CN113340934A - Device and method for simulating hot spot temperature field of guide blade - Google Patents
Device and method for simulating hot spot temperature field of guide blade Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 239000007789 gas Substances 0.000 claims abstract description 109
- 238000005485 electric heating Methods 0.000 claims abstract description 77
- 239000002737 fuel gas Substances 0.000 claims abstract description 16
- 238000004088 simulation Methods 0.000 claims abstract description 13
- 239000002131 composite material Substances 0.000 claims description 15
- 239000012530 fluid Substances 0.000 claims description 8
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000013508 migration Methods 0.000 abstract description 7
- 230000005012 migration Effects 0.000 abstract description 7
- 230000002776 aggregation Effects 0.000 abstract description 4
- 238000004220 aggregation Methods 0.000 abstract description 4
- 238000001816 cooling Methods 0.000 description 20
- 238000010586 diagram Methods 0.000 description 9
- 238000002474 experimental method Methods 0.000 description 7
- 239000003350 kerosene Substances 0.000 description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 5
- 230000004907 flux Effects 0.000 description 5
- 239000001301 oxygen Substances 0.000 description 5
- 229910052760 oxygen Inorganic materials 0.000 description 5
- 239000012159 carrier gas Substances 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 238000009826 distribution Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 238000002156 mixing Methods 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- 238000013021 overheating Methods 0.000 description 3
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 3
- 229910010271 silicon carbide Inorganic materials 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000004590 computer program Methods 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
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- 230000033001 locomotion Effects 0.000 description 2
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- 230000008569 process Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 241001155433 Centrarchus macropterus Species 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000001514 detection method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
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- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
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Abstract
A simulation device and method of a hot spot temperature field of a guide vane are disclosed, wherein the device comprises: the high-temperature fuel gas generating assembly is used for generating high-temperature fuel gas; the electric heating airflow generating assembly is used for generating electric heating airflow; one end of the high-temperature gas channel is communicated with the high-temperature gas generating device, and the other end of the high-temperature gas channel is aligned to the guide vane; one end of the electric heating airflow channel is communicated with the electric heating airflow generating device, and the other end of the electric heating airflow channel is aligned to the guide blade; the electric heating airflow channel is arranged around the high-temperature gas channel; the other ends of the high-temperature gas channel and the electric heating airflow channel are aligned; the working blade is arranged on one side of the guide blade, which is far away from the high-temperature gas channel; the working blade turbine disc is provided with working blades; and the rotating assembly is connected with the center of the working blade turbine disc and is used for rotating the working blade turbine disc. The hot spot ratio of the hot spots is simulated and controlled in the mode, and a real basis is provided for the migration and aggregation rule of the hot spots on the blade in the turbine flow passage.
Description
Technical Field
The invention relates to the technical field of testing of thermal barrier coatings of turbine blades of aeroengines, in particular to a device and a method for simulating a hot spot temperature field of a guide blade.
Background
The development of an aircraft engine is developed towards higher turbine front temperature and a more compact combustion chamber structure, so that the problems of complex flow rule at the inlet of a turbine, uneven distribution of flow field parameters and the like are caused, the local highest temperature can reach about twice of the lowest temperature, and a gas flow mass with an obvious high-temperature core area is formed at the inlet of the turbine, namely the phenomenon of 'hot spots'. As hot streaks enter the turbine stage, the uncertainty in the turbine stage is exacerbated and additional secondary flows are created. Due to the relative movement between the movable and static blade rows, cold and hot air flows generate migration in the movable blade rows, hot air flow is often accumulated on the pressure surface of the movable blade to generate a local overheating area, so that the movable blade bears huge heat load, the influence can also extend to the second-stage static blade, the thermal stress of the blade body of the guide blade is increased, and the local ablation of the blade can be caused in severe cases. However, in the prior art, a scheme capable of accurately simulating a hot spot temperature field is not provided.
Therefore, how to simulate the hot spot temperature field of the guide blade by adopting an economic and effective method is a practical engineering problem directly faced in research work in the field, so that the development of a service environment loading device capable of truly simulating the hot spot temperature field is very important, an important experimental platform is provided for hot spot migration in a turbine flow passage and an aggregation rule on the blade, and an important basis is provided for the design and optimization of an efficient cooling scheme.
Disclosure of Invention
Objects of the invention
The invention aims to provide a simulation device and a method capable of accurately simulating a hot spot temperature field of a guide vane.
