CN116517866B - In-plant test device and method for main compressor of continuous transonic wind tunnel - Google Patents
In-plant test device and method for main compressor of continuous transonic wind tunnel Download PDFInfo
- Publication number
- CN116517866B CN116517866B CN202310726137.4A CN202310726137A CN116517866B CN 116517866 B CN116517866 B CN 116517866B CN 202310726137 A CN202310726137 A CN 202310726137A CN 116517866 B CN116517866 B CN 116517866B
- Authority
- CN
- China
- Prior art keywords
- compressor
- butterfly valve
- pressure
- closed loop
- opening
- 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.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 59
- 238000000034 method Methods 0.000 title claims abstract description 32
- 238000011056 performance test Methods 0.000 claims abstract description 27
- 238000001035 drying Methods 0.000 claims abstract description 16
- 230000008569 process Effects 0.000 claims abstract description 15
- 230000003068 static effect Effects 0.000 claims description 40
- 238000012545 processing Methods 0.000 claims description 9
- 238000009423 ventilation Methods 0.000 claims description 9
- 238000013461 design Methods 0.000 claims description 5
- 238000005086 pumping Methods 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 239000013589 supplement Substances 0.000 claims description 3
- 238000000605 extraction Methods 0.000 abstract description 3
- 238000011156 evaluation Methods 0.000 abstract 1
- 230000008901 benefit Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B30/00—Energy efficient heating, ventilation or air conditioning [HVAC]
- Y02B30/70—Efficient control or regulation technologies, e.g. for control of refrigerant flow, motor or heating
Abstract
A continuous transonic wind tunnel main compressor in-plant test device and method belong to the field of wind tunnel tests. The invention comprises a closed loop, wherein a compressor, a vacuum system, a medium-pressure drying air tank, a heat exchanger, a quick-opening butterfly valve, a flowmeter and a dew point meter are sequentially arranged on the closed loop in a anticlockwise manner, a driving motor is arranged on the closed loop, the output end of the driving motor is connected with the compressor, the vacuum system controls the air extraction quantity through the opening degree of a stop valve, the medium-pressure drying air tank controls the air charging quantity through the opening degree of the medium-pressure stop valve, and the butterfly valve is arranged on the closed loop and is connected with the quick-opening butterfly valve in parallel. Aiming at the characteristic that the flow-pressure ratio of the main compressor of the large continuous transonic wind tunnel is wide in working condition range, the method solves the problem that performance tests of different use working conditions such as pressurization, vacuum, normal pressure and the like can be met, meanwhile, the resistance characteristics of a closed loop are precisely controlled through two groups of valves in the process, the high-precision test of the flow-pressure ratio of the compressor unit is realized, the cost is saved, and comprehensive and detailed performance evaluation is provided.
Description
Technical Field
The invention relates to a continuous transonic wind tunnel main compressor in-plant test device and method, and belongs to the field of wind tunnel tests.
Background
Wind tunnel tests are widely adopted as aerodynamic research methods, and necessary guarantees are provided for development in the fields of aviation, aerospace, railway transportation and the like. The axial flow compressor unit is a key power device of a large continuous wind tunnel and is used for compensating pressure loss generated by airflow movement of the wind tunnel and maintaining the stability of a flow field of the wind tunnel. The large-scale continuous transonic wind tunnel axial compressor needs to meet the requirements of wide flow and pressure ratio, and most of the compressors need a two-dimensional adjustment mode of rotating speed adjustment and blade angle adjustment. The conventional industrial axial flow compressor generally performs only mechanical operation in the highest rotation speed state without load in a factory to test indexes such as vibration of a unit. Because the large continuous transonic wind tunnel main compressor has wide flow-pressure ratio performance range, the flow-pressure ratio characteristics of a plurality of blade angles and different rotating speed intervals are related, and besides the conventional mechanical operation, corresponding performance tests are required to be carried out before leaving a factory so as to ensure that the performance of the unit meets design indexes. The main compressor shaft of the large continuous transonic wind tunnel has high power, and the adoption of full power operation can generate huge electric power burden, so that huge electric power cost is caused.
Therefore, it is needed to provide a continuous transonic wind tunnel main compressor in-plant test device and method to solve the above technical problems.
Disclosure of Invention
Aiming at the characteristic that the flow-pressure ratio of a main compressor of a large continuous transonic wind tunnel is wider than the working condition range, the invention provides an in-plant test device and method for the main compressor of the continuous transonic wind tunnel, which solve the problem that performance tests of different working conditions such as pressurization, vacuum, normal pressure and the like can be met, meanwhile, the resistance characteristics of a closed loop are precisely controlled through two groups of valves in the process, and the high-precision test of the flow-pressure ratio of the compressor unit is realized. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention.
