CN113623027B - Exhaust diffuser experiment table capable of performing steady-state and transition-state tests - Google Patents
Exhaust diffuser experiment table capable of performing steady-state and transition-state tests Download PDFInfo
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- CN113623027B CN113623027B CN202111097265.4A CN202111097265A CN113623027B CN 113623027 B CN113623027 B CN 113623027B CN 202111097265 A CN202111097265 A CN 202111097265A CN 113623027 B CN113623027 B CN 113623027B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention discloses an experimental bench for measuring the pneumatic performance of an exhaust diffuser, which can be used for carrying out steady-state and transition-state test measurement. When the quick response pneumatic valve in the experiment table is kept in a normally open state, the steady-state experiment measurement of the exhaust diffuser can be carried out; through adjusting the action time of quick response pneumatic valve, this laboratory bench can simulate gas turbine and open and stop, accelerate, the exhaust condition under the transition state operating mode such as speed reduction, and then carries out exhaust diffuser transition state experiment and measure. Meanwhile, the exhaust diffuser model in the experimental platform adopts a modular design, and different air inlet guide vanes and support plate structures can be replaced, so that the aerodynamic performance of the exhaust diffuser model with different structures can be measured under different air inlet rotational flow conditions. Through comparing and analyzing the experimental measurement results of the steady state and the transition state, the method is helpful for deeply understanding the real aerodynamic characteristics of the gas turbine under the variable working condition, and provides reference for the research and development of the advanced and efficient exhaust diffuser.
Description
Technical Field
The invention belongs to the technical field of gas turbine aerodynamics, and particularly relates to an experimental bench for measuring the aerodynamic performance of an exhaust diffuser, which can be used for carrying out steady-state and transition-state experimental measurement.
Background
The static pressure recovery capability of the exhaust diffuser can convert partial kinetic energy of gas at the outlet of the turbine into static pressure at the outlet of the exhaust diffuser, and the static pressure at the outlet of the exhaust diffuser is generally a fixed value (ambient pressure), so that the exhaust diffuser can reduce the back pressure at the outlet of the turbine, improve the expansion ratio of the turbine and increase the power output of the turbine. Research shows that the overall output power of the gas turbine can be improved by 0.8% when the static pressure recovery coefficient of the exhaust diffuser is increased by 0.1. Nowadays, parts such as a combustion chamber, a turbine and the like have very high efficiency, and the cost and difficulty for further improving the efficiency of the parts are high, while the improvement of an exhaust diffuser still has considerable scope, so that the research on the aerodynamic performance of the exhaust diffuser of the gas turbine has very important significance.
At present, most of the experiment tables for measuring the pneumatic performance of the exhaust diffuser subjected to the rational research at home and abroad are experiment tables capable of carrying out a steady-state measurement test, and the change of the pneumatic performance of the exhaust diffuser of a real gas turbine under variable working conditions cannot be simulated. And the exhaust diffuser model adopts an integrated design, so that the measured air inlet condition and the exhaust diffuser structure are single.
Disclosure of Invention
In order to overcome the defects of the current test table for measuring the pneumatic performance of the exhaust diffuser, the invention aims to provide the test table for measuring the pneumatic performance of the exhaust diffuser, which can be used for carrying out steady-state and transition-state test measurement, can carry out steady-state and transition-state tests, and is convenient to adjust the air inlet rotational flow conditions and the support plate structure. By researching the difference between the transition state measurement experiment data and the steady state measurement experiment data, the change rule of the aerodynamic performance of the exhaust diffuser in the variable working condition operation process of the gas turbine is further deeply and truly researched, reference is provided for optimization and improvement of the exhaust diffuser, and the overall operation efficiency of the gas turbine is further improved.
