CN111693379A - System and method for testing high-temperature mechanical properties of tiny samples of turbine blades with complex configurations - Google Patents
System and method for testing high-temperature mechanical properties of tiny samples of turbine blades with complex configurations Download PDFInfo
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- G—PHYSICS
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/18—Performing tests at high or low temperatures
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- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
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- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/06—Special adaptations of indicating or recording means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
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- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0071—Creep
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- G—PHYSICS
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
- G01N2203/0226—High temperature; Heating means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
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Abstract
The invention belongs to the field of turbine blade technology and material mechanical property testing of an aircraft engine, and particularly relates to a high-temperature mechanical property testing system and method for a turbine blade micro sample with a complex configuration. The invention aims to serve the strength evaluation of the turbine blade after service and repair, is also suitable for the turbine blade with solid and small cooling channels, and has high universality in a sampling method and a special fixture designed by the method.
Description
Technical Field
The invention belongs to the field of aeroengine turbine blade technology and material mechanical property testing, and particularly relates to a high-temperature mechanical property testing system and method for a small sample of a turbine blade with a complex configuration, which are particularly suitable for mechanical property tests of the small sample of the turbine blade with the complex geometry configuration at room temperature and high temperature.
Background
The turbine blade of the aircraft engine is in service in high-speed, high-temperature and gas-corrosion environments for a long time, so that the mechanical properties of the blade and the material are inevitably changed. The change of the high-temperature mechanical property of the blade directly influences the safety service, the propulsion performance and the maintenance cost of the whole engine.
Turbine blades are expensive to manufacture and are easily discarded from damage, making the daily use and maintenance costs of the engine extremely high. If the life safety boundary of the turbine blade in service can be found, the maintenance interval of the engine can be prolonged, the replacement amount of the damaged turbine blade is reduced, and the turbine blade has important economic and safety values.
The turbine blade needs to be evaluated in terms of the structural state and mechanical properties after being in service and repaired during overhaul so as to determine whether the blade can be continuously in service and repaired and whether the blade can be used after being repaired. However, most of the existing research works are based on standard samples and laboratories.
The turbine blade of the aircraft engine has the characteristics of complex geometric structure, prominent thin-wall effect, unclear service course and the like, which can not be replaced by a standard sample and a service condition simulation sample. This requires sampling of the turbine blades after service and mechanical performance assessment of the turbine blade samples under typical service loading conditions.
Disclosure of Invention
In order to solve the technical problems, the invention provides a system and a method for testing the high-temperature mechanical properties of a tiny sample of a turbine blade with a complex configuration, aims to serve the strength evaluation of the turbine blade after service and repair, and is also suitable for the turbine blade with a solid cooling channel and a small number of cooling channels.
The invention is realized in such a way, and provides a high-temperature mechanical property test system for a tiny sample of a turbine blade with a complex configuration, which comprises a material tensile testing machine, a clamp, a load control system and a temperature control system, wherein the load control system comprises a load control computer, a load sensor and a displacement sensor, the temperature control system comprises a box-type resistance heating furnace, a thermocouple and a temperature control box, the tiny sample of the turbine blade is arranged on the clamp, the clamp is clamped on the material tensile testing machine, the load sensor, the displacement sensor and the thermocouple are respectively used for collecting different parameters of the tiny sample of the turbine blade, the material tensile testing machine, the load sensor and the displacement sensor are respectively connected with the load control computer, the box-type resistance heating furnace is arranged at the periphery of the clamp, and the box-.
Preferably, anchor clamps include two clamping unit, and every clamping unit includes main chuck, locating pin and tighrening ring, and main chuck one end surface is equipped with the recess formula dress appearance district that link up that the cross-section matches with the little sample tip shape of turbine blade, and the other end is the double-screw bolt, and two locating pins of installation matching in the dress appearance district, the little sample tip of turbine blade press from both sides between two locating pins, the double-screw bolt be used for with material tensile test machine connects, and the tighrening ring cup joints in the main chuck outside, and two clamping unit are from top to bottom in the opposite direction when using and are cliied the little.
Further preferably, the load sensor and the displacement sensor are connected to a cross beam of the material tensile testing machine, and the thermocouple is connected to the turbine blade micro sample.
