is increased, the visibility of a test result is improved, and the teaching effect is improved obviously in the test effect.
In some embodiments of the present invention, the rotating mechanism further includes a motor, an output shaft of the motor is connected to the driving sprocket, and the output shaft can drive the driving sprocket to rotate along its own axis direction under the driving of the motor.
Adopt motor drive driving sprocket can improve this analogue means's intelligent degree, simultaneously, the motor has the characteristics that output is stable and output is big, and output is stable can improve experimental precision, and output can improve the dynamic characteristic of movable vane simulation component and gas contact greatly for the air current circumference turns and improves experimental apparent.
In some embodiments of the present invention, the wake generating mechanism includes a plurality of stirring rods, the number of the stirring rods is the same as the number of the pins, and the stirring rods and the pins are in one-to-one correspondence and are connected to each other.
The stirring rod has the characteristics of simple structure, stable function and low cost, and can bring about good circumferential turning of air flow after being matched with the pin shaft, thereby realizing effective conversion of mechanical work and fluid potential energy.
In some embodiments of the present invention, a plurality of the stirring rods are disposed on the chain at regular intervals along a plurality of the pins.
The stirring rods arranged at uniform intervals can uniformly do work on the air flow, so that the air flow generates circumferential turning in the movable blade and increases the absolute stagnation temperature (or total temperature for short) and absolute stagnation pressure (or total pressure for short), and meanwhile, the static pressure and the absolute speed of the air flow are also increased at the same time.
In some embodiments of the present invention, the turbomachinery pneumatic test simulation device further includes a casing assembly having an accommodating chamber, and the moving blade simulation assembly and the stationary blade assembly are disposed in the accommodating chamber. The shell assembly is further provided with a gas outlet, the gas outlet comprises two side openings and a gas outlet channel, the fixed blade assembly is arranged in the gas outlet channel, the gas outlet assembly is communicated with any one of the openings, and a rotating plate detachably connected with the other opening is arranged on the other opening.
The casing assembly is arranged to enable the periphery of the inner movable blade simulation assembly to have a boundary of a surface body, namely, gas moves in a channel of the movable blade simulation assembly between the inner wall surface and the outer wall surface, so that stable circumferential turning can be generated, and the absolute stagnation temperature and the absolute stagnation pressure of the movable blade simulation assembly can be increased.
In some embodiments of the present invention, the air outlet assembly includes an air outlet channel and an air tunnel, and the air tunnel is in fluid communication with the opening through the air outlet channel.
The air outlet channel and the wind tunnel are arranged, so that the airflow has an outlet, and a plurality of sensors are arranged in the air outlet channel and the wind tunnel, so that required test data can be measured.
In some embodiments of the present invention, a cross section of the wind tunnel is trapezoidal, and a small end of the wind tunnel is connected to the wind outlet channel.
The small end and the air outlet channel of the trapezoidal wind tunnel are connected with each other, and the large end faces outwards, so that more people can be arranged in the large end, and the accuracy of test data detection is improved.
In some embodiments of the invention, the housing assembly is elliptical in cross-section.
The oval shell assembly and the chain are mutually matched, the structure is simple, the cost is low, and the space can be saved.
Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:
this pneumatic experimental analogue means of impeller machinery can be through setting up movable vane simulation subassembly simulation movable vane, and its simple slewing mechanism and wake take place the mechanism and can make the air current take place circumference turn, have simulated the workflow of movable vane, have reduced experimental cost and the degree of difficulty, and this structural design is reasonable, and the practicality is strong.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of an impeller mechanical pneumatic test simulation device provided in an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a bucket simulation assembly according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of a vane assembly according to an embodiment of the present invention.