In order to achieve the purpose, the invention adopts the technical scheme that:
the utility model provides a can carry out steady state and transition state experiment measurement's exhaust diffuser aerodynamic performance measurement experiment platform, includes the exhaust diffuser model, the experiment pipeline is connected to the entry end of exhaust diffuser model, and the exit end sets up the removal measuring platform, along the air current direction, thermal type flowmeter, quick response pneumatic valve and steady voltage cavity have set gradually on the experiment pipeline, the removal measuring platform is used for measuring exhaust diffuser model outlet pressure field and velocity field.
Furthermore, the exhaust diffuser model comprises a shell and an inner hub located in the shell in the axial direction, the inner hub is installed in the shell through a support plate structure, a turbulence grid structure and an air inlet guide vane structure are arranged between the inner hub and the wall surface of the shell, the turbulence grid structure is located at the inlet end of the exhaust diffuser model, and the air inlet guide vane structure is located behind the turbulence grid structure and used for simulating wake flow and rotational flow generated by a power turbine in a real gas turbine.
Furthermore, the exhaust diffuser model adopts a modular design, and the turbulence grid structure, the air inlet guide vane structure and the support plate structure are replaceable modular units.
Furthermore, the shell wall surface material and the inner hub material of the exhaust diffuser model are 7-series aviation aluminum, the turbulence grid structure is stainless steel, and the air inlet guide vane structure and the support plate structure are made of tough resin materials through 3D printing.
Furthermore, a plurality of three-hole probe measuring holes are uniformly distributed in the exhaust diffuser model behind the air inlet guide vane structure along the circumferential direction, the rear three-hole probe is fixed by a probe clamp, a pressure field and a velocity field behind the air inlet guide vane structure are measured in a moving mode along the radial direction, and wall static pressure measuring points are distributed on the wall surface of the shell of the exhaust diffuser model.
Furthermore, the response frequency of the thermal flowmeter is less than 100ms, mass flow signals are collected by an NI-9234 acquisition card, the rapid response pneumatic valve supplies air independently through an air pump air supply pipeline, the action time of the rapid response pneumatic valve is adjusted within the range of 1-10s, so that pressure fields with different change rates are formed at the downstream of the rapid response pneumatic valve, and the pressure fields of the gas turbine under the transition state working conditions of starting and stopping, accelerating, decelerating and the like are simulated; and the valve switch trigger signal of the quick response pneumatic valve is controlled by a special control box, and a pulse voltage signal is output when the quick response pneumatic valve starts and finishes the action, so that the time for starting and finishing the action of the valve is accurately positioned.
Furthermore, a steady flow honeycomb is fixed in the pressure stabilizing cavity, the diameter of a core grid of the steady flow honeycomb is 3mm, and the steady flow honeycomb is used for providing uniform and stable experimental airflow for the downstream.
Furthermore, an inlet three-hole probe capable of moving in the radial direction is arranged between the pressure stabilizing chamber and the inlet end of the exhaust diffuser model in the experimental pipeline and used for measuring the speed and pressure distribution curve of the fluid in the pipeline in the radial direction.
Furthermore, when the quick response pneumatic valve is kept in a full-open state, a passage is formed in the pipeline of the whole experiment platform, the air flow of the compressor flows into the exhaust diffuser model through the flowmeter, the quick response pneumatic valve and the pressure stabilizing chamber, and the inlet pressure, the outlet velocity field and the internal pressure and the internal velocity field of the exhaust diffuser model are measured by the inlet three-hole probe, the rear three-hole probe, the wall surface static pressure measuring point and the outlet moving measuring platform.
Furthermore, the mobile measurement platform comprises a probe, the probe is fixed on a sliding block, the sliding block is arranged on a screw rod, the servo motor is controlled by a controller to drive the sliding block to slide along the screw rod, the reciprocating movement of the probe at the outlet of the exhaust diffuser model is further driven to perform measurement, and the repeated positioning precision of the mobile measurement platform is 0.05 mm.
