WO2025025317A1 - 评估涡轮发动机燃烧室的出口温度分布因子的方法及装置 - Google Patents

评估涡轮发动机燃烧室的出口温度分布因子的方法及装置 Download PDF

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WO2025025317A1
WO2025025317A1 PCT/CN2023/120425 CN2023120425W WO2025025317A1 WO 2025025317 A1 WO2025025317 A1 WO 2025025317A1 CN 2023120425 W CN2023120425 W CN 2023120425W WO 2025025317 A1 WO2025025317 A1 WO 2025025317A1
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temperature
combustion chamber
turbine engine
temperature distribution
reconstructed
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French (fr)
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朱旭
张轲
郑培英
温孟阳
杨合理
娄方远
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Tsinghua University
AECC Shenyang Engine Research Institute
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Tsinghua University
AECC Shenyang Engine Research Institute
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    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • 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
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation

Definitions

  • the present application relates to, but is not limited to, gas turbine engine technology, and more particularly to a method and device for evaluating an outlet temperature distribution factor of a turbine engine combustion chamber.
  • Gas turbine engines are widely used in various applications, including aircraft propulsion, power generation, and marine propulsion.
  • the temperature field on the combustion chamber outlet cross section is complex and unstable, with large radial and circumferential variations.
  • the method used to characterize the non-uniformity of the combustion chamber outlet temperature requires a rotating rake to measure hundreds of circumferential points, which is time-consuming and costly.
  • the present application provides a method and device for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber, which can solve any of the above-mentioned technical problems.
  • the present application embodiment provides a method for evaluating an outlet temperature distribution factor of a turbine engine combustion chamber, comprising:
  • the temperature field of the turbine engine combustion chamber outlet section is reconstructed using the multi-wave number approximation method
  • the radial temperature distribution factor and the overall temperature distribution factor are obtained to quantify the temperature non-uniformity of the turbine engine combustion chamber outlet section.
  • the method further includes:
  • the confidence of the reconstructed temperature field is evaluated based on the Pearson correlation coefficient.
  • the calculation formula of the Pearson correlation coefficient ⁇ is as follows:
  • Ti represents the measured true temperature value associated with the i-th wave number
  • T fit,i represents the temperature value associated with the i-th wave number of the temperature field obtained after the reconstruction
  • subscript i is used to indicate the parameter associated with the i-th wave number.
  • the method further includes:
  • the accuracy of the reconstructed temperature field is evaluated based on one or any combination of the following parameters: radial temperature variation, overall temperature variation, circumferential temperature variation, and circumferential average radial temperature distribution parameter.
  • the calculation formula of the radial temperature variation RTV is as follows:
  • T 4,max represents the maximum temperature at the combustion chamber outlet
  • T 4,max (r) represents the maximum temperature within the circumferential position in the radial direction r;
  • the temperature measurement value is obtained using any one or any combination of the following measurement techniques: thermocouple, gas analysis, laser induced fluorescence or infrared thermal imaging.
  • the preset number is less than 20.
  • the temperature field of the turbine engine combustion chamber outlet cross section reconstructed by using the multi-wave number approximation method includes: calculating by the following formula:
  • T( ⁇ ) represents the temperature field at the radius R and position ⁇
  • c 0 represents the DC component of the temperature signal
  • W n represents the selected dominant wave number
  • a and represent the amplitude and phase of the temperature related to the i-th wave number respectively
  • the subscript i is used to indicate the parameter related to the i-th wave number
  • N represents the number of dominant wave numbers.
  • the radial temperature distribution factor and the overall temperature distribution factor are obtained based on the circumferential integration of the reconstructed temperature field.
  • the method further includes: optimizing the distribution of cooling airflow of the turbine engine combustion chamber according to the obtained radial temperature distribution factor and the overall temperature distribution factor.
  • the turbine engine combustion chamber outlet cross-section includes: a single-head combustion chamber outlet cross-section, a double-head sector combustion chamber outlet cross-section, or a full-annular combustion chamber outlet cross-section.
  • An embodiment of the present application also provides a computer-readable storage medium storing computer-executable instructions, wherein the computer-executable instructions are used to execute any of the above-mentioned methods for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber.
  • An embodiment of the present application further provides a device for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber, comprising a memory and a processor, wherein the memory stores the following instructions executable by the processor: steps for executing any of the above-described methods for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber.
  • the present application embodiment further provides a device for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber, comprising: an acquisition module, a reconstruction module, and an evaluation module; wherein:
  • An acquisition module used to acquire a preset number of temperature measurement values on the outlet cross section of the turbine engine combustion chamber
  • a reconstruction module used to reconstruct the temperature field of the turbine engine combustion chamber outlet cross section using a multi-wave number approximation method based on the acquired temperature measurement values
  • the evaluation module is used to obtain the radial temperature distribution factor and the overall temperature distribution factor according to the reconstructed temperature field, so as to quantify the temperature non-uniformity of the turbine engine combustion chamber outlet section.
  • the reconstruction module is further used to: evaluate the Estimate the confidence of the reconstructed temperature field.
  • the reconstruction module is further used to: evaluate the accuracy of the reconstructed temperature field based on one or any combination of the following parameters: radial temperature variation, overall temperature variation, circumferential temperature variation, and circumferential average radial temperature distribution parameter.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided by the embodiment of the present application can simply and accurately predict the temperature non-uniformity of the turbine engine combustion chamber, and reduce the cost.
  • the embodiment of the present application effectively solves the problem of hot spot related features in reconstructing the temperature field, and uses sparse measurement to obtain a radial temperature distribution factor that is almost the same as the actual measurement, which is highly practical.
  • FIG1 is a schematic flow chart of a method for evaluating an outlet temperature distribution factor of a turbine engine combustion chamber in an embodiment of the present application
  • FIG2 is a schematic diagram showing a process of reconstructing the temperature field of a turbine engine combustion chamber outlet cross section using a multi-wave number approximation method in an embodiment of the present application;
  • FIG3( a ) is a schematic diagram of the time-averaged temperature field actually measured at the outlet of the engine combustion chamber in the related art
  • FIG3( b ) is a schematic diagram of the temperature field reconstructed at the outlet of the engine combustion chamber in a scenario where an embodiment of the present application is applied to a single-head combustion chamber;
  • FIG4 is a schematic diagram showing a comparison of RTP obtained from experimental results and a reconstructed data set in a scenario where an embodiment of the present application is applied to a single-head combustion chamber;
  • FIG5( a ) is a schematic diagram of dimensionless temperature distribution obtained by two independent measurements in a scenario where an embodiment of the present application is applied to a double-headed sector combustion chamber;
  • FIG5( b ) is a schematic diagram of temperature distribution reconstructed in a scenario where an embodiment of the present application is applied to a double-head sector combustion chamber;
  • FIG6 is a comparison diagram of radial temperature distribution RTP of the measurement a experiment and the reconstructed temperature field when the embodiment of the present application is applied to a double-head sector-shaped combustion chamber;
  • FIG7 is a comparison diagram of radial temperature distribution RTP of the measurement b experiment and the reconstructed temperature field when the embodiment of the present application is applied to a double-head sector-shaped combustion chamber;
  • FIG8( a ) is a schematic diagram of the temperature field measured at the outlet cross section of a typical annular tube combustion chamber
  • FIG8( b ) is a schematic diagram of temperature distribution reconstructed in a full annular combustion chamber according to an embodiment of the present application
  • FIG9 is a schematic diagram showing a comparison of RTP obtained from the experiment and the reconstructed temperature field when the embodiment of the present application is applied to a full annular combustion chamber;
  • FIG. 10 is a schematic diagram of the composition structure of an apparatus for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber in an embodiment of the present application.
  • Wave number approximation method predicts flow field.
  • the combustion chamber of an aircraft engine it is located between the compressor and the turbine.
  • Its design goal is to maintain stable combustion and uniform outlet temperature field under any conditions.
