CN110261433B - Modeling experiment device for internal heat transfer of movable blade of aviation gas turbine - Google Patents
Modeling experiment device for internal heat transfer of movable blade of aviation gas turbine Download PDFInfo
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- 238000002474 experimental method Methods 0.000 title claims abstract description 68
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Abstract
The invention discloses a modeling experiment device for internal heat transfer of an aviation gas turbine movable blade, which comprises an experiment bench, a rotating shaft, a pressurizing cabin, a motor, a wireless transmission module, an experiment section and a test assembly, wherein the experiment section and the test assembly are arranged in the pressurizing cabin; the pressurizing cabin is connected to the rotating shaft and can rotate along with the rotating shaft; the experiment section comprises a cooling channel, the cooling channel is communicated with an external air supply device, and the test assembly is used for acquiring test data of the experiment section; the wireless transmission module is connected to the test assembly and used for controlling the experiment test assembly and transmitting test data. The modeling experiment device obtains the heat transfer performance data of the inner cooling channel wall surface of the experiment section through a visual measurement means under the condition of meeting the internal cooling rotation characteristic criterion number of the aviation gas turbine movable blade, and can provide important basic data for the fine design of the aviation gas turbine movable blade.
Description
Technical Field
The invention belongs to the technical field of measuring devices, and particularly relates to a modeling experiment device for internal heat transfer of an aviation gas turbine movable blade.
Background
The cooling of the turbine blades has a significant effect on the efficiency and thrust of gas turbines and aircraft engines. In the gas turbine and the aircraft engine which are put into operation at present, the temperature of gas at the inlet of the turbine is far higher than the allowable temperature of high-temperature alloy of the blade, so that the blade needs to be cooled to ensure the safe and stable operation of the blade. Internal cooling is one of the important ways to reduce the temperature of the turbine blades, and cooler cooling air flows through serpentine channels inside the hollow blades to carry heat away in a convective heat transfer. The working blades of the turbine are in a high-speed rotation state, and the centrifugal force and the rotary buoyancy caused by the rotation have very important influence on the internal heat transfer of the blades.
However, under real high-speed and high-temperature environments, measuring the heat transfer characteristics inside the moving blade has technical difficulties that are difficult to overcome, and therefore, basic experiments for accumulating design data are performed at normal temperature in a modeling manner based on similar theories. The three modeling criterion numbers selected by the modeling experiment include Reynolds number (Re), rotation number (Ro), and buoyancy coefficient (Bo), which are defined as follows:
u is the fluid velocity, DH is the hydraulic diameter of the channel, upsilon is the hydrodynamic viscosity coefficient, omega is the rotating speed, rho is the fluid density, and R is the rotating radius. The three modeling criterion numbers are similar to the turbine movable blades under the real condition, namely the similarity of the heat transfer characteristics under the rotating condition is ensured.
Existing modeling laboratory devices typically include configurations using rotating arms and pressurized chambers and configurations using rotating disks. By using the structure of the rotating arm and the pressurizing chamber, the kinetic viscosity coefficient of the air is reduced after pressurization, and a higher Reynolds number (Re) can be achieved at a lower airflow flow speed. When the fluid speed is low, the modeling criterion numbers (Re, Ro and Bo) of the real working condition can be reached through relatively low rotating speed. The device is favorable to improving the security, saves experimental system cost, but is difficult to realize visual measurement, can't provide the heat transfer coefficient distribution on surface, and measured data is drawn forth by the electrical slip ring in addition, and the slip ring is serious after long-term the use, and data transmission is unstable, and probably mutual interference when transmitting analog signal.
The measuring device is mounted on a rotating disk using a rotating disk structure. The structure can adopt visual measurement means (such as temperature-sensitive liquid crystal, thermal infrared imager and the like) to measure the convection heat transfer characteristic of the cold channel in the turbine movable blade so as to provide detailed heat transfer coefficient distribution, but the measurement range in a single experiment is greatly limited; if the heat transfer characteristics of the whole internal cooling channel are measured, multiple experiments are needed, and the time cost is high; in order to meet the requirement of visual measurement, the experimental section is made of transparent materials, generally has low strength and cannot pressurize air.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a modeling experiment device for internal heat transfer of an aviation gas turbine movable blade. The technical problem to be solved by the invention is realized by the following technical scheme:
the invention provides a modeling experiment device for internal heat transfer of an aviation gas turbine movable blade, which comprises an experiment bench, a rotating shaft, a pressurizing cabin, a motor, a wireless transmission module, an experiment section and a test assembly, wherein the experiment section and the test assembly are arranged in the pressurizing cabin,
the rotating shaft is vertically arranged on the experiment bench and is connected to the motor;
the compression chamber is connected to the rotating shaft and can rotate along with the rotating shaft;
the experimental section comprises a cooling channel, the cooling channel is communicated with an external air supply device, and the test assembly is used for acquiring test data of the experimental section;
the wireless transmission module is connected to the test assembly and used for controlling the test assembly and transmitting the test data.