Compared with the prior art, the invention has the beneficial effects that:
at present, an experimental platform for measuring the pneumatic performance of an exhaust diffuser can only perform measurement experiments under a steady-state working condition, but in the actual operation process of a gas turbine, the gas turbine can undergo transition state operation processes such as deceleration, acceleration, start-stop and the like. In these processes, the aerodynamic parameters inside the exhaust diffuser of the gas turbine are changed dramatically, and the aerodynamic performance of the exhaust diffuser, which is a key component of the outlet portion of the gas turbine, affects the exhaust environment of the power turbine, and thus affects the overall operation of the gas turbine. The experiment table can measure the pneumatic performance of the exhaust diffuser under the conventional steady-state working condition, can simulate pressure fields with different change rates through the quick response pneumatic valve with adjustable valve action time, and can synchronously trigger the acquisition system through multiple matched physical quantities to obtain pneumatic data of the exhaust diffuser changing along with the air inlet condition under the transition state working condition. The change rule of the aerodynamic performance of the exhaust diffuser under the working condition of the transition state and the influence of the change rule on the whole gas turbine are favorably and deeply understood, the operation safety of the gas turbine is enhanced, meanwhile, reference is provided for the optimized design of the exhaust diffuser and the research and development of the advanced exhaust diffuser, and finally the whole operation efficiency of the gas turbine is improved.
Drawings
FIG. 1 is a schematic view of the entire experimental table of the present invention.
FIG. 2 is an experimental model of an exhaust diffuser of the present invention.
Fig. 3 is a turbulence grid within a plenum chamber of the present invention.
FIG. 4 is a schematic view of a mobile measurement platform according to the present invention.
Detailed Description
The embodiments of the present invention will be described in detail below with reference to the drawings and examples.
As shown in figure 1, the experimental bench for measuring the pneumatic performance of the exhaust diffuser capable of carrying out steady-state and transition-state experimental measurement comprises an experimental pipeline 3, an exhaust diffuser model 6 and a mobile measurement platform 7, wherein a thermal flowmeter 1, a quick-response pneumatic valve 2 and a pressure stabilizing chamber 4 are sequentially arranged on the experimental pipeline 3 along the airflow direction, the outlet end of the experimental pipeline 3 is connected with the inlet end of the exhaust diffuser model 6, and the mobile measurement platform 7 is arranged at the outlet end of the exhaust diffuser model 6 and used for measuring the outlet pressure field and the velocity field of the exhaust diffuser model 6.
As shown in fig. 2, in one embodiment of the present invention, the exhaust diffuser model 6 includes a housing within which is mounted an inner hub axially, the inner hub being mounted within the housing by a support plate structure 6 c. A turbulence grid structure 6a and an air inlet guide vane structure 6b are arranged between an inner hub and the wall surface of a shell, wherein the turbulence grid structure 6a is positioned at the inlet end of an exhaust diffuser model 6, and the air inlet guide vane structure 6b is positioned behind the turbulence grid structure 6a along the airflow direction and is used for simulating wake flow and rotational flow generated by a power turbine in a real gas turbine. The inlet guide vane structure 6b is generally located forward of the support plate structure 6 c.
Illustratively, in the present invention, the exhaust diffuser model 6 is of a modular design, and the turbulence grid structure 6a, the inlet guide vane structure 6b and the support plate structure 6c are all modular units that can be quickly disassembled and replaced. Therefore, the experiment table can measure the aerodynamic performance of the exhaust diffuser under different turbulence degrees, different airflow prerotations and different supporting plate structures.
As a part of the process, the wall surface of the shell and the inner hub of the exhaust diffuser model 6 of the invention are made of 7-series aviation aluminum, the turbulence grid structure 6a is made of stainless steel, and the air inlet guide vane structure 6b and the support plate structure 6c are made of tough resin materials through 3D printing. Obviously, other suitable materials may be used for the above components.