Icon: 100-impeller mechanical pneumatic test simulation device; 10-a bucket simulation assembly; 101-a rotation mechanism; 1011-a drive sprocket; 1012-driven sprocket; 1013-a chain; 1014-a pin shaft; 1015-chain plate; 102-a wake generating mechanism; 11-a vane assembly; 111-stationary blades; 12-an air outlet component; 121-an air outlet channel; 122-a wind tunnel; 123-a rotating plate; 13-housing assembly.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the embodiments of the present invention, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are usually placed in when used, the orientations or positional relationships are only used for convenience of describing the present invention and simplifying the description, but the terms do not indicate or imply that the devices or elements indicated must have specific orientations, be constructed in specific orientations, and operate, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not require that the components be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Examples
Referring to fig. 1 and fig. 3, fig. 1 is a schematic structural diagram of an impeller mechanical pneumatic test simulation apparatus 100. Fig. 3 is a schematic structural view of the vane assembly 11 according to the embodiment of the present invention. The present embodiment provides an aerodynamic test simulation apparatus 100 for a turbomachinery, including a movable blade simulation assembly 10, a stationary blade assembly 11, and an air outlet assembly 12. The moving blade simulation assembly 10 includes a rotating mechanism 101 and a wake generating mechanism 102, and the wake generating mechanism 102 is disposed on the rotating mechanism 101 and can rotate along with the rotating mechanism 101, so that the airflow turns circumferentially. The stationary blade assembly 11 includes a plurality of stationary blades 111 arranged at intervals, a gap is formed between adjacent stationary blades 111, and the stationary blade assembly 11 is in fluid communication with the air outlet assembly 12 through the gap.
It is worth to say that, the aerodynamic test simulation device 100 for impeller machinery can simulate the movable impeller by arranging the movable impeller simulation assembly 10, and the simple rotating mechanism 101 and the wake generation mechanism 102 can enable the airflow to turn circumferentially, so that the working flow of the movable impeller is simulated, the test cost and difficulty are reduced, and the structural design is reasonable and the practicability is high.
The impeller machine is a generic name of working machines (such as pumps, gas compressors, fans and the like) and power machines (such as steam turbines, water turbines and the like) which take continuously flowing fluid as a working medium, take blades as main working elements and realize effective conversion of mechanical work and fluid potential energy through interaction of the working medium and the working elements. The turbo machine of a gas turbine mainly refers to a compressor that inputs mechanical work from the outside to compress gas, and a turbine in which combustion gas expands and outputs mechanical work to the outside.
The working principle is as follows: the flow of gas in the turbomachinery is an internal flow. It has two main differences from the external flow assistance of two-dimensional wings and axial symmetry object streaming. First, conversion between mechanical work and internal energy of gas is performed in the turbomachinery. Secondly, there are boundaries of the body around, that is, the gas is moving in the vane passages between the inner and outer wall surfaces. The simulation apparatus of the present embodiment includes a movable blade (i.e., the movable blade simulation assembly 10) and a stationary blade ring (i.e., the stationary blade assembly 11). In this device, the rotating mechanism 101 applies work to the airflow by the moving blades, so that the airflow is turned in the circumferential direction in the moving blades to increase the absolute stagnation temperature (or total temperature for short) and the absolute stagnation pressure (or total pressure for short), and the static pressure and the absolute velocity of the airflow are also increased. Then, in the stationary blade, the gas flow is further diffused, and a part of the kinetic energy of the gas is converted into potential energy of the gas. The airflow also has circumferential turning in the stationary blade to meet the requirement of the inlet of the next stage of movable blade. And finally flows out of the air outlet assembly 12 to obtain test data.
Referring to fig. 2, fig. 2 is a schematic structural diagram of the bucket simulation assembly 10 according to the embodiment of the present invention. The rotating mechanism 101 includes a driving sprocket 1011, a driven sprocket 1012, and a chain 1013, wherein the chain 1013 is looped around the driving sprocket 1011, a contact surface between the driving sprocket 1011 and the chain 1013 is a sliding surface capable of sliding relative to each other, and a contact surface between the driven sprocket 1012 and the chain 1013 is a sliding surface capable of sliding relative to each other.