(II) technical scheme
To solve the above problems, a first aspect of the present invention provides a device for simulating a hot spot temperature field of a guide vane, including: the high-temperature fuel gas generating assembly is used for generating high-temperature fuel gas; the electric heating airflow generating assembly is used for generating electric heating airflow; one end of the high-temperature gas channel is communicated with the high-temperature gas generating device, and the other end of the high-temperature gas channel is aligned to the guide vane; one end of the electric heating airflow channel is communicated with the electric heating airflow generating device, and the other end of the electric heating airflow channel is aligned to the guide blade; the electric heating airflow channel is arranged around the high-temperature fuel gas channel; the guide vane is aligned with the other ends of the high-temperature gas channel and the electric heating airflow channel; the working blade is arranged on one side of the guide blade, which is far away from the high-temperature gas channel; a working blade turbine disk on which the working blades are disposed; a rotating assembly connected to the center of the working blade turbine disk for rotating the working blade turbine disk.
Optionally, the electric heating airflow channels are arranged in a plurality, and the electric heating airflow channels are distributed around the high-temperature gas channel at intervals and uniformly in the circumferential direction.
Optionally, the high-temperature gas channel and the electric heating gas flow channel are arranged in parallel.
Optionally, the temperature ratio of the total temperature of the fluid in the center of the hot spot to the total temperature of the fluid around the hot spot is 1.3-1.7.
Optionally, the other ends of the high-temperature gas channel and the electric heating airflow channel are provided with high-temperature water-cooling butterfly valves for controlling the injection speeds of the high-temperature gas and the electric heating airflow.
Optionally, the device for simulating a hot spot temperature field of a guide vane further includes: and the gas loading assembly is communicated with the high-temperature gas generation assembly and the electric heating gas flow generation assembly and is used for providing gas for the high-temperature gas generation assembly and the electric heating gas flow generation assembly.
Optionally, the device for simulating a hot spot temperature field of a guide vane further includes: the temperature-resistant sleeve is sleeved outside the high-temperature gas channel and the electric heating airflow channel and used for fixing the electric heating airflow channel and uniformly distributing along the circumferential direction, so that the composite airflow formed by the terminal is more uniform.
Optionally, the high temperature gas channel and/or the electric heating air flow channel are arranged at a first preset angle with the guide vane.
A second aspect of the invention provides a method of simulating a guide vane hot spot temperature field using a die of the guide vane hot spot temperature field as provided in the first aspect of the inventionA device, comprising: setting a temperature range parameter of the high-temperature fuel gas, a temperature range of the electric heating air flow and a gas flow parameter based on a preset hot spot ratio; wherein the ratio of heat spots T1/T2The ratio of the total temperature of the fluid in the center of the hot spot to the total temperature of the fluid around the hot spot.
(III) advantageous effects
The technical scheme of the invention has the following beneficial technical effects:
according to the invention, the electric heating airflow and the high-temperature gas airflow form the composite airflow, so that the hot spot ratio of the guide blade is accurately adjusted by adjusting the flow and the temperature of the electric heating airflow and the high-temperature gas airflow, important experimental basis is provided for hot spot migration in a turbine runner and an aggregation rule on the guide blade, important basis is provided for design and optimization of an efficient cooling scheme, and the method is economical and effective.
Drawings
FIG. 1 is a schematic structural diagram of a simulation apparatus according to a first embodiment of the present invention;
FIG. 2 is a schematic side view of a high temperature gas channel and an electric heat gas flow channel of the simulation apparatus according to the first embodiment of the present invention;
FIG. 3 is a schematic side view of a simulation apparatus according to a first embodiment of the present invention;
FIG. 4 is a flow chart of a simulation method according to a second embodiment of the present invention;
FIG. 5 is a plurality of hot spot temperature field patterns of the high temperature core region at different temperatures for a turning vane according to a specific example of the second embodiment of the present invention;
FIG. 6 is a plurality of hot spot temperature field patterns of the high temperature core region at the same temperature for a guide vane of an embodiment of the second embodiment of the present invention;
fig. 7 is an infrared cloud of the hot spot pattern of a sample of a flat piece according to a second embodiment of the present invention.