In one embodiment of the invention, a plurality of three-hole probe measuring holes 6d are uniformly arranged in the exhaust diffuser model 6 behind the air inlet guide vane structure 6b along the circumferential direction, and the rear three-hole probe is fixed by a probe clamp and can move in the three-hole probe measuring holes 6d along the radial direction to measure the pressure field and the speed field behind the air inlet guide vane structure 6 b. A wall static pressure measuring point 6e is arranged on the wall surface of the casing of the exhaust diffuser model 6.
In one embodiment of the invention, a thermal flow meter 1 is installed upstream of an experimental pipeline 3 to monitor the mass flow of fluid in the pipeline during the experiment. The thermal flow meter 1 has a response frequency of less than 100ms, and mass flow signals are collected by an NI-9234 acquisition card having a 102dB dynamic range, while digitizing the signals at a rate of up to 51.2kHz per channel.
In one embodiment of the invention, the quick response pneumatic valve 2 is independently supplied with air by the air pump 8 through the air pump air supply pipeline 9, and the action time (the time from the valve being turned on to the valve being turned off or from the valve being turned off to the valve being turned on) of the quick response pneumatic valve 2 can be adjusted within the range of 1-10s, so that pressure fields with different change rates are formed at the downstream of the quick response pneumatic valve, and the pressure fields of the gas turbine under the transition state working conditions of starting and stopping, accelerating, decelerating and the like are simulated. And the valve switch trigger signal of the quick response pneumatic valve 2 is controlled by a special control box, and the action time can be acquired by an NI-9234 acquisition card. The quick response pneumatic valve 2 can output pulse voltage signals when the action starts and finishes, so as to accurately position the time for starting and finishing the action of the valve.
As shown in fig. 3, in one embodiment of the present invention, a flow stabilization honeycomb 4a is fixed in the pressure stabilization chamber 4, and the flow stabilization honeycomb 4a is fixed by a fastening ring 4 b. The core grid diameter of the steady flow honeycomb is 3mm and is used for providing uniform and stable experimental airflow for the downstream.
In one embodiment of the invention, an inlet three-hole probe 5 capable of moving in the radial direction is arranged in the experimental pipeline 3 between the pressure stabilizing chamber 4 and the inlet end of the exhaust diffuser model 6, and is used for measuring the speed and pressure distribution curve of the fluid in the pipeline in the radial direction.
As shown in fig. 4, in one embodiment of the present invention, the mobile measurement platform 7 includes a probe 7a, and the probe 7a may be a five-hole probe. The probe 7a is fixed on the sliding block 7b, the sliding block 7b is arranged on the screw rod 7c, the servo motor is controlled by the controller to drive the sliding block 7b to slide along the screw rod 7c, and then the probe 7a is driven to perform reciprocating movement measurement at the outlet of the exhaust diffuser model 6, the repeated positioning precision of the movable measuring platform 7 is 0.05mm, the planar range of 300 x 300mm can be covered, and the pressure field and the speed field at the outlet of the exhaust diffuser model 6 can be measured. Illustratively, the flow signal and the valve trigger signal of the thermal flowmeter 1 are collected by an NI-9234 acquisition card and then processed by a Labview program. The control program of the mobile measurement platform 7 is also embedded in the Labview program.
During measurement, compressor airflow flows into the exhaust diffuser model 6 through the flowmeter 1, the quick response pneumatic valve 2 and the pressure stabilizing chamber 4, the inlet and outlet pressure and speed fields and the internal pressure and speed field of the exhaust diffuser model 6 are measured by the inlet three-hole probe 5, the three-hole probe behind the inlet guide vane structure 6b, the wall surface static pressure measuring point 6e and the outlet movable measuring platform 7, all pressure signals of the experiment table are processed by the PSI9216 pressure scanning valve, the measurement precision of the instrument is 0.05%, and the measurement of the pneumatic performance of the exhaust diffuser is completed.