In one embodiment of the invention, the compression chamber comprises two compression chambers and a connecting plate connecting the two compression chambers;
the connecting plate is fixedly mounted on the rotating shaft so that the two pressurizing compartments are symmetrical about the rotating shaft and can rotate with the rotating shaft.
In one embodiment of the invention, the pressurizing chamber comprises a chamber body and a chamber cover, wherein a sealing ring installation groove is arranged on the combining surface of the chamber body and the chamber cover along the circumferential direction.
In one embodiment of the invention, the rotating shaft is a hollow shaft, an air inlet hose and an air outlet hose are arranged in an inner cavity of the rotating shaft, and an air inlet joint and an air outlet joint are respectively arranged at two ends of the rotating shaft;
the air inlet hose is connected with the air inlet joint, and the exhaust hose is connected with the exhaust joint.
In one embodiment of the present invention, two through holes are opened on the side wall of the rotating shaft, and the air inlet hose passes through one of the two through holes to communicate with the pressurizing chamber; the exhaust hose passes through one of the two through holes to be communicated with the experimental section.
In one embodiment of the invention, the experimental section comprises an air inlet opening to the interior of the pressurizing chamber and an air outlet opening connected to the exhaust hose.
In one embodiment of the invention, the experimental section is made of a transparent material.
In one embodiment of the invention, the rotating shaft is sleeved with an electric slip ring, wherein,
the outer ring of the electric slip ring is connected to an external power supply;
the inner ring of the electrical slip ring is fixed to the rotating shaft and is connected to the test assembly through a cable.
In an embodiment of the invention, the testing assembly comprises a temperature acquisition module, a pressure acquisition module and an image acquisition module which are respectively connected to the wireless transmission module, and the temperature acquisition module, the pressure acquisition module and the image acquisition module are all arranged on the inner wall of the pressurizing cabin so as to respectively acquire the temperature, the pressure and the image information of the experimental section.
In one embodiment of the present invention, the experiment bench comprises a base and a mounting beam fixed on the base, wherein a first end of the rotating shaft is rotatably mounted on the base, and the other end is rotatably mounted on the mounting beam.
Compared with the prior art, the invention has the beneficial effects that:
1. the experimental section is made of transparent materials, and the modeling experimental device obtains the heat transfer performance data of the wall surface of the internal cooling channel through a visual measurement means under the condition of meeting the internal cooling rotation characteristic criterion number of the aviation gas turbine movable blade, so that important basic data can be provided for the fine design of the aviation gas turbine movable blade.
2. The wireless transmission module is arranged, the measurement data can be transmitted out by a wireless signal or stored in the memory card, the experimental process can be monitored on line, and the instability caused by the electric slip ring when the measurement data is led out by the electric slip ring and the mutual interference during the transmission of analog signals are reduced.
3. The cooling channel of the experimental section of the invention has relatively small size, so that the heat transfer data in the whole channel can be obtained through single measurement, and the time cost is saved.
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Drawings
FIG. 1 is a schematic structural diagram of a modeling experiment device for internal heat transfer of an aircraft gas turbine bucket according to an embodiment of the invention;
FIG. 2 is a schematic view of the portion of FIG. 1 showing the compression chamber;
FIG. 3 is a schematic structural diagram of an experimental section provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of the components and connections of a test assembly according to an embodiment of the present invention;
description of reference numerals:
1-experiment bench; 2-a rotating shaft; 3-a pressurized cabin; 31-a pressurized chamber; 311-a cabin body; 312-a hatch; 313-a seal ring mounting groove; 32-a connecting plate; 4-experimental section; 41-cooling channels; 42-an air inlet; 43-air outlet; 5-an air inlet hose; 6-an exhaust hose; 7-an air inlet joint; 8-an exhaust joint; 9-an electrical slip ring; 10-a wireless transmission module; 11-a temperature acquisition module; 12-a pressure acquisition module; 13-an image acquisition module; 14-a base; 15-mounting a cross beam; 16-a threaded hole; 17-pipe joint.