Reference numerals:
1: a supersonic flame ejector; 2: an electric heater; 3: a high temperature gas channel; 4: an electrically heated airflow channel; 5: a high-temperature water-cooled butterfly valve; 6: a gas loading assembly; 7: a temperature-resistant sleeve;
10: a guide blade; 101: a guide vane turbine disk; 20: a working blade; 201: a working blade turbine disk; 30: a high-speed rotating power assembly; 40: a high-speed spindle; 50: a combustion chamber; 501: a quartz window; 60: an infrared thermal imager; 70: a high-speed CCD camera; 80: and fixing the base.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
In the drawings a schematic view of a layer structure according to an embodiment of the invention is shown. The figures are not drawn to scale, wherein certain details are exaggerated and possibly omitted for clarity. The shapes of various regions, layers, and relative sizes and positional relationships therebetween shown in the drawings are merely exemplary, and deviations may occur in practice due to manufacturing tolerances or technical limitations, and a person skilled in the art may additionally design regions/layers having different shapes, sizes, relative positions, as actually required.
It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
First embodiment
As shown in fig. 1 to 3, a first embodiment of the present invention provides a device for simulating a hot spot temperature field of a guide blade, including: the high-temperature fuel gas generating assembly is used for generating high-temperature fuel gas; the electric heating airflow generating assembly is used for generating electric heating airflow; one end of the high-temperature gas channel 3 is communicated with the high-temperature gas generating device, and the other end of the high-temperature gas channel is used for aligning to the guide vane; one end of the electric heating airflow channel 4 is communicated with the electric heating airflow generating device, and the other end of the electric heating airflow channel is aligned to the guide blade; the electric heating airflow channel 4 is arranged around the high-temperature gas channel 3, and the guide blade 10 is aligned with the high-temperature gas channel 3 and the other end of the electric heating airflow channel 4; the working blade 20 is arranged on one side of the guide blade 10 far away from the high-temperature gas channel 3; a working blade turbine disk 201, on which the working blades 20 are disposed; a rotating assembly 30 connected to the center of the working blade turbine disk 201 for rotating the working blade turbine disk 201. According to the embodiment, the electric heating airflow and the high-temperature gas airflow form the composite airflow, so that the hot spot ratio of the guide blade is accurately adjusted by adjusting the parameters of the electric heating airflow and the high-temperature gas airflow, important experimental basis is provided for hot spot migration in a turbine runner and an aggregation rule on the blade, important basis is provided for design and optimization of an efficient cooling scheme, and the method is economical and effective. Wherein, the high-temperature fuel gas generating assembly can comprise a supersonic flame ejector 1; the electrically heated airflow generating assembly may include an electric heater 2. The hot spot migration is caused by the relative motion between the moving and stationary blade rows, the cold and hot air flows generate migration in the moving blade rows, the hot air flow is often accumulated on the pressure surface of the moving blade to generate a local overheating area, so that the local overheating area bears huge heat load, and the influence can also extend to the moving and stationary blade of the next stage. The invention mainly uses infrared to shoot the temperature field of the guide blade 10, but the shooting is carried out under the composite system of a moving blade row and a static blade row, the moving blade rotates at high speed, the formed composite airflow can flow under the complex flow field environment, so that the flow channel between the surface of the moving blade and the moving blade at the same stage can form a high-temperature core area, namely a hot spot temperature field, and the composite airflow is in dynamic flow, so the shooting is mainly carried out on the guide blade 10, namely the static blade. The turbine blade comprises a guide blade and a working blade, and the hot spot temperature field of the guide blade is mainly simulated.
In an optional embodiment, the number of the electric heating airflow channels 4 is multiple, the electric heating airflow channels 4 are uniformly distributed around the high-temperature gas channel 3 at intervals, and the high-temperature gas channel 3 and the electric heating airflow channels 4 are arranged in parallel. The high-temperature airflow and the electric heating airflow form a composite annular airflow so as to load the service environment of the hot spot temperature field on the guide blade. Specifically, the hot spot ratio can be controlled by controlling the flow rate, temperature and distance from the guide vanes of the hot gas and electric heat gas flow, wherein the most important factor is controlling the temperature of the hot gas and electric heat gas flow. The gas channel is annular and comprises a high-temperature gas channel 3, an electric heating airflow channel 4, a high-temperature water-cooling butterfly valve 5 and a temperature-resistant sleeve 7, and the absolute length and the shape of the channels are kept consistent; a plurality of groups of hot gas flow channels are annularly distributed around the high-temperature gas channel 3, wherein after hot spots of the guide vanes are generated in the hot gas flow channels, the electric heater 2 is cut off, and cooling gas flow is introduced for cooling the specific hot spot positions of the guide vanes; the temperature-resistant sleeve 7 is fixedly connected with the plurality of groups of electric heating airflow channels 4 through bolts; and supporting structures are arranged below the gas channels. The temperature-resistant sleeve 7 is used for fixing the electric heating airflow channel 4 and is uniformly arranged around the gas channel along the circumferential direction, so that the composite airflow formed by high-temperature gas and electric heating airflow is more uniform and controllable.
