CN111060271A - Dynamic test method for vibration stress of turbine blade of small turbine engine - Google Patents
Dynamic test method for vibration stress of turbine blade of small turbine engine Download PDFInfo
- Publication number
- CN111060271A CN111060271A CN201911040466.3A CN201911040466A CN111060271A CN 111060271 A CN111060271 A CN 111060271A CN 201911040466 A CN201911040466 A CN 201911040466A CN 111060271 A CN111060271 A CN 111060271A
- Authority
- CN
- China
- Prior art keywords
- test
- blade
- strain gauge
- strain
- turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to a dynamic test method for vibration stress of a turbine blade of a small turbine engine, and relates to the technical field of turbine engines. According to the invention, through formulation of a test scheme, dynamic measurement of the vibration stress of the turbine blade is realized under the conditions that the highest rotating speed of an engine is 50000r/min and the working temperature of the turbine blade is higher than 850 ℃, wherein the survival rate of the strain gauge is improved under severe working environment through reasonable layout and laying mode of the strain gauge and reliable connection of leads.
Description
Technical Field
The invention relates to the technical field of turbine engines, in particular to a dynamic test method for vibration stress of turbine blades of a small turbine engine.
Background
The small turbine engine is a main power device of the cruise missile, can provide thrust, electric power and compressed air required by cruise flight for the missile, and is a high-speed rotating machine with advanced performance and complex structure. The working principle and the main structure of the small turbine engine are similar to those of an aircraft engine, but the small turbine engine still has differences in structure and technical characteristics, and is mainly represented as follows:
1) the small turbine engine has compact structure and small size, and provides challenges for component design, processing and test technologies;
2) the rotating speed of a small turbine engine reaches tens of thousands r/min, and a rotor system faces complex strength and vibration problems;
3) small turbine engines operate for short periods of time and are therefore more likely to take full advantage of the potential of existing materials and to adopt a more compact and lightweight construction.
Turbine blades are important parts of small turbine engines and work in severe environments such as high temperature, high rotational speed and strong vibration. Turbine blade failure is a common failure of engines, and during engine development, blade failure often occurs and the mechanism is complex. In order to thoroughly explain the failure mechanism of the blade fracture, key information such as the resonance rotating speed, the resonance frequency, the vibration mode and the like of the turbine blade can be obtained by carrying out dynamic measurement on the vibration stress of the turbine blade, and data support is provided for the research on the failure mechanism of the turbine blade; a feasible technical approach is provided for solving the fracture fault of the turbine blade.
Dynamic measurement of the vibration stress of the turbine blade is carried out by using a core machine or a whole engine; that is, the engine is fully disassembled, a test measuring device (slip ring current lead) is installed, a sufficient strain gauge is laid on the turbine blade, the strain gauge is connected with the test measuring device through a lead, and vibration information of the turbine blade is continuously obtained through a signal output by the test measuring device in a test process after a core machine or a whole engine is assembled. In order to reduce research cost and reduce development risk, a core machine is generally adopted to replace a whole engine to develop dynamic measurement of the vibration stress of the turbine blade.
In order to solve the blade fracture fault, part of domestic work is carried out on aspects such as blade vibration stress dynamic test and the like. At present, the rotation speed of the vibration stress test developed in China is lower, generally lower than 30000r/min and far lower than the working rotation speed of a small turbine engine, and the shortage of the vibration stress test developed under the working conditions of high rotation speed and high temperature still has a certain difference with the foreign test level.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: a turbine blade vibration stress dynamic test method is provided for a small turbine engine with the working speed higher than 50000r/min and the turbine blade working temperature higher than 850 ℃.
(II) technical scheme
In order to solve the technical problem, the invention provides a turbine blade vibration stress dynamic test method for a small turbine engine, which comprises the following steps:
carrying out formal tests: firstly, a high-pressure turbine blade vibration stress measurement system is built, in the test process, a strain gauge on the high-pressure turbine blade is used for detecting deformation of the blade, then the strain gauge transmits a detected signal to a slip ring electricity leading device, and then the slip ring electricity leading device transmits the signal to a data acquisition system for analysis and processing so as to obtain key data required in the test process, wherein the key data comprise turbine blade vibration modes, frequency, stress values and resonance rotating speed information in a working rotating speed range.