Detailed Description
In order to further illustrate the technical means and effects of the present invention adopted to achieve the predetermined purpose, the following detailed description is made on a modeling experiment apparatus for internal heat transfer of an aircraft gas turbine blade according to the present invention with reference to the accompanying drawings and the detailed description.
The foregoing and other technical matters, features and effects of the present invention will be apparent from the following detailed description of the embodiments, which is to be read in connection with the accompanying drawings. The technical means and effects of the present invention adopted to achieve the predetermined purpose can be more deeply and specifically understood through the description of the specific embodiments, however, the attached drawings are provided for reference and description only and are not used for limiting the technical scheme of the present invention.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that an article or device that comprises a list of elements does not include only those elements but may include other elements not expressly listed. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic structural diagram of a modeling experiment apparatus for internal heat transfer of an aircraft gas turbine bucket according to an embodiment of the present invention, and fig. 2 is a schematic partial structural diagram of fig. 1 showing a pressure chamber. The modeling experiment device comprises an experiment bench 1, a rotating shaft 2, a pressurizing chamber 3, a motor (not shown in the drawing), a wireless transmission module (not shown in the drawing), an experiment section 4 and a test component, wherein the experiment section 4 and the test component are arranged inside the pressurizing chamber 3.
Specifically, experiment rack 1 is formed by the steel pipe welding of high strength, including four landing legs and by the table surface that four landing legs supported, wherein, four landing legs all are fixed to the level subaerial, and rotation axis 2 and pressurized cabin 3 all carry on table surface is last, and experiment rack 1 is used for supporting and high-speed rotatory rotation axis 2 and pressurized cabin 3 when stabilizing the experiment. Rotation axis 2 vertical installation is on experiment rack 1 to be connected to the motor, and the motor provides power for rotation axis 2 for 2 axial rotations of rotation axis.
In the present embodiment, the experiment bench 1 comprises a base 14 and a mounting beam 15 fixed on the base 14, wherein a first end of the rotation shaft 2 is rotatably mounted on the base 14, and the other end is rotatably mounted on the mounting beam 15 to ensure the stability of the rotation shaft 2 during rotation.
With continued reference to fig. 1, the pressurized compartment 3 is connected to the rotating shaft 2 and is rotatable with the rotating shaft 2. The pressurizing chamber 3 of the present embodiment includes two pressurizing chambers 31 and a connecting plate 32 connecting the two pressurizing chambers 31; the connecting plate 32 is fixedly mounted on the rotating shaft 2 such that the two pressurizing chambers 31 are symmetrical with respect to the rotating shaft 2 and can rotate with the rotating shaft 2. In addition, the connecting plate 32 and the four walls of the two pressurizing chambers 31 are made of high-strength steel plates, and the connecting plate 32 and the two pressurizing chambers 31 may be directly welded by steel plates, and it is necessary to ensure the sealing property of the pressurizing chambers 31 so as to withstand the gas pressure inside the pressurizing chambers 31 during the experiment.
Specifically, the connecting plate 32 is formed with a through hole in the middle thereof, penetrates and is fixed to the rotating shaft 2, and the two pressurizing chambers 31 are symmetrical with respect to the rotating shaft 2 to maintain dynamic balance when rotating together with the rotating shaft 2. During the simulation, only one pressurizing chamber 31 was operated, and the other was used only to maintain dynamic balance.
Further, the pressurizing chamber 31 includes a chamber body 311 and a cover 312, wherein a joint surface between the chamber body 311 and the cover 312 is provided with a seal ring mounting groove 313 along a circumferential direction. A sealing ring is arranged in the sealing ring mounting groove 313 to ensure the sealing performance of the closed part of the cabin 311 and the cabin cover 312.
The rotating shaft 2 of the embodiment is a hollow shaft, an air inlet hose 5 and an air outlet hose 6 are axially accommodated in an inner cavity of the rotating shaft 2, and an air inlet joint 7 and an air outlet joint 8 are respectively arranged at two ends of the rotating shaft 2; the air inlet hose 5 is connected to an air inlet joint 7, and the air outlet hose 6 is connected to an air outlet joint 8. Two through holes are arranged on the side wall of the rotating shaft 2, and the air inlet hose 5 extends out of one of the two through holes and is communicated with the pressurizing chamber 31; an exhaust hose 6 extends from one of the two through holes and communicates with the test section 4.
