CN110260919B - Method for simultaneously measuring temperature and strain of turbine blade tip - Google Patents
Method for simultaneously measuring temperature and strain of turbine blade tip Download PDFInfo
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- CN110260919B CN110260919B CN201910537019.2A CN201910537019A CN110260919B CN 110260919 B CN110260919 B CN 110260919B CN 201910537019 A CN201910537019 A CN 201910537019A CN 110260919 B CN110260919 B CN 110260919B
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- 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
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention discloses a method for simultaneously measuring the temperature and the strain of the tip of a turbine blade, and belongs to the technical field of aeroengine measurement. Blade rotating speed information and blade tip radiation information are measured through an optical probe for collecting radiation information and a rotating speed synchronous sensor at the end part of a rotating shaft, a blade tip radiation pulse waveform in a period is obtained through later data processing, and a radiation value of a low level is substituted into a black body furnace for calibration and then the blade tip temperature is obtained through a V-K function relation corrected through two-point calibration. The blade tip strain is measured by measuring the period of a low-level signal, calculating the length of the strained blade tip to be compared with the original length, and substituting the length into a strain measurement formula. The blade tip radiation information is collected through the optical probe, the waveform period and amplitude information are fully utilized, the simultaneous measurement of the blade tip strain and temperature is realized, a practical and powerful basis is provided for analyzing the thermal load of the turbine blade in real time, and the normal operation of an engine is ensured.
Description
Technical Field
The invention belongs to the technical field of aeroengine measurement, and discloses a method for simultaneously measuring the temperature and the strain of a turbine blade tip.
Background
With the increasing thrust-weight ratio of the aero-engine, the inlet temperature of the turbine rises continuously, and the inlet temperature of the turbine blade reaches 2000-2250K at most at present. The turbine blade of the aero-engine bearing the composite action of high temperature, high rotating speed, complex aerodynamic exciting force and larger centrifugal load is easy to break and break, thereby causing serious accidents of the engine and the airplane. With the improvement of the technical level of the low-cycle fatigue basic test, the main failure mode of the turbine blade of the engine is converted from the traditional static strength failure into the vibration fatigue failure at high temperature, and in order to ensure that the turbine blade works in a normal working state, the temperature and vibration stress measurement of the turbine blade must be carried out. Therefore, extensive research is carried out at home and abroad. Firstly, for the temperature measurement of the turbine blade, the traditional contact type temperature measurement method needs the sensor to be in contact with a measured element, a target surface temperature field is damaged, and the sensor is extremely easy to damage in an extremely complex gas environment for a long time. In the prior art of strain measurement, telemetry or slip ring resistance strain gauges are the most widely used methods, but the range of application of this technique is limited to around 700 degrees due to thermal drift and meter attachment issues. And the strain gauge is time-consuming and labor-consuming to install, the service life is short, the load and the volume of the sensor can influence the aerodynamic characteristics of the blade, and the like, so that the application of the technology is greatly limited. The traditional contact temperature and strain measurement method also has the problem of difficult lead wire.
Disclosure of Invention
The invention aims to solve the technical problem that the temperature and the strain of the tip of the turbine blade are simultaneously monitored by adopting an optical monitoring method, and the thermal load and the vibration fatigue condition of the turbine blade under the actual working condition are analyzed in real time. The measuring device comprises an optical probe fixedly arranged on a casing cover for collecting radiation signals, a rotating speed synchronous sensor arranged at the end part of a rotating shaft, a refrigeration type detector module for realizing photoelectric sensing, a circuit amplification module for realizing circuit signal processing and a rear-end data processing module. An optical probe is adopted to go deep into a casing to collect radiation information in real time, the radiation information is transmitted to a photoelectric sensor through an optical fiber to be converted into an electric signal, subsequent data processing is carried out, and the output signal of a rotating speed synchronous sensor is combined to obtain the tip temperature and strain information of the turbine blade.
The principle of temperature measurement to be realized by the invention is as follows: the corresponding relation between the radiation voltage and the temperature of the black body is calibrated by adopting a standard black body furnace, the variation caused by the distance and the emissivity is calibrated by two points on the line, the V-K function relation is corrected, during actual test, the radiation voltage of the blade is measured by a detector, and the radiation voltage is substituted into the calibrated V-K function relation to obtain the actual temperature of the measured target.