  • Drawing on the methods used in compressors and turbines an attempt is made to use a multi-wave number approximation method to reconstruct the combustion chamber temperature field. It is necessary to verify whether this method can be applied to scenarios such as component-level combustion chambers or full-annular combustion chambers, and to verify that the accuracy of the reconstructed temperature field meets expectations.
  • FIG. 1 is a flow chart of a method for evaluating an outlet temperature distribution factor of a turbine engine combustion chamber in an embodiment of the present application. As shown in FIG. 1 , the method may include:
  • Step 100 Obtain a preset number of temperature measurement values on the outlet cross section of the turbine engine combustion chamber.
  • a measurement probe is arranged at an outlet of a combustion chamber of a turbine engine to obtain a predetermined number of temperature measurement values on a cross section of the outlet of the combustion chamber of the turbine engine.
  • the temperature measurements include a small number of less than 20 discrete measurements.
  • the temperature measurement may be obtained using any one or any combination of the following measurement techniques: thermocouples, gas analysis, laser induced fluorescence, or infrared thermal imaging.
  • Step 101 Reconstruct the temperature field of the turbine engine combustion chamber outlet cross section using a multi-wave number approximation method based on the acquired temperature measurement values.
  • the temperature field of the turbine engine combustion chamber outlet cross section reconstructed using the multi-wave number approximation method in step 101 can be calculated by formula (1):
  • T( ⁇ ) represents the temperature field at the radius R and position ⁇
  • c 0 represents the DC component of the temperature signal
  • W n represents the selected dominant wave number
  • a and They represent the amplitude and phase of the temperature associated with the ith wave number
  • the subscript i is used to indicate the parameter associated with the ith wave number
  • N represents the number of dominant wave numbers.
  • the dominant wave number refers to the wave number of the dominant beam, that is, the number of times the beam repeats along the circumferential direction.
  • T( ⁇ ) represents the temperature field at a radius of R and a position of ⁇
  • c 0 represents the DC component of the temperature signal
  • W n represents the wave number
  • a and The table shows the amplitude and phase of the temperature signal
  • the subscript i is used to indicate the parameter related to the i-th wave number.
  • the temperature flow field of the combustion chamber of an aircraft engine is usually dominated by a few wave numbers along the circumferential direction. Therefore, there is no need to use the infinite number of wave numbers described in equations (3) or (4).
  • the circular flow in the temperature flow field of the combustion chamber can be approximated by several (such as N) dominant wave numbers, thereby obtaining the formula (1).
  • Formula (1) is a formula for reconstructing the circular flow field in an embodiment of the present application. Since formula (1) reduces the number of unknowns in formula (2) from infinity to 2N+1, when the amplitude and phase of all dominant wave numbers Wn are determined, formula (1) can be used to reconstruct the circular flow field.
  • ⁇ ( ⁇ 1 , ⁇ 2 , ⁇ 3 , ... ⁇ m ).
  • AF T
  • A is called the design matrix with a dimension of m ⁇ (2N+1)
  • F represents a vector containing 2N+1 unknown coefficients
  • T represents an m-element vector containing all measured data points from different circumferential positions.
  • W n,1 , W n,2 ...W n,N represent N dominant wave numbers
  • ⁇ ( ⁇ 1 , ⁇ 2 , ⁇ 3 , ... ⁇ m ) represents m measuring points at different circumferential positions.
  • the number of data points in vector T must be greater than the number of unknown
  • the number of coefficients is m ⁇ 2N + 1.
  • the reconstructed signal contains errors, and it is crucial to evaluate the confidence of the reconstructed signal, which requires additional data points in T( ⁇ ). Therefore, at least 2N + 2 measurement points are required to characterize the N dominant wave numbers. However, this will result in an overdetermined system with more equations than unknowns.
  • the condition number of the design matrix A is a function of the dominant wave number Wn and the measurement position ⁇ .
  • the two-norm can be used to calculate the vector and matrix norms.
  • Wn the condition number of A measures the sensitivity of the reconstructed temperature to the probe placement error. From the above analysis, it can be concluded that the optimal measurement position corresponds to the condition number of the minimum design matrix A.
  • Step 102 According to the reconstructed temperature field, a radial temperature distribution factor and an overall temperature distribution factor are obtained to quantify the temperature non-uniformity of the turbine engine combustion chamber outlet cross section.
  • the temperature field at the outlet of the gas turbine engine combustor is highly three-dimensional with large radial and circumferential variations.
  • the temperature distribution factor (TDF) is used to quantify the temperature non-uniformity at the outlet of the combustor.
  • Two widely used parameters include radial TDF (RTDF) and overall TDF (OTDF), where RTDF is a profile factor used to measure the non-uniformity of the circumferential average temperature field and OTDF is a mode factor used to measure the difference between the hottest spot and the average temperature.
  • RTDF radial TDF
  • OTDF overall TDF
  • the expressions of RTDF and OTDF are shown in equations (4) and (5), respectively:
  • T3 represents the temperature at the combustion chamber inlet
  • T4 represents the temperature at the combustion chamber outlet
  • the superscript area represents the regional average
  • the superscript cir represents the circumferential average
  • max represents the maximum.
  • T4 ,max represents the maximum temperature at the combustion chamber outlet.
  • the reconstructed temperature field can be integrated along the circumferential direction to obtain Radial temperature distribution factor and overall temperature distribution factor.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in the embodiment of the present application simply and accurately predicts the temperature non-uniformity of the turbine engine combustion chamber and reduces the cost.
  • the embodiment of the present application effectively solves the problem of hot spot related features in reconstructing the temperature field and uses sparse measurement to obtain a radial temperature distribution factor that is almost the same as the actual measurement, which is highly practical.
  • step 101 after reconstructing the temperature field of the turbine engine combustion chamber outlet cross section in step 101 and before step 102, the following may also be included:
  • the confidence of the reconstructed temperature field was evaluated based on the Pearson correlation coefficient.
  • the Pearson correlation coefficient ⁇ is used to compare the consistency of the predicted flow characteristics with the actual values of all measurement positions for the reconstructed circumferential flow field to evaluate the confidence of the reconstructed temperature field.
  • the calculation of the Pearson correlation coefficient ⁇ is shown in formula (6):
  • Ti represents the actual signal value of the measurement
  • T fit,i represents the signal value obtained after reconstruction
  • subscript i is used to indicate the parameter related to the i-th wave number.
  • the range of the Pearson correlation coefficient ⁇ is between 0 and 1.
  • the predicted flow characteristics should be consistent with the actual values of all measurement positions, and the value of the Pearson correlation coefficient ⁇ is close to 1.
  • the value of the Pearson correlation coefficient ⁇ is far from 1.
  • Ti represents the temperature measurement value related to the i-th wave number obtained in step 100
  • T fit,i represents the temperature value related to the i-th wave number in the temperature field obtained after reconstruction in step 101.
  • step 101 after reconstructing the temperature field of the turbine engine combustion chamber outlet cross section in step 101 and before step 102, the following may also be included:
  • the accuracy of the reconstructed temperature field is evaluated based on one or any combination of the following parameters: radial temperature variation, overall temperature variation, circumferential temperature variation, and circumferential average radial temperature distribution parameter.
  • RTV radial temperature variation
  • OTV overall temperature variation
  • RTV RTV
  • RTDF RTDF
  • OTV C 0 OTDF
  • RTV and OTV are all linear relationships.
  • CTV circumferential temperature variation
  • T 4,max (r) represents the maximum temperature within the circumferential position in the radial direction r.
  • RTP circumferentially averaged radial temperature distribution
  • TTP circumferentially averaged radial temperature distribution Temperature Profile
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in the embodiment of the present application can be applied to component-level combustion chamber tests, such as single-head combustion chambers and double-head fan-shaped combustion chambers, and can also be applied to full-annular combustion chambers, such as straight-through full-annular combustion chambers, baffled full-annular combustion chambers, and annular tube combustion chambers.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in the embodiment of the present application is robust and easy to implement. Using the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in the embodiment of the present application, the cost of test verification in the development process of a gas turbine engine is significantly reduced by reducing the circumferential measuring points.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in the embodiment of the present application can also be used for real-time health monitoring during the operation and maintenance of aircraft engines.