It is worth to say that the chain transmission is the meshing transmission taking the chain 1013 as the middle flexible part, and compared with the belt transmission, the chain transmission has the advantages of inelastic sliding, high friction coefficient, compact structure, small shaft pressing force and capability of working in severe environments such as high temperature and humidity; compared with gear transmission, the gear transmission has the advantages of suitability for remote transmission, low manufacturing cost and low installation precision, and the gear transmission is adopted, so that the structure is compact, the pressure shaft force is small, the cost is low, and the rotating working state of the moving blade can be simulated easily.
In this embodiment, the chain 1013 includes a pin 1014 and a link 1015, the pin 1014 is disposed on the link 1015, the wake generating mechanism 102 and the pin 1014 are connected to each other, and the extending direction of the wake generating mechanism 102 is perpendicular to the transmission direction of the chain 1013.
It can be understood that the extending direction of the wake generating mechanism 102 and the transmission direction of the chain 1013 are always perpendicular, so that the contact surface between the wake generating mechanism 102 and the gas can be enlarged, the circumferential turning of the gas flow can be increased, the visibility of the test result can be improved, and the teaching effect can be improved more remarkably.
Optionally, the rotating mechanism 101 further includes a motor, an output shaft of the motor is connected to the driving sprocket 1011, and the output shaft can drive the driving sprocket 1011 to rotate along its own axis direction under the driving of the motor.
Specifically, adopt motor drive driving sprocket 1011 can improve this analogue means's intelligent degree, simultaneously, the motor has the characteristics that output is stable and output is big, and output is stable can improve experimental precision, and output can improve the dynamic characteristic of movable vane simulation component and gas contact greatly for the air current circumference turns and improves experimental apparent.
Referring again to fig. 2, the wake generating mechanism 102 includes a plurality of stirring rods, the number of the stirring rods is the same as the number of the pins 1014, and the stirring rods and the pins 1014 are in one-to-one correspondence and are connected to each other.
It can be understood that the stirring rod has the characteristics of simple structure, stable function and low cost, and can bring about good airflow circumferential turning after being matched with the pin shaft 1014, thereby realizing the effective conversion of mechanical work and fluid potential energy.
In this embodiment, a plurality of stirring rods are disposed on the chain 1013 along with a plurality of pins 1014 at regular intervals. It can be understood that the stirring rods arranged at uniform intervals can uniformly apply work to the air flow, so that the air flow generates circumferential turning in the movable blade and increases the absolute stagnation temperature (or total temperature for short) and absolute stagnation pressure (or total pressure for short), and meanwhile, the static pressure and the absolute speed of the air flow are also increased at the same time.
Referring to fig. 1 again, the turbomachinery aerodynamic test simulation device 100 further includes a casing assembly 13, the casing assembly 13 has an accommodating chamber, and the moving blade simulation assembly 10 and the stationary blade assembly 11 are disposed in the accommodating chamber. The shell assembly 13 is further provided with an air outlet, the air outlet comprises two side openings and an air outlet channel, the stationary blade assembly 11 is arranged in the air outlet channel, the air outlet assembly 12 is communicated with any one of the openings, and the other opening is provided with a rotating plate 123 which is detachably connected.
It should be noted that the casing assembly 13 is arranged to make the boundary of the body around the inner moving blade simulation assembly 10, that is, the gas moves in the channel of the moving blade simulation assembly 10 between the inner and outer wall surfaces, so that it is able to generate a stable circumferential transition and increase the absolute stagnation temperature and pressure.
In the present embodiment, the air outlet assembly 12 includes an air outlet channel 121 and an air tunnel 122, and the air tunnel 122 is in fluid communication with the opening through the air outlet channel 121.
It should be noted that the air outlet duct and the air tunnel 122 are arranged so that the air flow has an outlet, and a plurality of sensors are arranged in the air outlet duct so that the required test data can be measured.
Optionally, the cross section of the wind tunnel 122 is trapezoidal, and the small end of the wind tunnel 122 and the air outlet channel 121 are connected to each other.
Specifically, the small end of the trapezoidal wind tunnel 122 is connected with the air outlet channel 121, and the large end faces outwards, so that more people can set the sensor unit in the large end, and the accuracy of test data detection is improved.