The technical scheme of the invention is as follows:
scheme one, a continuous transonic wind tunnel main compressor in-plant test device includes: the device comprises a compressor, a closed loop, a vacuum system, a vacuum stop valve, a medium-pressure drying air tank, a medium-pressure stop valve, a heat exchanger, a quick-opening butterfly valve, a flowmeter, a dew point meter and a driving motor, wherein the compressor, the vacuum system, the medium-pressure drying air tank, the heat exchanger, the quick-opening butterfly valve, the flowmeter and the dew point meter are sequentially arranged on the closed loop in a anticlockwise manner, the driving motor is arranged outside the closed loop, the output end of the driving motor is connected with a rotor piece of the compressor, the vacuum system controls the air extraction amount through the opening of the stop valve, the medium-pressure drying air tank controls the air charging amount through the opening of the medium-pressure stop valve, and the butterfly valve is arranged on the closed loop and connected with the quick-opening butterfly valve in parallel.
Preferably: the closed loop on the right side of the flowmeter is sequentially provided with a total temperature measuring point and a first static pressure measuring point, and the front side and the rear side of the compressor are respectively provided with a second static pressure measuring point and a third static pressure measuring point.
Preferably: the closed loop is provided with four corner sections, and a flow guiding device is arranged inside each corner section.
Preferably: the flow guiding device is a plurality of arc-shaped bent plates which are arranged side by side.
Preferably: the flowmeter is in the form of a pitot tube.
Scheme II, a continuous transonic wind tunnel main compressor in-plant test method, based on scheme I a continuous transonic wind tunnel main compressor in-plant test device implementation, including:
step 1, a preparation stage before performance test, which specifically comprises the following steps:
step 1.1, the vacuum system pumps air from the closed loop, namely, a vacuum stop valve is opened, the vacuum system is used for pumping air in the closed loop to negative pressure, and then the vacuum stop valve and the vacuum system are closed;
step 1.2, the medium-pressure drying gas tank supplements gas to the closed loop, namely, a medium-pressure stop valve is opened, clean drying gas in the medium-pressure drying gas tank is filled into the closed loop to perform ventilation;
step 1.3, judging whether the dew point meets the requirement, namely, observing the indication of a dew point meter after ventilation, judging whether the gas dew point in the closed loop meets the requirement, and repeating the steps 1.1 to 1.2 when the gas dew point in the closed loop does not meet the requirement, and carrying out ventilation for a plurality of times until the gas in the closed loop meets the dew point requirement;
step 2, a performance test stage, specifically comprising:
step 2.1, starting the compressor to a specified rotating speed, opening the butterfly valve quickly, keeping static pressure at the inlet of the compressor and the blade angle at a certain fixed state when the butterfly valve is fully opened, and operating the compressor at the rotating speed [ n ] min ，n max ]Selecting a set of rotation speeds n 1 ，n 2 ，n 3 … …; fixing the rotation speed of the compressor at n 1 ；
Step 2.2, rough adjusting the quick-opening butterfly valve, and fine adjusting the butterfly valve 10, namely slowly adjusting the opening of the quick-opening butterfly valve, and fine adjusting the butterfly valve after approaching a test working condition, wherein the index to be measured is stable;
step 2.3, recording the data of the measuring points, recording the data of the first static pressure measuring point, the total temperature measuring point, the second static pressure measuring point and the third static pressure measuring point and the pressure difference data of the flowmeter after the index to be measured is stable, and calculating to obtain the volume flow rate、/>，
Record data get，/>，n 1 ]Wherein->For the volume flow of the compressor at a specific opening of the quick-opening butterfly valve and the fine-tuning butterfly valve with a rotational speed n1>The pressure ratio of the compressor corresponding to the volume flow of the compressor under a certain specific opening degree of the quick-opening butterfly valve and the fine-adjustment butterfly valve is n 1;
step 2.4, opening the butterfly valve to full open after the data recording is completed;
step 2.5, repeating the steps 2.2 to 2.4, and continuously recording the data of the corresponding compressor volume flow and the corresponding pressure ratio of the quick-opening butterfly valve and the fine-tuning butterfly valve under different valve openings, namely
Step (a)2.6 stopping reducing the opening of the quick-opening butterfly valve when the compressor pressure ratio of the compressor no longer increases with the decrease of the volume flow rate, and obtaining an operation boundary point at the rotation speed ；
Step 2.7, adjusting the driving motor to enable the running rotating speed of the compressor to be n 2 Repeating the steps 2.2 to 2.6 to obtain the rotating speed n 2 Compressor volumetric flow under operating conditionsPressure ratio feature point->，… … and the operating boundary point->The method comprises the steps of carrying out a first treatment on the surface of the Continuously changing the running rotation speed of the compressor to obtain flow and pressure ratio characteristic points and running boundary points of all running rotation speed intervals until the test is finished;
step 3, calculating the flow pressure ratio:
inlet temperature T of compressor during test in After performance test is finished, the data of each pressure ratio are converted into 310K temperature conditions uniformly for data processing, and the data processing is carried out to obtain:
the compressor operating pressure ratio formula is as follows:
formula (201)
In the method, in the process of the invention,for compressor pressure ratio, +.>For the static pressure at the inlet of the compressor, the unit is Pa, < >>The unit is Pa for the static pressure at the outlet of the compressor;
the compressor volumetric flow Q is calculated as follows:
Q=formula (202)
Where Pi is a constant, pi= 3.1415; d is the inner diameter of a flowmeter mounting pipeline, and the unit is m; k is a flow coefficient obtained by calibration;measuring a differential pressure value for the flow meter in Pa; rg is a gas constant, and the unit is J/(kg. Times.K); t is a measured value of the total temperature measuring point 12, and the unit is K; p is a measured value of a first static pressure measuring point, and the unit is Pa;
inlet temperature T of compressor during performance test in When slight variation occurs, the compressor pressure ratio is uniformly corrected to 310K according to the following formula, so that data processing is facilitated:
formula (203)
In the method, in the process of the invention,correcting the compressor to a pressure ratio with an inlet temperature of 310K; />For the inlet temperature of the compressor to be measuredIs a ratio of the pressure of the mixture; k is the specific heat ratio of the gas;
and 4, after the compressor volume flow, the pressure ratio characteristic points and the operation boundary points of all the rotating speed intervals of the compressor are completed, connecting the flow with the same rotating speed obtained through testing to obtain a flow-pressure ratio working curve of all the rotating speed intervals of the compressor, and connecting the operation boundary points with different rotating speeds to obtain an operation boundary line.