The air inlet connector 7 is connected to an external air supply device for supplying experiment air to the pressurizing chamber 31 and the experiment section 4 positioned in the pressurizing chamber 31 through the air inlet hose 5 so as to increase the pressure of the air in the pressurizing chamber 31 and the experiment section 4. The test gas circulating in the pressurizing chamber 31 and the test section 4 is directly discharged to the atmosphere through the exhaust port 8. In the present embodiment, a screw hole 16 is provided on a side wall of the pressurizing chamber 31 facing the rotary shaft 2, the screw hole 16 is used for mounting a pipe joint 17, and the air inlet hose 5 and the air outlet hose 6 are connected to the pressurizing chamber 31 or the experimental section 4 through the pipe joint 17 mounted in the screw hole 16.
Referring to fig. 3, fig. 3 is a schematic structural diagram of an experimental section according to an embodiment of the present invention. The experimental section 4 of the present embodiment comprises a cooling channel 41, a gas inlet 42 and a gas outlet 43, wherein the cooling channel 41 is in communication with the inner cavity of the pressurizing chamber 31, i.e. gas can be conducted, and the testing assembly is capable of acquiring test data of the experimental section 4. In the present embodiment, the hydraulic diameter of the cooling channel 41 is about 40 mm. Because the kinematic viscosity coefficient of the air is reduced after the air is pressurized, the Reynolds number Re required by a modeling experiment can be met at a lower gas flow rate; the reduction in gas flow rate, defined by the number of revolutions, ensures that the desired number of revolutions Ro is achieved even with smaller channel sizes, and therefore the cooling channel 41 of the present embodiment can have a smaller hydraulic diameter. Specifically, the air inlet 41 opens to the inside of the pressurizing chamber 31, and the air outlet 43 is connected to the exhaust hose 6 through the pipe joint 17 fitted in the threaded hole 16. That is, in the course of the simulation experiment, the experimental gas provided by the external gas supply device enters the sealed pressurizing chamber 31 through the gas inlet hose 5, and since the pressurizing chamber 31 is communicated with the cooling channel 41, the experimental gas simultaneously enters the cooling channel 41, and then since the gas outlet hose 6 is connected to the gas outlet 43, the experimental gas in the pressurizing chamber 31 is discharged through the gas outlet 43 and the gas outlet hose 6, and the gas circulation of the experimental gas in the pressurizing chamber 31 and the cooling channel 41 is completed. Note that a regulating valve is provided at the exhaust joint 8 to regulate the flow rate of the test gas, thereby controlling the gas pressure in the pressurizing chamber 31 and the cooling passage 41. The wireless transmission module is connected to the test assembly and used for controlling the test assembly and transmitting test data.
Further, referring to fig. 4, fig. 4 is a schematic composition diagram of a testing assembly according to an embodiment of the present invention. The test assembly comprises a temperature acquisition module 11, a pressure acquisition module 12 and an image acquisition module 13 which are respectively connected to the wireless transmission module 10, wherein the temperature acquisition module 11, the pressure acquisition module 12 and the image acquisition module 13 are all arranged on the inner wall of the pressurizing cabin 31 so as to respectively acquire the temperature, the pressure and the image information of the experimental section 4.
In this embodiment, the temperature acquisition module 11 is a thermocouple, the pressure acquisition module 12 is a pressure sensor, and the image acquisition module 13 is a camera. It should be noted that, because the experiment section material and the test component generally cannot bear a large pressure, the whole of the experiment section material and the test component is placed in the pressurizing chamber 31 in the embodiment, so that the internal and external pressures of the experiment section and the test component are balanced, and the safe and stable operation of the experiment section and the test component is ensured.
Because the experiment section of this embodiment is small in size, therefore, the heat transfer data in the whole channel can be obtained through single measurement, namely the temperature, the pressure and the image information of the whole channel can be obtained through the single temperature acquisition module 11, the single pressure acquisition module 12 and the single image acquisition module 13, so that the time cost of the experiment is saved.
The wireless transmission module of the present embodiment is mounted outside the pressurizing chamber 31 so as to control the test assembly and transmit experimental data. The experimental data are transmitted out in a digital signal mode through the wireless transmission module. The wireless transmission modules all rotate together with the pressurizing chamber 31.