Preferably, in the measurement and construction process, the layout mode of the strain gauge is determined by combining numerical simulation and blade vibration fatigue test: selecting 12 blades in the high-pressure turbine rotor, laying a strain gauge on each blade in a flame spraying mode, wherein each 4 blades are a group of blades in one position and are A, B, C, wherein A, B, C represents three laying positions of the strain gauge and is a position where the vibration strain is larger than a preset threshold value under a resonance condition.
Preferably, A is the height of the blade at the exhaust edge 2/3 of the blade back, B is the position of the exhaust edge of the blade back which is 5mm or less from the blade root, C is the middle position of the root of the blade back, and two lead positions are reserved for wiring after the strain gauge is laid on the blade.
Preferably, after the strain gauge is laid on the blade 2, the blade is assembled on a high-pressure turbine disc, one end of a high-temperature-resistant wire is connected with the strain gauge, one end of the high-temperature-resistant wire is wired according to a wiring path, penetrates through the whole turbine component, penetrates through a high-pressure shaft after penetrating through the turbine component and is connected with the slip ring electricity-leading device 1, and after the line connection is complete, the slip ring electricity-leading device 1 can obtain vibration information of the blade 2 in real time in the test process, so that the whole signal acquisition and transmission process is realized.
Preferably, the process of analyzing and processing by the data acquisition system comprises: and the data acquisition system corrects the sensitivity, the measurement lead and the elastic modulus according to the acquired strain quantity and calculates a vibration stress value.
Preferably, the process of analyzing and processing by the data acquisition system specifically includes:
the strain gauge stress calculation formula is as follows:
σ＝Eε
wherein E is the elastic modulus, epsilon is the strain value, and sigma is the stress value;
and correcting the measured strain value according to the actual sensitivity coefficient of the strain gauge, wherein the correction formula is as follows:
wherein epsilon/For correction of strain as a function of sensitivity, eiFor strain measurements, kiSensitivity of the data acquisition System, kTFor the sensitivity of the strain gauge at different temperatures T, the measured values are corrected, namely:
where ε is the strain value corrected by the sensitivity and measurement lead, rLMeasuring the resistance of the lead for each strain gauge, wherein R is the resistance of the strain gauge;
under high temperature, the elastic modulus changes with temperature, and the following are:
Preferably, a system debugging test is further included before the formal test:
firstly, debugging and pre-testing a multi-wheel core machine system are carried out under the conditions that strain gauges are not laid and slip ring electricity-leading devices are not installed, the rotor of the tester is ensured to reach a preset test rotating speed, and the over-temperature, over-rotation and surging are avoided in the test process.
Preferably, the method further comprises the following test scheme research before the system debugging test:
a) determining the working rotating speed range of the core engine tester as the range covering the working rotating speed of the core engine of the engine, stably working in the range, and avoiding abnormal working states such as overtemperature, overturning, surging, flameout and the like;
b) the air flow parameters of the air compressor inlet and the high-pressure turbine outlet of the core machine tester are consistent with or close to the air flow parameters of the high-pressure air compressor inlet and the high-pressure turbine outlet of the engine;
c) determining the reasonable layout of the strain gauges by combining numerical simulation and a blade vibration fatigue test, and laying the strain gauges on the high-pressure turbine blades in a flame spraying mode in a formal test;
d) the influence of the swinging amount on the reliability of the lead of the strain gauge is eliminated by adopting a locking plate jacking mode.
(III) advantageous effects
According to the invention, through formulation of a test scheme, dynamic measurement of the vibration stress of the turbine blade is realized under the conditions that the highest rotating speed of an engine is 50000r/min and the working temperature of the turbine blade is higher than 850 ℃, wherein the survival rate of the strain gauge is improved under severe working environment through reasonable layout and laying mode of the strain gauge and reliable connection of leads.