Preferably: in the performance test stage of the step 2, in the process of obtaining the operation boundary point test of the compressor 1, when the compressor enters a dangerous operation working area, namely, the vibration index of a compressor shaft exceeds a design index, a quick-opening butterfly valve is quickly opened, so that the operation working condition point of the axial flow compressor quickly enters a stable operation area.
The invention has the following beneficial effects:
1. the invention solves the problems that the operation working condition range of the main compressor of the large continuous transonic wind tunnel is wide, and the performance of the unit is difficult to be comprehensively evaluated in the conventional in-plant mechanical operation mode;
2. the invention makes the compressor set perform mechanical operation and necessary performance test in the factory, and is convenient for analyzing the performance of the compressor set in detail before leaving factory;
3. the invention can test the working conditions of vacuum, pressurization and normal pressure, meets the test of different total pressure states, and has wider application range;
4. because the rated power of the main compressor of the large continuous transonic wind tunnel is high, the invention can greatly reduce the energy consumption of mechanical operation and performance test by reducing the pressure in the closed loop under the vacuum state, and generate great economic benefit.
Drawings
FIG. 1 is a schematic diagram of a continuous transonic wind tunnel main compressor in-plant test device;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is an enlarged view at B of FIG. 1;
FIG. 4 is a graph showing measured and expected contrast between flow-to-pressure ratios of different blade angles at a certain rotational speed under negative pressure conditions in accordance with an embodiment of the present invention;
FIG. 5 is a flow chart of the performance test of step 1 and step 2 of the present invention;
in the figure: 1-compressor, 2-closed loop, 3-vacuum system, 4-vacuum stop valve, 5-corner section, 6-medium pressure drying air tank, 7-medium pressure stop valve, 8-heat exchanger, 9-quick-opening butterfly valve, 10-butterfly valve, 111-first static pressure measuring point, 112-second static pressure measuring point, 113-third static pressure measuring point, 12-total temperature measuring point, 13-flowmeter, 14-dew point meter, 15-driving motor.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The connection mentioned in the present invention is divided into a fixed connection and a detachable connection, wherein the fixed connection (i.e. the non-detachable connection) includes, but is not limited to, a conventional fixed connection manner such as a hemmed connection, a rivet connection, an adhesive connection, a welded connection, etc., and the detachable connection includes, but is not limited to, a conventional detachable manner such as a threaded connection, a snap connection, a pin connection, a hinge connection, etc., and when the specific connection manner is not specifically limited, at least one connection manner can be found in the existing connection manner by default, so that the function can be realized, and a person skilled in the art can select the connection according to needs. For example: the fixed connection is welded connection, and the detachable connection is hinged connection.
The first embodiment is as follows: referring to fig. 1 to 4, a test device in a continuous transonic wind tunnel main compressor in-plant of the present embodiment is described, and includes a compressor 1, a closed loop 2, a vacuum system 3, a vacuum stop valve 4, a medium pressure dry gas tank 6, a medium pressure stop valve 7, a heat exchanger 8, a quick-opening butterfly valve 9, a butterfly valve 10, a flow meter 13, a dew point meter 14 and a driving motor 15, wherein the compressor 1, the vacuum system 3, the medium pressure dry gas tank 6, the heat exchanger 8, the quick-opening butterfly valve 9, the flow meter 13 and the dew point meter 14 are sequentially installed on the closed loop 2 in a counterclockwise direction, the driving motor 15 is arranged outside the closed loop 2, and an output end of the driving motor 15 is connected with a rotor piece of the compressor 1; the rotor of the compressor 1 passes through the closed loop 2 and is provided with a sealing structure, so that the communication between the gas in the closed loop 2 and the outside atmosphere can be effectively prevented, the vacuum system 3 controls the pumping quantity through the opening degree of the stop valve 4, the medium-pressure dry gas tank 6 controls the charging quantity through the opening degree of the medium-pressure stop valve 7, and the static pressure at the inlet of the compressor 1 can be maintained to be vacuum, normal pressure or a supercharging condition for testing; the pressure in the control device of the vacuum system 3 is maintained in a certain relatively stable negative pressure state, so that the electric cost for developing high-speed mechanical operation and performance tests in a main compressor plant of a large continuous transonic wind tunnel can be greatly reduced, a butterfly valve 10 is arranged on a closed loop 2 and is connected with a quick-opening butterfly valve 9 in parallel, and the driving motor 15 is a variable frequency motor and can drive the compressor 1 to operate in a wide speed range so as to meet the actual speed requirement of the wind tunnel; before performance test, through vacuum stop valve 4, use vacuum system 3, middling pressure stop valve 7 and middling pressure dry gas pitcher 6 cooperation to use, can ensure that test medium in the test loop is unanimous with the practical application occasion in the wind tunnel, and the test result is accurate.