In the present embodiment, in order to meet the requirement of visual measurement (i.e. obtaining the heat transfer coefficient distribution on the whole surface of the inner wall of the experimental section by the picture taken by the camera), the cooling channel 41 of the experimental section 4 is made of transparent material, and the color distribution of the side wall of the cooling channel 41 can be taken by the camera, and generally, the color distribution of the side wall of the cooling channel 41 can reflect the temperature distribution of the side wall of the cooling channel 41.
Further, an electric slip ring 9 is sleeved on the rotating shaft 2, wherein the outer ring of the electric slip ring 9 is connected to an external power supply; the inner ring is fixed on the rotating shaft 2 and is connected to the test assembly and the wireless transmission module through cables. The electrical slip ring 9 of this embodiment is only used to power the test assembly and the wireless transmission module. In particular, the cables that supply the test components inside the pressurized compartment 31 need to be sealed by means of a glan head.
In the actual modeling experiment process, firstly, the motor is turned on, the rotating shaft 2 drives the pressurizing chamber 3 to rotate at a high speed, the experimental gas provided by the external gas supply device enters the sealed pressurizing chamber 31 through the gas inlet hose 5, the experimental gas simultaneously enters the cooling channel 41 because the pressurizing chamber 31 is communicated with the cooling channel 41, and then the exhaust hose 6 is connected to the gas outlet 43, so that the experimental gas in the pressurizing chamber 31 is exhausted through the gas outlet 43 and the exhaust hose 6, the gas circulation of the experimental gas in the pressurizing chamber 31 and the cooling channel 41 is completed, and the heat exchange is carried out with the wall surface of the cooling channel 41. Meanwhile, a regulating valve is provided at the exhaust joint 8 to control the flow rate of the test gas so that a predetermined gas pressure is reached in the pressurizing chamber 31. Subsequently, the air pressure in the pressurizing chamber 31 is measured by the pressure sensor to ensure that it is within the predetermined pressure range required for the test; measuring the temperature of the air inside the pressurizing chamber 31 by the thermocouple; the image of the wall surface of the experimental section is shot through the camera, the temperature distribution condition of the surface of the experimental section is obtained, the obtained measurement data is transmitted to the upper computer through the wireless transmission module for online monitoring and analysis, and finally, the heat transfer coefficient of the device can be calculated according to the temperature of the introduced air and the measured wall surface temperature. The embodiment is provided with the wireless transmission module, and the measured data can be transmitted out or stored in the memory card by a wireless signal, so that the experimental process can be monitored on line, and the instability caused by the electric slip ring when the measured data is led out by the electric slip ring and the mutual interference during the transmission of the analog signal are reduced.
As mentioned above, the three modeling criterion numbers selected by the modeling experiment include reynolds number (Re), rotation number (Ro), and buoyancy coefficient (Bo), which are defined as follows:
wherein U is the fluid velocity, DHIs the hydraulic diameter of the channel, upsilon is the hydrodynamic viscosity coefficient, omega is the rotating speed, upsilon is the fluid density, and R is the rotating radius. The three modeling criterion numbers are similar to the turbine movable blades under the real condition, namely the similarity of the heat transfer characteristics under the rotating condition is ensured.
By increasing the air pressure in the pressurizing chamber 31 and increasing the size of the cooling channel 41 appropriately (compared to the real blade), the reynolds number (5 × 10) required for the modeling experiment can be satisfied at a lower rotation speed4) And the rotation number (0.25) ensures that the shooting range of the camera can cover the whole experimentSegment 4, such that heat transfer data in the entire channel is obtained in a single experiment. Ratio of the radius of rotation of the experimental section 4 to its hydraulic diameter (R/D)H) About 40, which easily satisfies the buoyancy coefficient (0.5) required by the modeling experiment. At the moment, the 3 modeling criterion numbers all meet the requirements of the internal cooling modeling experiment of the aviation gas turbine movable blade.