Drawings
FIG. 1 is a general schematic of the test method of the present invention;
FIG. 2 is a block diagram of a vibration stress testing system constructed according to the present invention;
FIG. 3 is a schematic diagram of a layout of a strain gage according to the present invention;
FIG. 4 is a schematic diagram of a wiring method after a strain gauge is laid on a blade;
FIG. 5 is a schematic diagram showing the relationship between the slip ring current lead, the blade and the lead;
FIG. 6 is a three-dimensional vibration waterfall plot of strain gage test data;
fig. 7 is a graph of strain distribution over various frequencies.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
The invention provides a turbine blade vibration stress dynamic test method by applying the current test equipment and test means aiming at a small turbine engine with the working speed higher than 50000r/min and the turbine blade working temperature higher than 850 ℃, measures the turbine blade vibration stress through a core dynamic test, provides test data support for clarifying the turbine blade fracture mechanism, and provides a feasible technical approach for solving the turbine blade fracture fault.
The flow of the dynamic test method for the vibration stress of the turbine blade of the small turbine engine is shown in figure 1, and the dynamic test method comprises 6 steps of researching a test scheme, formulating a test outline, carrying out a system debugging test, carrying out a formal test, processing test data and forming a final test report; the formal test can be further adjusted according to the condition of the system debugging test, so that the effectiveness and the reliability of the test are ensured.
Step one, research of test scheme
Because the core machine tester does not have low-pressure systems such as a fan, a low-pressure turbine and the like, the inlet airflow environment of the high-pressure compressor and the outlet airflow environment of the high-pressure turbine are different from those of a real engine, and the thermal environment and the flowing environment of the turbine blades are also different from those of the real engine; the maximum rotating speed of the engine is 50000r/min, the working temperature of the turbine blade is higher than 850 ℃, and great tests are provided for reasonable layout and laying of the turbine blade strain gauges and reliability of the strain gauges and lead wires of the testing equipment under the conditions. In order to obtain a relatively real vibration stress, research on a core machine test simulation method and research on the laying of strain gauges and the reliability of leads need to be carried out:
a) the working rotating speed range of the core engine tester covers the working rotating speed range of the core engine of the engine, the core engine tester stably works in the range, and abnormal working states such as overtemperature, overturning, surging, flameout and the like cannot occur;
b) the air flow parameters of the inlet of the compressor and the outlet of the high-pressure turbine of the core machine tester are consistent with or close to the air flow parameters of the inlet of the high-pressure compressor and the outlet of the high-pressure turbine of the engine;
c) determining the reasonable layout of the strain gauge by combining numerical simulation and blade vibration fatigue test, and laying the strain gauge on the high-pressure turbine blade by adopting a flame spraying mode;
d) the turbine blade is connected with the turbine disc through the joggle structure, so that a certain swinging amount exists between the turbine blade and the wheel disc, and the influence of the swinging amount on the reliability of the lead of the strain gauge is eliminated by adopting a locking plate jacking mode.
Second, making a test outline
The test outline specifies relevant contents such as test pieces, measurement parameter requirements, test preparation and requirements, test schemes, test programs, abnormal condition handling plans and the like of system debugging tests and formal tests in detail.
Thirdly, carrying out a system debugging test
Because the high-pressure turbine blade vibration stress core maneuvering test has large risk and high cost (the strain gauge is expensive), in order to ensure the success of the test, firstly, the debugging and the pre-test of a multi-wheel core machine system are carried out under the condition that the strain gauge is not laid and test equipment (a slip ring electrical leading device) is not installed, the control strategy and the test method of the core machine tester are groped and verified, the rotor of the tester is ensured to reach the preset test rotating speed, the overtemperature, the overturning and the surging are avoided in the test process, and the relation between the control parameters such as the total pressure of incoming flow, the flow of fuel oil, the exhaust back pressure regulating mechanism and the rotating speed of the rotor of the tester is obtained.