The heat exchanger 8 is used for cooling energy input into the wind tunnel in the operation process of the compressor 1 and maintaining the temperature in the wind tunnel stable; the quick-opening butterfly valve 9 and the butterfly valve 10 can change the resistance characteristic of the closed loop 2 in the test process by adjusting the opening, the quick-opening butterfly valve 9 is used for coarse adjustment, and the butterfly valve 10 is used for fine adjustment;
the closed loop 2 on the right side of the flowmeter 13 is sequentially provided with a total temperature measuring point 12 and a first static pressure measuring point 111, and the front side and the rear side of the compressor 1 are respectively provided with a second static pressure measuring point 112 and a third static pressure measuring point 113, so as to obtain corresponding static pressure data in the test process, two identical static pressure, total temperature and dew point measuring points can be arranged on the same section, the measured data obtained by the measuring points at the same position are compared, the processed measured data are used as calculation basis, and measurement deviation caused by a single measuring point is avoided.
The closed loop 2 is provided with four corner sections 5, and a flow guiding device is arranged in each corner section 5 and is a plurality of arc-shaped bent plates arranged side by side, so that the air flow resistance loss in the test process is reduced.
The flowmeter 13 is in the form of a pitot tube type flowmeter.
A closed-loop test loop, namely a closed loop 2 is built in a factory, and the closed loop 2 is provided with a heat exchanger for maintaining stable temperature of air flow in the loop when a unit operates; the vacuum system 3 is used for discharging the humid air in the closed loop 2 out of the test loop, and the medium-pressure dry air tank 6 can fill the dry and clean air into the test loop, so that the test performance of the compressor 1 is ensured to be closer to the actual use state; in addition, the vacuum system 3 can be used for ensuring that the pressure in the loop is maintained in a certain relatively stable negative pressure state during the test process so as to reduce the electric cost of the high-rotation-speed test working condition;
the quick-opening butterfly valves 9 and 10 are used for changing the resistance characteristics in a loop and the inlet flow of the compressor so as to test the pressure ratio and other data of different inlet flows of the compressor 1; the equal straight section of the inlet of the compressor 1 is provided with a flowmeter 13, a total temperature measuring point 12 and a first static pressure measuring point 111, so that the volume flow of the inlet of the compressor 1 can be accurately calculated; the inlet and outlet of the compressor 1 are provided with a second static pressure measuring point 112 and a third static pressure measuring point 113, which are used for measuring static pressure data of the inlet and outlet of the compressor 1 under different operation conditions and calculating to obtain corresponding pressure ratios.
When the performance of the compressor 1 is debugged, the static pressure at the inlet of the compressor 1 is controlled by the vacuum system 3 to be maintained under the same condition, the rotating speed of the compressor 1 is fixed, the opening of the quick-opening butterfly valve 9 and the opening of the butterfly valve 10 are gradually adjusted, the wind tunnel resistance loss is changed, a plurality of groups of stable volume flow and pressure ratio data are recorded, and a flow-pressure ratio curve of the compressor 1 at a certain rotating speed can be obtained; after the performance curve test of the rotating speed of the compressor 1 is completed, the running rotating speed of the compressor 1 is changed, and the test work is repeated until all the running rotating speeds of the compressor 1 are completed, so that the performance curve of the compressor 1 under the pressure condition and the blade angle can be obtained, namely, the actual measurement and the design expected comparison curve graph of the flow-pressure ratio of different blade angles under a certain rotating speed under the negative pressure working condition as shown in fig. 4;
the second embodiment is as follows: 1-5, based on the first specific embodiment, a method for in-plant testing of a main compressor of a continuous transonic wind tunnel according to the first specific embodiment includes:
step 1, a preparation stage before performance test, which specifically comprises the following steps:
step 1.1, the vacuum system 3 pumps air from the closed loop 2, namely, the vacuum stop valve 4 is opened, the vacuum system 3 is used for pumping air in the closed loop 2 to negative pressure, and then the vacuum stop valve 4 and the vacuum system 3 are closed;
step 1.2, the medium-pressure dry gas tank 6 supplements gas for the closed loop 2, namely, the medium-pressure stop valve 7 is opened, clean dry gas in the medium-pressure dry gas tank 6 is filled into the closed loop 2 for ventilation;
step 1.3, judging whether the dew point meets the requirement, namely, observing the indication of the dew point meter 14 after ventilation, judging whether the gas dew point in the closed loop 2 meets the requirement, and repeating the steps 1.1 to 1.2 when the gas dew point in the closed loop 2 does not meet the requirement, and ventilation for a plurality of times until the gas in the closed loop 2 meets the dew point requirement;