  • the present application also provides a computer-readable storage medium storing computer-executable instructions, wherein the computer-executable instructions are used to execute any of the above-mentioned methods for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber.
  • the present application further provides a device for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber, comprising a memory and a processor, wherein the memory stores the following instructions executable by the processor: steps for executing any of the above-described methods for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in an embodiment of the present application is applied to a single-head combustion chamber scenario.
  • a single-head combustion chamber of a Rolls-Royce aircraft engine is selected as an example.
  • FIG3(a) shows the actual measured time-averaged temperature field at the outlet of the engine combustion chamber. This is the measurement result of a single-head combustion chamber disclosed in the related art.
  • the measurement structure is an isotherm made using 90 measurement points (represented by small black dots in the figure), including 10 radial positions and 9 circumferential positions of the entire combustion chamber.
  • FIG3(b) shows a method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in an embodiment of the present application, and a temperature field reconstructed using the measured values at five circumferential positions, as shown by the small black dots in FIG3(b).
  • a single wavelet with a wave number equal to the number of combustion chambers can be selected to reconstruct the circumferential temperature distribution at all radii.
  • the reconstructed temperature field captures the hot spots well, including the location, area and intensity of these hot spots.
  • the RTV of the temperature field reconstructed in the embodiment of the present application is in excellent agreement with the experiment, with a deviation of only 0.8 points, as shown in Table 1, which is a comparison of the RTV and OTV of the single-head combustion chamber experiment and the reconstruction.
  • Table 1 is a comparison of the RTV and OTV of the single-head combustion chamber experiment and the reconstruction.
  • the reconstructed signal overestimates the size of the OTV, resulting in a deviation of 6.8% from the experiment.
  • Table 2 shows the CTV comparison between the single-head combustion chamber experiment and the reconstruction.
  • the CTV values of the reconstructed signal at all span-direction positions and the corresponding Pearson correlation coefficients are shown in Table 2.
  • the CTV values obtained by the reconstructed signal are in the same order of magnitude as the experimental results.
  • the Pearson correlation coefficient value in the mid-span area is higher, that is, using the method for evaluating the outlet temperature distribution factor of the turbine engine combustion chamber provided by the embodiment of the present application, the reconstructed signal obtained by the single wave number approximation method in the mid-span area is more accurate.
  • the multi-wave number approximation method used in the embodiment of the present application shows good potential in characterizing the hot spot at the combustion chamber outlet with fewer measurements; moreover, the reconstructed combustion chamber outlet temperature distribution also captures the characteristics related to the hot spot well, and the generated RTP is almost the same as the RTP obtained from the detailed experimental results; in addition, the reconstructed signal also produces a similar value of RTV.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in an embodiment of the present application is applied to a scenario of a double-headed sector combustion chamber.
  • a double-headed sector combustion chamber of a Rolls-Royce aircraft engine is selected as an example (including two fuel nozzles).
  • the temperature field is obtained from an enhanced simulator developed by Oxford University, QinetiQ and Rolls-Royce.
  • Figure 5(a) shows the dimensionless temperature distribution from two independent measurements, in this example: To measure a and b, each measurement consists of 9 radial measurement points and 19 circumferential measurement points. The difference between the two measurements is reflected in the position of the probe. Between measurement a and measurement b, the probe is offset by 3 mm (about 5% of the height). Therefore, the measured temperature field is compared and analyzed, and the measured dimensionless temperature is In addition, as shown in Figure 5(a), there are significant inhomogeneities in both radial and circumferential directions, such as a maximum dimensionless variation of 28% in the average radial direction (((T max -T min )/T)) and 17% in the circumferential direction. The temperature distributions of the two measurements are very similar and have excellent symmetry.
  • Figure 5(b) shows the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided by an embodiment of the present application.
  • the temperature distribution reconstructed using measurements at seven circumferential positions reduces the data size by 63%.
  • a single wavelet with a wave number equal to the number of combustion chambers is selected to reconstruct the temperature distribution.
  • the reconstructed temperature distribution well characterizes the hot spot characteristics.
  • the experimental results and the reconstruction results have achieved good consistency in RTP. At all altitudes, the maximum deviation of the dimensionless radial temperature measured twice is less than 1.4%.
  • the method for evaluating the outlet temperature distribution factor of the turbine engine combustion chamber provided in the embodiment of the present application is applied to the scenario of a double-head sector combustion chamber, and the RTV of the reconstructed signal is in excellent agreement with the experiment.
  • Table 3 compares the RTV and OTV of the double-head sector combustion chamber experiment and the reconstruction. As shown in Table 3, the deviations of the two different measurement results are less than half a percentage point. Similarly, the reconstructed signal also overestimates the amplitude of the OTV, resulting in a deviation of about 7% from the experiment.
  • Table 4 shows the CTV comparison of the double-head sector combustion chamber experiment and reconstruction (measurement a).
  • Table 5 shows the CTV comparison of the double-head sector combustion chamber experiment and reconstruction (measurement b).
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in an embodiment of the present application is applied to a scenario of a full annular combustion chamber.
  • the full annular combustion chamber of QinetiQ's aircraft engine is taken as an example, which has 20 injectors.
  • Figure 8(a) shows the temperature field measured at the outlet cross section of a typical annular combustion chamber. As shown in Figure 8(a), for an average temperature of 2072K, the measured dimensionless temperature is range. As expected, there is significant non-uniformity in the radial direction, and there are relatively low temperature areas at the hub and casing end wall caused by the combustion chamber coolant flow.
  • Figure 8(b) shows the reconstructed temperature distribution when measured at ten circumferential positions using a single wave number approximation method on all radii, with the wave number equal to the number of injectors (i.e., 20 in this example). Similarly, these measured circumferential positions, as indicated by the small black dots in the figure, are selected to produce the minimum value of the relevant condition number.
  • the reconstructed temperature field captures the main features related to the combustion chamber outlet temperature flow field well, such as the temperature distribution of the cold flow area near the hub and the casing end wall and the hot spot in the upper middle area. However, the asymmetric features of the corresponding areas of different heads of the combustion chamber are also absent in the reconstructed temperature field.
  • Figure 9 compares the RTP obtained from the experiment and the reconstructed temperature field.
  • the reconstructed temperature field produces a shape similar to the RTDF obtained from the experiment, and the circumferential average temperature value of the end wall area is very consistent between the reconstructed flow and the measured flow.
  • the peak circumferential average temperature value produced by the reconstructed temperature field is lower than the estimated value.
  • Table 6 is a comparison of the RTV and OTV of the full annular combustion chamber experiment and the reconstruction. As shown in Table 6, unlike the single-head combustion chamber and the double-head fan-shaped combustion chamber, the reconstructed temperature distribution in the full annular combustion chamber underestimates the OTV by 2.4%.
  • Table 7 is a comparison diagram of the experimental and reconstructed CTV of the full annular combustion chamber.
  • Table 7 lists the CTV values of the experimental and reconstructed signals at all span-wise positions, as well as the corresponding Pearson correlation coefficients of the experiments. As shown in Table 7, the CTV values obtained from the reconstructed signals are in the same order of magnitude as the experimental results.
  • the Pearson correlation coefficient of the reconstructed temperature distribution in the full annular combustion chamber is lower, probably due to the non-periodicity of the different head outlet temperature distributions in the temperature distribution at the combustion chamber outlet.
  • the effectiveness of the multi-wave number approximation method in reconstructing the non-uniform temperature field at the combustion chamber outlet in the method for evaluating the outlet temperature distribution factor of the turbine engine combustion chamber provided by the embodiment of the present application was verified.
  • the combustion chamber outlet temperature distribution shows good circumferential symmetry, and the temperature distribution reconstructed using the single wave number approximation method captures the hot spot at the combustion chamber outlet well, including its area, center position and intensity.
  • the RTP and RTV generated by the reconstructed temperature distribution are almost the same as those obtained from the experiment.
  • the temperature distribution reconstructed using the single wavelet method can still capture the main hot spot related features and produce a shape similar to the representative values of RTP and RTV in the experiment, that is, although only sparse sampling measurements along the circumferential direction are used, it still shows that the use of the multi-wave number approximation method to approximate the combustion chamber outlet temperature distribution factor has great potential.