On the basis, the control model is solidified into the control software, so that the rapid adjustment is realized, the test time is shortened, the high-temperature strain gauge in the formal test process is ensured to have higher survival rate, and more and reliable test data are obtained. The core machine measurement parameters include total temperature and total pressure of the air flow for measuring the key section of the core machine tester, the rotor speed of the core machine tester, and the like, as shown in table 1.
TABLE 1 complete machine performance measurement parameter table of core machine tester
Fourthly, carrying out formal test
Firstly, a high-pressure turbine blade vibration stress measuring system is built for a formal test, and a block diagram of the high-pressure turbine blade vibration stress measuring system is shown in FIG. 2. In the test process, firstly, a strain gauge on a high-pressure turbine blade is used for detecting the deformation of the blade, then the strain gauge transmits a detected signal to a slip ring electricity leading device, the slip ring electricity leading device transmits the signal to a data acquisition system for analysis and processing so as to obtain key data required by the test process, wherein the key data comprises key information such as the vibration mode, the frequency, the stress value, the resonance rotating speed and the like of the turbine blade in the working rotating speed range, the data is recorded in the whole process of the test, the channel sampling frequency and the strain test equipment are selected according to the test requirements, and the measurement error is generally required to be +/-0.5%.
In the system building process, the layout mode of the strain gauges is determined by combining numerical simulation and a blade vibration fatigue test, as shown in fig. 3, 12 blades are selected from a high-pressure turbine rotor, each blade is provided with one strain gauge in a flame spraying mode, every 4 blades are a group of blades with one position, namely one position corresponding to fig. 3 is A, B, C, wherein A, B, C is the position where the strain gauge is provided, is the position where the vibration strain is large under the resonance condition, specifically, A is the position at the blade back exhaust edge 2/3 blade height, B is the position at the blade back exhaust edge 5mm away from the blade root or below, C is the middle position of the blade back root, and two lead positions are reserved for wiring after the strain gauges are provided on the blades (for example, indicated by arrows in fig. 4).
The relationship among the slip ring current lead 1, the blades 2 and the lead 3 is shown in fig. 5, wherein the blades 2 are assembled on a high-pressure turbine disc after being provided with strain gauges, one end of each high-temperature-resistant wire is connected with the strain gauge, the other end of each high-temperature-resistant wire is wired according to the wiring path in fig. 4, penetrates through the whole turbine component, penetrates through the turbine component, penetrates through a high-pressure shaft according to the route of the lead 3 in fig. 5, and is connected with the slip ring current lead 1. After the circuit connection is complete, the slip ring current leading device 1 can obtain vibration information of the blade 2 in real time in the test process, and the whole signal acquisition and transmission process is realized.
Fifth step, processing test data
And the data acquisition system corrects the sensitivity, the measurement lead and the elastic modulus according to the acquired strain quantity and calculates a vibration stress value.
The strain gauge stress calculation formula is as follows:
σ＝Eε
wherein E is the elastic modulus under the high-temperature condition, epsilon is the strain value, and sigma is the stress value;
and correcting the measured strain value according to the actual sensitivity coefficient of the high-temperature strain gauge, wherein the correction formula is as follows:
wherein epsilon/For correction of strain as a function of sensitivity, eiFor strain measurements, kiSensitivity of the data acquisition System, kTFor the sensitivity of the strain gauge at different temperatures T, the resistivity of the high-temperature-resistant alloy wire under the high-temperature condition is high, and the measured value needs to be corrected, namely:
where ε is the strain value, r, corrected by the sensitivity and measurement leadLMeasuring the resistance of the wire for a single strain gage, R beingAnd (4) changing the sheet resistance.
Under high temperature, the elastic modulus changes with temperature, and the following are:
step six, forming a test report according to the step one to the step five
By researching and applying the test method, the invention successfully obtains key information such as the vibration mode, the frequency, the stress amplitude, the resonance rotating speed and the like of the turbine blade in the working rotating speed range. The three-dimensional vibration waterfall plot 6 of the strain gage test data shows the distribution of strain at each frequency as shown in fig. 7.