In an alternative embodiment, the other ends of the high-temperature gas channel 3 and the electric heating airflow channel 4 are provided with high-temperature water-cooling butterfly valves 5 for controlling the injection speeds of the high-temperature gas and the electric heating airflow. The jet velocity of the high-temperature gas and the jet velocity of the electric heating air flow are consistent, the surfaces of the guide vanes are reached as far as possible, the loading of the hot spot ratio is better realized only at the same time, and the surface temperature field of the guide vanes can be more uniform. The high-temperature water-cooling butterfly valve 5 can be fixedly connected with the channel through a bolt, the adjusting angle of the butterfly rod is 0-90 ℃, and the inner cavity of the valve body is filled with circulating water for cooling, so that the high-temperature water-cooling butterfly valve is used for adjusting the air flow ratio of high-temperature gas air flow and hot air flow, and the spraying speeds of the high-temperature gas air flow and the hot air flow tend to be consistent.
In an optional embodiment, the device for simulating a hot spot temperature field of a guide vane further includes: and the gas loading assembly is communicated with the high-temperature gas generation assembly and the electric heating gas flow generation assembly and is used for providing gas for the high-temperature gas generation assembly and the electric heating gas flow generation assembly. The gas loading assembly comprises an air compressor 8, air compressed by the air compressor 8, and after the first part of air is input into the electric heating airflow generating assembly, the air compressed by the air compressor 8 is heated by the electric heating airflow generating assembly to form electric heating airflow which is introduced into the electric heating airflow channel 4; the second part is input into a water cooler, and the water cooler cools the air compressed by the air compressor 8 to form cooling airflow; the third part is input into a high-temperature gas generation assembly, is uniformly mixed with aviation kerosene and then is used for supporting combustion, and generates high-temperature gas flow. The other part of the compressed air is divided into small carrier gas and large carrier gas according to different purposes after being input, wherein the small carrier gas is used for ejecting high-temperature flame in the combustion chamber 50, and the large carrier gas is used for cooling the supersonic flame ejector 1 and the sleeve after the supersonic flame ejector 1 is flamed out. Specifically, after the cooling air flow is used for forming the high-temperature core area of the guide blades, the cooling air flux is increased at the hot spot center of one guide blade/group of guide blades, and the cooling air flux at the non-hot spot positions of the rest guide blades is reduced, so that the thermal efficiency of the turbine engine is improved.
In an alternative embodiment, the supersonic flame injectors 1 are arranged annularly and provided in plurality, with a support structure moving slide mounted on the lower part. The nozzle is an atomizing nozzle, and the diameter range of the atomizing nozzle is phi 5 mm-phi 65 mm; preferably the nozzle diameter size is one or more of 10mm, 16mm, 20mm, 25mm or 40 mm. The resulting hot spots were approximately circular in shape and had radii of about 40.0mm, 55.0mm, and 68.0mm, respectively, and the corresponding infrared clouds from the infrared thermal imager were A, B and C, respectively, of FIG. 7. The purpose of the supersonic flame ejector 1 is to vary the nozzle to guide vane distance to vary the hot spot temperature field.
In an alternative embodiment, the hot gas channel 3 and/or the electric heat gas flow channel 4 are disposed at a first predetermined angle with respect to the guide vane 10. The preset angle may be set to-45 deg. as desired.
In an optional embodiment, the device for simulating a hot spot temperature field of a guide vane further includes: gate, stationary base 80 and guide vane passages. The rotating assembly 30 includes a high speed spindle 40. The working blade turbine disk 201 is sleeved on the high-speed main shaft 40, and a plurality of groups of mortises are formed in the working blade turbine disk 201 in the circumferential direction and are in joggle joint with the plurality of groups of working blades 20; the guide vane channel corresponds to the channel position of the temperature-resistant sleeve 7, the gate and the working blade turbine disc 201 are arranged in parallel and are separated by a preset distance, and the fixed base is fixedly connected with the casing. The high speed main shaft is coaxial with the working blade turbine disk 201. Wherein the preset rotating speed is in a numerical range of 0r/min-30000 r/min.