Preferably, the turbine blade micro sample comprises an examination scale distance section in the middle, stress transition arc sections positioned at two ends of the examination scale distance section, a loading arc section connected with the stress transition arc sections and end parts;
the turbine blade micro sample size is 30mm long multiplied by 8mm wide multiplied by 0.8mm thick, the size of the examination scale distance section is 6mm long multiplied by 3mm wide, the arc radius of the loading arc section is 10mm, and the arc radius of the stress transition arc section is 17 mm.
Further preferably, the load sensor is a high-precision load sensor, the minimum resolution of the load sensor is 0.1N, the displacement sensor is a high-precision displacement sensor, the linearity of the displacement sensor is 0.1%, and the resolution of the displacement sensor is 0.015 micrometer.
The invention also provides a method for carrying out a high-temperature mechanical property test on the turbine blade micro sample with the complex configuration by using the system, which comprises the following steps:
1) according to the sampling scheme, a small-size blank sample is taken from a turbine blade with a complex configuration, and then the small-size blank sample is subjected to secondary processing to be processed into a symmetrical hanging-piece type thin-wall turbine blade micro sample;
2) installing the sample processed in the step 1) into the clamp, opening the box type resistance heating furnace, installing the clamp to the threaded installation end of the material tensile testing machine, and completing clamping of the turbine blade micro sample;
3) fixing the thermocouple on a turbine blade micro sample, closing and sealing the box type resistance heating furnace, and connecting the load sensor and the displacement sensor on a cross beam of a material tensile testing machine;
4) starting the box type resistance heating furnace through the temperature control box, heating the turbine blade micro sample to a certain temperature, and then preserving heat for a certain time;
5) starting the load control computer and the material tensile testing machine, executing a preset loading program on the material tensile testing machine by the load control computer, acquiring load and displacement data of the turbine blade micro sample by the load sensor and the displacement sensor, transmitting the load and displacement data to the load control computer, and finishing the test after the turbine blade micro sample breaks;
6) and closing the temperature control box, taking down the turbine blade micro sample after the temperature of the turbine blade micro sample is reduced to the room temperature, and storing the load, displacement and service life data of the turbine blade micro sample in the load control computer.
Preferably, step 1) specifically comprises:
a) measuring the dimension of a geometric solid model of the turbine blade to be sampled, selecting a strength checking section position, determining a sampling position, taking the blade height direction of the turbine blade as the sampling length direction, taking the blade thickness direction as the sampling thickness direction, and taking the minimum width and thickness of a blank sample which can be taken out as the width and thickness constraints of all sampling blank samples of the whole blade;
b) cutting off the tenon part of the blade, and taking out a small-size blank sample on the turbine blade by adopting a wire cut electrical discharge machining method according to the sampling scheme determined in the step a);
c) carrying out secondary processing on the taken small-size blank sample to prepare a turbine blade micro sample, wherein the turbine blade micro sample comprises an examination gauge length section in the middle, stress transition arc sections positioned at two ends of the examination gauge length section, a loading arc section connected with the stress transition arc sections and end parts;
in the step 3), the thermocouple is fixed on an examination scale distance section of the turbine blade micro sample.
Further preferably, the turbine blade micro sample size is 30mm long × 8mm wide × 0.8mm thick, the size of the assessment gauge length section is 6mm × 3mm wide, the arc radius of the loading arc section is 10mm, and the arc radius of the stress transition arc section is 17 mm.
Further preferably, in the step 4), after the turbine blade micro sample is heated to a specified temperature, the temperature is kept for 30min, and the temperature range is 25-1300 ℃.
Compared with the prior art, the invention has the advantages that:
1. the invention adopts a small-size thin-wall sheet-shaped sampling form, can adapt to different turbine blade configurations, has better universality for the turbine blades which are solid and contain a small amount of cooling channels and complex cooling channels, the loading direction of the taken sample is along the blade height direction of the turbine blade, the sampling position is flexibly changed according to the examination position, and the real service load state of each position of the turbine blade can be simulated in the mechanical property experiment of a laboratory.