when the performance test is performed, the air extraction amount of the vacuum system 3 is controlled by the opening of the vacuum stop valve 4, the air charging amount of the medium-pressure drying air tank 6 is controlled by the opening of the medium-pressure stop valve 7, the static pressure at the inlet of the compressor 1 is maintained to be vacuum or a supercharging condition, and the test is performed under a vacuum working condition, so that the power consumption required by the test can be greatly reduced;
step 2, a performance test stage, specifically comprising:
step 2.1, starting the compressor 1 to a specified rotating speed, enabling the quick-opening butterfly valve 9 and the butterfly valve 10 to be in a fully-opened state, maintaining static pressure at the inlet of the compressor and the blade angle to be in a certain fixed state, and operating the compressor 1 at the rotating speed [ n ] min ，n max ]Selecting a set of rotation speeds n 1 ，n 2 ，n 3 … …; fixing the rotation speed of the compressor 1 at n 1 ；
Step 2.2, coarse-tuning the quick-opening butterfly valve 9, fine-tuning the butterfly valve 10, namely slowly tuning the opening of the quick-opening butterfly valve 9, fine-tuning the butterfly valve 10 after approaching a test working condition, and stabilizing the index to be measured;
step 2.3, recording the data of the measuring points, recording the data of the first, the total temperature, the second and the third static pressure measuring points 111, 12, 112 and 113 and the differential pressure data of the flowmeter 13 after the measured index is stable, and calculating to obtain the volume flow rate、/>Record data +.>Wherein->For the compressor volume flow at a certain specific opening of the quick-opening butterfly valve 9 and the fine-tuning butterfly valve 10 with a rotational speed n1 +.>For the compressor 1 with the rotation speed of n1 and a specific opening degree of the quick-opening butterfly valve 9 and the fine-adjusting butterfly valve 10, the pressure ratio of the volume flow of the compressor corresponds to the pressure ratio of the volume flow of the compressor;
step 2.4, opening the butterfly valve 10 to full open after the data recording is completed;
step 2.5, repeating steps 2.2 to 2.4, and continuously recording the data of the corresponding compressor volume flow and the corresponding pressure ratio of the quick-opening butterfly valve 9 and the fine-tuning butterfly valve 10 under different valve openings, namely，；
Step 2.6, stopping decreasing the opening of the quick-opening butterfly valve 9 when the compressor pressure ratio of the compressor 1 no longer increases with decreasing volume flow, and obtaining the operating boundary point at this rotational speed；
Step 2.7, adjusting the driving motor 15 to make the operation speed of the compressor 1 to n 2 Repeating the steps 2.2 to 2.6 to obtain the rotating speed n 2 Compressor volumetric flow under operating conditionsPressure ratio characteristic pointAnd an operation boundary point->The method comprises the steps of carrying out a first treatment on the surface of the Continuously changing the running rotation speed of the compressor 1 to obtain flow, pressure ratio characteristic points and running boundary points of all running rotation speed intervals until the test is finished;
in the performance test stage of the step 2, in the process of obtaining the operation boundary point test of the compressor 1, when the compressor 1 enters a dangerous operation working area, that is, the vibration index of the shaft of the compressor 1 exceeds the design index, the quick-opening butterfly valve 9 is quickly opened, so that the operation working point of the axial flow compressor 1 rapidly enters a stable operation area.
Step 3, calculating the flow pressure ratio:
inlet temperature T of compressor 1 during the test in After performance test is finished, the data of each pressure ratio are converted into 310K temperature conditions uniformly for data processing, and the data processing is carried out to obtain:
the compressor operating pressure ratio formula is as follows:
formula (201)
In the method, in the process of the invention,for compressor pressure ratio, +.>For the static pressure at the inlet of the compressor, the unit is Pa, < >>The unit is Pa for the static pressure at the outlet of the compressor;
the compressor volumetric flow Q is calculated as follows:
Q=formula (202)
Where Pi is a constant, pi= 3.1415; d is the inner diameter of the installation pipeline of the flowmeter 13, and the unit is m; k is a flow coefficient obtained by calibration;measuring a differential pressure value in Pa for the flow meter 13; rg is a gas constant, and the unit is J/(kg. Times.K); t is a measured value of the total temperature measuring point 12, and the unit is K; p is a measured value of the first static pressure measuring point 111, and the unit is Pa;
inlet temperature T of compressor 1 during performance test in When slight variation occurs, the compressor pressure ratio is uniformly corrected to 310K according to the following formula, so that data processing is facilitated:
formula (203)
In the method, in the process of the invention,a pressure ratio corrected for compressor 1 to an inlet temperature of 310K; />For the inlet temperature of the compressor 1 to be measured asIs a ratio of the pressure of the mixture; k is the specific heat ratio of the gas;
and 4, after the compressor volume flow, the pressure ratio characteristic points and the operation boundary points of all the rotating speed intervals of the compressor 1 are completed, connecting the flow of the same rotating speed obtained by testing to obtain a flow-pressure ratio working curve of all the rotating speed intervals of the compressor 1, and connecting the operation boundary points of different rotating speeds to obtain an operation boundary line.
