CN113740370A - Hot spot simulation device and method for working blade - Google Patents
Hot spot simulation device and method for working blade Download PDFInfo
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- CN113740370A CN113740370A CN202110966505.3A CN202110966505A CN113740370A CN 113740370 A CN113740370 A CN 113740370A CN 202110966505 A CN202110966505 A CN 202110966505A CN 113740370 A CN113740370 A CN 113740370A
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- G—PHYSICS
- 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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- G—PHYSICS
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Abstract
The invention discloses a hot spot simulation device and a hot spot simulation method for a working blade, wherein the simulation device comprises: a guide vane turbine disk; the guide vane is arranged at the edge of the guide vane turbine disc; the working blade is arranged on one side of the guide blade; the high-temperature channel is arranged on one side of the guide blade, which is far away from the working blade, and one end of the high-temperature channel is aligned to the guide blade and is used for transmitting high-temperature airflow; the low-temperature channel is arranged on one side of the guide blade, which is far away from the working blade, and one end of the low-temperature channel is aligned to the guide blade and is used for transmitting low-temperature airflow; the rotating assembly is connected with the center of the guide vane turbine disc and is used for rotating the guide vane turbine disc; and the centrifugal force loading device is used for loading centrifugal force on the working blade. The technical scheme can accurately simulate the service environment of the working blade, and accurately adjust the hot spot temperature ratio and the hot spot pressure ratio of the working blade by adjusting the flow and the temperature of the high-temperature airflow and the low-temperature airflow so as to provide important experimental basis for hot spot migration in a turbine runner and an aggregation rule on the working blade.
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 hot spot simulation device and method of a working 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 motion 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 a pressure surface of the movable blade to generate a local overheating area, so that the movable blade bears huge heat load, and the working blade can rotate at a high speed during working, so that a hot spot scheme capable of accurately simulating the working blade is not provided in the prior art.
Disclosure of Invention
Objects of the invention
The invention aims to provide a simulation device and a method capable of accurately simulating hot spots of a working blade.
(II) technical scheme
To solve the above problems, a first aspect of the present invention provides a hot spot simulation apparatus for a working blade, comprising: a guide vane turbine disk; the guide vane is arranged at the edge of the guide vane turbine disc; the working blade is arranged on one side of the guide blade; the high-temperature channel is arranged on one side of the guide blade, which is far away from the working blade, and one end of the high-temperature channel is aligned with the guide blade and is used for transmitting high-temperature airflow; wherein the temperature of the high-temperature airflow is 700-1500 ℃; the low-temperature channel is arranged on one side of the guide blade, which is far away from the working blade, and one end of the low-temperature channel is aligned with the guide blade and is used for transmitting low-temperature airflow; wherein the temperature of the low-temperature airflow is 50-500 ℃; a rotating assembly connected to the center of the guide vane turbine disk for rotating the guide vane turbine disk; and the centrifugal force loading device is connected with the working blades and is used for loading centrifugal force on the working blades.
Optionally, the guide vane comprises a simulated guide vane, a tenon of the simulated guide vane is the same as a tenon of a real guide vane, and a curvature of a blade body of the simulated guide vane is the same as a curvature of a characteristic position of the real guide vane; wherein the feature locations comprise: the leading edge, the trailing edge, the basin and the back of the blade body.
Optionally, the high temperature channel and the low temperature channel are parallel and equal in length; the low-temperature channel is provided with a plurality of, and a plurality of low-temperature channels interval and evenly ring to distribute in high temperature channel is all around.
Optionally, the working blade forms a first preset angle with the high-temperature channel and the high-temperature channel; the high-temperature channel and the low-temperature channel are aligned to the preset positions of the working blades and used for adjusting the radial height and the circumferential angle of the working blades impacted by the composite airflow formed by the high-temperature airflow and the low-temperature airflow.
Optionally, the hot spot simulation apparatus for a working blade further includes: and the flow regulating device is arranged at one end of the high-temperature channel and one end of the low-temperature channel and is used for regulating the pressure and the flow of the high-temperature airflow and the low-temperature airflow.