The invention also provides an experimental method of the experimental table for measuring the aerodynamic performance of the exhaust diffuser based on steady-state and transition-state experimental measurement, which comprises the following steps:
when a steady-state experiment is carried out, the air pump 8 is started after the relevant measuring instruments and the signal acquisition devices are arranged, so that the pressure of the air storage tank of the air pump 8 reaches a set value. Then, the valve on the air pump air supply line 9 is opened, so that the air pump 8 maintains the air supply state to the quick response pneumatic valve 2. And triggering an opening signal of the control box of the quick response pneumatic valve 2, opening the valve of the quick response pneumatic valve 2 and keeping the valve in a fully open state, forming a passage on the pipeline of the experiment platform at the moment, and performing a steady-state measurement experiment.
The compressor is started, the compressor starts to provide an air source for the experiment table, the thermal flowmeter 1 and the inlet three-hole probe 5 are used for monitoring the gas flow and the pressure in the experiment pipeline 3, the flow and the pressure of the gas at the outlet of the compressor are adjusted through the bypass valve until the inlet pressure and the flow required by the steady-state experiment are reached. And starting to perform experimental measurement after the flow and the pressure monitored by the thermal flowmeter 1 and the inlet three-hole probe 5 are stable. The three-hole inlet probe 5 can move along the radial direction to obtain the speed and pressure distribution of fluid at the inlet of the exhaust diffuser model 6, and the three-hole rear probe can measure the flow field state behind the air inlet guide vane structure 6 b. A wall static pressure measuring point 6e is arranged on the wall surface of the exhaust diffuser model 6, and the wall pressure distribution characteristics of the exhaust diffuser can be measured. And the Labview can be used for controlling the mobile measuring platform 7, the five-hole probe 7a fixed on the mobile measuring platform measures the outlet flow field under the control of the Labview program until all measurements are finished.
Through changing the turbulence grid structure 6a, the air inlet guide vane structure 6b or the supporting plate structure 6c of different structures, the above operation is repeated, different turbulence conditions and different air inlet rotational flow conditions can be carried out, and under different supporting plate structures, the measurement of the aerodynamic performance of the exhaust diffuser model 6 can be carried out.
When the transition state experiment is carried out, the air pump 8 is started after the relevant measuring instruments and the signal acquisition devices are arranged, so that the pressure of the air storage tank of the air pump 8 reaches a set value. Then, the valve on the air pump air supply line 9 is opened, so that the air pump 8 maintains the air supply state to the quick response pneumatic valve 2. The valve action time of the quick response pneumatic valve 2 is set according to the required pressure change rate, firstly, an opening signal of a control box of the quick response pneumatic valve 2 is triggered, the valve of the quick response pneumatic valve 2 is opened and is kept in a fully open state, and at the moment, the pipeline of the experiment platform forms a passage.
The compressor is started, the compressor starts to provide an air source for the experiment table, the thermal flowmeter 1 and the three-hole inlet probe 5 are used for monitoring the gas flow and the pressure in the experiment pipeline 3, the flow and the pressure of the gas at the outlet of the compressor are adjusted through the bypass valve until the initial inlet pressure and the flow required by the transition state experiment are reached.
And adjusting the control knob of the quick response pneumatic valve 2 according to the required change condition of the transition state pressure. Triggering the 'off' signal of the control box of the quick response pneumatic valve 2, the quick response pneumatic valve 2 can be closed according to the set valve action time, and in the closing process of the quick response pneumatic valve 2, the flow and pressure in the experimental pipeline 3 are dynamically changed, and the transition state measurement can be carried out at the moment.
In the same way, the quick response pneumatic valve 2 can be kept in a closed state at the beginning, and the control knob of the quick response pneumatic valve 2 is adjusted according to the required change condition of the transition state pressure. Triggering the 'on' signal of the control box of the quick response pneumatic valve 2, starting the quick response pneumatic valve 2 until the quick response pneumatic valve is fully opened according to the set valve action time, and dynamically changing the flow and the pressure in the experimental pipeline 3 in the opening process of the quick response pneumatic valve 2, and then performing transition state measurement.