The embodiment provides a brand new in-plant test device in a large continuous wind tunnel, which can meet the performance test of different use conditions such as pressurization, vacuum, normal pressure and the like, and the resistance characteristic is accurately controlled through two groups of valves in the process, so that the high-precision test is realized; the pressure in the control device of the vacuum system 3 is maintained in a certain relatively stable negative pressure state, so that the electric cost for developing high-rotation-speed mechanical operation and performance tests in a main compressor plant of a large continuous transonic wind tunnel can be greatly reduced.
It should be noted that, in the above embodiments, as long as the technical solutions that are not contradictory can be arranged and combined, those skilled in the art can exhaust all the possibilities according to the mathematical knowledge of the arrangement and combination, so the present invention does not describe the technical solutions after the arrangement and combination one by one, but should be understood that the technical solutions after the arrangement and combination have been disclosed by the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A continuous transonic wind tunnel main compressor in-plant test device is characterized in that: comprises a compressor (1), a closed loop (2), a vacuum system (3), a vacuum stop valve (4), a medium pressure drying air tank (6), a medium pressure stop valve (7), a heat exchanger (8), a quick opening butterfly valve (9), a butterfly valve (10), a flowmeter (13), a dew point meter (14) and a driving motor (15), wherein the compressor (1), the vacuum system (3), the medium pressure drying air tank (6), the heat exchanger (8), the quick opening butterfly valve (9), the flowmeter (13) and the dew point meter (14) are sequentially arranged on the closed loop (2) anticlockwise, the driving motor (15) is arranged outside the closed loop (2), the output end of the driving motor (15) is connected with a rotor piece of the compressor (1), the vacuum system (3) controls the pumping quantity through the opening of the stop valve (4), the opening of the medium pressure drying air tank (6) is controlled through the medium pressure stop valve (7), the butterfly valve (10) is arranged on the closed loop (2) and is connected with the quick opening butterfly valve (9) in parallel, the butterfly valve (9) and the butterfly valve (10) can be used for coarsely adjusting the opening degree of the butterfly valve (2) through adjusting the butterfly valve, the characteristics of the butterfly valve (10) in the closed loop (2) for fine adjustment, the resistance characteristic of the closed loop (2) is precisely controlled through two groups of valves, and the performance test of different use conditions of supercharging, vacuum and normal pressure is met aiming at the characteristic that the flow-pressure ratio working condition range of the main compressor of the large continuous transonic wind tunnel is wide;
a closed loop (2) on the right side of the flowmeter (13) is sequentially provided with a total temperature measuring point (12) and a first static pressure measuring point (111), and the front side and the rear side of the compressor (1) are respectively provided with a second static pressure measuring point (112) and a third static pressure measuring point (113);
the method is realized by the continuous transonic wind tunnel main compressor in-plant test device, and is characterized by comprising the following steps of:
step 1, a preparation stage before performance test, which specifically comprises the following steps:
step 1.1, the vacuum system (3) pumps air from the closed loop (2), namely, the vacuum stop valve (4) is opened, and after the vacuum system (3) pumps air in the closed loop (2) to negative pressure, the vacuum stop valve (4) and the vacuum system (3) are closed;
step 1.2, the medium-pressure drying gas tank (6) supplements the closed loop (2), namely, a medium-pressure stop valve (7) is opened, clean drying gas in the medium-pressure drying gas tank (6) is filled into the closed loop (2) for ventilation;
step 1.3, judging whether the dew point meets the requirement, namely, observing the indication of a dew point meter (14) after ventilation, judging whether the gas dew point in the closed loop (2) meets the requirement, and repeating the steps 1.1 to 1.2 when the gas dew point in the closed loop (2) does not meet the requirement, and performing ventilation for a plurality of times until the gas in the closed loop (2) meets the dew point requirement;
step 2, a performance test stage, specifically comprising:
step 2.1, starting the compressor (1) to a specified rotating speed, enabling a quick-opening butterfly valve (9) and a butterfly valve (10) to be in a full-opening state, maintaining static pressure at an inlet of the compressor and a blade angle to be in a certain fixed state, and operating the compressor (1) at a rotating speed [ n ] min ，n max ]Selecting a set of rotation speeds n 1 ，n 2 ，n 3 … …; fixing the rotation speed of the compressor (1) at n 1 ；