2. The test piece designed by the invention is a small-size thin-wall test piece, a check section with a certain length is reserved to ensure that the stress on the test piece is uniform in the test process, a high-precision load and displacement sensor is adopted to record the stress and strain information of the test piece, and the deformation information of the turbine blade sampling test piece can be obtained through the post-processing of test data so as to analyze the strength storage and failure behavior of the turbine blade.
3. The special fixture for the thin-wall small-size sample fixes the sample in the sample loading area of the main chuck by the interaction between the conical surfaces, the outward extending stud of the main chuck is connected with the threaded mounting end of the testing machine, complex modes such as threaded fastening and the like are avoided, mechanical property tests such as tensile property, fatigue, creep and the like can be performed at room temperature and high temperature, the operation is simple and convenient, the universality is high, and the problem that some small-size non-standard samples are difficult to directly mount and connect with the testing machine due to the undersize is solved.
Drawings
FIG. 1 is a flow chart of the sampling process of the present invention;
FIG. 2 is a schematic diagram of a high-temperature mechanical property test system for a tiny sample of a turbine blade with a complex configuration, which is disclosed by the invention;
FIG. 3(a) is a schematic diagram of a sample distribution along the blade height direction of a certain type of aeroengine turbine blade.
FIG. 3(b) is a schematic view of a sample taken from a turbine blade of an aircraft engine along a cross-section of the blade body.
FIG. 4 is a thin-walled small-sized test specimen made specifically according to the present invention.
FIG. 5 is a three-dimensional schematic view of the special fixture for the special thin-wall small-size sample of the invention.
FIG. 6 is a three-dimensional view of the clamp primary collet;
FIG. 7 is a three-dimensional view of a clamp locating pin;
FIG. 8 is a three-dimensional view of a clamp fastening ring
FIG. 9 is a cloud of stress distributions of a tailored thin-walled small-scale sample of the invention under a certain test load.
FIG. 10(a) is a tensile load-displacement curve of a small sample taken from a turbine blade of an aircraft engine of a certain type.
FIG. 10(b) is a fatigue S-N curve of a small sample taken from a turbine blade of an aircraft engine of a certain type.
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 and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides a system and a method for testing high-temperature mechanical properties of a tiny sample of a turbine blade with a complex configuration, and the following concrete implementation modes of the invention are specifically described by taking the sampling of a turbine blade of a certain type of aeroengine and the high-temperature tensile and fatigue tests of the sampled sample as examples:
referring to the sampling flow of fig. 1, the geometric characteristics of the turbine blade of this type of aircraft engine are first analyzed by taking the turbine blade in service for two overhaul periods as an example, the blade body has a height of about 40mm and a thinnest thickness of 1mm, and the blade body contains 6 internal cooling channels with different shapes, as shown in fig. 3(a) and 3 (b). The selected blade has the appraisal section of 60 percent of blade height, and the size of a sampling blank is determined to be 35mm in length, 9mm in width and 1mm in thickness according to the geometric characteristics of the blade.
According to the geometric characteristics of the cooling channel of the blade and the sweepback characteristics of the blade body, 5 sampling positions are determined, namely, the No. 2 cooling rib plate, the No. 3 cooling rib plate, the blade basin, the blade back and the trailing edge, as shown in fig. 3 (b).
Cutting blade tenons along blade roots by a medium-speed wire cut electrical discharge machining method, leaving blade body parts, cutting along 2 nd and 3 rd cooling channels to obtain a blank sample at the position of a 2 nd cooling rib plate, cutting along 3 rd and 4 th cooling channels to obtain a blank sample at the position of a 3 rd cooling rib plate, cutting along a 6 th cooling channel to obtain a blank sample at a tail edge position, and finally cutting a 5 th cooling rib plate to obtain a blank sample at a blade basin and a blade back position.
And (4) carrying out secondary high-precision fine machining on the blank samples from the first position to the fifth position according to the geometric form of the samples shown in the figure 4 by using a slow wire electrical discharge wire cutting machining method, removing burrs and defects on the surfaces of the blank samples, and manufacturing small-size thin-wall turbine blade micro samples 9.