The experimental section of this embodiment adopts transparent material to make, and the modeling experimental apparatus obtains its interior cold passageway wall heat transfer performance data through visual measurement means under the condition that satisfies aviation gas turbine movable vane internal cooling rotation characteristic criterion number, can provide important basic data for aviation gas turbine movable vane refined design. In addition, the cooling channel size of the experimental section of this embodiment is less relatively, consequently can obtain the heat transfer data in the whole passageway through single measurement, save time cost, and this modularization experimental apparatus area is less, and is lower to the experiment place requirement.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (10)
1. A modeling experiment device for internal heat transfer of an aviation gas turbine movable blade is characterized by comprising an experiment bench (1), a rotating shaft (2), a pressurizing cabin (3), a motor, a wireless transmission module (10), an experiment section (4) and a test component, wherein the experiment section and the test component are arranged in the pressurizing cabin (3),
the rotating shaft (2) is vertically arranged on the experiment bench (1) and is connected to the motor;
the compression chamber (3) is connected to the rotating shaft (2) and can rotate with the rotating shaft (2);
the experimental section (4) comprises a cooling channel (41), the cooling channel (41) is communicated with an external air supply device, and the testing component is used for acquiring testing data of the experimental section (4);
the wireless transmission module is connected to the test assembly and used for controlling the test assembly and transmitting the test data.
2. The modeling experiment device for internal heat transfer of aviation gas turbine blade according to claim 1, characterized in that the compression chamber (3) comprises two compression chambers (31) and a connecting plate (32) connecting the two compression chambers (31);
the connecting plate (32) is fixedly mounted on the rotating shaft (2) such that the two pressurizing chambers (31) are symmetrical about the rotating shaft (2) and can rotate with the rotating shaft (2).
3. The modeling experiment device for internal heat transfer of the aviation gas turbine blade as claimed in claim 2, wherein the pressurizing chamber (31) comprises a chamber body (311) and a chamber cover (312), and a sealing ring installation groove (313) is arranged on the joint surface of the chamber body (311) and the chamber cover (312) along the circumferential direction.
4. The modeling experiment device for internal heat transfer of the aviation gas turbine movable blades according to claim 2, wherein the rotating shaft (2) is a hollow shaft, an air inlet hose (5) and an air outlet hose (6) are arranged in an inner cavity of the rotating shaft, and an air inlet joint (7) and an air outlet joint (8) are respectively arranged at two ends of the rotating shaft (2);
the air inlet hose (5) is connected with the air inlet joint (7), and the air outlet hose (6) is connected with the air outlet joint (8).
5. The modeling experiment device for internal heat transfer of the aviation gas turbine blade according to claim 4, wherein two through holes are formed in the side wall of the rotating shaft (2), and the air inlet hose (5) passes through one of the two through holes to be communicated with the pressurizing chamber (31); the exhaust hose (6) passes through one of the two through holes to be communicated with the experimental section (4).
6. Modelling test device of aircraft gas turbine blade internal heat transfer according to claim 5, characterized in that said test section (4) comprises an air inlet (42) and an air outlet (43), said air inlet (42) opening into the interior of said pressurized compartment (31), said air outlet (43) being connected to said exhaust hose (6).
7. The modeling experiment device for internal heat transfer of the aviation gas turbine blade is characterized in that the experiment section (4) is made of transparent materials.
8. The modeling experiment device for internal heat transfer of the aviation gas turbine blade according to the claim 1, characterized in that the rotating shaft (2) is sleeved with an electric slip ring (9), wherein,
the outer ring of the electric slip ring (9) is connected to an external power supply;
the inner ring of the electric slip ring (9) is fixed to the rotating shaft (2) and is connected to the test assembly through a cable.
9. The modeling experiment device for internal heat transfer of the aviation gas turbine movable blade is characterized in that the testing assembly comprises a temperature acquisition module (11), a pressure acquisition module (12) and an image acquisition module (13) which are respectively connected to the wireless transmission module (10), and the temperature acquisition module (11), the pressure acquisition module (12) and the image acquisition module (13) are all arranged on the inner wall of the pressurizing cabin (31) so as to respectively acquire the temperature, the pressure and the image information of the experiment section (4).
10. Modelling test device for internal heat transfer of aircraft gas turbine blades according to any of claims 1 to 9, characterised in that the test bench (1) comprises a base (14) and a mounting cross-beam (15) fixed to the base (14), wherein the rotating shaft (2) is rotatably mounted on the base (14) at a first end and on the mounting cross-beam (15) at the other end.
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| CN112595748A (en) * | 2020-12-11 | 2021-04-02 | 西安交通大学 | Rotary experiment section for simulating cooling structure of gas turbine blade |
| CN112697445B (en) * | 2020-12-11 | 2021-10-22 | 西安交通大学 | Turbine experimental device capable of rapidly replacing test and measuring blade cascade |
| CN113588234B (en) * | 2021-07-14 | 2023-03-24 | 北京航空航天大学 | Comprehensive cold effect testing method and system for rotation of turbine movable blades |
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