In an optional embodiment, the device for simulating a hot spot temperature field of a guide vane further includes: a real-time feedback system. The real-time feedback system comprises an infrared thermal imager and a high-speed CCD camera which are both arranged at the quartz glass observation window; the infrared detector is FLIR GF309 type infrared detection equipment produced by the Flier company in America, a lens of the infrared detector is aligned to the guide blade component through a quartz glass observation window, and infrared image acquisition is carried out on the surface temperature gradient of the guide blade; the high-speed CCD camera is aligned to the guide vane through the quartz glass observation window, and real-time feedback is carried out on the hot spot shape and the position of the guide vane, so that the parameters of the simulation device of the hot spot temperature field of the guide vane can be adjusted as required. Wherein, the parameter of infrared thermal imager includes: emissivity, outside temperature, humidity, filter transmittance and photographing frequency. Setting the highest temperature of the muffle furnace according to the temperature range of the ejected preset high-temperature fuel gas, putting the guide vane sample into the muffle furnace, and calibrating the infrared thermal imager at the same temperature to obtain the emissivity of the guide vane.
Second embodiment
As shown in fig. 4, the present embodiment provides a method for simulating a guide vane hot spot temperature field, and a simulation apparatus using the guide vane hot spot temperature field according to the first embodiment of the present invention includes: setting parameters of high-temperature gas and electric heating airflow based on a preset hot spot ratio; wherein the hot spot ratio is the ratio of the temperature of the high-temperature fuel gas to the temperature of the electric heating airflow. Wherein the parameters include gas flow, temperature and distance from the guide vanes.
In one particular embodiment, S100: presetting the temperature range of high-temperature gas flow, and realizing the purpose by changing the mixing ratio of aviation kerosene and oxygen/air in the supersonic flame ejector 1, wherein the flow rate of the kerosene is 0-15L/h, and the flow rate of the oxygen/air is 0-800L/min; the preferred mixing range is 4-10L/h kerosene flow, and 500L/min oxygen/air flow 140-.
S200: the gas flow and the temperature range of the electric heating gas flow in the electric heater 2 are preset, wherein the gas flow is 0-400L/min, and the temperature range is 50-500 ℃.
S300: starting the experimental simulator to realize the hot spot ratio T1/T2Precise regulation and control.
S400: and the cooling air flow flux at the hot spot high-temperature core area of one guide blade/group of guide blades is increased, and the cooling air flow flux at the non-hot spot positions of the rest guide blades is reduced. Alternatively, the temperature range in which the composite gas stream is generated is, to some extent, directly related to the absolute position of the terminal end of the composite gas stream from the guide vanes. Optionally, the temperature of the cooling air flow in step S400 is in the range of 5 ℃ to 25 ℃ for targeted cooling of the hot spot high temperature core area generated in step S300, thereby eliminating the thermal load influence of the hot spot high temperature core area on the guide blade and specifically reducing the cooling air flux at the non-hot spot position.
In one embodiment, referring to fig. 6, the simulation apparatus is used to perform a loading experiment on different hot spot high-temperature core regions of the guide vane, that is, the temperature ratio of the 700-;
wherein, as shown in A diagram in FIG. 5, T is when the temperature of the high temperature core region of the hot spot is 1100 + -10 deg.C1/T21.51; as shown in B in FIG. 5, T when the temperature of the high temperature core region of the hot spot is 1200. + -. 10 deg.C1/T21.60; as shown in the C diagram in FIG. 5, T when the temperature of the high temperature core region of the hot spot is 1300 + -10 deg.C1/T2＝1.70。
Specifically, the temperature of the hot spot high-temperature core area is selected to be 1100 +/-10 ℃, and T is1/T2When the ratio is 1.51, the detailed steps for obtaining the hot spot temperature ratio under the hot spot high-temperature core area are as follows:
the first step, the selection and calibration of the guide vane material: the material is a novel silicon carbide material, the whole silicon carbide guide blade is put into a tubular furnace, and the temperature is raised to 1100 ℃ along with a muffle furnace; the two measurements are provided with S-type thermocouples A and B which are calibrated and traceable to national standard; the method comprises the steps of keeping the temperature of A, B at 1100 ℃ for 10 minutes by adjusting the position of a guide vane, stabilizing the temperature for 10 minutes, aligning the center of the vane with an infrared thermometer, adjusting the emissivity to make the measured temperature be 1100 ℃, recording the emissivity and repeatedly averaging for multiple times, finally obtaining the novel silicon carbide material with the emissivity of 0.84, and adding an external optical device with the transmissivity tau being 0.84 in front of the lens of an infrared thermal imager.