The rapid response pneumatic valve 2 sends out pulse voltage when starting to act, after the acquisition card acquires the pulse voltage, the Labview program triggers the PSI pressure scanning valve and the NI9234 acquisition card to synchronously record pressure data and flow data, when the rapid response pneumatic valve 2 acts, the Labview program stops the PSI pressure scanning valve and the NI9234 acquisition card to record the pressure data and the flow data, and the transient state experiment working condition measurement corresponding to the one-time rapid response pneumatic valve 2 from 'on' to 'off' or from 'off' to 'on' is completed. And changing the positions of the inlet three-hole probe 5, the rear three-hole probe and the probe 7a on the outlet mobile measuring platform 7, and repeating the operation until the transition state pressure change process of all measuring points is recorded.
Claims (10)
1. The utility model provides a can carry out steady state and transition state experiment measurement's exhaust diffuser aerodynamic performance measurement laboratory bench, a serial communication port, including exhaust diffuser model (6), experiment pipeline (3) are connected to the entry end of exhaust diffuser model (6), and the exit end sets up movable measurement platform (7), along the air current direction, thermal type flowmeter (1), quick response pneumatic valve (2) and steady voltage cavity (4) have set gradually on experiment pipeline (3), movable measurement platform (7) are used for measuring exhaust diffuser model (6) outlet pressure field and velocity field.
2. The experimental bench for measuring the aerodynamic performance of an exhaust diffuser capable of steady-state and transition-state experimental measurement according to claim 1, characterized in that the exhaust diffuser model (6) comprises a housing and an axial inner hub located in the housing, the inner hub is installed in the housing through a support plate structure (6c), a turbulence grid structure (6a) and an intake guide vane structure (6b) are arranged between the inner hub and the wall surface of the housing, wherein the turbulence grid structure (6a) is located at the inlet end of the exhaust diffuser model (6), and the intake guide vane structure (6b) is located behind the turbulence grid structure (6a) and is used for simulating wake flow and rotational flow generated by a power turbine in a real gas turbine.
3. The experimental bench for measuring the aerodynamic performance of an exhaust diffuser capable of steady-state and transition-state experimental measurements according to claim 2, characterized in that the exhaust diffuser model (6) is of modular design, and the turbulence grid structure (6a), the inlet guide vane structure (6b) and the support plate structure (6c) are replaceable modular units.
4. The experimental bench for measuring the aerodynamic performance of the exhaust diffuser capable of steady-state and transition-state experimental measurement according to claim 2 or 3, wherein the material of the wall surface of the casing and the material of the inner hub of the exhaust diffuser model (6) are 7-series aircraft aluminum, the turbulence grid structure (6a) is stainless steel, and the air inlet guide vane structure (6b) and the support plate structure (6c) are made of flexible resin materials and manufactured by 3D printing.
5. The experimental bench for measuring the pneumatic performance of the exhaust diffuser capable of carrying out the steady-state and transition-state experimental measurement according to claim 2 or 3, characterized in that a plurality of three-hole probe measuring holes (6d) are uniformly arranged in the exhaust diffuser model (6) at the rear of the air inlet guide vane structure (6b) along the circumferential direction, the rear three-hole probe is fixed by a probe clamp, a pressure field and a velocity field at the rear of the air inlet guide vane structure (6b) are measured in a radial movement manner, and wall surface static pressure measuring points (6e) are arranged on the wall surface of the casing of the exhaust diffuser model (6).