Meanwhile, in one embodiment of the present embodiment, the cross section of the housing assembly 13 is an ellipse. It will be appreciated that the oval housing assembly 13 and the chain 1013 are adapted to each other, which is simple, cost effective and space saving. The cross section of the housing assembly 13 may also be circular, square, or irregular, etc. according to different implementation environments, and this embodiment does not constitute a limitation to the specific structural features of the housing assembly 13.
In a specific test process, the aerodynamic test simulation device 100 for the impeller machinery is applied to a plane blade cascade test piece, namely a blade cascade, namely a stationary blade 111, and is tested by replacing different blade cascades to quantitatively research the influence of quantitative changes of the Mach number characteristic, the relative attack angle characteristic and the Moving Bar characteristic of the blade cascade on the aerodynamic performance of the blade cascade.
Test 1: and selecting at least six planar blade cascades with different geometric structures, and recording the Mach number characteristics. Under the condition of the same Reynolds number and inlet attack angle, the Mach number of the outlet of the blade cascade is changed, the aerodynamic performance of the blade cascade is measured, and a variation curve of the evaluation parameters along with the Mach number is obtained.
A test matrix for recording Mach number characteristics of different geometric configurations is shown in a table 1, and the adjustment precision range of the Mach number of the cascade outlet of each state is +/-0.02.
Table 1 mach number characteristic test matrix
The following test results were produced by this test:
1) under different Mach numbers, parameters such as energy loss coefficient, outlet airflow angle and the like are distributed along the circumferential direction;
2) the energy loss coefficient and the change characteristic of the outlet airflow angle along with the Mach number;
3) under different outlet Mach numbers, the pressure distribution curve of the surface of the blade with the middle section is obtained;
4) and carrying out repeatability tests under partial working conditions.
Test 2: and (4) recording the attack angle characteristics aiming at 6 planar blade cascades with different geometric configurations. And under the conditions of the same Mach number and Reynolds number, changing the air inlet attack angle of the blade cascade, measuring the aerodynamic performance of the blade cascade, and obtaining a change curve of the examination parameters along with the relative attack angle. A test matrix for recording relative attack angle characteristics of different geometric configurations is shown in a table 2, and the relative attack angle adjustment precision range of each state is +/-0.5 degrees.
TABLE 2 Angle of attack characteristic test matrix
1) Under different attack angles, parameters such as energy loss coefficients, outlet airflow angles and the like are distributed along the circumferential direction;
2) the energy loss coefficient and the change characteristic of the outlet airflow angle along with the attack angle;
3) the pressure distribution curve of the surface of the blade with the middle section under different attack angles.
In summary, the embodiment of the present invention provides an impeller mechanical pneumatic test simulation apparatus 100. The device comprises a movable blade simulation assembly 10, a static blade assembly 11 and an air outlet assembly 12. The moving blade simulation assembly 10 includes a rotating mechanism 101 and a wake generating mechanism 102, and the wake generating mechanism 102 is disposed on the rotating mechanism 101 and can rotate along with the rotating mechanism 101, so that the airflow turns circumferentially. The stationary blade assembly 11 includes a plurality of stationary blades 111 arranged at intervals, a gap is formed between adjacent stationary blades 111, and the stationary blade assembly 11 is in fluid communication with the air outlet assembly 12 through the gap. This pneumatic experimental analogue means of impeller machinery 100 can be through setting up movable vane simulation subassembly 10 simulation movable vane, and its simple slewing mechanism 101 and wake take place mechanism 102 and can make the air current take place the circumference turn, have simulated the workflow of movable vane, have reduced experimental cost and degree of difficulty, and this structural design is reasonable, and the practicality is strong.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A pneumatic test simulator of impeller machinery is characterized by comprising a movable blade simulation component, a fixed blade component and an air outlet component,
the movable blade simulation assembly comprises a rotating mechanism and a trail generating mechanism, and the trail generating mechanism is arranged on the rotating mechanism and can rotate along with the rotating mechanism so as to enable the airflow to have circumferential turning;
the fixed blade assembly comprises a plurality of fixed blades arranged at intervals, gaps are formed between every two adjacent fixed blades, and the fixed blade assembly is communicated with the air outlet assembly through the gaps.