Optionally, the hot spot simulation apparatus for a working blade further includes: the high-temperature gas generating device is connected with the other end of the high-temperature channel and is used for generating high-temperature gas; and the low-temperature gas generating device is connected with the other end of the low-temperature channel and is used for generating low-temperature gas.
Optionally, the hot spot simulation apparatus for a working blade further includes: and the light positioning system is used for positioning the position of the hot spot temperature field on the working blade.
Optionally, the hot spot simulation apparatus for a working blade further includes: and the hot spot pressure field detection device is arranged on one side of the guide blade, which is far away from the high-temperature channel, and is used for detecting the hot spot pressure field of the working blade.
Optionally, the hot spot pressure field detection device includes: the pressure sensor is used for detecting the pressure born by the working blade; and the temperature sensor is used for detecting the temperature born by the pressure sensor.
A second aspect of the present invention provides a hot spot simulation method for a working blade, which uses the hot spot simulation apparatus for a working blade according to the first aspect of the present invention to perform simulation.
(III) advantageous effects
The technical scheme of the invention has the following beneficial technical effects:
according to the invention, the rotary airflow is formed around the working blade through the rotary guide blade to simulate the airflow of the working blade during working, the centrifugal force generated by the rotation of the working blade during working is simulated through the centrifugal force loading device to accurately simulate the loading environment of the working blade during working, and the high-temperature airflow and the low-temperature airflow form the composite airflow so as to accurately adjust the hot spot temperature ratio and the hot spot pressure ratio of the working blade by adjusting the flow rate and the temperature of the high-temperature airflow and the low-temperature airflow, so that important experimental basis is provided for hot spot migration in a turbine runner and the gathering rule on the working blade, and important basis is provided for the design and optimization of an efficient cooling scheme, and the method is economical and effective.
Drawings
FIG. 1 is a schematic structural view of a hot spot simulation apparatus for a working blade according to a first embodiment of the present invention;
FIG. 2 is a side view schematically illustrating the structure of the high temperature path and the low temperature path according to the first embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a centrifugal force loading device according to a first embodiment of the present invention;
fig. 4 is a load time curve obtained by using a structural schematic diagram of a centrifugal force loading device according to a first embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a light ray positioning system according to a first embodiment of the present invention;
FIG. 6 is a schematic diagram of the placement of a hot spot pressure field detection device according to a first embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a hot spot pressure field detection apparatus according to a first embodiment of the present invention;
FIGS. 8A-8D are sets of hot spot temperature field patterns for the high temperature core region at different temperatures for a working blade according to an example of the second embodiment of the present invention;
FIG. 9 is a plurality of hot spot temperature field patterns of the high temperature core region at different locations of a working blade according to a specific example of the second embodiment of the present invention;
fig. 10 is a flowchart of a hot spot simulation method according to a second embodiment of the present invention.
Reference numerals
1: a guide vane turbine disk; 2: a guide blade; 3: a working blade; 4: a high temperature channel; 5: a cryogenic channel; 6: a rotating assembly; 71: clamping a clamp; 72: a force applying medium; 73: an electronic universal testing machine; 8: a flow regulating device; 9: an optical fiber positioning system; 91 a filter segment; 92 light pulse laser; 93 a photoelectric converter; 94 a data acquisition system; 95 a computer; 10: a hot spot pressure field detection device; 101: a pressure sensor; 102: a temperature sensor; 103: a temperature sensor lead; 104: a pressure sensor lead; 105: a head portion; 11: a temperature-resistant sleeve; 12: a working blade turbine disk; 13: a case; 14: a combustion chamber; 15: a fixed base; 16: an infrared thermal imager; 17: high-speed CCD camera.
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
Referring to fig. 1, a first embodiment of the present invention provides a hot spot simulation apparatus of a working blade, including: a guide vane turbine disk 1; a guide vane 2 provided at an edge of the guide vane turbine disk 1; the working blade 3 is arranged on one side of the guide blade 2; the high-temperature channel 4 is arranged on one side of the guide blade 2 far away from the working blade 3, and one end of the high-temperature channel is aligned with the guide blade 2 and used for transmitting high-temperature airflow; wherein the temperature of the high-temperature airflow is 700-1500 ℃; the low-temperature channel 5 is arranged on one side of the guide blade 2 far away from the working blade 3, and one end of the low-temperature channel is aligned with the guide blade 2 and used for transmitting low-temperature airflow; wherein the temperature of the low-temperature airflow is 50-500 ℃; a rotating assembly 6 connected to the center of the guide blade turbine disk 1 for rotating the guide blade turbine disk 1; and the centrifugal force loading device is connected with the working blade 3 and is used for loading the centrifugal force on the working blade 3. According to the embodiment, the rotary air flow is formed around the working blade 3 through the rotary guide blade 2 so as to simulate the air flow of the working blade 3 during working, the centrifugal force of the working blade 3 during working is simulated through the centrifugal force loading device so as to accurately simulate the loading environment of the working blade 3 during working, and the high-temperature air flow and the low-temperature air flow form the composite air flow so as to accurately adjust the hot spot temperature ratio and the hot spot pressure ratio of the working blade 3 by adjusting the flow rate and the temperature of the high-temperature air flow and the low-temperature air flow, so that important experimental basis is provided for hot spot migration in a turbine runner and the gathering rule on the working blade 3, important basis is provided for the design and optimization of an efficient cooling scheme, and the method is economical and effective. Wherein the hot spot temperature ratio 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 is P1/P2Is the ratio of the total pressure of the fluid in the center of the hot spot to the total pressure of the fluid around the hot spot. In addition, the rotor blade 3 is fixed on a fixed base 15, and the hot spot simulation deviceThe main body is located within the combustion chamber 14.
In an alternative embodiment, the guide vane 2 comprises a simulated guide vane 2, the tenon of the simulated guide vane 2 is the same as the tenon of the real guide vane 2 and is integrally formed with the guide vane turbine disc 1; the curvature of the blade body of the simulated guide blade 2 is the same as the curvature of the characteristic position of the real guide blade 2; wherein the feature locations comprise: the leading edge, the trailing edge, the basin and the back of the blade body. Specifically, the curvature radius of the blade body portion of the simulated guide blade 2 is determined by the curvature of the real guide blade 2, i.e., r is 1/ρ. One of the advantages of using a simulated guide vane 2 is that it is cost effective because of the high cost of the actual guide vanes 2 used in aviation. Meanwhile, the curvature of any position of the real turbine blade can be simulated in a targeted manner, so that the specific influence of the curvature of the turbine blade on the hot spot field can be studied in a targeted manner. The most important point of using simulation guide vane 2 is can be through the curvature radius of fine setting simulation guide vane 2, and then change the flow direction of high temperature air current, finally realize that hot spot position changes on the working vane 3, compare in traditional mechanical type change guide vane 2's installation angle and realize the regulation of air current angle, the more accurate of the regulation mode of this embodiment.
Referring to fig. 2, in an alternative embodiment, the high temperature channel 4 is parallel to the low temperature channel 5, and has the same length, the low temperature channel 5 is provided in plurality, and the plurality of low temperature channels 5 are circumferentially distributed around the high temperature channel 4 at intervals and uniformly. Specifically, the low temperature channel 5 of this embodiment is provided with a plurality ofly, and is a plurality of low temperature channel 5 interval and evenly the ring distributes around high temperature channel 4, and high temperature channel 4 with low temperature channel 5 parallel arrangement. The high-temperature airflow and the low-temperature airflow form composite annular airflow to load the service environment of the hot spot field on the working blade 3, wherein the hot spot field comprises a hot spot temperature field and a hot spot pressure field. Further specifically, the hot spot temperature field and the hot spot pressure field can be controlled by controlling the flow rate, temperature, and distance from the working vane 3 of the high temperature gas and the low temperature gas, wherein the most important factor is controlling the temperature of the high temperature gas and the low temperature gas.
Wherein, the temperature-resistant sleeve pipe is sleeved outside the high-temperature channel 4 and the low-temperature channel 5, and the temperature-resistant sleeve pipe 11, the high-temperature channel 4 and the low-temperature channel 5 are annular. The absolute length and shape of the channels remain consistent; groups of low temperature channels 5 are distributed annularly around the high temperature channels 4. The low-temperature channel 5 can discharge low-temperature airflow through electric heating, and after the hot spots of the working blade 3 are generated or after the test is finished, the electric heater is switched off, and cooling airflow is introduced to cool the working blade 3 or cool the specific hot spot position of the working blade 3; the temperature-resistant sleeve is fixedly connected with the multiple groups of low-temperature channels 5 through bolts; and supporting structures are arranged below the gas channels. The temperature-resistant sleeve 11 is used for fixing the low-temperature channel 5 and is uniformly arranged around the fuel gas channel along the circumferential direction, so that the composite airflow formed by the high-temperature airflow and the low-temperature airflow is more uniform and controllable. Wherein the high temperature gas flow may be a gas flow.
In an alternative embodiment, the working vane 3 and the high temperature channel 4 form a first predetermined angle; the high-temperature channel 4 and the low-temperature channel 5 are aligned to the preset positions of the working blades 3 and used for adjusting the radial height and the circumferential angle of the working blades 3 impacted by the composite airflow formed by the high-temperature airflow and the low-temperature airflow, wherein the first preset angle is-45 degrees to 45 degrees and can be adjusted.
In an alternative embodiment, the present embodiment provides a method for adjusting the angle of the composite airflow borne by the working blade 3, which includes two specific steps:
the first step is coarse adjustment: the angle of the composite air flow and the degree of the air flow borne by the working blade 3 are macroscopically adjusted by changing the relative positions of the high-temperature passage 4 and/or the low-temperature passage 5 and the guide blade 2 and the first preset angle.
The second step is the fine setting, further adjusts simulation guide vane 2's curvature radius, and curvature radius is big more, and is stronger to the direction of compound air current, and the air current also can change and then realize that hot spot position changes on the working vane 3 to the local position that arrives working vane 3, compares and changes guide vane 2's installation angle in traditional mechanical type and realizes the regulation of air current angle, the more accurate of the regulation mode of this embodiment.
Wherein, high temperature passageway 4 is 0 degree with guide vane 2's predetermined angle, and high temperature passageway 4 parallel placement promptly, when compound air current impacted guide vane 2 dead ahead, compound air current can be sheared into two strands of not equidirectional air currents, and the flow direction of first air current still is along dead ahead, and second air current is then along guide vane 2 direction of rotation's reversal. The speed of the first air flow depends on the air input, namely the Mach number, of the high-temperature air flow. The velocity of the second air flow depends on the magnitude of the angular velocity of the rotation of the guide vane 2, and can be obtained by the formula v-wr.
In an alternative embodiment, the hot spot simulation apparatus for a working blade 3 further includes: and the flow regulating device 8 is arranged at one end of the high-temperature channel 4 and one end of the low-temperature channel 5 and is used for regulating the pressure and the flow of the high-temperature airflow and the low-temperature airflow. Wherein, the flow regulating device 8 includes: a high-temperature water-cooled butterfly valve; the high-temperature water-cooling butterfly valve is arranged at the other ends of the high-temperature channel 4 and the low-temperature channel 5 and is used for controlling the jetting speed of high-temperature airflow and low-temperature airflow. The jet velocity of the high-temperature air flow is consistent with that of the low-temperature air flow, the high-temperature air flow and the low-temperature air flow reach the surface of the working blade 3 at the same time, the loading of the hot spot ratio can be better realized only when the high-temperature air flow and the low-temperature air flow reach the surface of the working blade at the same time, and the surface temperature field and the pressure field of the guide blade 2 can be more uniform. The high-temperature water-cooling butterfly valve and the channel can be fixedly connected through a bolt, the adjusting angle of the butterfly rod is 0-90 ℃, the inner cavity of the valve body is cooled by circulating water and is used for adjusting the ratio of high-temperature air flow and low-temperature air flow, and the spraying speeds of the high-temperature water-cooling butterfly valve and the channel tend to be consistent.
Referring to fig. 3 and 4, in an alternative embodiment, the centrifugal force loading device specifically includes a clamping fixture 71, a force application medium 72, and an electronic universal tester 73. Wherein, the profile of centre gripping anchor clamps laminating rotor blade 3 designs, the clamping part divide into pressure side and suction surface again, respectively correspond suction surface and the pressure surface who hugs closely in rotor blade 3, and extend rotor blade 3's suction surface and pressure surface, extend the part of suction surface and pressure surface with the clamping fixture, use bolted connection, make clamping part's front and back two parts press from both sides tight rotor blade 3, the middle zone of front and back two parts closely laminates in rotor blade 3 surface, be fixed in the blade surface through the extrusion force that produces at the pressure surface, suction surface. The resultant force acting on the rotor blade 3 is applied to the blade root via the blade center of gravity. Wherein, the range of the electronic universal tester is selected to be 5-5000N according to the material of the working blade 3. The electronic universal testing machine stretches the clamping fixture through the force application medium, the force application medium is selected to only bear tensile force and not bear pressure materials, and the electronic universal testing machine can be a steel wire rope, a high-strength elastic rope and the like. Wherein, the adjustment of the centrifugal force loading position and angle can be realized by changing the angle of the relative position of the working blade 3 and the clamping fixture. At this time, the blade material is nickel-based superalloy, the emissivity of the blade is 0.75, and the blade is loaded by using a centrifugal force loading device at 900 ℃, and the obtained load time curve is shown in fig. 4.
In an alternative embodiment, the hot spot simulation apparatus for a working blade 3 further includes: the high-temperature gas generating device is connected with the other end of the high-temperature channel 4 and is used for generating high-temperature gas; and the low-temperature gas generating device is connected with the other end of the low-temperature channel 5 and is used for generating low-temperature gas.
Referring to fig. 5, in an alternative embodiment, the hot spot simulation apparatus for the working blade 3 further includes: and the light positioning system is used for positioning the position of the hot spot field on the working blade 3. Wherein, light positioning system includes: a filter 91, a light pulse laser 92, a photoelectric converter 93, a data acquisition system 94 and a computer 95. The computer 95 sends a control command to the optical pulse laser 92, and the optical pulse laser 92 emits a light beam which is filtered by the optical filter 91 to obtain laser with a specific wavelength lambda required by radial/circumferential displacement change. Then, the photoelectric converter 93 acquires the light reflected by the working blade 3, obtains a displacement signal, and then transmits the displacement signal to the computer 95 via the data acquisition system. The specific wavelength lambda is different from a flame flow field, a plurality of marking surfaces are processed at the positions of a blade basin, a blade back, a front edge and a tail edge of the working blade 3, the marking surfaces at the four positions have different light reflection capacities but are stronger than those at other positions, and the marking surfaces are easy to distinguish, so that the real-time feedback of the hot spot position of the working blade 3 is realized; the positioning surface can not influence the integral strength of the blade, and the direction of the emitted light beam is required to be perpendicular to the positioning surface as much as possible at the position closest to the optical fiber positioning system. Wherein, the hot spot simulation apparatus of the working blade 3 further includes: an infrared thermal imager 16 and a high-speed CCD camera 17. The hot spot position is fed back in real time through an optical fiber positioning system, and then the hot spot position is captured by an infrared thermal imager and a high-speed CCD camera together to obtain a temperature cloud picture and a high-definition image in real time.
Specifically, the displacement signal refers to the migration of the heat spot at a local position of the working blade 3, the heat spot is cut into discontinuous heat spots due to the rotation of the guide blade 2, the heat spots partially move downstream along the pressure surface (i.e. the basin) of the guide blade 2, and the heat spots partially move downstream along the suction surface (i.e. the back) of the blade, i.e. the downstream movement randomly reaches a certain local position of the working blade 3. Because a plurality of marking surfaces are processed at the positions of the basin, the back, the front edge and the tail edge of the working blade 3, and the reflection capacities of the marking surfaces at the four positions to light are different, namely the wavelength lambda required by measuring the displacement is different.
Referring to fig. 6 and 7, optionally, the hot spot simulation apparatus for the working blade 3 further includes: and the hot spot pressure field detection device 10 is arranged on one side of the guide blade 2, which is far away from the high-temperature channel 4, and is used for detecting the hot spot pressure field of the working blade 3. Wherein, the hot spot pressure field detection device 10 includes: when the axis of the pressure sensing hole is opposite to the coming direction of the composite airflow, the airflow passes through the pressure sensor 101 and the temperature sensor 102 and is subjected to isentropic stagnation at the head of the pressure sensing hole, and the pressure sensed by the pressure sensing hole is the total pressure of the airflow. And then the hot spot pressure field detection is realized by connecting the terminal with the lead wires of the pressure sensor 101 and the temperature sensor 102 respectively. Specifically, the temperature sensor 102 functions to sense the temperature of the composite gas flow, eliminate measurement errors of the dynamic pressure sensor due to temperature drift, and avoid damage caused by the actual temperature of the composite gas flow exceeding the upper limit of the normal operating temperature range of the pressure sensor.
Wherein, the hot spot pressure field detection device 10 is used for detecting the hot spot pressure field of the working blade 3, and is embodied by a hot spot pressure ratio, and the hot spot pressure ratio is P1/P2Is a hot spotThe ratio of the total pressure of the central fluid to the total pressure of the fluid surrounding the hot spot. The total pressure of the hot spot central fluid is measured by a hot spot pressure detection device behind the working blade 3, and the total pressure of the surrounding fluid is measured by a pressure detection device behind the guide blade 2. Preferably, the hot spot pressure field detection device can be provided with a plurality of hot spot pressure field detection devices, and the average value is finally obtained, so that the result can be more accurate. Further preferably, the hot spot pressure field detection device 10 is respectively arranged at the lateral rear part of the guide blade 2 and the working blade 3, and the specific angle of the hot spot pressure field detection device is 45 degrees with the front composite airflow; the hot spot pressure field detection device 10 is fixedly connected with the wall surface of the machine brake 13 through bolts.
Second embodiment
Referring to fig. 10, a second embodiment of the present invention provides a hot spot simulation method for a rotor blade 3, which is performed by using the hot spot simulation apparatus for a rotor blade 3 according to the first embodiment of the present invention, and specifically includes the following steps:
s100, starting a hot spot simulation device of the working blade 3, and presetting the temperature ranges and gas flow rates of high-temperature gas in the supersonic flame ejector and low-temperature gas in the heater;
s200, starting a centrifugal force loading device, and presetting a numerical range and a loading position of a tensile load;
s300, starting the thermal infrared imager and the pressure detection system, and presetting the corresponding emissivity of the thermal barrier coating of the working blade 3;
s400, connecting and calibrating the optical fiber positioning system, and feeding back the hot spot position on the working blade 3 in real time;
s500, cutting off the heating device, increasing the cold air flux at the specific hot spot of one group of working blades 3, and reducing the cold air flux at the non-hot spot high-temperature core area of the rest working blades 3.
In a specific embodiment, referring to fig. 8, the simulation apparatus is used to perform a loading experiment on different hot spot high-temperature core regions of the working blade 3, that is, the temperature ratio ranges from 1.20 to 1.70 in the high-temperature core regions at 900-;
as shown in graph A of FIG. 8, the heat spot ratio T1/T21.20; as shown in the B diagram in FIG. 8, the heat spot ratio T1/T21.41; as shown in the C diagram of FIG. 8, the heat spot ratio T1/T21.63; as shown in D of FIG. 8, the heat spot ratio T1/T2＝1.70。
In a specific embodiment, referring to fig. 9, the present simulation apparatus was used to perform loading experiments on the high temperature core region at different positions of the rotor blade 3.
As shown in A of FIG. 9, it is a heat spot temperature field diagram of the back surface (suction surface) of the rotor blade 3, and the heat spot ratio T thereof1/T2＝1.48；
As shown in B of FIG. 9, it is a heat spot temperature field diagram of the basin (pressure surface) of the working blade 3, and the heat spot ratio T thereof1/T2＝1.57；
As shown in fig. 9C, which is a hot spot temperature field diagram of the leading edge of the working blade 3, the hot spot ratio T thereof is1/T2＝1.59；
As shown in fig. 9D, which is a hot spot temperature field diagram of the trailing edge of the working blade 3, the hot spot ratio T thereof1/T2＝1.52。
The invention discloses a hot spot simulation device and a hot spot simulation method for a working blade 3, wherein the simulation device comprises: a guide vane turbine disk 1; a guide vane 2 provided at the edge of the guide vane turbine disk 1; a rotor blade 3 provided on one side of the guide blade 2; the high-temperature channel 4 is arranged on one side of the guide blade 2 far away from the working blade 3, and one end of the high-temperature channel is aligned with the guide blade 2 and used for transmitting high-temperature airflow; the low-temperature channel 5 is arranged on one side of the guide blade 2 far away from the working blade 3, and one end of the low-temperature channel is aligned with the guide blade 2 and used for transmitting low-temperature airflow; a rotating assembly 6 connected to the center of the guide vane turbine disk 1 for rotating the guide vane turbine disk 1; and a centrifugal force loading device for loading the working blade 3 with a centrifugal force. The scheme can accurately simulate the service environment of the working blade 3, and accurately adjust the hot spot temperature ratio and the hot spot pressure ratio of the working blade 3 by adjusting the flow and the temperature of the high-temperature airflow and the low-temperature airflow so as to provide important experimental basis for hot spot migration in a turbine runner and the gathering rule on the working blade 3.
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.
Claims (10)
1. A hot spot simulation apparatus for a working blade, comprising:
a guide vane turbine disc (1);
the guide vane (2) is arranged at the edge of the guide vane turbine disc (1);
the working blade (3) is arranged on one side of the guide blade (2);
the high-temperature channel (4) is arranged on one side, away from the working blade (3), of the guide blade (2), one end of the high-temperature channel is aligned with the guide blade (2), and the high-temperature channel is used for transmitting high-temperature airflow; wherein the temperature of the high-temperature airflow is 700-1500 ℃;
the low-temperature channel (5) is arranged on one side, away from the working blade (3), of the guide blade (2), one end of the low-temperature channel is aligned with the guide blade (2) and used for transmitting low-temperature airflow; wherein the temperature of the low-temperature airflow is 50-500 ℃;
a rotating assembly (6) connected to the center of the guide vane turbine disc (1) for rotating the guide vane turbine disc (1);
and the centrifugal force loading device is connected with the working blade (3) and is used for loading centrifugal force on the working blade (3).
2. The hot spot simulation apparatus of a working blade according to claim 1,
the guide blade (2) comprises a simulated guide blade (2), the tenon of the simulated guide blade (2) is the same as that of the real guide blade (2), and the curvature of the blade body of the simulated guide blade (2) is the same as that of the characteristic position of the real guide blade (2);
wherein the feature locations comprise: the leading edge, the trailing edge, the basin and the back of the blade body.
3. The hot spot simulation apparatus of a working blade according to claim 1,
the high-temperature channel (4) and the low-temperature channel (5) are parallel and equal in length;
the low-temperature channels (5) are arranged in a plurality, and the low-temperature channels (5) are uniformly distributed around the high-temperature channel (4) at intervals in the circumferential direction.
4. A hot spot simulation apparatus of a working blade according to claim 3,
the working blade (3) and the high-temperature channel (4) form a first preset angle; the high-temperature channel (4) and the low-temperature channel (5) are aligned to the preset position of the working blade (3) and used for adjusting the radial height and the circumferential angle of the working blade (3) impacted by the composite airflow formed by the high-temperature airflow and the low-temperature airflow.
5. The hot spot simulation apparatus of a working blade according to any one of claims 1 to 4, further comprising:
and the flow regulating device (8) is arranged at one end of the high-temperature channel (4) and one end of the low-temperature channel (5) and is used for regulating the pressure and the flow of the high-temperature airflow and the low-temperature airflow.
6. The hot spot simulation apparatus of a working blade according to claim 1, further comprising:
the high-temperature gas generating device is connected with the other end of the high-temperature channel (4) and is used for generating high-temperature gas;
and the low-temperature gas generating device is connected with the other end of the low-temperature channel (5) and is used for generating low-temperature gas.
7. The hot spot simulation apparatus of a working blade according to claim 1, further comprising:
and the optical fiber positioning system (9) is used for positioning the position of the hot spot field on the working blade (3).
8. The hot spot simulation apparatus of a working blade according to claim 1, further comprising:
and the hot spot pressure field detection device (10) is arranged on one side of the guide blade (2) far away from the high-temperature channel (4) and is used for detecting the hot spot pressure field of the working blade (3).
9. A hot spot simulation apparatus of a working blade according to claim 8, wherein the hot spot pressure field detection means (10) comprises:
a pressure sensor (101) for detecting the pressure to which the rotor blade (3) is subjected;
the temperature sensor (102) is used for detecting the temperature born by the pressure sensor (101).
10. A hot spot simulation method of a working blade, characterized in that a hot spot simulation apparatus of a working blade according to any one of claims 1 to 9 is used for the simulation.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050167820A1 (en) * | 2004-01-30 | 2005-08-04 | Oriental Institute Of Technology | Device and method for cooling hot spot in micro system |
| US8087893B1 (en) * | 2009-04-03 | 2012-01-03 | Florida Turbine Technologies, Inc. | Turbine blade with showerhead film cooling holes |
| CN109443773A (en) * | 2018-12-10 | 2019-03-08 | 湘潭大学 | Turbine model is used in a kind of test of thermal barrier coating service Work condition analogue |
| CN109459286A (en) * | 2018-12-10 | 2019-03-12 | 湘潭大学 | Real-time detection method is damaged in a kind of thermal barrier coating of turbine blade simulation test procedure |
| CN109580410A (en) * | 2018-12-10 | 2019-04-05 | 湘潭大学 | A kind of equivalent loading device and method of working-blade thermal barrier coating service load |
| CN208782778U (en) * | 2018-08-21 | 2019-04-23 | 佛山职业技术学院 | A kind of photovoltaic module hot spot detection system |
| CN109780739A (en) * | 2019-01-31 | 2019-05-21 | 哈尔滨工业大学 | A kind of porous heat dump of graded gap formula solar energy containing quartz foam |
| CN109781377A (en) * | 2019-03-11 | 2019-05-21 | 湘潭大学 | A kind of turbo blade Work condition analogue flow passage structure and turbo blade Work condition analogue device |
| CN109855977A (en) * | 2018-12-10 | 2019-06-07 | 湘潭大学 | A kind of equivalent loading device and method of thermal barrier coating of turbine blade military service load |
-
2021
- 2021-08-23 CN CN202110966505.3A patent/CN113740370A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050167820A1 (en) * | 2004-01-30 | 2005-08-04 | Oriental Institute Of Technology | Device and method for cooling hot spot in micro system |
| US8087893B1 (en) * | 2009-04-03 | 2012-01-03 | Florida Turbine Technologies, Inc. | Turbine blade with showerhead film cooling holes |
| CN208782778U (en) * | 2018-08-21 | 2019-04-23 | 佛山职业技术学院 | A kind of photovoltaic module hot spot detection system |
| CN109443773A (en) * | 2018-12-10 | 2019-03-08 | 湘潭大学 | Turbine model is used in a kind of test of thermal barrier coating service Work condition analogue |
| CN109459286A (en) * | 2018-12-10 | 2019-03-12 | 湘潭大学 | Real-time detection method is damaged in a kind of thermal barrier coating of turbine blade simulation test procedure |
| CN109580410A (en) * | 2018-12-10 | 2019-04-05 | 湘潭大学 | A kind of equivalent loading device and method of working-blade thermal barrier coating service load |
| CN109855977A (en) * | 2018-12-10 | 2019-06-07 | 湘潭大学 | A kind of equivalent loading device and method of thermal barrier coating of turbine blade military service load |
| CN109780739A (en) * | 2019-01-31 | 2019-05-21 | 哈尔滨工业大学 | A kind of porous heat dump of graded gap formula solar energy containing quartz foam |
| CN109781377A (en) * | 2019-03-11 | 2019-05-21 | 湘潭大学 | A kind of turbo blade Work condition analogue flow passage structure and turbo blade Work condition analogue device |
Non-Patent Citations (4)
| Title |
|---|
| 《THOMAS POVEY》: "Developments in Hot-Streak Simulators for Turbine Testing", 《JOURNAL OF TURBOMACHINERY》 * |
| 白江涛;朱惠人;张宗卫;许都纯;: "叶片全表面换热系数和冷却效率的实验测量", 西安交通大学学报 * |
| 苗辉: "热斑压力比对气冷涡轮叶栅表面热负荷的影响", 《燃气涡轮试验与研究》 * |
| 谢金伟 等: "涡轮叶栅进口热斑迁移及其影响因素研究试验装置设计", 《燃气涡轮试验与研究》 * |
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