Secondly, installing and aligning the guide vanes: determining the installation number of the guide blades according to the mode, wherein the ratio of the number of each group of guide blades 10 to the number of each group of working blades 20 in the experimental process is 2: 3; specifically, 2 guide blades 10 in each group are selected to form an airflow channel, 3 working blades 20 in each group are selected to form a simulated experiment environment of a hot spot temperature field under high-speed rotation; the nozzle (phi 10mm) of the supersonic flame injector 2 and the outlet of the hot gas flow channel 32 are directly aligned to the center of the leading edge of the guide vane 10, namely 50% of the height of the guide vane, so as to form high-temperature gas flow mass.
Step three, parameters of high-temperature fuel gas and hot gas flow are as follows: when the temperature of the high-temperature core area is 1100 +/-10 ℃, the kerosene flow in the supersonic flame ejector 2 in the loading experiment process is 5.5L/h, the kerosene pressure is 0.63Mpa, the oxygen flow is 295L/Min, the oxygen pressure is 1.64Mpa, after full mixing, a high-temperature gas flow is formed after ignition, and the high-temperature gas flow is ejected to the guide vane channel through the high-temperature gas channel 3; the cooling gas generated by the gas loading component is heated by the high-power electric heater 2 to form electric heating airflow with the flow rate of 300L/Min, the electric heating airflow is sprayed to the guide vane channel through the hot airflow channel 2, the electric heating airflow and the guide vane channel are mixed into composite airflow through the front section of the guide vane channel, and the distance between the terminal outlet of the composite airflow and the front edge of the guide vane 10 is about 6 cm.
Fourthly, analyzing and collating experimental data: after the guide blade hot spot temperature field loading experiment is completed, inputting the gradient temperature image acquired by the infrared thermal imager 62 into a computer, analyzing the plaque, the number of plaques, the size and the color of the plaque in the thermal image, and obtaining the temperature and the variable quantity of the time-averaged hot spot high-temperature core area. Wherein the temperature of the high-temperature core region is 1108.9 ℃, the total temperature of the surrounding air flow is 735.2 ℃, and the heat shift temperature ratio T is1/T2About 1.50, absolute difference temperatureDegree (T)1-T2) At 373.7 ℃ and a relative difference temperature of ((T)1-T2)/T1) About 0.337; and selecting a plurality of groups of temperature points at the same leaf height in the guide blade thermal image radial temperature distribution through analysis to obtain an average value as a hot spot temperature point at a certain leaf height of the guide blade, wherein the hot spot temperature average value at the certain leaf height is taken as an abscissa, and the percentage of the guide blade at the relative leaf height is taken as an ordinate, so as to obtain a guide blade hot spot temperature field radial temperature distribution point diagram corresponding to infrared, namely a scatter diagram corresponding to A, B in fig. 5 and the right side of a C diagram.
In a specific embodiment, referring to fig. 6, the simulation apparatus is used to perform a loading experiment on the high-temperature core region of the guide vane at the same temperature, so as to ensure that the temperature range of the high-temperature fuel gas is not changed in a certain interval, and different temperature ratios in the same hot spot high-temperature core region are realized by regulating and controlling the temperature intervals of the plurality of groups of electrothermal airflows, that is, a certain temperature value is arbitrarily selected from the range of the high-temperature core region at 700-.
Specifically, the temperature of the hot spot high-temperature core region is selected to be 1100 +/-10 ℃ to obtain T1/T2Equal values of 1.30 and 1.42, respectively, correspond to a and B in fig. 7. The temperature and the flow of hot gas flow are changed in real time, and the gas related parameters are the same as the above and are fixed values, and can only slightly fluctuate, and the rest of the detailed steps in the first embodiment in fig. 5 are referred to, and radial temperature distribution diagrams of the hot spot temperature field of the guide vane, namely scatter diagrams corresponding to the right sides of the diagrams A and B in fig. 7, are also obtained. Thereby further realizing different hot spot temperature ratios under the same hot spot temperature.