2. The turbomachinery aerodynamic test simulation device of claim 1, wherein the rotating mechanism comprises a driving sprocket, a driven sprocket and a chain, the chain is wound around the driving sprocket, the contact surfaces of the driving sprocket and the chain are sliding surfaces capable of sliding relative to each other, and the contact surfaces of the driven sprocket and the chain are sliding surfaces capable of sliding relative to each other.
3. The turbomachinery aerodynamic test simulation device of claim 2, wherein the chain comprises a pin shaft and a chain plate, the pin shaft is arranged on the chain plate in a penetrating manner, the wake generation mechanism is connected with the pin shaft, and the extending direction of the wake generation mechanism is perpendicular to the transmission direction of the chain.
4. The turbomachinery pneumatics test simulation device of claim 3, wherein the rotating mechanism further comprises a motor, an output shaft of the motor and the driving sprocket are connected to each other, and the output shaft can drive the driving sprocket to rotate along its own axis direction under the driving of the motor.
5. The aerodynamic test simulation device of the impeller machine according to claim 3 or 4, wherein the wake generation mechanism comprises a plurality of stirring rods, the number of the stirring rods is the same as that of the pin shafts, and the stirring rods and the pin shafts are in one-to-one correspondence and are connected with each other.
6. The turbomachine aerodynamic test simulation device of claim 5, wherein a plurality of said stirring rods are disposed on said chain at regular intervals following a plurality of said pins.
7. The turbomachinery aerodynamic test simulation device of claim 1, further comprising a housing assembly having an accommodation chamber, the movable blade simulation assembly and the stationary blade assembly being disposed in the accommodation chamber;
the shell assembly is further provided with a gas outlet, the gas outlet comprises two side openings and a gas outlet channel, the stationary blade assembly is arranged in the gas outlet channel, the gas outlet assembly and any one of the openings are communicated with each other, and a rotating plate detachably connected is arranged on the other opening.
8. The turbomachinery aerodynamic test simulation device of claim 7, wherein the air outlet assembly comprises an air outlet channel and an air tunnel, and the air tunnel is in fluid communication with the opening through the air outlet channel.
9. The aerodynamic test simulation device of impeller mechanics of claim 8, wherein the cross section of the wind tunnel is trapezoidal, and the small end of the wind tunnel and the air outlet channel are connected with each other.
10. The turbomachinery aerodynamic test simulation device of claim 7, wherein the cross-section of the housing assembly is elliptical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110723275.8A CN113252279A (en) | 2021-06-28 | 2021-06-28 | Pneumatic test simulation device for impeller machinery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110723275.8A CN113252279A (en) | 2021-06-28 | 2021-06-28 | Pneumatic test simulation device for impeller machinery |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113252279A true CN113252279A (en) | 2021-08-13 |
Family
ID=77190116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110723275.8A Pending CN113252279A (en) | 2021-06-28 | 2021-06-28 | Pneumatic test simulation device for impeller machinery |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113252279A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113418709A (en) * | 2021-08-24 | 2021-09-21 | 中国航发上海商用航空发动机制造有限责任公司 | Cartridge container holding test device and design method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1202224A (en) * | 1995-11-14 | 1998-12-16 | 西屋电气公司 | Optimization of turbomachinery harmonics |
| CN101067586A (en) * | 2007-06-11 | 2007-11-07 | 哈尔滨工业大学 | Air compressor louver experiment device with adjustable additional blades based on relative motion concept |
| CN106441782A (en) * | 2016-10-21 | 2017-02-22 | 大连理工大学 | Reciprocating blade wake generator |