  • the multi-wave number approximation method is used to reconstruct the exit cross section of a single-head combustion chamber, a double-head fan-shaped combustion chamber or a full-annular combustion chamber, and the reconstructed temperature field is integrated along the circumferential direction to obtain RTDF and OTDF.
  • the method for evaluating the outlet temperature distribution factor of a turbine engine combustion chamber provided in an embodiment of the present application is used to achieve high-precision flow field reconstruction and calculation of the mean value of the key cross-section flow field, and the mean error of RTDF and OTDF of the combustion chamber outlet cross section obtained based on the reconstructed temperature field is within 1.0%.
  • the embodiment of the present application uses sparse measurement to obtain a radial temperature distribution factor that is almost the same as the measurement based on a rotating rake every 1° to 2.5° along the circumference in the related art, and the difference in most of the predicted values is less than 1.0%.
  • the method for quantifying the temperature non-uniformity of a turbine engine combustion chamber provided in the embodiment of the present application can be applied to scenarios such as single-head combustion chambers, double-head fan-shaped combustion chambers, and full-annular combustion chambers. By reducing the circumferential measurement points, the cost of developing and testing the combustion chamber of a gas turbine engine is significantly reduced.
  • the method for quantifying the temperature non-uniformity of a turbine engine combustion chamber provided in the embodiment of the present application can also be used for real-time health monitoring during the operation and maintenance of aircraft engines.
  • further optimization can also use the RTDF and OTDF obtained by the method for evaluating the outlet temperature distribution factor of the turbine engine combustion chamber provided by the embodiment of the present application to optimize the design of the combustion chamber, especially the distribution of the cooling airflow.
  • a slight surface temperature over-high of the high pressure turbine (HPT) blades or rotor blades can cause serious damage or significantly shorten the life of the components.
  • the cooling size of the HPT blades/rotors is generally designed for the worst case, usually the predicted peak temperature, which will lead to a large amount of cooling demand, which has now reached 30% of the high pressure compressor flow, causing significant performance losses to the engine.
  • the temperature field can be reconstructed through a small number of measured values, and the RTDF and OTDF can be obtained relatively easily. Compared with the previous need to obtain temperature field data through complex and expensive experiments, this has a positive significance for optimizing the design of the combustion chamber.
  • FIG10 is a schematic diagram of the composition structure of the device for evaluating the outlet temperature distribution factor of the combustion chamber of a turbine engine in an embodiment of the present application.
  • the device comprises: an acquisition module, a reconstruction module, and an evaluation module; wherein,
  • the acquisition module is used to obtain a preset number of temperature measurements on the turbine engine combustion chamber outlet section. Quantity;
  • a reconstruction module used to reconstruct the temperature field of the turbine engine combustion chamber outlet cross section using a multi-wave number approximation method based on the acquired temperature measurement values
  • the evaluation module is used to obtain the radial temperature distribution factor and the overall temperature distribution factor according to the reconstructed temperature field, so as to quantify the temperature non-uniformity of the turbine engine combustion chamber outlet section.
  • the temperature measurements include a small number of discrete measurements less than 20.
  • the temperature measurements may be obtained using any one or any combination of the following measurement techniques: thermocouples, gas analysis, laser induced fluorescence, or infrared thermography.