In one embodiment, referring to fig. 5 and 6, the present simulation apparatus was used to perform a vane hot spot location loading experiment, wherein the hot spot location includes a radial location and a circumferential location. Wherein the radial position refers to the leading edge of the guide vane, i.e. the direction of the spanwise height; the circumferential position refers to the guide vane side surfaces, namely the vane basin and the vane back; the hot spot position can be determined according to the local loading position of the composite gas flow output by the gas channel terminal on the guide vane. The final loading position of the composite air flow is mainly obtained by adjusting the alignment position of a nozzle in the supersonic flame ejector relative to the guide vanes, including radial alignment and circumferential alignment, and adjusting the absolute alignment position of the nozzle and the guide vanes in time according to an infrared cloud picture captured by the infrared thermal imaging instrument 60 and the hot spot loading position fed back by the high-speed CCD camera 70, so that the accurate loading and real-time regulation and control of the hot spot position of the guide vanes are realized.
In one embodiment, referring to fig. 7, the pilot vane hot spot shape loading experiment was conducted by using the test apparatus, and the change of the hot spot shape was achieved mainly by changing the nozzle diameter of the supersonic flame injector 2 and amplifying the flame in a uniformly selected lance sleeve of the same type.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
Claims (9)
1. A simulation device of a hot spot temperature field of a guide vane is characterized by comprising:
the high-temperature fuel gas generating assembly is used for generating high-temperature fuel gas;
the electric heating airflow generating assembly is used for generating electric heating airflow;
one end of the high-temperature gas channel (3) is communicated with the high-temperature gas generating device, and the other end of the high-temperature gas channel is used for aligning to the guide vane;
one end of the electric heating airflow channel (4) is communicated with the electric heating airflow generating device, and the other end of the electric heating airflow channel is used for aligning to the guide blade; the electric heating airflow channel (4) is arranged around the high-temperature gas channel (3);
guide vanes (10) aligned with the other ends of the high temperature gas channel (3) and the electric heat gas flow channel (4);
the working blade (20) is arranged on one side, far away from the high-temperature gas channel (3), of the guide blade (10);
a moving blade turbine disk (201), the moving blades (20) being disposed on the moving blade turbine disk (201);
a rotating assembly (30) connected to the center of the working blade turbine disk (201) for rotating the working blade turbine disk (201).
2. The simulator of guide vane hot spot temperature field according to claim 1,
the electric heating airflow channels (4) are arranged in a plurality of numbers, and the electric heating airflow channels (4) are uniformly distributed around the high-temperature gas channel (3) at intervals in the circumferential direction.
3. The device for simulating a hot spot temperature field of guide vanes according to claim 1, wherein the high-temperature gas channel (3) and the electric heating gas flow channel (4) are arranged in parallel.
4. The simulator of the guide vane hot spot temperature field according to claim 1, wherein the temperature ratio of the total temperature of the fluid in the center of the hot spot to the total temperature of the fluid around the hot spot is 1.3-1.7.
5. The simulator of the hot spot temperature field of the guide vanes as claimed in claim 1, wherein the other ends of the high temperature gas channel (3) and the electric heating air flow channel (4) are provided with high temperature water-cooled butterfly valves (5) for controlling the injection speed of the high temperature gas and the electric heating air flow.
6. The device for simulating a hot spot temperature field of a guide vane of claim 1, further comprising:
and the gas loading assembly is communicated with the high-temperature gas generation assembly and the electric heating gas flow generation assembly and is used for providing gas for the high-temperature gas generation assembly and the electric heating gas flow generation assembly.
7. The device for simulating a hot spot temperature field of a guide vane of claim 1, further comprising:
the temperature-resistant sleeve is sleeved outside the high-temperature gas channel (3) and the electric heating airflow channel (4) and used for fixing the electric heating airflow channel (4) and uniformly distributing the electric heating airflow channel along the circumferential direction, so that the composite airflow formed by the terminal is more uniform.
8. The simulator of guide vane hot spot temperature field according to claim 1,
the high-temperature gas channel (3) and/or the electric heating airflow channel (4) and the guide vanes (10) are arranged at a first preset angle.
9. A method for simulating a guide vane hot spot temperature field, using a guide vane hot spot temperature field simulation apparatus according to any one of claims 1 to 8, comprising:
setting parameters of high-temperature fuel gas and parameters of electric heating airflow based on a preset hot spot ratio;
wherein the ratio of heat spots T1/T2The ratio of the total temperature of the fluid in the center of the hot spot to the total temperature of the fluid around the hot spot.
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Application publication date: 20210903 |