Step 2.2, coarse-adjusting the quick-opening butterfly valve (9), fine-adjusting the butterfly valve (10), namely slowly adjusting the opening of the quick-opening butterfly valve (9), fine-adjusting by using the butterfly valve (10) after approaching a test working condition, wherein the index to be measured is stable;
step 2.3, recording the data of the measuring points, and recording after the index to be measured is stableRecording data of a first static pressure measuring point (111), a total temperature measuring point (12), a second static pressure measuring point (112) and a third static pressure measuring point (113) and pressure difference data of a flowmeter (13), and calculating to obtain volume flowRecord data->Wherein->For the volume flow of the compressor at a specific opening of the quick-opening butterfly valve (9) and the fine-tuning butterfly valve (10) with a rotational speed n1 +.>In order to ensure that the pressure ratio of the compressor (1) corresponding to the volume flow of the compressor under a certain specific opening degree of the quick-opening butterfly valve (9) and the fine-adjustment butterfly valve (10) is n 1;
step 2.4, opening the butterfly valve (10) to full open after the data recording is finished;
step 2.5, repeating steps 2.2 to 2.4, and continuously recording the data of the corresponding compressor volume flow and the corresponding pressure ratio of the quick-opening butterfly valve (9) and the fine-tuning butterfly valve (10) under different valve openings, namely
Step 2.6, stopping reducing the opening of the quick-opening butterfly valve (9) when the compressor pressure ratio of the compressor (1) is no longer increased along with the reduction of the volume flow, and obtaining an operation boundary point at the rotating speed
Step 2.7, adjusting the driving motor (15) to compressThe running speed of the machine (1) reaches n 2 Repeating the steps 2.2 to 2.6 to obtain the rotating speed n 2 Compressor volumetric flow under operating conditionsPressure ratio characteristic point-> Operation boundary Point->Continuously changing the running rotating speed of the compressor (1) to obtain flow, pressure ratio characteristic points and running boundary points of all running rotating speed intervals until the test is finished;
in the performance test stage of the step 2, in the process of obtaining an operation boundary point test by the compressor (1), when the compressor (1) enters a dangerous operation working area, namely, the vibration index of the shaft of the compressor (1) exceeds a design index, a quick-opening butterfly valve (9) is quickly opened, so that the operation working condition point of the axial flow compressor (1) quickly enters a stable operation area;
step 3, calculating the flow pressure ratio:
inlet temperature T of compressor (1) during the test in After performance test is finished, the data of each pressure ratio are converted into 310K temperature conditions uniformly for data processing, and the data processing is carried out to obtain:
the compressor operating pressure ratio formula is as follows:
wherein epsilon is the compressor pressure ratio, P in Is the inlet static pressure of the compressor, and has the unit of Pa and P out The unit is Pa for the static pressure at the outlet of the compressor;
the compressor volumetric flow Q is calculated as follows:
where Pi is a constant, pi= 3.1415; d is the inner diameter of a pipeline for installing the flowmeter (13), and the unit is m; k is a flow coefficient obtained by calibration; Δp is the differential pressure value measured by the flowmeter (13) and is expressed in Pa; rg is a gas constant, and the unit is J/(kg. Times.K); t is a measured value of a total temperature measuring point (12), and the unit is K; p is a measured value of a first static pressure measuring point (111), and the unit is Pa;
inlet temperature T of compressor (1) during performance test in When slight variation occurs, the compressor pressure ratio is uniformly corrected to 310K according to the following formula, so that data processing is facilitated:
wherein ε 1 Correcting the pressure ratio of the inlet temperature to 310K for the compressor (1); epsilon 0 For the inlet temperature T of the compressor (1) to be measured in Is a ratio of the pressure of the mixture; k is the specific heat ratio of the gas;
and 4, after the compressor volume flow, the pressure ratio characteristic points and the operation boundary points of all the rotating speed intervals of the compressor (1) are finished, connecting the flow of the same rotating speed obtained through testing to obtain a flow-pressure ratio working curve of all the rotating speed intervals of the compressor (1), and connecting the operation boundary points of different rotating speeds to obtain an operation boundary line.
2. The continuous transonic wind tunnel main compressor in-plant test device of claim 1, wherein: the closed loop (2) is provided with four corner sections (5), and a flow guiding device is arranged inside the corner sections (5).
3. The continuous transonic wind tunnel main compressor in-plant test device of claim 2, wherein: the flow guiding device is a plurality of arc-shaped bent plates which are arranged side by side.