The principle of strain measurement to be realized by the invention is as follows: the turbine blade rapidly rotates under the impact of high-temperature gas, an optical probe arranged on a casing receives heat radiation from a rotating blade and the high-temperature gas, the temperature of the gas is much higher than that of the blade, when the measured blade passes through the optical probe, the received light intensity can obviously change, a detector obtains a group of pulse waveforms changing along with time, the time of the blade tip of each blade passing through the probe is obtained according to the waveforms, the blade rotating speed and the period obtained by combining rotating speed synchronous signals are combined, the length of the blade tip is calculated, and the blade tip length and the original blade tip length measured under the condition of no strain are substituted into a strain calculation formula together to obtain the strain condition of the blade tip.
Therefore, the technical scheme of the invention is as follows: a method of simultaneously measuring turbine blade tip temperature and strain, the method comprising:
step 1: calibrating a corresponding curve of blackbody radiation voltage and temperature by adopting a standard blackbody furnace under the line, and correcting the curve;
step 2: measuring by a rotating speed synchronous sensor to obtain a rotating speed pulse waveform, and calculating a pulse period T;
and step 3: measuring the radiation voltage of the tip of the turbine blade after the turbine blade is filled with fuel gas at the initial stage of operation through an optical probe to obtain an original pulse waveform, calculating the time t0 of low level, and calculating the original width of the blade tip
R is the rotating radius of the blade;
and 4, step 4: when the engine actually runs, the radiation voltage of the tip of the turbine blade is collected in real time through an optical probe, the pulse waveform comprises the radiation voltage V of the blade tip and the fuel gas, and the low-level time t1 … tn;
and 5: substituting the radiation voltage low level signal obtained in the step 4 into the V-K function relation corrected in the step 1, and calculating the actual temperature K of the blade tip;
step 6: substituting the low level time t1 … tn obtained in the step 4 into the formula in the step 3, and calculating to obtain the blade tip width L of each blade1…Ln；
And 7: and (3) substituting each blade tip length obtained in the step (6) and the blade tip original length obtained in the step (3) into the following strain measurement formula:
and 8: sampling the strain epsilon of the blade tip of the turbine blade to obtain the comprehensive strain epsilonFinal i
Further, the specific method in step 1 is as follows:
sequentially heating the black body furnace at the step length of 1 ℃, stabilizing for half an hour after each heating, measuring the radiation voltage of the temperature point by using an optical probe to obtain n groups of voltage-temperature information, and obtaining a V0-K0 relation curve by using 1stopt fitting, wherein V0 represents the radiation voltage, and K0 represents the temperature; and then arranging a plurality of temperature acquisition points on the surface of the blade by a thermocouple, acquiring the temperature of the acquisition points by the thermocouple under the working condition, acquiring the radiation voltage at the sampling points by an optical probe, sampling a plurality of groups of radiation voltages corresponding to the temperatures under the working condition, taking two linear equations consisting of the radiation voltages of the highest temperature point and the lowest temperature point in the data acquired under the working condition and the radiation voltages of the two temperature points corresponding to the black body furnace, calculating a conversion coefficient of the radiation equation of the black body furnace changing to the radiation equation of the thermocouple, and correcting the obtained V0-K0 curve by the coefficient to obtain the corrected V-K relation.
Further, the sampling method of the step 8 is;
step 8.1: firstly, randomly selecting a strain as an initial epsilon within a first pulse period T0；
Step 8.2: x (ε) is selected in the next 1000m pulses0)＝|8000(0.005-ε0) L strain, where m represents the number of pulses in 1 pulse period, | · | represents the rounding, and the selected strains are averaged to obtain the comprehensive strain epsilonFinal 1Epsilon to be obtainedFinal 1Outputting in real time;
step 8.3: x (epsilon) is selected in every 1000m pulses that followFinal i-1)＝|8000(0.005-εFinal i-1) I strains are selected, then the selected strains are averaged to obtain the comprehensive strain epsilon at the momentFinal iEpsilon to be obtainedFinal iAnd outputting in real time.
The invention adopts an optical probe to go deep into a casing to measure the radiation of the blade tip of the turbine blade and the radiation pulse waveform of the fuel gas, and because the fuel gas temperature and the blade tip temperature have obvious difference, the blade information is separated according to the difference, and the low-level blade radiation voltage signal is substituted into the V-K function relationship which is calibrated by two points after the black body furnace is calibrated before, so as to calculate the temperature value of the blade tip. And meanwhile, calculating the length of the blade tip according to the time of the low level, and comparing the original length to calculate the strain of the blade tip.
Drawings
FIG. 1 is a general flow diagram of the present invention;
FIG. 2 is a schematic diagram of the distribution of the optical probe and the rotational speed synchronization sensor on the turbine;
fig. 3 shows a rotation speed synchronization signal, a radiation voltage signal in the absence of strain, and a radiation voltage signal under an actual working condition.
Detailed Description
Referring to fig. 2, the measuring device of the present invention includes an optical probe fixedly installed on a casing housing to collect radiation signals, a rotational speed synchronization sensor installed at an end of a rotating shaft, a refrigeration type detector module for implementing photoelectric sensing, a circuit amplification module for implementing circuit signal processing, and a rear end data processing module. Thermal radiation emitted by the blades rotating at a high speed and gas radiation enter the optical probe together, a series of optical components collect radiation information, signals are led out by using optical fibers, the gas influence is avoided, optical signals are converted into electric signals through the photoelectric sensors, and the electric signals enter the subsequent data processing module to output blade tip temperature and strain information.
Under the laboratory condition, an optical probe is adopted to measure the temperature of the black body furnace which is heated to 2500 ℃ from 500 ℃, the temperature and the voltage of the black body furnace are measured every 1 ℃, a group of temperature and voltage discrete data points (V500, T500), (V501, T501) … (V2500, T2500) are obtained, the function relation of the temperature and the voltage is worked out through nonlinear curve fitting based on the least square method, then two temperature and voltage values are selected to carry out two-point correction when a sample piece is actually tested, and the influence caused by the change of distance and emissivity is calibrated.
In practical on-machine test, before the blade is not strained, an optical probe and a rotating speed synchronous sensor are used for testing a blade tip signal TS and referenceSee figure 3. According to the rotating speed synchronizing signal ZS, the sampling time between two pulses is the rotating period T of the turbine blade, the reciprocal of the sampling time is the rotating speed omega of the turbine blade, and the rotating speed synchronizing signal ZS between two pulses of the rotating speed synchronizing signal ZS is a periodic signal of the turbine blade, so that the voltage signal of each circle of the turbine blade is divided. Because the gas temperature is far higher than the blade tip temperature, the high level of the blade tip signal TS is a gas radiation signal, the low level is a blade tip voltage signal, and in one period, the time period of each low level is calculated. At the point when the turbine blade is just in use, the tip strain is almost zero, so the tip low signal period should be almost the same, at a same value t 0. Under the condition that the rotating radius R and the rotating period T of the blade are known, the original width passing through the optical probe under the condition that the blade tip is not strained is calculated to be
The turbine blade is in an extremely complex gas environment with high temperature, high pressure and high load for a long time, and the turbine blade bears huge stress change under the action of cyclic load and generates thermal fatigue under the impact of high-temperature gas. In the same step, the optical probe and the rotating speed synchronous sensor are adopted to test the blade tip signal TS and the rotating speed synchronous signal ZS, the low level period t1 … tn at the moment is calculated, and the length L of each blade tip signal is calculated according to the low level period t1 … tn1…Ln。
Continuously acquiring a tip signal and a rotating speed synchronous signal by adopting an optical probe and a rotating speed synchronous sensor, calculating the voltage amplitude of the level tip signal and the time period of each low level, calculating the tip temperature according to the amplitude, and calculating the strain according to the time period of each low level. The temperature calculation principle is as follows: and substituting the amplitude of the low level into the voltage-temperature relation which is calibrated and corrected before to obtain the temperature value of each blade tip. The strain measurement method comprises the following steps: the strain calculation formula is a strain calculation formula in which, when an object is deformed by an external factor (stress, humidity, change in temperature field, or the like), an internal force that interacts with each other is generated between each part in the object, and the strain is intended to restore the object from a position after the deformation to a position before the deformation in order to resist the effect of the external factorIs composed of
The length L of the blade tip after strain1…LnLength L of blade tip before deformation0And substituting the strain measurement formula to obtain the strain condition of the blade tip of each rotating blade.
Firstly, randomly selecting a strain as an initial epsilon within a first pulse period T0(ii) a X (ε) is selected in the next 1000m pulses0)＝|8000(0.005-ε0) L strain, where m represents the number of pulses in 1 pulse period, | · | represents the rounding, and the selected strains are averaged to obtain the comprehensive strain epsilonFinal 1Epsilon to be obtainedFinal 1Outputting in real time; x (epsilon) is selected in every 1000m pulses that followFinal i-1)＝|8000(0.005-εFinal i-1) I strains are selected, then the selected strains are averaged to obtain the comprehensive strain epsilon at the momentFinal iEpsilon to be obtainedFinal iAnd outputting in real time.
Claims (3)
1. A method of simultaneously measuring turbine blade tip temperature and strain, the method comprising:
step 1: calibrating a corresponding curve of blackbody radiation voltage and temperature by adopting a standard blackbody furnace under the line, and correcting the curve;
step 2: measuring by a rotating speed synchronous sensor to obtain a rotating speed pulse waveform, and calculating a pulse period T;
and step 3: measuring the radiation voltage of the tip of the turbine blade after the turbine blade is filled with fuel gas at the initial stage of operation through an optical probe to obtain an original pulse waveform, calculating the time t0 of low level, and calculating the original width of the blade tip
R is the rotating radius of the blade;
and 4, step 4: when the engine actually runs, the radiation voltage of the tip of the turbine blade is collected in real time through an optical probe, the pulse waveform comprises the radiation voltage V of the blade tip and the fuel gas, and the low-level time t1 … tn;
and 5: substituting the radiation voltage low level signal obtained in the step 4 into the V-K function relation corrected in the step 1, and calculating the actual temperature K of the blade tip;
step 6: substituting the low level time t1 … tn obtained in the step 4 into the formula in the step 3, and calculating to obtain the blade tip width L of each blade1…Ln；
And 7: and (3) substituting each blade tip length obtained in the step (6) and the blade tip original length obtained in the step (3) into the following strain measurement formula:
and 8: sampling the strain epsilon of the blade tip of the turbine blade to obtain the comprehensive strain epsilonFinal i。
2. The method for simultaneously measuring the temperature and the strain of the tip of the turbine blade according to claim 1, wherein the specific method in the step 1 is as follows:
sequentially heating the black body furnace at the step length of 1 ℃, stabilizing for half an hour after each heating, measuring the radiation voltage of the temperature point by using an optical probe to obtain n groups of voltage-temperature information, and obtaining a V0-K0 relation curve by using 1stopt fitting, wherein V0 represents the radiation voltage, and K0 represents the temperature; and then arranging a plurality of temperature acquisition points on the surface of the blade by a thermocouple, acquiring the temperature of the acquisition points by the thermocouple under the working condition, acquiring the radiation voltage at the sampling points by an optical probe, sampling a plurality of groups of radiation voltages corresponding to the temperatures under the working condition, forming two linear equations by the radiation voltages of the highest temperature point and the lowest temperature point in the data acquired under the working condition and the radiation voltages of two temperature points corresponding to the black body furnace, calculating a conversion coefficient from the change of the radiation equation of the black body furnace to the radiation equation of the thermocouple, and acquiring a corrected V-K relation by adopting a V0-K0 curve obtained before the coefficient is corrected.
3. The method for simultaneously measuring the temperature and the strain of the tip of the turbine blade according to claim 1, wherein the sampling method of the step 8 is;
step 8.1: firstly, randomly selecting a strain as an initial epsilon within a first pulse period T0；
Step 8.2: x (ε) is selected in the next 1000m pulses0)＝|8000(0.005-ε0) L strain, where m represents the number of pulses in 1 pulse period, | · | represents the rounding, and the selected strains are averaged to obtain the comprehensive strain epsilonFinal 1Epsilon to be obtainedFinal 1Outputting in real time;
step 8.3: x (epsilon) is selected in every 1000m pulses that followFinal i-1)＝|8000(0.005-εFinal i-1) I strains are selected, then the selected strains are averaged to obtain the comprehensive strain epsilon at the momentFinal iEpsilon to be obtainedFinal iAnd outputting in real time.
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| CN112855352B (en) * | 2019-11-28 | 2022-03-22 | 中国航发商用航空发动机有限责任公司 | Calculation method and control method for real-time blade tip clearance of high-pressure turbine |
| CN111043949B (en) * | 2019-12-31 | 2021-04-30 | 电子科技大学 | Device for detecting blade tip clearance of turbine blade |
| CN111551138B (en) * | 2020-02-17 | 2021-07-06 | 电子科技大学 | Method for measuring radial strain of blade by using radiation signal difference of turbine blade and casing |
| CN112729147A (en) * | 2020-12-28 | 2021-04-30 | 南京航空航天大学 | Blade strain measurement test system and method under complex environment |
| CN113012147B (en) * | 2021-04-13 | 2021-09-24 | 电子科技大学 | Turbine blade strain field full-field measurement method based on dual-mode fusion |
| CN114354202B (en) * | 2022-01-06 | 2023-03-21 | 北京化工大学 | Device and method for monitoring vibration and temperature of turbine blade in real time |
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