  • the evaluation module may be used to obtain a radial temperature distribution factor and an overall temperature distribution factor based on a circumferential integration of the reconstructed temperature field.
  • the reconstruction module may be further configured to: evaluate the confidence of the reconstructed temperature field based on a Pearson correlation coefficient.
  • the reconstruction module may also be used to evaluate the accuracy of the reconstructed temperature field based on one or any combination of the following parameters: radial temperature variation, overall temperature variation, circumferential temperature variation, and circumferential average radial temperature distribution parameter.
  • the device for evaluating the outlet temperature distribution factor of the turbine engine combustion chamber provided in the embodiment of the present application simply and accurately predicts the temperature non-uniformity of the turbine engine combustion chamber and reduces the cost.
  • the embodiment of the present application effectively solves the problem of hot spot related features in reconstructing the temperature field, and uses sparse measurement to obtain a radial temperature distribution factor that is almost the same as the actual measurement, which is highly practical.

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Abstract

本申请公开了一种评估涡轮发动机燃烧室的出口温度分布因子的方法及装置，简单、准确地预测涡轮发动机燃烧室的温度非均匀性，且降低成本。本申请实施例有效地解决了热斑相关特征在重构温度场中的问题，并使用稀疏测量获得了与实际测量几乎相同的径向温度分布因子，实用性强。

Description

评估涡轮发动机燃烧室的出口温度分布因子的方法及装置 技术领域
本申请涉及但不限于燃气涡轮发动机技术，尤指一种评估涡轮发动机燃烧室的出口温度分布因子的方法及装置。
背景技术
燃气涡轮发动机广泛用于各种应用领域，包括飞机推进、发电和海上推进等。燃气涡轮发动机中，燃烧室出口截面上的温度场是复杂且不稳定的，存在大的径向和周向变化。目前，用于表征燃烧室出口温度非均匀性的方法需要旋转耙子进行数百个周向测点测量，费时且成本高昂。
如何简单、准确地量化涡轮发动机燃烧室的温度非均匀性，成为亟需解决的技术问题。
发明概述
本申请提供一种评估涡轮发动机燃烧室的出口温度分布因子的方法及装置，能够解决上述任意技术问题。
本申请实施例提供了一种评估涡轮发动机燃烧室的出口温度分布因子的方法，包括：
获取涡轮发动机燃烧室出口截面上预设数量的温度测量值；
根据获取的温度测量值，利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场；
根据重构得到的温度场，获取径向温度分布因子和整体温度分布因子，以量化涡轮发动机燃烧室出口截面的温度不均匀性。
在一种示例性实例中，所述重构涡轮发动机燃烧室出口截面的温度场之后，所述获取径向温度分布因子和整体温度分布因子之前，还包括：
基于皮尔逊相关系数评估所述重构的温度场的置信度。
在一种示例性实例中，所述皮尔逊相关系数ρ的计算公式如下：
其中，Ti表示测量的与第i个波数相关的真实温度值，Tfit,i表示所述重构后得到的温度场的与第i个波数相关的温度值，脚标i用于指示与第i个波数相关的参数。
在一种示例性实例中，所述重构涡轮发动机燃烧室出口截面的温度场之后，所述获取径向温度分布因子和整体温度分布因子之前，还包括：
基于以下参数之一或任意组合评价重构的温度场的精确度：径向温度变化、整体温度变化、周向温度变化、周向平均径向温度分布参数。
在一种示例性实例中，对于基于所述径向温度变化评价重构的温度场的精确度的情况，所述径向温度变化RTV的计算公式如下：
其中，表示所述涡轮发动机燃烧室出口的周向平均最大温度，表示所述涡轮发动机燃烧室出口的区域平均温度；
对于基于所述整体温度变化评价重构的温度场的精确度的情况，所述整体温度变化OTV的计算公式如下：
其中，T4,max表示燃烧室出口的最大温度；
对于基于所述周向温度变化评价重构的温度场的精确度的情况，所述周向温度变化CTV的计算公式如下：
其中，T4,max(r)表示在径向r的圆周位置内最高温度；
对于基于所述周向平均径向温度分布参数评价重构的温度场的精确度的情况，所述周向平均径向温度分布参数RTP的计算公式如下：
其中，表示在径向r位置沿周向平均温度值。
在一种示例性实例中，使用以下任一或任意组合方式获取所述温度测量值：热电偶、燃气分析、激光诱导荧光或红外热成像等测量技术。
在一种示例性实例中，所述预设数量为少于20。
在一种示例性实例中，所述利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场包括：通过下面公式计算：
T(θ)表示半径为R，位置为θ处的温度场，c0表示温度信号的直流分量，Wn表示所选取的主导波数，其中，A和分别表示第i波数相关所述温度的幅度和相位，脚标i用于指示与第个i波数相关的参数，N表示主导波数的数目。
在一种示例性实例中，基于所述重构得到的温度场沿周向积分，获取所述径向温度分布因子和所述整体温度分布因子。
在一种示例性实例中，还包括：根据所述获取的径向温度分布因子和整体温度分布因子优化所述涡轮发动机燃烧室的冷却气流的分布。
在一种示例性实例中，所述涡轮发动机燃烧室出口截面包括：单头部燃烧室出口截面，或双头部扇形燃烧室出口截面，或全环形燃烧室出口截面。
本申请实施例还提供一种计算机可读存储介质，存储有计算机可执行指令，所述计算机可执行指令用于执行上述任一项所述评估涡轮发动机燃烧室的出口温度分布因子的方法。
本申请实施例再提供一种实现评估涡轮发动机燃烧室的出口温度分布因子的设备，包括存储器和处理器，其中，存储器中存储有以下可被处理器执行的指令：用于执行上述任一项所述的评估涡轮发动机燃烧室的出口温度分布因子的方法的步骤。
本申请实施例又提供一种评估涡轮发动机燃烧室的出口温度分布因子的装置，包括：获取模块、重构模块，以及评估模块；其中，
获取模块，用于获取涡轮发动机燃烧室出口截面上预设数量的温度测量值；
重构模块，用于根据获取的温度测量值，利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场；
评估模块，用于根据重构得到的温度场，获取径向温度分布因子和整体温度分布因子，以量化涡轮发动机燃烧室出口截面的温度不均匀性。
在一种示例性实例中，所述重构模块还用于：基于皮尔逊相关系数评 估所述重构的温度场的置信度。
在一种示例性实例中，所述重构模块还用于：基于以下参数之一或任意组合评价所述重构的温度场的精确度：径向温度变化、整体温度变化、周向温度变化、周向平均径向温度分布参数。
通过本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，简单、准确地预测涡轮发动机燃烧室的温度非均匀性，且降低成本。本申请实施例有效地解决了热斑相关特征在重构温度场中的问题，并使用稀疏测量获得了与实际测量几乎相同的径向温度分布因子，实用性强。
本发明的其它特征和优点将在随后的说明书中阐述，并且，部分地从说明书中变得显而易见，或者通过实施本发明而了解。本发明的目的和其他优点可通过在说明书、权利要求书以及附图中所特别指出的结构来实现和获得。
附图概述
附图用来提供对本申请技术方案的进一步理解，并且构成说明书的一部分，与本申请的实施例一起用于解释本申请的技术方案，并不构成对本申请技术方案的限制。
图1为本申请实施例中评估涡轮发动机燃烧室的出口温度分布因子的方法的流程示意图；
图2为本申请实施例中利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场的过程演示示意图；
图3(a)为相关技术中发动机燃烧室出口的实际测量的时均温度场示意图；
图3(b)为本申请实施例应用于单头部燃烧室的场景中发动机燃烧室出口重构的温度场示意图；
图4为本申请实施例应用于单头部燃烧室的场景中，从实验结果和重构数据集中获得的RTP的对比示意图；
图5(a)为本申请实施例应用于双头部扇形燃烧室的场景中，两次独立测量的无量纲温度分布示意图；