The turbine blade vibration stress dynamic test verifies that the dangerous excitation frequency doubling causing turbine blade resonance is measured by the method. The improvement direction is provided for the improvement of the turbine structure of the long-life small turbine engine.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (9)
1. A dynamic test method for vibration stress of a turbine blade of a small turbine engine is characterized by comprising the following steps:
carrying out formal tests: firstly, a high-pressure turbine blade vibration stress measurement system is built, in the test process, a strain gauge on the high-pressure turbine blade is used for detecting deformation of the blade, then the strain gauge transmits a detected signal to a slip ring electricity leading device, and then the slip ring electricity leading device transmits the signal to a data acquisition system for analysis and processing so as to obtain key data required in the test process, wherein the key data comprise turbine blade vibration modes, frequency, stress values and resonance rotating speed information in a working rotating speed range.
2. The method according to claim 1, wherein in the measurement building process, the layout mode of the strain gauge is determined by combining numerical simulation and blade vibration fatigue test: selecting 12 blades in the high-pressure turbine rotor, laying a strain gauge on each blade in a flame spraying mode, wherein each 4 blades are a group of blades in one position and are A, B, C, wherein A, B, C represents three laying positions of the strain gauge and is a position where the vibration strain is larger than a preset threshold value under a resonance condition.
3. The method of claim 2, wherein a is the leaf height of the blade back exhaust edge 2/3, B is the position of the blade back exhaust edge 5mm or less from the blade root, and C is the middle position of the blade back root, and two lead locations are left for wiring after the strain gauge is applied to the blade.
4. The method as claimed in claim 3, wherein the blade 2 is assembled on a high-pressure turbine disc after the strain gauge is laid, one end of the high-pressure turbine disc is connected with the strain gauge by using a high-temperature-resistant wire, the other end of the high-pressure turbine disc is wired according to a routing path, penetrates through the whole turbine part, penetrates through a high-pressure shaft after penetrating through the turbine part and is connected with the slip ring electricity-leading device (1), and after the circuit is connected completely, the slip ring electricity-leading device (1) can obtain vibration information of the blade (2) in real time in a test process, so that the whole signal obtaining and transmitting process is.
5. The method of claim 4, wherein the analyzing process performed by the data acquisition system comprises: and the data acquisition system corrects the sensitivity, the measurement lead and the elastic modulus according to the acquired strain quantity and calculates a vibration stress value.
6. The method of claim 5, wherein the analyzing and processing performed by the data acquisition system specifically comprises:
the strain gauge stress calculation formula is as follows:
σ＝Eε
wherein E is the elastic modulus, epsilon is the strain value, and sigma is the stress value;
and correcting the measured strain value according to the actual sensitivity coefficient of the strain gauge, wherein the correction formula is as follows:
wherein epsilon/For correction of strain as a function of sensitivity, eiFor strain measurements, kiSensitivity of the data acquisition System, kTFor the sensitivity of the strain gauge at different temperatures T, the measured values are corrected, namely:
where ε is the strain value corrected by the sensitivity and measurement lead, rLMeasuring the resistance of the lead for each strain gauge, wherein R is the resistance of the strain gauge;
under high temperature, the elastic modulus changes with temperature, and the following are:
7. The method of claim 6, further comprising, prior to the official testing, a system commissioning test:
firstly, debugging and pre-testing a multi-wheel core machine system are carried out under the conditions that strain gauges are not laid and slip ring electricity-leading devices are not installed, the rotor of the tester is ensured to reach a preset test rotating speed, and the over-temperature, over-rotation and surging are avoided in the test process.
8. The method of claim 7, further comprising, prior to the system commissioning test, a test protocol study:
a) determining the working rotating speed range of the core engine tester as the range covering the working rotating speed of the core engine of the engine, stably working in the range, and avoiding abnormal working states such as overtemperature, overturning, surging, flameout and the like;
b) the air flow parameters of the air compressor inlet and the high-pressure turbine outlet of the core machine tester are consistent with or close to the air flow parameters of the high-pressure air compressor inlet and the high-pressure turbine outlet of the engine;
c) determining the reasonable layout of the strain gauges by combining numerical simulation and a blade vibration fatigue test, and laying the strain gauges on the high-pressure turbine blades in a flame spraying mode in a formal test;
d) the influence of the swinging amount on the reliability of the lead of the strain gauge is eliminated by adopting a locking plate jacking mode.