6. The experimental bench for measuring the pneumatic performance of the exhaust diffuser, which can perform steady-state and transient-state experimental measurement according to claim 1, 2 or 3, is characterized in that the response frequency of the thermal flowmeter (1) is less than 100ms, the mass flow rate signals are collected by an NI-9234 acquisition card, the fast-response pneumatic valve (2) is independently supplied by an air pump (8) through an air pump air supply pipeline (9), and the action time of the fast-response pneumatic valve (2) is adjusted within the range of 1-10s, so that pressure fields with different change rates are formed at the downstream of the fast-response pneumatic valve, and the pressure fields of a gas turbine under transient-state working conditions of starting, stopping, accelerating and decelerating are simulated; and the valve switch triggering signal of the quick response pneumatic valve (2) is controlled by a special control box, and a pulse voltage signal is output when the quick response pneumatic valve (2) starts and finishes the action, so that the time for starting and finishing the action of the valve is accurately positioned.
7. The experimental bench for measuring the aerodynamic performance of an exhaust diffuser capable of steady-state and transient-state experimental measurements according to claim 1, 2 or 3, characterized in that a flow stabilizing honeycomb (4a) is fixed in the pressure stabilizing chamber (4), and the core cell diameter of the flow stabilizing honeycomb is 3mm, so as to provide uniform and stable experimental airflow for the downstream.
8. The experimental bench for measuring the aerodynamic performance of an exhaust diffuser capable of steady-state and transient-state experimental measurements according to claim 1, 2 or 3, characterized in that an inlet three-hole probe (5) movable in a radial direction is arranged in the experimental pipe (3) between the surge chamber (4) and the inlet end of the exhaust diffuser model (6) for measuring the radial distribution curve of the velocity and pressure of the fluid in the pipe.
9. The experimental bench for measuring the pneumatic performance of the exhaust diffuser capable of performing the steady-state and transient-state experimental measurements according to claim 8, wherein when the fast response pneumatic valve (2) is kept in a fully open state, a passage is formed in the whole experimental bench pipeline, the compressor air flows into the exhaust diffuser model (6) through the flowmeter (1), the fast response pneumatic valve (2) and the pressure stabilizing chamber (4), and the inlet and outlet pressure and velocity fields and the internal pressure and velocity field of the exhaust diffuser model (6) are measured by using the inlet three-hole probe (5), the three-hole probe behind the inlet guide vane, the wall static pressure measuring point (6e) and the outlet moving measuring bench (7).
10. The experimental bench for measuring the pneumatic performance of the exhaust diffuser, which can perform the steady-state and transition-state experimental measurements, according to claim 1, 2 or 3, is characterized in that the mobile measuring platform (7) comprises a probe (7a), the probe (7a) is fixed on a sliding block (7b), the sliding block (7b) is arranged on a screw rod (7c), the servo motor is controlled by the controller to drive the sliding block (7b) to slide along the screw rod (7c), so as to drive the probe (7a) to perform the reciprocating movement measurement at the outlet of the exhaust diffuser model (6), and the repeated positioning accuracy of the mobile measuring platform (7) is 0.05 mm.
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| KR20060003629A (en) * | 2004-07-07 | 2006-01-11 | 건국대학교 산학협력단 | Supersonic wind tunnel for education |
| JP2007206023A (en) * | 2006-02-06 | 2007-08-16 | Mitsubishi Heavy Ind Ltd | Temperature measuring device, combustion monitoring device, and gas turbine |
| RU2381472C1 (en) * | 2008-08-01 | 2010-02-10 | Российская Федерация, от имени которой выступает государственный заказчик Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Method for testing of pulsating detonating engine and aerodynamic installation for its realisation |
| CN204831793U (en) * | 2015-06-05 | 2015-12-02 | 湖南科技大学 | Whirlpool shaft generator dynamic characteristic studies experimental apparatus |
| CN207556798U (en) * | 2017-12-14 | 2018-06-29 | 中国航发沈阳发动机研究所 | Diffuser performance test device |
| CN110726562A (en) * | 2019-08-30 | 2020-01-24 | 浙江大学 | Diffuser and flame tube optimization matching experimental research device |
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