图5(b)为本申请实施例应用于双头部扇形燃烧室的场景中重构的温度分布示意图；
图6为本申请实施例应用于双头部扇形燃烧室，测量a实验和重构温度场径向温度分布RTP的比较图；
图7为本申请实施例应用于双头部扇形燃烧室，测量b实验和重构温度场径向温度分布RTP的比较图；
图8(a)为典型环管形燃烧室的出口截面测量的温度场示意图；
图8(b)为本申请实施例应用于全环形燃烧室中重构的温度分布示意图；
图9为本申请实施例应用于全环形燃烧室，从实验中和重构的温度场获得的RTP比较示意图；
图10为本申请实施例中评估涡轮发动机燃烧室的出口温度分布因子的装置的组成结构示意图。
详述
为使本申请的目的、技术方案和优点更加清楚明白，下文中将结合附图对本申请的实施例进行详细说明。需要说明的是，在不冲突的情况下，本申请中的实施例及实施例中的特征可以相互任意组合。
为了便于理解本申请，下面将参照相关附图对本申请进行更全面的描述。附图中给出了本申请的实施例。但是，本申请可以以许多不同的形式来实现，并不限于本文所描述的实施例。相反地，提供这些实施例的目的是使本申请的公开内容更加透彻全面。
除非另有定义，本文所使用的所有的技术和科学术语与属于本申请的技术领域的技术人员通常理解的含义相同。本文中在本申请的说明书中所使用的术语只是为了描述具体的实施例的目的，不是旨在于限制本申请。
在航空发动机的转动部件(压气机和涡轮)中，相关技术提出应用多 波数近似的方法预测流场。对于航空发动机的燃烧室，其位置位于压气机和涡轮之间，结构与转动部件(压气机和涡轮)存在着较大的差异，其设计目标是在任何条件下保持稳定燃烧并且出口温度场均匀。借鉴在压气机和涡轮中使用的方法，尝试使用一种多波数近似方法来重构燃烧室温度场，需要检验本方法可以适用于部件级燃烧室或全环形燃烧室等场景，验证重构的温度场的精度满足期望。
图1为本申请实施例中评估涡轮发动机燃烧室的出口温度分布因子的方法的流程示意图，如图1所示，可以包括：
步骤100：获取涡轮发动机燃烧室出口截面上预设数量的温度测量值。
在一种示例性实例中，在涡轮发动机燃烧室出口布置测量探针位置，以在涡轮发动机燃烧室出口截面上获取预设数量的温度测量值。
在一种示例性实例中，温度测量值包括少于20的少量离散的测量值。
在一种示例性实例中，可以使用以下任一或任意组合方式获取温度测量值：热电偶、燃气分析、激光诱导荧光或红外热成像等测量技术。
步骤101：根据获取的温度测量值，利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场。
本申请实施例中利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场的过程如图2所示。在一种示例性实例中，步骤101中的利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场，可以通过公式(1)计算：
公式(1)中，T(θ)表示半径为R，位置为θ处的温度场，c0表示温度信号的直流分量，Wn表示所选取的主导波数，和其中，A和分别表示第i波数相关温度的幅度和相位，脚标i用于指示与第i个波数相关的参数，N表示主导波数的数目。其中，主导波数指主导波束的波数(Wavenumber)即波束沿周向重复的次数。
理论上，空间周期为2π的半径为R的燃烧室出口截面处的稳态(时均)温度场可以如公式(2)所示，用不同波数的无限序列来描述：
公式(2)中，T(θ)表示半径为R，位置为θ处的温度场，c0表示温度信号的直流分量，Wn表示波数，A和分表表示温度信号的幅度和相位，脚标i用于指示与第i波数相关的参数。定义那么公式(2)可以转换为如公式(3)所示：
以航空发动机燃烧室为例，航空发动机燃烧室的温度流场沿着圆周方向通常由少数几个波数主导，因此，不用使用方程(3)或(4)中描述的无限数量的波数。燃烧室的温度流场中的圆周流动可以采用几个(如N个)主导波数来近似，从而得到如公式(1)所示。公式(1)是本申请实施例中重构圆周流场的公式，由于公式(1)将公式(2)中的未知数数量从无穷大减小到2N+1，因此，当确定了所有主导波数Wn的幅度和相位，则可以使用公式(1)来重构圆周流场。
在一种示例性实例中，为了求解包含2N+1个未知数的方程，需要在不同圆周位置测量的最少数量的数据点包括：θ＝(θ1,θ2,θ3,…θm)。该系统可以描述为：AF＝T，其中，A称为设计矩阵，维度为m×(2N+1)，F表示包含2N+1个未知系数的向量，T表示包含来自不同圆周位置的所有测量数据点的m个元素向量。A、F和T的数学表达式如下所示：
其中，Wn,1、Wn,2…Wn,N表示N个主导波数，θ＝(θ1,θ2,θ3,…θm)表示在不同圆周位置上的m个测点。
求解方程中描述的N个主导波数，向量T中数据点的个数必须大于未知 系数的个数，即m≥2N+1。然而，在实践应用中，由于T(θ)的不确定性，重构信号包含误差，评估重构信号的置信度至关重要，这需要T(θ)中的额外数据点，因此，至少需要2N+2个测量点来表征N个主导波数。但是，这样又会产生一个方程多于未知数的超定系统。
设计矩阵A的条件数是主导波数Wn和测量位置θ的函数。矩阵条件数的计算公式有多种，本实施例中可以采用二范数进行向量和矩阵范数计算。条件数使用k＝‖A‖‖A+‖来计算，其中，A+是方阵A的逆，或者是非方阵A的穆尔-彭罗斯(Moore-Penrose)广义逆矩阵。使用一组选定的Wn，A的条件数衡量重构温度对探针放置误差的敏感程度。通过上述分析可以得出，最佳测量位置对应最小设计矩阵A的条件数。
步骤102：根据重构得到的温度场，获取径向温度分布因子和整体温度分布因子，以量化涡轮发动机燃烧室出口截面的温度不均匀性。
燃气涡轮发动机燃烧室出口处的温度场是高度三维的，具有较大的径向和周向变化。温度分布因子(TDF)用于量化燃烧室出口处的温度不均匀性。两个广泛采用的参数包括径向TDF(RTDF)和整体TDF(OTDF)，其中，RTDF是用于测量周向平均温度场不均匀性的剖面因子，OTDF是用于测量最热斑与平均温度的差异的模式因子。RTDF和OTDF的表示分别如公式(4)和公式(5)所示：

公式(4)、公式(5)中，T3表示燃烧室进口的温度，T4表示燃烧室出口的温度，上标area表示区域平均，上标cir表示周向平均，max表示最大。公式(4)、公式(5)中，表示燃烧室出口的周向平均最大温度，表示燃烧室出口的区域平均温度，表示燃烧室进口的区域平均温度，T4,max表示燃烧室出口的最大温度。
在一种示例性实例中，可以基于重构得到的温度场沿周向积分，获取 径向温度分布因子和整体温度分布因子。
本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，简单、准确地预测涡轮发动机燃烧室的温度非均匀性，且降低成本。本申请实施例有效地解决了热斑相关特征在重构温度场中的问题，并使用稀疏测量获得了与实际测量几乎相同的径向温度分布因子，实用性强。
在一种示例性实例中，在步骤101中重构涡轮发动机燃烧室出口截面的温度场之后，步骤102之前，还可以包括：
基于皮尔逊相关系数评估重构的温度场的置信度。
为了评估重构信号的置信度，在一种实施例中，使用皮尔逊相关系数ρ来针对重构的圆周流场，预测的流动特性与所有测量位置的实际值的一致性，以评估重构的温度场的置信度。皮尔逊相关系数ρ的计算如公式(6)所示：
公式(6)中，Ti表示测量的真实信号值，Tfit,i表示重构后得到的信号值，脚标i用于指示与第i个波数相关的参数。皮尔逊相关系数ρ的范围在0和1之间。对于重构良好的圆周流场，预测的流动特性应与所有测量位置的实际值一致，皮尔逊相关系数ρ的值接近1，反之，皮尔逊相关系数ρ的值远离1。在本申请实施例中，Ti表示步骤100获取的与第i个波数相关的温度测量值，Tfit,i表示步骤101重构后得到的温度场中与第i个波数相关的温度值。
在一种示例性实例中，在步骤101中重构涡轮发动机燃烧室出口截面的温度场之后，步骤102之前，还可以包括：
基于以下参数之一或任意组合评价重构的温度场的精确度：径向温度变化、整体温度变化、周向温度变化、周向平均径向温度分布参数。
为了评估重构信号的精确度，本申请实施例中引入以下一些参数定义。如公式(4)和公式(5)所示，在RTDF和OTDF的定义中包含有但是，缺少燃烧室入口的区域平均温度本申请实施例中，使用燃烧 室出口的区域平均温度来定义如下参数指标：
比如：燃烧室出口的径向温度变化(RTV，Radial Temperature Variation)，用于表征燃烧室出口的周向平均温度场的不均匀性。RTV的计算公式如公式(7)所示：
再如：整体温度变化(OTV，Overall Temperature Variation)，用于表征最热斑与平均温度的偏差，OTV的计算公式如公式(8)所示：
RTV与RTDF的关系如公式(9)所示，OTV与OTDF的关系如公式(10)所示：
RTV＝C0RTDF       (9)
OTV＝C0OTDF       (10)
公式(9)、公式(10)中的C0如公式(11)所示：
从本申请实施例中的RTV和OTV的定义可以看出，RTV与RTDF、OTV与OTDF都是线性关系。
又如：周向温度变化(CTV，Circumferential Temperature Variation)，用来评估热斑的温度偏差幅度。CTV的计算公式如公式(12)所示：
公式(12)中，T4,max(r)表示在径向r的圆周位置内最高温度。
还如：周向平均径向温度分布(RTP，circumferentially averaged Radial  Temperature Profile)，RTP的计算公式如公式(13)所示：
公式(13)中，表示在径向r位置沿周向平均温度值。