9. The method of claim 6, further comprising the step of forming a test report after the data analysis process is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911040466.3A CN111060271A (en) | 2019-10-29 | 2019-10-29 | Dynamic test method for vibration stress of turbine blade of small turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911040466.3A CN111060271A (en) | 2019-10-29 | 2019-10-29 | Dynamic test method for vibration stress of turbine blade of small turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111060271A true CN111060271A (en) | 2020-04-24 |
Family
ID=70297601
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911040466.3A Pending CN111060271A (en) | 2019-10-29 | 2019-10-29 | Dynamic test method for vibration stress of turbine blade of small turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111060271A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112049695A (en) * | 2020-08-28 | 2020-12-08 | 湖南天雁机械有限责任公司 | Detection device and method for high-cycle fatigue test of supercharger impeller and turbine |
| CN112431686A (en) * | 2020-11-20 | 2021-03-02 | 北京动力机械研究所 | A culvert spray tube for high pressure turbine blade vibration stress measurement tester |
| CN112446146A (en) * | 2020-11-20 | 2021-03-05 | 北京动力机械研究所 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
| CN113565583A (en) * | 2021-07-19 | 2021-10-29 | 中国航发沈阳发动机研究所 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
| CN113844677A (en) * | 2021-10-25 | 2021-12-28 | 中国航发沈阳发动机研究所 | Axial lead structure for measuring dynamic stress of whole high-pressure turbine of turbofan engine |
| CN114243403A (en) * | 2021-12-13 | 2022-03-25 | 中国船舶重工集团公司第七0三研究所 | Variable-diameter lead device for gas turbine hollow wheel disc rotation test |
| CN114717505A (en) * | 2022-03-21 | 2022-07-08 | 北京动力机械研究所 | High-temperature strain gauge lead laying method for measuring vibration stress of turbine blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2261614A1 (en) * | 2009-06-12 | 2010-12-15 | Mechanical Solutions Inc. | Combined amplitude and frequency measurements for non-contacting turbomachinery blade vibration |
| CN205015110U (en) * | 2015-04-30 | 2016-02-03 | 中国航空动力机械研究所 | Installation device is measured to aeroengine's compressor blade dynamic stress |
| CN105388004A (en) * | 2015-10-22 | 2016-03-09 | 西安航空动力股份有限公司 | Aeroengine blisk safe excess-revolution testing system and method |
| CN109883389A (en) * | 2019-03-22 | 2019-06-14 | 西安交通大学 | A kind of rotating vane dynamic strain field measurement method and its system |
-
2019
- 2019-10-29 CN CN201911040466.3A patent/CN111060271A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2261614A1 (en) * | 2009-06-12 | 2010-12-15 | Mechanical Solutions Inc. | Combined amplitude and frequency measurements for non-contacting turbomachinery blade vibration |
| CN205015110U (en) * | 2015-04-30 | 2016-02-03 | 中国航空动力机械研究所 | Installation device is measured to aeroengine's compressor blade dynamic stress |
| CN105388004A (en) * | 2015-10-22 | 2016-03-09 | 西安航空动力股份有限公司 | Aeroengine blisk safe excess-revolution testing system and method |
| CN109883389A (en) * | 2019-03-22 | 2019-06-14 | 西安交通大学 | A kind of rotating vane dynamic strain field measurement method and its system |
Non-Patent Citations (1)
| Title |
|---|
| 吴学岗: "航空发动机涡轮叶片动应力测量技术研究", 《中国优秀硕士学位论文全文数据库 工程科技II辑》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112049695A (en) * | 2020-08-28 | 2020-12-08 | 湖南天雁机械有限责任公司 | Detection device and method for high-cycle fatigue test of supercharger impeller and turbine |
| CN112431686A (en) * | 2020-11-20 | 2021-03-02 | 北京动力机械研究所 | A culvert spray tube for high pressure turbine blade vibration stress measurement tester |
| CN112446146A (en) * | 2020-11-20 | 2021-03-05 | 北京动力机械研究所 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