As shown in fig. 4, the turbine blade micro sample 9 is designed to have the size of 30mm long × 8mm wide × 0.8mm thick, the size of the examination scale distance section 904 is 6mm × 3mm long, in order to enable the maximum stress to appear in the examination scale distance section 904, a stress transition circular arc section 903 is added after the loading circular arc section 902, and the circular arc radius of the loading circular arc section 902 is finally determined to be 10mm and the circular arc radius of the stress transition circular arc section 903 is finally determined to be 17mm through a parametric modeling and optimization method.
The high-temperature mechanical property test system for the small-size thin-wall sample of the turbine blade with the complex configuration provided by the invention is used for carrying out high-temperature tensile and fatigue tests on the small-size thin-wall sample of the turbine blade in service:
first, referring to fig. 2, 5, 6, 7 and 8, the box-type resistance heating furnace 6 is opened, the turbine blade micro-sample 9 is mounted in the sample mounting area 2011 of the main chuck 201 of the lower clamping unit according to the structure shown in fig. 5, two positioning pins 202 are mounted in the sample mounting area 2011 of the main chuck 201 for determining the position of the turbine blade micro-sample 9, the positioning pins 202 face the turbine blade micro-sample 9, the conical surfaces face the conical surfaces of the main chuck 201, and the fastening ring 203 is sleeved in the main chuck 201 to fasten the positioning pins 202 and the turbine blade micro-sample 9. And (3) installing the upper end of the turbine blade micro sample 9 on the upper clamping unit by adopting the same scheme, and correspondingly installing the stud 2012 of the extending end of the main chuck at the thread installation end of the material tensile testing machine 1 after the installation is finished, so as to finish the clamping of the turbine blade micro sample 9.
And secondly, fixing the contact thermocouple 7 on a gauge length section of the turbine blade micro sample 9 by using asbestos wires to monitor the temperature of the turbine blade micro sample 9 and close and seal the box type resistance heating furnace 6.
And thirdly, the temperature control box 8 controls and starts the box type resistance heating furnace 6, heats the turbine blade micro sample 9 to 850 ℃ and keeps the temperature for 30 minutes.
And fourthly, starting the material tensile testing machine 1 and the load control computer 3, controlling the material tensile testing machine 1 by the load control computer 3 to execute a preset loading program, acquiring load and displacement data of the turbine blade micro sample 9 by using the high-precision load sensor 4 and the high-precision displacement sensor 5, transmitting the load and displacement data to the load control computer 1, and judging the fracture of the turbine blade micro sample 9 as a tensile and fatigue test termination criterion.
And fifthly, after the test is finished, closing the box type resistance heating furnace 6 through the temperature control box 8, taking down the failed turbine blade micro sample 9 when the temperature of the turbine blade micro sample 9 is reduced to the room temperature, and storing the collected load displacement and the service life data of the test piece.
As shown in fig. 9, stress analysis is performed on the turbine blade micro-sample 9 of the present invention by using a finite element method, and the scale on the left side of the turbine blade micro-sample 9 distinguishes the magnitudes of the Mises stress in different color depths, and the maximum stress of the turbine blade micro-sample 9 can be found to appear in the examination scale distance section 904.
As shown in fig. 10(a), the tensile load displacement curve of the small-sized thin-walled turbine blade micro-sample 9 has obvious linear section and yield plasticity section, which shows that the result of the experimental method is reliable, and the yield strength and the tensile strength of the turbine blade micro-sample 9 can be obtained by analyzing the load displacement curve.
As shown in fig. 10(b), after the life data of the small-sized thin-walled turbine blade micro sample 9 of the turbine blade under a plurality of load states are acquired, the fatigue life S-N curve of the test piece can be obtained by fitting using the Basquin equation, which is as follows:
σ＝a·(Nf)b
where σ is the test stress, NfAnd a and b are model parameters for the fatigue life of the test piece, and can be obtained by performing least square fitting on test data.
Claims (9)
1. The high-temperature mechanical property test system for the turbine blade micro sample with the complex configuration is characterized by comprising a material tensile testing machine (1), a clamp (2), a load control system and a temperature control system, wherein the load control system comprises a load control computer (3), a load sensor (4) and a displacement sensor (5), the temperature control system comprises a box-type resistance heating furnace (6), a thermocouple (7) and a temperature control box (8), the turbine blade micro sample (9) is installed on the clamp (2), the clamp (2) is clamped on the material tensile testing machine (1), the load sensor (4), the displacement sensor (5) and the thermocouple (7) are respectively used for collecting different parameters of the turbine blade micro sample, the material tensile testing machine (1), the load sensor (4) and the displacement sensor (5) are respectively connected with the load control computer (3), the box-type resistance heating furnace (6) is arranged at the periphery of the clamp (2), and the box-type resistance heating furnace (6) and the thermocouple (7) are respectively connected with the temperature control box (8).
2. The system for testing the high-temperature mechanical property of the micro sample of the turbine blade with the complex configuration as claimed in claim 1, its characterized in that, anchor clamps (2) include two clamping unit, every clamping unit includes main chuck (201), locating pin (202) and tighrening ring (203), main chuck (201) one end surface is equipped with the through groove formula dress appearance district (2011) that cross-section and the little sample of turbine blade (9) tip shape match, and the other end is double-screw bolt (2012), and two locating pins (202) of installation match in dress appearance district (2011), and the little sample of turbine blade (9) tip clamp is between two locating pins (202), double-screw bolt (2012) be used for with material tensile testing machine (1) is connected, and tighrening ring (203) cup joints in main chuck (201) outside, and two clamping unit are from top to bottom in the opposite direction and are cliied the little sample of turbine blade (9) during the use.
3. The high-temperature mechanical property test system for the turbine blade micro specimen with the complex configuration as claimed in claim 1, wherein the load sensor (4) and the displacement sensor (5) are connected to a cross beam of the material tensile tester (1), and the thermocouple (7) is connected to the turbine blade micro specimen (9).
4. The high-temperature mechanical property test system for the small samples of the turbine blades with the complex configurations as claimed in claim 1, wherein the small samples (9) of the turbine blades comprise an examination scale distance section (904) in the middle, stress transition circular arc sections (903) positioned at two ends of the examination scale distance section (904), a loading circular arc section (902) connected with the stress transition circular arc sections (903) and end parts (901);
the turbine blade tiny sample (9) is 30mm long, 8mm wide and 0.8mm thick, the assessment gauge length section (904) is 6mm long, 3mm wide, the arc radius of the loading arc section is 10mm, and the arc radius of the stress transition arc section (903) is 17 mm.
5. The system for testing the high-temperature mechanical property of the micro sample of the turbine blade with the complex configuration as set forth in claim 1, wherein the load sensor (4) is a high-precision load sensor with the minimum resolution of 0.1N, and the displacement sensor (5) is a high-precision displacement sensor with the linearity of 0.1% and the resolution of 0.015 micrometer.
6. The method for carrying out the high-temperature mechanical property test on the tiny sample of the turbine blade with the complex configuration by using the system as claimed in claim 2 is characterized by comprising the following steps:
1) according to the sampling scheme, a small-size blank sample is taken from the turbine blade with the complex configuration, and then the small-size blank sample is subjected to secondary processing to be processed into a symmetrical hanging-piece type thin-wall turbine blade micro sample (9);
2) installing the sample processed in the step 1) into the clamp (2), opening the box-type resistance heating furnace (6), installing the clamp (2) to the threaded installation end of the material tensile testing machine (1), and completing clamping of the turbine blade micro sample (9);
3) fixing the thermocouple (7) on a turbine blade micro sample (9), closing and sealing a box type resistance heating furnace (6), and connecting the load sensor (4) and the displacement sensor (5) on a cross beam of a material tensile testing machine (1);
4) starting the box type resistance heating furnace (6) through the temperature control box (8), heating the turbine blade micro sample (9) to a certain temperature, and then preserving heat for a certain time;
5) starting the load control computer (3) and the material tensile testing machine (1), wherein the load control computer (3) executes a preset loading program on the material tensile testing machine (1), the load sensor (4) and the displacement sensor (5) collect load and displacement data of the turbine blade micro sample (9) and transmit the load and displacement data to the load control computer (3), and the test is finished after the turbine blade micro sample (9) is broken;
6) and closing the temperature control box (8), taking down the turbine blade micro sample (9) after the temperature of the turbine blade micro sample is reduced to the room temperature, and storing the load, displacement and service life data of the turbine blade micro sample (9) in the load control computer (3).
7. The method for testing the high-temperature mechanical property of the micro sample of the turbine blade with the complex configuration as claimed in claim 6, wherein the step 1) specifically comprises the following steps:
a) measuring the dimension of a geometric solid model of the turbine blade to be sampled, selecting a strength checking section position, determining a sampling position, taking the blade height direction of the turbine blade as the sampling length direction, taking the blade thickness direction as the sampling thickness direction, and taking the minimum width and thickness of a blank sample which can be taken out as the width and thickness constraints of all sampling blank samples of the whole blade;
b) cutting off the tenon part of the blade, and taking out a small-size blank sample on the turbine blade by adopting a wire cut electrical discharge machining method according to the sampling scheme determined in the step a);
c) carrying out secondary processing on the taken small-size blank sample to prepare a turbine blade micro sample (9), wherein the turbine blade micro sample comprises an examination scale distance section (904) in the middle, stress transition arc sections (903) positioned at two ends of the examination scale distance section (904), a loading arc section (902) connected with the stress transition arc sections (903) and end parts (901);
in the step 3), the thermocouple (7) is fixed on an examination scale distance section (904) of the turbine blade micro sample (9).
8. The method for testing the high-temperature mechanical property of the turbine blade micro sample with the complex configuration as claimed in claim 7, wherein the turbine blade micro sample (9) has the dimensions of 30mm in length, 8mm in width and 0.8mm in thickness, the assessment gauge length section (904) has the dimensions of 6mm in length, 3mm in width, the loading arc section has the arc radius of 10mm, and the stress transition arc section (903) has the arc radius of 17 mm.
9. The method for testing the high-temperature mechanical property of the turbine blade micro sample with the complex configuration as claimed in claim 6, wherein in the step 4), the turbine blade micro sample (9) is heated to the specified test temperature and then is kept for 30min, and the temperature range is 25-1300 ℃.
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| CN112525736A (en) * | 2021-02-08 | 2021-03-19 | 中国航发上海商用航空发动机制造有限责任公司 | Fan blade cantilever beam element level strength test method |
| CN112903274A (en) * | 2021-02-02 | 2021-06-04 | 沈阳航空航天大学 | Turbine blade temperature cycle load test equipment |
| CN112903276A (en) * | 2021-02-02 | 2021-06-04 | 沈阳航空航天大学 | Open turbine blade test equipment |
| CN113640140A (en) * | 2021-07-28 | 2021-11-12 | 南京航空航天大学 | High-temperature double-shaft strength tester and method for ceramic matrix composite turbine guide vane |
| CN115114733A (en) * | 2022-07-22 | 2022-09-27 | 中国航发沈阳发动机研究所 | Multi-level test verification method for service life of turbine blade coating |
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| CN112903274A (en) * | 2021-02-02 | 2021-06-04 | 沈阳航空航天大学 | Turbine blade temperature cycle load test equipment |
| CN112903276A (en) * | 2021-02-02 | 2021-06-04 | 沈阳航空航天大学 | Open turbine blade test equipment |
| CN112525736A (en) * | 2021-02-08 | 2021-03-19 | 中国航发上海商用航空发动机制造有限责任公司 | Fan blade cantilever beam element level strength test method |
| CN113640140A (en) * | 2021-07-28 | 2021-11-12 | 南京航空航天大学 | High-temperature double-shaft strength tester and method for ceramic matrix composite turbine guide vane |
| CN113640140B (en) * | 2021-07-28 | 2022-06-17 | 南京航空航天大学 | High-temperature double-shaft strength tester and method for ceramic matrix composite turbine guide vane |
| US11644382B2 (en) | 2021-07-28 | 2023-05-09 | Nanjing University Of Aeronautics And Astronautics | High-temperature biaxial strength tester for ceramic matrix composite (CMC) turbine vane and test method thereof |
| CN115114733A (en) * | 2022-07-22 | 2022-09-27 | 中国航发沈阳发动机研究所 | Multi-level test verification method for service life of turbine blade coating |
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