本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，可以应用于部件级燃烧室试验，比如单头部燃烧室、双头部扇形燃烧室，也可应用于全环形燃烧室，如直流式全环形燃烧室、折流式全环形燃烧室，以及环管形燃烧室等。本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法具有鲁棒性，易于实现。使用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，通过减少周向测点，进而显著降低了燃气涡轮发动机研制过程中的试验验证成本。本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法还可用于航空发动机运维过程中的实时健康监测。
本申请还提供一种计算机可读存储介质，存储有计算机可执行指令，所述计算机可执行指令用于执行上述任一项所述的评估涡轮发动机燃烧室的出口温度分布因子的方法。
本申请再提供一种评估涡轮发动机燃烧室的出口温度分布因子的设备，包括存储器和处理器，其中，存储器中存储有以下可被处理器执行的指令：用于执行上述任一项所述的评估涡轮发动机燃烧室的出口温度分布因子的方法的步骤。
为了验证本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法的精确度，下面以几个实际应用场景进行描述。
在一种示例性实例中，本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法应用于单头部燃烧室的场景，在一种实施例中，选择Rolls-Royce公司航空发动机单头部燃烧室为例。图3(a)显示了发动机燃烧室出口的实际测量的时均温度场，这是相关技术中公开的单头部燃烧室的测量结果，该测量结构是使用90个测量点(如图中的小黑点表示)制作的等温线，包括整个燃烧室10个径向位置和9个圆周位置。从图3(a) 可见，在燃烧室出口处观察到明显的温度不均匀性，测得的无量纲温度范围是此外，从图3(a)可见，沿圆周方向和径向方向都存在显著的不均匀性，比如沿径向测得的无量纲温度范围是 而沿周向测得的无量纲温度范围是从图3(a)还可见，在喷油嘴的位置上有明显的热斑，温度分布比较对称。
图3(b)显示了采用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，使用五个圆周位置的测量值重构的温度场，位置如图3(b)中的小黑点所示。测量位置经过仔细选择，使得最佳测量位置对应最小设计矩阵A的条件数k，以实现上文中讨论的设计矩阵A的小条件数(本实施例中k＝1.61)。在一种实施例中，可以选择波数等于燃烧室数目的单个小波来重构所有半径处的周向温度分布。如图3(b)所示，重构的温度场很好地捕捉到了热斑，包括这些热斑的位置、面积和强度。然而，在端壁区域重构的温度分布和实验结果之间存在偏差。比如底部端壁附近重构的温度分布与实验中观察到的结构不同，这是由于只选择了一个小波来重构温度分布。因此，在燃烧室单头部覆盖周向范围内只有一个低温点，而不是在实验中观察到的下端壁区域附近的两个低温点。图4比较了从实验结果和重构数据集中获得的RTP，如图4所示，最大偏差小于1.6％，重构温度与实验测量值对比，取得了良好的一致性。需要说明的是，尽管测量温度场和重构温度场之间端壁区域附近的详细温度分布存在偏差，但是，由于端壁区域附近沿圆周方向的温度不均匀性较弱，因此，这种偏差并不会影响平均径向温度的一致性。
此外，本申请实施例中重构的温度场的RTV与实验产生了极好的一致性，偏差仅为0.8点，如表1所示，表1为单头部燃烧室实验和重构的RTV、OTV比较。然而，重构的信号高估了OTV的大小，导致与实验的偏差为6.8％。
表1
表2为单头部燃烧室实验和重构的CTV比较，表2中列出了实验和 重构信号在所有跨度方向位置的CTV值，以及相应的皮尔逊相关系数，如表2所示，总体而言，重构信号获得的CTV值与实验结果处于相同的数量级。此外，与端壁区域相比，中跨区域中的皮尔逊相关系数值更高，也就是说，使用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，单波数近似方法在中跨区域获得的重构信号更具精确性。
表2
从本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法应用于单头部燃烧室的场景来看，本申请实施例中利用多波数近似方法，在用更少的测量值表征燃烧室出口热斑方面显示出了良好的潜力；而且，重构得到的燃烧室出口温度分布也很好地捕捉到了与热斑相关的特征，并且，产生的RTP与从详细实验结果中获得的RTP几乎相同；之外，重构的信号还产生了RTV的相近值。从本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法用于单头部燃烧室的场景来看，验证了本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法用于单头部燃烧室出口截面温度场的精确度。
在一种示例性实例中，本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法应用于双头部扇形燃烧室的场景，在一种实施例中，选择Rolls-Royce公司航空发动机双头部扇形燃烧室为例(包含两个燃油喷嘴)。温度场从牛津大学、QinetiQ公司和Rolls-Royce公司开发的增强型模拟器中获得。
图5(a)显示了来自两次独立测量的无量纲温度分布，本实施例中分别 为测量a和测量b，每次测量由9个径向测量点和19个圆周测量点组成，两次测量的差异体现在探针的位置上，在测量a和测量b之间，探针偏移了3mm(约5％的高度)，因此，对测量的温度场进行比较分析，测得的无量纲温度为此外，如图5(a)所示，在径向方向和圆周方向上都存在显著的不均匀性，比如平均径向(((Tmax-Tmin)/T))的最大无量纲变化为28％，沿圆周方向的变化为17％。两次测量的温度分布非常相似，并且都具有极好的对称性。
图5(b)显示了采用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，使用七个圆周位置的测量重构的温度分布，数据量大小减少了63％。测量位置经过仔细选择，使得最佳测量位置对应最小设计矩阵A的条件数k，以实现上文中讨论的设计矩阵A的小条件数(本实施例中k＝1.22)。在一种实施例中，选择波数等于燃烧室数目的单个小波来重构温度分布。在这两种情况下，如图5(b)所示，重构的温度分布很好地表征了热斑特征。结合图6、图7所示，实验结果和重构结果在RTP中取得了良好的一致性，在所有高度上，两次测量的无量纲径向温度的最大偏差都小于1.4％。
与本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法应用于单头部燃烧室类似，本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法应用于双头部扇形燃烧室的场景中，重构信号的RTV与实验产生了极好的一致性，表3为双头部扇形燃烧室实验和重构的RTV、OTV比较，如表3中列出的两次不同测量结果相比，偏差都小于半个百分点。同样，重构的信号也高估了OTV的幅度，导致与实验的偏差大约为7％。
表3
表4为双头部扇形燃烧室实验和重构的CTV比较(测量a)。
表4
表5为双头部扇形燃烧室实验和重构的CTV比较(测量b)。
表5
如图4、表5所示，列出了来自实验的所有跨度方向位置的CTV值以及来自两次不同测量(即表4的测量a，和表5的测量b)的重构信号相应的皮尔逊相关系数。总体而言，从重构信号中获得的CTV值与实验结果处于相同的数量级，并且可以得出相同的结论。从本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法用于双头部扇形燃烧室的场景来看，验证了本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法用于双头部扇形燃烧室出口截面温度场的精确度。
在一种示例性实例中，本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法应用于全环形燃烧室的场景，在一种实施例中， 选择QinetiQ公司航空发动机全环形燃烧室为例，其具有20个喷油器。图8(a)是典型环管形燃烧室的出口截面测量的温度场，如图8(a)所示，对于2072K的平均温度，测得的无量纲温度在的范围内。正如预期的那样，沿径向方向存在显著的不均匀性，在轮毂和机匣端壁处存在由燃烧室冷却剂流引起的相对低温区域。此外，由于喷油嘴的离散特性，周向变化(热斑)也很明显。更重要的是，由于第一排和第二排混合喷嘴，燃烧室头部之间存在明显的变化，这样，也使得本实施例中的全环形燃烧室提供了一个很好的例子来检查本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法在存在燃烧室头部不对称的极端条件下的精确度。
图8(b)显示了在所有半径上使用单个波数近似方法在十个圆周位置进行测量时重构的温度分布，波数等于喷油嘴的数量(本实施例中即为20)。类似地，这些测量的圆周位置，如图中的小黑点所示，被选择以产生相关条件数的最小值。如图8(b)所示，重构的温度场很好地捕捉到了与燃烧室出口温度流场相关的主要特征，比如轮毂和机匣端壁附近的冷流区域以及上中部区域的热斑的温度分布得到了很好的解决。不过，在重构的温度场中，燃烧室不同头部对应区域不对称的特征也是不存在的。图9比较了从实验中获得的RTP和重构的温度场，如图9所示，重构的温度场产生了与从实验中获得的RTDF相似的形状，在重构的流量和测量的流量之间，端壁区域的周向平均温度值非常一致。重构的温度场产生的峰值周向平均温度值低于估计值，重构结果和测量结果之间的峰值周向平均温度存在最大2.4％的偏差，这种偏差是多波数近似方法无法处理圆周非周期特征的结果，也是几乎无法通过增加测量次数来减少。
尽管在重构的温度场中没有燃烧室不同头部非对称信息，但是，重构RTV的大小与实验方面产生了极好的一致性，偏差小于半个百分点，表6为全环形燃烧室实验和重构的RTV、OTV比较示意，如表6所示，与单头部燃烧室和双头部扇形燃烧室不同的是，全环形燃烧室中重构的温度分布低估了OTV 2.4％。