| CN112446146B (en) * | 2020-11-20 | 2023-11-03 | 北京动力机械研究所 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
| CN113565583A (en) * | 2021-07-19 | 2021-10-29 | 中国航发沈阳发动机研究所 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
| CN113565583B (en) * | 2021-07-19 | 2022-08-19 | 中国航发沈阳发动机研究所 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
| CN113844677A (en) * | 2021-10-25 | 2021-12-28 | 中国航发沈阳发动机研究所 | Axial lead structure for measuring dynamic stress of whole high-pressure turbine of turbofan engine |
| CN113844677B (en) * | 2021-10-25 | 2024-03-19 | 中国航发沈阳发动机研究所 | Axial lead structure for dynamic stress measurement of whole high-pressure turbine of turbofan engine |
| CN114243403A (en) * | 2021-12-13 | 2022-03-25 | 中国船舶重工集团公司第七0三研究所 | Variable-diameter lead device for gas turbine hollow wheel disc rotation test |
| CN114243403B (en) * | 2021-12-13 | 2024-04-02 | 中国船舶重工集团公司第七0三研究所 | Variable diameter lead device for rotation test of hollow wheel disc of gas turbine |
| CN114717505A (en) * | 2022-03-21 | 2022-07-08 | 北京动力机械研究所 | High-temperature strain gauge lead laying method for measuring vibration stress of turbine blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111060271A (en) | Dynamic test method for vibration stress of turbine blade of small turbine engine | |
| KR101503669B1 (en) | A diagnostic system and method for monitoring operating conditions of components of a turbine machine | |
| CN102507205B (en) | Method for checking vibration fault of fan blade of aerial engine | |
| CN110717219B (en) | Method and device for acquiring inlet flow of air compressor in complete machine state of aero-engine | |
| EP2705221B1 (en) | Method for predicting a remaining useful life of an engine and components thereof | |
| CN108731896B (en) | Vibration monitoring device for movable blade of gas turbine compressor | |
| US10677088B2 (en) | Wireless monitoring system for rotary machines | |
| CN110686764A (en) | Method for measuring asynchronous vibration frequency of constant-speed blade based on full-phase difference principle | |
| CN103775139A (en) | Gap control system and method for turbine engine | |
| EP2492657A1 (en) | Method and apparatus for calibrating a torque measurement | |
| CN102944789B (en) | A kind of fanjet complete machine electrical system Gernral Check-up device and method | |
| CN113776571A (en) | Online calibration method for thermal monitoring instrument of power plant | |
| CN102095561B (en) | Falling fault positioning method for rotating part of large-size steam turbine | |
| US5517852A (en) | Diagnostic performance testing for gas turbine engines | |
| CN212254562U (en) | Vibration monitoring system for moving blade of steam turbine | |
| CN115950639B (en) | Dynamic stress test line switching method for disc separation fan rotor blade | |
| KR20170028121A (en) | Model Calibration Apparatus for Power Facilities using Power System Disturbance Data and method thereof | |
| CN108760329B (en) | Low-pressure turbine noise test method and improvement method thereof | |
| US9897431B2 (en) | Edge detector | |
| KR20150071068A (en) | Centerfugal stress test device for turbine blades | |
| CN109341771B (en) | Pressure and temperature loss measuring method of pipeline working medium based on generator | |
| CN110441054A (en) | Rotating machinery shafting misaligns fault condition detection method under shaft coupling connection status | |
| CN216483953U (en) | Test system for reliability of engine telemetering instrument | |
| CN115342897A (en) | Steam turbine generator unit torsional vibration measuring system and measuring method thereof | |
| CN115560888A (en) | Axial force measuring method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200424 |