| CN108398227A (en) * | 2018-04-10 | 2018-08-14 | 哈尔滨工业大学 | Across the sound sector CASCADE EXPERIMENT platform of one kind and incoming uniformity control method |
| CN108692913A (en) * | 2018-04-20 | 2018-10-23 | 浙江大学 | A kind of circulating Stator tail generating means |
-
2021
- 2021-06-28 CN CN202110723275.8A patent/CN113252279A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1202224A (en) * | 1995-11-14 | 1998-12-16 | 西屋电气公司 | Optimization of turbomachinery harmonics |
| CN101067586A (en) * | 2007-06-11 | 2007-11-07 | 哈尔滨工业大学 | Air compressor louver experiment device with adjustable additional blades based on relative motion concept |
| CN106441782A (en) * | 2016-10-21 | 2017-02-22 | 大连理工大学 | Reciprocating blade wake generator |
| CN108398227A (en) * | 2018-04-10 | 2018-08-14 | 哈尔滨工业大学 | Across the sound sector CASCADE EXPERIMENT platform of one kind and incoming uniformity control method |
| CN108692913A (en) * | 2018-04-20 | 2018-10-23 | 浙江大学 | A kind of circulating Stator tail generating means |
Non-Patent Citations (1)
| Title |
|---|
| 王嘉炜: ""叶轮机械中若干非定常流动特征的初步研究"", 《中国优秀博硕士学位论文全文数据库(博士) 工程科技Ⅱ辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113418709A (en) * | 2021-08-24 | 2021-09-21 | 中国航发上海商用航空发动机制造有限责任公司 | Cartridge container holding test device and design method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Krain | Review of centrifugal compressor’s application and development | |
| Rice | An analytical and experimental investigation of multiple-disk turbines | |
| CN113252279A (en) | Pneumatic test simulation device for impeller machinery | |
| Schobeiri et al. | Aerodynamic and performance studies of a three-stage high pressure research turbine with 3-D-blades, design point and off-design experimental investigations | |
| Schobeiri et al. | A comparative aerodynamic and performance study of a three-stage high pressure turbine with 3-D bowed blades and cylindrical blades | |
| CN115680900A (en) | High fan tip speed engine | |
| Sheoran et al. | Advancements in the design of an adaptable swirl distortion generator for testing gas turbine engines | |
| CN115750135A (en) | Gas turbine engine with third flow | |
| Krain | Review of centrifugal compressor’s application and development | |
| Suder et al. | Results of an advanced fan stage operating over a wide range of speed and bypass ratio: Part I—Fan stage design and experimental results | |
| Simonassi et al. | On the Influence of an Acoustically Optimized Turbine Exit Casing Onto the Unsteady Flow Field Downstream of a Low Pressure Turbine Rotor | |
| Sinnette et al. | Performance of NACA Eight-stage Axial-flow Compressor Designed on the Basis of Airfoil Theory | |
| Kunte et al. | Experimental setup of a small supersonic turbine for an automotive ORC application running with ethanol | |
| CN108798795B (en) | Turbulence sensor for a turbomachine compressor | |
| Korakianitis et al. | Off-design performance of various gas-turbine cycle and shaft configurations | |
| Petry et al. | Influence of the swirling flow in the side cavities of a high-pressure centrifugal compressor on the characteristics of excited acoustic modes | |
| Capata et al. | Preliminary considerations on the thermodynamic feasibility and possible design of ultra-, micro-and nano-gas turbines | |
| Reutter et al. | Experimental investigation of inlet distortion in a 4.5-stage axial compressor | |
| Tamaki et al. | Experimental fluid dynamics applications in radial turbomachines: inlet recirculation in centrifugal compressor, rotating stall and flow in vaneless diffuser, and improvement in accuracy of CFD for predicting flow fields in a radial turbine rotor | |
| Mizuki et al. | Design and prototyping of micro centrifugal compressor for ultra micro gas turbine | |
| Saul et al. | Extended scaling method for nonsimilarity in reynolds number, stagger angle and blade number | |
| Schobeiri et al. | Aerodynamic and performance behavior of a three-stage high efficiency turbine at design and off-design operating points | |
| Denman | Aerodynamic evaluation of double annular combustion systems | |
| US11629606B2 (en) | Split-line stator vane assembly | |
| CN110375971B (en) | Accelerated life test device and method for radial flow type turbine impeller and gas compressor impeller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210813 |