4. A continuous transonic wind tunnel main compressor in-plant test device according to claim 3, characterized in that: the flowmeter (13) is in the form of a pitot tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310726137.4A CN116517866B (en) | 2023-06-19 | 2023-06-19 | In-plant test device and method for main compressor of continuous transonic wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310726137.4A CN116517866B (en) | 2023-06-19 | 2023-06-19 | In-plant test device and method for main compressor of continuous transonic wind tunnel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116517866A CN116517866A (en) | 2023-08-01 |
| CN116517866B true CN116517866B (en) | 2023-09-08 |
Family
ID=87401399
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310726137.4A Active CN116517866B (en) | 2023-06-19 | 2023-06-19 | In-plant test device and method for main compressor of continuous transonic wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116517866B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA237610A (en) * | 1924-02-05 | Brown Stanley | Heat regulating system | |
| CN101639406A (en) * | 2008-12-23 | 2010-02-03 | 上海德尔福汽车空调系统有限公司 | Method for testing surface frosting resistance of vehicle evaporator |
| CN102410975A (en) * | 2011-12-06 | 2012-04-11 | 青岛海纳光电环保有限公司 | Wind-tunnel smoke dust concentration generator calibrator |
| CA2914247A1 (en) * | 2015-11-06 | 2017-05-06 | Florida Turbine Technologies, Inc. | Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir |
| CN111379728A (en) * | 2020-04-29 | 2020-07-07 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test device |
| CN113738687A (en) * | 2021-08-11 | 2021-12-03 | 杭州汽轮动力集团有限公司 | Gas compressor test bed with power recovery turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1401923B1 (en) * | 2010-09-09 | 2013-08-28 | Nuovo Pignone Spa | METHODS AND DEVICES FOR TESTING A LOW-SPEED LOW-TIME ROTOR IN A TURBOMACCHINE |
-
2023
- 2023-06-19 CN CN202310726137.4A patent/CN116517866B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA237610A (en) * | 1924-02-05 | Brown Stanley | Heat regulating system | |
| CN101639406A (en) * | 2008-12-23 | 2010-02-03 | 上海德尔福汽车空调系统有限公司 | Method for testing surface frosting resistance of vehicle evaporator |
| CN102410975A (en) * | 2011-12-06 | 2012-04-11 | 青岛海纳光电环保有限公司 | Wind-tunnel smoke dust concentration generator calibrator |
| CA2914247A1 (en) * | 2015-11-06 | 2017-05-06 | Florida Turbine Technologies, Inc. | Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir |
| CN111379728A (en) * | 2020-04-29 | 2020-07-07 | 北京动力机械研究所 | Closed circulation centrifugal compressor characteristic test device |
| CN113738687A (en) * | 2021-08-11 | 2021-12-03 | 杭州汽轮动力集团有限公司 | Gas compressor test bed with power recovery turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116517866A (en) | 2023-08-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114323667B (en) | High-altitude environment test system and adjusting method for air compressor | |
| CN101887267B (en) | Mach number controller in wind tunnel | |
| CN115186398B (en) | Method for determining key angle parameters of inlet guide vane modeling of axial flow compressor | |
| CN2859601Y (en) | Wind-pressure adjusting system equipped with independent but the same valve and its locator | |
| CN110926824B (en) | Device and method for measuring internal circulation wind resistance characteristic and heat dissipation capacity of generator | |
| CN116517866B (en) | In-plant test device and method for main compressor of continuous transonic wind tunnel | |
| CN114880885A (en) | Temperature effect evaluation and correction method for wind tunnel test data | |
| CN113029576B (en) | Method for jointly adjusting spray pipe and test section in plane cascade subsonic test device | |
| CN116480618B (en) | Large continuous transonic wind tunnel axial flow compressor test device and method | |
| CN111487029B (en) | High-speed wind tunnel air inlet passage throttling cone with accurately controlled flow and test throttling device | |
| Lieblein et al. | Experimental Investigation of an Axial Flow Compressor Inlet Stage Operating at Transonic Relative Inlet Mach Numbers I: Over-all Performance of Stage with Transonic Rotor and Subsonic Stators up to Rotor Relative Inlet Mach Number of 1.1 | |
| CN115390435A (en) | Control system and method for coupling adjustment of wind tunnel Mach number and axial dense flow ratio | |
| Dalbert et al. | Development, testing, and performance prediction of radial compressor stages for multistage industrial compressors | |
| CN115455844A (en) | Method for predicting performance of gas compressor under influence of Reynolds number distortion coupling | |
| Medeiros et al. | Analysis of off-design performance of a 16-stage axial-flow compressor with various blade modifications | |
| Zell et al. | Performance and test section flow characteristics of the national full-scale aerodynamics complex 40-by 80-foot wind tunnel | |
| Schleer et al. | Design of a high pressure-ratio centrifugal compressor for studying Reynolds number effects | |
| CN111677683B (en) | Method and device for testing pneumatic performance of micro fan based on flow compensation method | |
| Li et al. | Aerodynamic design and experimental study of small flow rate centrifugal compressor | |
| CN112253545B (en) | Method for measuring and calculating influence of angle change of adjustable stationary blade of gas compressor on flow | |
| CN116255355B (en) | Special type air inlet coupling air compressor test platform | |
| CN219809151U (en) | Radial flow passage structure suitable for heavy gas turbine compressor | |
| CN116086810A (en) | Multipath pressure acquisition and calibration system and method suitable for high-speed rotating equipment | |
| CN117648766A (en) | Turbine transition section meridian runner molded line design method | |
| Standahar et al. | Some Effects of Changing Solidity by Varying the Number of Blades on Performance of an Axial Flow Compressor Stage |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |