CN114993638A - Rotating turbine blade cooling test system and method - Google Patents
Rotating turbine blade cooling test system and method Download PDFInfo
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- CN114993638A CN114993638A CN202210494780.4A CN202210494780A CN114993638A CN 114993638 A CN114993638 A CN 114993638A CN 202210494780 A CN202210494780 A CN 202210494780A CN 114993638 A CN114993638 A CN 114993638A
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- 238000012360 testing method Methods 0.000 title claims abstract description 152
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 27
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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
- G01M13/00—Testing of machine parts
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
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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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- 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
- F02C7/22—Fuel supply systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to the technical field of gas turbines, and discloses a rotating turbine blade cooling test system and a rotating turbine blade cooling test method. The rotary turbine blade cooling test system provided by the invention has the advantages of low test cost, no position limitation of the test device and flexible starting.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a system and a method for a cooling test of a rotating turbine blade.
Background
To improve market competitiveness, gas turbines require a continuous increase in the output and efficiency of the unit, resulting in a continuous increase in turbine blade inlet temperature. In order to ensure safe, stable and long-life operation of the turbine blade at higher temperature, a high-efficiency turbine blade cooling design technology is introduced in addition to the adoption of more advanced materials.
In the related technology, part of indexes of a high-efficiency turbine blade cooling design can be verified through a turbine blade cooling effect test in a static state, but the flow and heat transfer phenomena in a multistage turbine runner of a heavy-duty gas turbine are very complex and highly coupled, a secondary flow vortex system interacts with a main flow area of the turbine, and interstage interference can cause blade excitation, so that the cooling effect of an actual turbine blade in a rotating working state is greatly different from the cooling effect measured in the static state, the measurement in the rotating state is more consistent with the actual situation of engineering, a rotating turbine blade cooling effect test device needs to be established for verifying the influence of cooling air mixing on the turbine stage aerodynamic performance and the influence of the rotating state on the turbine moving blade cooling effect, and the high-temperature rotating turbine blade flowing and cooling test research is carried out.
Disclosure of Invention
The present invention is directed to solving, at least in part, one of the technical problems in the related art.
Therefore, the embodiment of the invention provides a rotary turbine blade cooling test system which has the advantages of low test cost, no position limitation of a test device and flexible starting.
According to the rotary turbine blade cooling test system of the embodiment of the invention, the rotary turbine blade cooling test system comprises a rotary turbine blade cooling test device, an aircraft engine, a cooling air source device, a test cooling water device, a control system and a data acquisition system, wherein the aircraft engine comprises a gas generator for providing main stream gas for the rotary turbine blade cooling test device and a gas compressor for providing cooling air for the rotary turbine blade cooling test device, the cooling air source device is connected with the rotary turbine blade cooling test device, the cooling air source device is used for controlling the flow and pressure of the cooling air entering the rotary turbine blade cooling test device, the test cooling water device is connected with the rotary turbine blade cooling test device, and the test cooling water device is used for cooling the inlet and the outlet of the rotary turbine blade cooling test device, the control system is respectively connected with the rotating turbine blade cooling effect test device, the cooling air source device and the test cooling water device, the control system is used for controlling the output quantities of the main flow gas, the cooling air and the cooling water, the data acquisition system is electrically connected with the control system, and the data acquisition system is used for acquiring the operation parameters of the test system and sending the operation parameters to the control system.
The rotating turbine blade cooling test system provided by the embodiment of the invention has the advantages of low test cost, no position limitation on the test device and flexibility in starting.
In some embodiments, the rotating turbine blade cooling test device includes mainstream gas admission valve, turbine blade test section, sprays section and amortization tower in proper order, mainstream gas admission valve is used for the control to get into the mainstream gas flow of turbine blade test section, turbine blade test section spray the section with the amortization tower links to each other in proper order, the section that sprays is used for rapid cooling mainstream gas, the amortization tower is used for eliminating noise.
In some embodiments, the cooling air supply means includes a cooling air inlet valve connected to the compressor and a cooling air regulating valve connected to the turbine blade test section, the cooling air inlet valve and the cooling air regulating valve being configured to control the flow and pressure of cooling air entering the turbine blade test section.
In some embodiments, the test cooling water device comprises a cooling tower, a water inlet pipeline, a water replenishing pipeline and a water outlet pipeline, wherein the cooling tower is connected with the outlet of the fuel gas generator and the spray section through the water inlet pipeline, the cooling tower is connected with the inlet and the outlet of the test turbine section through the water outlet pipeline, and the water replenishing pipeline is connected with the cooling tower.
In some embodiments, the turbine blade test section includes a test turbine cylinder assembly, a turbine assembly, an inlet measurement section, an outlet measurement section, and an exhaust volute coupled to the test turbine cylinder and the spray section for collecting the turbine assembly outlet flow.
In some embodiments, the turbine assembly has a modeling ratio of 1/4 to 1/3.
In some embodiments, the turbine blade test section further comprises a hydraulic clearance adjustment device for adjusting a clearance of the turbine blade from the test turbo cylinder assembly.
In some embodiments, the data collection system includes a pressure collection device, a temperature collection device, a flow collection device, a transmission system collection device, a dynamic stress collection device, and a vibration collection device, the pressure collection device collects the pressure of the main stream gas inlet pipeline, the outlet pressure of the turbine assembly, and the pressure of the cooling air, the temperature collection module collects the temperatures of the main stream gas and the cooling air, the flow collection device collects the flow of the main stream gas and the cooling air, the transmission collection device collects the rotational speed, torque, and power data of the turbine assembly, the dynamic stress collection device collects the dynamic stress of the turbine blade, and the vibration collection device collects the casing vibration data.
In some embodiments, the transmission acquisition device comprises a hydraulic dynamometer, and an output shaft of the turbine blade test section is connected with the hydraulic dynamometer, and the hydraulic dynamometer is used for measuring shaft power of the turbine assembly and controlling output rotating speed of the turbine assembly.
In some embodiments, the control system comprises a data storage module, a control switching module, a communication module and a safety module, wherein the data storage module is used for storing test system operation parameters sent by the data acquisition system, the control switching module is used for switching a low-voltage electric manual control mode and a computer remote control mode, the communication module is used for communicating with the data acquisition system and an upper computer, and the safety module is used for monitoring corresponding parameter values according to preset parameters to realize emergency protection.
According to the cooling test method for the rotating turbine blade, the cooling test method for the rotating turbine blade comprises the following steps: extracting gas at the outlet of a gas generator of the aero-engine as main stream gas, and extracting air at the outlet of a compressor of the aero-engine as cooling air; respectively introducing main flow gas and cooling air into a main flow channel of a turbine blade test section and a cooling channel inside a turbine blade, and performing a cooling effect test of the rotating turbine blade; and collecting outlet airflow of the turbine blade test section, rapidly cooling the outlet airflow and discharging the outlet airflow into a silencing tower.
Drawings
FIG. 1 is a schematic block diagram of a rotary turbine blade cooling test system according to an embodiment of the present invention.
Reference numerals: 1. an aircraft engine; 2. a compressor; 3. a combustion chamber; 4. a gas turbine; 5. a power turbine; 6. a gas generator; 7. a rotating turbine blade cooling effect test device; 8. a cooling gas source device; 9. testing a cooling water device; 10. a control system; 11. a data acquisition system; 12. a mainstream gas inlet valve; 13. a main flow gas regulating valve; 14. a ripple compensator; 15. a turbine blade test section; 16. a spraying section; 17. an exhaust butterfly valve; 18. a silencing tower; 19. a hydraulic clearance adjustment device; 20. a hydraulic dynamometer; 21. a cooling air intake valve; 22. a cooling air regulating valve; 23. a water pump; 24. a water replenishing pipeline; 25. a water inlet pipe; 26. a cooling tower; 27. a water outlet pipeline; 28. a flow rate measurement point; 29. measuring a pressure point; 30. and (6) measuring the temperature.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
According to the rotary turbine blade cooling test system of the embodiment of the invention, as shown in fig. 1, the rotary turbine blade cooling test system comprises a rotary turbine blade cooling test device, an aircraft engine 1, a cooling air source device 8, a test cooling water device 9, a control system 10 and a data acquisition system 11, wherein the aircraft engine 1 comprises a gas generator 6 for providing main flow gas for the rotary turbine blade cooling test device, a compressor 2 for providing cooling air for the rotary turbine blade cooling test device and a power turbine 5, and the power turbine 5 mainly converts the energy of high-temperature and high-pressure gas at the inlet of the gas turbine 4 into mechanical energy of the power turbine 5. The cooling air source device 8 is connected with the rotary turbine blade cooling test device, the cooling air source device 8 is used for controlling the flow and pressure of cooling air entering the rotary turbine blade cooling test device, the test cooling water device 9 is connected with the rotary turbine blade cooling test device, the test cooling water device 9 is used for cooling the inlet and the outlet of the rotary turbine blade cooling test device, the control system 10 is respectively connected with the rotating turbine blade cooling effect test device 7, the cooling air source device 8 and the test cooling water device 9, the control system 10 is used to control the output of the mainstream fuel gas, the cooling air and the cooling water, the data acquisition system 11 is electrically connected with the control system 10, and the data acquisition system 11 is used for acquiring the operation parameters of the test system and sending the operation parameters to the control system 10. Compared with a specially established working condition rotating turbine blade cooling effect test device, the aero-engine 1 adopting the retired aero-engine 1 can reduce the equipment purchase cost of the test device and the power consumption cost of corresponding equipment by reducing an air compressor, an air electric heater, a combustion chamber 3 for providing high-temperature gas, an air blower, a filter, an air heater and the like for providing cooling air. The rotary turbine blade cooling test device adopting the air supply of the aircraft engine 1 is limited by the space position, and does not need the work of power grid dispatching, unit transformation and the like, so that the test is flexible to start and consumes less time.
The rotating turbine blade cooling test system provided by the embodiment of the invention has the advantages of low test cost, no position limitation of a test device and flexibility in use.
In some embodiments, as shown in fig. 1, the rotating turbine blade cooling test device sequentially includes a main flow gas inlet valve 12, a turbine blade test section 15, a spray section 16 and a silencer tower 18, where the main flow gas inlet valve 12 is used to control a flow rate of main flow gas entering the turbine blade test section 15, the spray section 16 and the silencer tower 18 are sequentially connected, the spray section 16 is used to rapidly cool the main flow gas, and the silencer tower 18 is used to eliminate noise.
Specifically, a main flow gas inlet valve 12 is connected with an outlet air extraction pipeline of a gas generator 6 of the aircraft engine 1, a main flow gas regulating valve 13 is further arranged, the control of the inlet flow and the pressure of the main flow gas is realized through the opening degrees of the main flow gas inlet valve 12 and the main flow gas regulating valve 13, and exhaust gas of a spray section 16 enters a silencing tower 18 after passing through an exhaust butterfly valve 17 and is discharged into the atmosphere after being subjected to noise reduction.
In some embodiments, as shown in fig. 1, the cooling air supply device 8 includes a cooling air intake valve 21 and a cooling air regulating valve 22, the cooling air intake valve 21 is connected to the compressor 2, the cooling air regulating valve 22 is connected to the turbine blade test section 15, and the cooling air intake valve 21 and the cooling air regulating valve 22 are used for controlling the flow and pressure of the cooling air entering the turbine blade test section 15.
Specifically, a cooling air inlet valve 21 is connected with an exhaust cylinder of a compressor 2 of the aircraft engine 1, and a cooling air regulating valve 22 is connected with the turbine blade test section 15 through a pipeline. The cooling air enters the turbine blade internal cooling passage from the tip of the stationary blade or the root of the moving blade. The pipeline connecting the cooling air control valve 22 and the turbine blade test section 15 is provided with a flow measuring point 28, a pressure measuring point 29 and a temperature measuring point 30.
In some embodiments, as shown in fig. 1, the test cooling water device 9 comprises a cooling tower 26, a water pump 23, a water inlet pipe 25, a water replenishing pipe 24 and a water outlet pipe 27, wherein the cooling tower 26 is connected with the outlet of the gas generator 6 and the spray section 16 through the water inlet pipe 25, the cooling tower 26 is connected with the inlet and the outlet of the test turbine section through the water outlet pipe 27, and the water replenishing pipe 24 is connected with the cooling tower 26. The water pump 23 is provided on the water inlet pipe 25.
Specifically, the test chilled water unit is used to cool the inlet and outlet of the turbine blade test section 15. Cooling water of the cooling tower 26 is sprayed into the spraying section 16, the exhaust temperature after the turbine test section is reduced to be below 100 ℃, and a downstream back pressure valve and the silencing tower 18 are ensured not to exceed the use temperature; the pipe section in front of the spraying section 16 adopts a high-temperature alloy double-layer water jacket structure, and the material of the sprayed pipe is 304 stainless steel.
In some embodiments, the turbine blade test section 15 includes a test turbine cylinder assembly, a turbine assembly, an inlet measurement section, an outlet measurement section, and an exhaust volute coupled to the test turbine cylinder and the spray section 16 for collecting the turbine assembly outlet flow.
Specifically, the turbine assembly includes a first stage turbine vane, a first stage turbine blade, a second stage turbine vane, and a second stage turbine blade. The turbine blade test section 15 may operate in a single row blade row, single stage turbine, one stage semi-permeable, and two stage turbine configuration. The inlet temperature of the turbine blade test section 15 can reach 900 ℃, and the inlet pressure can reach 2.8 MPa. The shell of the turbine blade test section 15 is designed as a double-layer shell, a heat insulating material is additionally arranged between the double-layer shell, and the corrugated compensator 14 is installed on a main flow air inlet pipeline to absorb the expansion amount of the air inlet pipeline.
In some embodiments, the turbine assembly has a mold ratio of 1/4 to 1/3. Therefore, the simulation effect of the turbine assembly is appropriate, and the test cost is reduced while the test effect is ensured.
In some embodiments, as shown in FIG. 1, the turbine blade test section 15 further comprises a hydraulic lash adjuster 19, and the hydraulic lash adjuster 19 is configured to adjust a clearance between the turbine blade and the test turbine cylinder assembly.
Specifically, the hydraulic clearance adjusting device 19 drives the piston to push a thrust bearing and a rotor of the test turbine through hydraulic oil, so that axial displacement is realized, the clearance between the top of the movable blade of the test turbine and the cylinder of the test turbine is adjusted, and meanwhile, a limiter is arranged to limit the axial displacement. The hydraulic clearance adjusting device 19 is used for moving the rotor for a certain distance along the direction of the reverse airflow through the hydraulic device when the gas turbine enters a completely warm-up state, namely, when the dynamic and static clearances are not changed any more, so that the dynamic and static clearances of the gas turbine 4 are reduced, and the aero-engine 1 can reach higher efficiency and power, thereby enabling the cooling effect test of the rotating turbine blades to meet the actual situation as much as possible.
In some embodiments, the data collection system 11 includes a pressure collection device, a temperature collection device, a flow collection device, a transmission system collection device, a dynamic stress collection device, and a vibration collection device, the pressure collection device collects the pressure of the main stream gas inlet pipeline, the outlet pressure of the turbine assembly, and the pressure of the cooling air, the temperature collection device collects the temperature of the main stream gas and the cooling air, the flow collection device collects the flow of the main stream gas and the cooling air, the transmission collection device collects the rotational speed, torque, and power data of the turbine assembly, the dynamic stress collection device collects the dynamic stress of the turbine blade, and the vibration collection device collects the casing vibration data.
Specifically, the pressure acquisition device comprises a pressure scanning valve, a pressure transmitter and the like for acquisition, and the temperature acquisition device comprises a thermocouple, temperature indicating paint and the like for acquisition; the flow acquisition device adopts a flow nozzle, a mass flowmeter and the like for acquisition; the transmission system acquisition device acquires the turbine rotation speed, the turbine torque and the turbine power; the dynamic stress acquisition device measures the dynamic stress of the blade by adopting a method of combining a plasma ceramic ion spraying high-temperature strain gauge and a film strain gauge, and selects according to the shape and the test position of the blade; the vibration of the casing in the vibration acquisition device is measured by an acceleration sensor. The test piece pressure test includes a steady state pressure test and a dynamic pressure test. The data acquisition system 11 acquires data such as the temperature of the main stream gas inlet, the total pressure of the main stream gas inlet, the static pressure of the outlet of the test section, the flow rate of the main stream air, the temperature and pressure of the fuel of the combustion chamber 3, the flow rate of the cooling air, the temperature and pressure, and the torque and power of the test turbine.
In some embodiments, as shown in fig. 1, the transmission collection device comprises a hydraulic dynamometer 20, an output shaft of the turbine blade test section 15 is connected with the hydraulic dynamometer 20, and the hydraulic dynamometer 20 is used for measuring shaft power of the turbine assembly and controlling output rotation speed of the turbine assembly.
Specifically, the hydraulic dynamometer 20 is coupled to an output shaft of the turbine blade test section 15, and the other hydraulic dynamometer 20 is coupled to an output shaft of the power turbine 5 of the aircraft engine 1 to consume the output power of the aircraft engine 1.
In some embodiments, the control system 10 includes a data storage module, a control switching module, a communication module, and a safety module, where the data storage module is configured to store test system operation parameters sent by the data acquisition system 11, the control switching module is configured to switch a low-voltage electrical manual control mode and a computer remote control mode, the communication module is configured to communicate with the data acquisition system 11 and an upper computer, and the safety module is configured to monitor corresponding parameter values according to preset parameters to implement emergency protection.
Specifically, the control system 10 has a data management function and is implemented by a data storage module, and the data storage module has functions of data recording, data playback, parameter configuration and the like; the control system 10 has a local mode and a remote mode, and the control system 10 realizes the independent control function of low-voltage electric manual control and computer remote control through a control switching module; the control system 10 has the function of data communication, so that data transmission and data receiving of the data acquisition system 11 are facilitated; the control system 10 has a safety protection function, and implements emergency protection processing by configuring alarm limit values of corresponding parameters.
According to the rotating turbine blade cooling test method of the embodiment of the invention, the rotating turbine blade cooling test method comprises the following steps: extracting gas at the outlet of a gas generator 6 of the aero-engine 1 as main stream gas, and extracting air at the outlet of a gas compressor 2 of the aero-engine 1 as cooling air; respectively introducing main flow gas and cooling air into a main flow channel of a turbine blade test section 15 and a cooling channel inside a turbine blade, and performing a cooling effect test of the rotating turbine blade; and collecting the outlet airflow of the turbine blade test section 15, rapidly cooling the outlet airflow and discharging the outlet airflow into a silencing tower 18.
The technical advantages of the method for testing the cooling of a rotating turbine blade according to an embodiment of the present invention are the same as the technical advantages of the system for testing the cooling of a rotating turbine blade described above and will not be described herein again.
For a certain type of 300MW grade F-grade unit, the air flow at the inlet of the air compressor is 730kg/s, and the air flow at the inlet of the air compressor of a certain type of retired aircraft engine is 138 kg/s; the calculation results of the air flow and the main flow gas flow of the 1/4 modeling test turbine consisting of the 1-stage stationary blade and the 1-stage movable blade in the cooling effect test are listed in the following table; the air flow at the outlet of the compressor of the retired aircraft engine extracted by the cooling effect test of the rotating turbine blade accounts for about 5.47% of the air flow at the outlet of the compressor, and the safe operation of the gas turbine of the power station cannot be influenced.
The invention saves the equipment purchase and engineering cost of 8000-; if the industrial power consumption is calculated according to the power consumption cost of 0.9 yuan/kwh, the method provided by the invention can save 201600-.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, but are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be construed as limiting the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be interconnected within two elements or in a relationship where two elements interact with each other unless otherwise specifically limited. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature "under," "beneath," and "under" a second feature may be directly under or obliquely under the second feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described, it is understood that the above embodiments are illustrative and not to be construed as limiting the present invention and that many changes, modifications, substitutions and alterations can be made in the above embodiments by one of ordinary skill in the art without departing from the scope of the present invention.
Claims (11)
1. A rotating turbine blade cooling test system, comprising:
a rotating turbine blade cooling test apparatus;
an aircraft engine comprising a gas generator for providing a main stream of combustion gas to the rotary turbine blade cooling test apparatus and a compressor for providing cooling air to the rotary turbine blade cooling test apparatus;
the cooling air source device is connected with the rotary turbine blade cooling test device and is used for controlling the flow and pressure of cooling air entering the rotary turbine blade cooling test device;
the test cooling water device is connected with the rotary turbine blade cooling test device and is used for cooling an inlet and an outlet of the rotary turbine blade cooling test device;
the control system is respectively connected with the rotating turbine blade cooling effect test device, the cooling air source device and the test cooling water device and is used for controlling the output quantities of the main flow gas, the cooling air and the cooling water; and
the data acquisition system is electrically connected with the control system and is used for acquiring the running parameters of the test system and sending the running parameters to the control system.
2. The system of claim 1, wherein the rotary turbine blade cooling test device comprises a mainstream gas inlet valve, a turbine blade test section, a spray section and a silencer tower in sequence, the mainstream gas inlet valve is used for controlling the mainstream gas flow entering the turbine blade test section, the spray section and the silencer tower are connected in sequence, the spray section is used for rapidly cooling the mainstream gas, and the silencer tower is used for eliminating noise.
3. The system of claim 2, wherein the cooling air supply means includes a cooling air inlet valve and a cooling air regulating valve, the cooling air inlet valve being connected to the compressor, the cooling air regulating valve being connected to the turbine blade test section, the cooling air inlet valve and the cooling air regulating valve being configured to control the flow and pressure of cooling air entering the turbine blade test section.
4. The system of claim 2, wherein the cooling water supply device comprises a cooling tower, a water inlet pipe, a water supply pipe and a water outlet pipe, the cooling tower is connected with the outlet of the gas generator and the spray section through the water inlet pipe, the cooling tower is connected with the inlet and the outlet of the test turbine section through the water outlet pipe, and the water supply pipe is connected with the cooling tower.
5. The system of claim 2, wherein the turbine blade test section comprises a test turbine cylinder assembly, a turbine assembly, an inlet measurement section, an outlet measurement section, and an exhaust volute, the exhaust volute is connected to the test turbine cylinder and the spray section, and the exhaust volute is configured to collect an outlet flow of the turbine assembly.
6. The system for testing the cooling effectiveness of rotating turbine blades for aircraft engine air supply of claim 5, wherein said turbine assembly has a modeling ratio of 1/4 to 1/3.
7. The system of claim 5, wherein the turbine blade test section further comprises a hydraulic clearance adjustment device for adjusting the clearance between the turbine blade and the test turbine cylinder assembly.
8. The system of claim 5 for testing the cooling effectiveness of rotating turbine blades used to supply air to an aircraft engine, it is characterized in that the data acquisition system comprises a pressure acquisition device, a temperature acquisition device, a flow acquisition device, a transmission system acquisition device, a dynamic stress acquisition device and a vibration acquisition device, the pressure acquisition device acquires the pressure of the main flow gas inlet pipeline, the outlet pressure of the turbine assembly and the pressure of the cooling air, the temperature acquisition module acquires the temperature of the main flow gas and the cooling air, the flow acquisition device acquires the flow of the main flow gas and the cooling air, the transmission acquisition device acquires the rotating speed, torque and power data of the turbine assembly, the dynamic stress acquisition device acquires the dynamic stress of the turbine blade, and the vibration acquisition device acquires the vibration data of the casing.
9. The system for testing the cooling effect of the rotating turbine blades of an aircraft engine supply air of claim 8, wherein the transmission acquisition device comprises a hydraulic dynamometer, an output shaft of the turbine blade test section is connected with the hydraulic dynamometer, and the hydraulic dynamometer is used for measuring the shaft power of the turbine assembly and controlling the output rotating speed of the turbine assembly.
10. The system for testing the cooling effect of the rotary turbine blade supplied with air by the aircraft engine according to claim 1, wherein the control system comprises a data storage module, a control switching module, a communication module and a safety module, the data storage module is used for storing the test system operation parameters sent by the data acquisition system, the control switching module is used for switching a low-voltage electric manual control mode and a computer remote control mode, the communication module is used for communicating with the data acquisition system and an upper computer, and the safety module is used for monitoring corresponding parameter values according to preset parameters to realize emergency protection.
11. A method for testing the cooling of a rotating turbine blade, comprising the steps of:
extracting gas at the outlet of a gas generator of the aero-engine as main flow gas, and extracting air at the outlet of a compressor of the aero-engine as cooling air;
respectively introducing main flow gas and cooling air into a main flow channel of a turbine blade test section and a cooling channel inside a turbine blade, and performing a rotating turbine blade cooling effect test;
and collecting outlet airflow of the turbine blade test section, rapidly cooling the outlet airflow and discharging the outlet airflow into a silencing tower.
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