表6
表7为全环形燃烧室实验和重构的CTV比较示意，表7列出了实验和重构信号在所有跨度方向位置的CTV值，以及实验的相应皮尔逊相关系数。如表7所示，从重构信号获得的CTV值与实验结果处于相同的数量级。与单头部燃烧室和双头部扇形燃烧室相比，可能是由于燃烧室出口处的温度分布中的不同头部出口温度分布非周期性，使得全环形燃烧室中重构的温度分布的皮尔逊相关系数的值较低。从本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法用于全环形燃烧室的场景来看，验证了本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法用于全环形燃烧室出口截面温度场的精确度。
表7
通过上述三个具有代表性的发动机燃烧室测试实施例，包括单头部燃烧室、双头部扇形燃烧室和全环形燃烧室，检验了本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法中多波数近似方法在重构燃烧室出口非均匀温度场方面的有效性。在前两种情况即应用于单头部燃烧室、双头部扇形燃烧室的场景下，燃烧室出口温度分布显示出了良好的周向对称性，使用单波数近似方法重构的温度分布很好地捕捉到了燃烧室出口的热斑，包括其区域、中心位置和强度。而且，重构的温度分布产生的RTP和RTV与从实验中获得的几乎相同。在存在明显的头部-头部出口温度场非对称的情况下，使用单小波方法重构的温度分布仍然可以捕捉主要的热斑相关特征，并产生与实验中的RTP和RTV的代表值相似的形状，也就是说，虽然仅使用沿圆周方向的稀疏采样测量，还是表明使用多波数近似方法来近似燃烧室出口温度分布因子具有的巨大潜力。
在一种示例性实例中，进一步的优化还可以使用本申请实施例中提到 的多波数近似方法来对单头部燃烧室、双头部扇形燃烧室或全环形燃烧室出口截面进行重构，基于重构的温度场沿周向积分以得到RTDF和OTDF。结果表明，基于少数离散探针数据，采用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，实现了高精度的流场重构及关键截面流场均值计算，而且，基于重构温度场获取的燃烧室出口截面的RTDF、OTDF均值误差在1.0％以内。
本申请实施例使用稀疏测量获得了与相关技术中基于旋转耙子沿周向每1°～2.5°测量几乎相同的径向温度分布因子，而且其中大部分预测值的差异小于1.0％。本申请实施例提供的量化涡轮发动机燃烧室的温度非均匀性的方法可以应用于单头部燃烧室、双头部扇形燃烧室和全环形燃烧室等场景，通过减少周向测点，进而显著降低了燃气涡轮发动机燃烧室研制及试验验证成本。本申请实施例提供的量化涡轮发动机燃烧室的温度非均匀性的方法还可用于航空发动机运维过程中的实时健康监测。
在一种示例性实例中，进一步的优化还可以使用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法得到的RTDF和OTDF来优化燃烧室的设计，尤其是冷却气流的分布。举个例子来看，高压涡轮(HPT)叶片或转子叶片的轻微表面温度超高会导致严重损坏或显著缩短部件寿命，相关技术中，由于在燃烧室出口处没有直接的温度测量，HPT叶片/转子的冷却尺寸一般是为最坏的情况设计的，通常是预测的峰值温度，这会导致大量的冷却量需求，目前已经达到了高压压气机流量的30％，对发动机造成了显著的性能损失。在一种示例性实例中，使用本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的方法，可以通过少量的测量值来重构温度场，比较容易地获得RTDF和OTDF，相比与以前需要通过复杂和昂贵的实验来获得温度场数据，这对优化燃烧室的设计取到了积极的意义。
图10为本申请实施例中评估涡轮发动机燃烧室的出口温度分布因子的装置的组成结构示意图，如图10所示，包括：获取模块、重构模块，以及评估模块；其中，
获取模块，用于获取涡轮发动机燃烧室出口截面上预设数量的温度测 量值；
重构模块，用于根据获取的温度测量值，利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场；
评估模块，用于根据重构得到的温度场，获取径向温度分布因子和整体温度分布因子，以量化涡轮发动机燃烧室出口截面的温度不均匀性。
在一种示例性实例中，温度测量值包括少于20的少量离散的测量值。在一种实施例中，可以使用以下任一或任意组合方式获取温度测量值：热电偶、燃气分析、激光诱导荧光或红外热成像等测量技术。
在一种示例性实例中，评估模块可以用于：基于重构得到的温度场沿周向积分，获取径向温度分布因子和整体温度分布因子。
在一种示例性实例中，重构模块还可以用于：基于皮尔逊相关系数评估重构的温度场的置信度。
在一种示例性实例中，重构模块还可以用于：基于以下参数之一或任意组合评价重构的温度场的精确度：径向温度变化、整体温度变化、周向温度变化、周向平均径向温度分布参数。
本申请实施例提供的评估涡轮发动机燃烧室的出口温度分布因子的装置，简单、准确地预测涡轮发动机燃烧室的温度非均匀性，且降低成本。本申请实施例有效地解决了热斑相关特征在重构温度场中的问题，并使用稀疏测量获得了与实际测量几乎相同的径向温度分布因子，实用性强。
虽然本申请所揭露的实施方式如上，但所述的内容仅为便于理解本申请而采用的实施方式，并非用以限定本申请。任何本申请所属领域内的技术人员，在不脱离本申请所揭露的精神和范围的前提下，可以在实施的形式及细节上进行任何的修改与变化，但本申请的专利保护范围，仍须以所附的权利要求书所界定的范围为准。

Claims (16)

  1. 一种评估涡轮发动机燃烧室的出口温度分布因子的方法，其特征在于，包括：
    获取涡轮发动机燃烧室出口截面上预设数量的温度测量值；
    根据获取的温度测量值，利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场；
    根据重构得到的温度场，获取径向温度分布因子和整体温度分布因子，以量化涡轮发动机燃烧室出口截面的温度不均匀性。
  2. 根据权利要求1所述的方法，所述重构涡轮发动机燃烧室出口截面的温度场之后，所述获取径向温度分布因子和整体温度分布因子之前，还包括：
    基于皮尔逊相关系数评估所述重构的温度场的置信度。
  3. 根据权利要求2所述的方法，其中，所述皮尔逊相关系数ρ的计算公式如下：
    其中，Ti表示测量的与第i个波数相关的真实温度值，Tfit,i表示所述重构后得到的温度场的与第i个波数相关的温度值，脚标i用于指示与第i个波数相关的参数。
  4. 根据权利要求2所述的方法，所述重构涡轮发动机燃烧室出口截面的温度场之后，所述获取径向温度分布因子和整体温度分布因子之前，还包括：
    基于以下参数之一或任意组合评价重构的温度场的精确度：径向温度变化、整体温度变化、周向温度变化、周向平均径向温度分布参数。
  5. 根据权利要求4所述的方法，其中，对于基于所述径向温度变化评价重构的温度场的精确度的情况，所述径向温度变化RTV的计算公式如下：
    其中，表示所述涡轮发动机燃烧室出口的周向平均最大温度，表示所述涡轮发动机燃烧室出口的区域平均温度；
    对于基于所述整体温度变化评价重构的温度场的精确度的情况，所述整体温度变化OTV的计算公式如下：
    其中，T4,max表示燃烧室出口的最大温度；
    对于基于所述周向温度变化评价重构的温度场的精确度的情况，所述周向温度变化CTV的计算公式如下：
    其中，T4,max(r)表示在径向r的圆周位置内最高温度；
    对于基于所述周向平均径向温度分布参数评价重构的温度场的精确度的情况，所述周向平均径向温度分布参数RTP的计算公式如下：
    其中，表示在径向r位置沿周向平均温度值。
  6. 根据权利要求1、2或4所述的方法，其中，使用以下任一或任意组合方式获取所述温度测量值：热电偶、燃气分析、激光诱导荧光或红外热成像等测量技术。
  7. 根据权利要求1、2或4所述的方法，其中，所述预设数量为少于20。
  8. 根据权利要求1、2或4所述的方法，其中，所述利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场包括：通过下面公式计算：
    其中，
    T(θ)表示半径为R，位置为θ处的温度场，c0表示温度信号的直流分量，Wn表示所选取的主导波数，其中，A和分别表示第i波数相关所述温度的幅度和相位，脚标i用于指示与第个i波数相关的参数，N表示主导波数的数目。
  9. 根据权利要求1、2或4所述的方法，其中，基于所述重构得到的温度场沿周向积分，获取所述径向温度分布因子和所述整体温度分布因子。
  10. 根据权利要求1、2或4所述的方法，还包括：根据所述获取的径向温度分布因子和整体温度分布因子优化所述涡轮发动机燃烧室的冷却气流的分布。
  11. 根据权利要求1、2或4所述的方法，其中，所述涡轮发动机燃烧室出口截面包括：单头部燃烧室出口截面，或双头部扇形燃烧室出口截面，或全环形燃烧室出口截面。
  12. 一种计算机可读存储介质，存储有计算机可执行指令，所述计算机可执行指令用于执行权利要求1～权利要求11任一项所述评估涡轮发动机燃烧室的出口温度分布因子的方法。
  13. 一种实现评估涡轮发动机燃烧室的出口温度分布因子的设备，包括存储器和处理器，其中，存储器中存储有以下可被处理器执行的指令：用于执行权利要求1～权利要11任一项所述的评估涡轮发动机燃烧室的出口温度分布因子的方法的步骤。
  14. 一种评估涡轮发动机燃烧室的出口温度分布因子的装置，其特征在于，包括：获取模块、重构模块，以及评估模块；其中，
    获取模块，用于获取涡轮发动机燃烧室出口截面上预设数量的温度测量值；
    重构模块，用于根据获取的温度测量值，利用多波数近似方法重构涡轮发动机燃烧室出口截面的温度场；
    评估模块，用于根据重构得到的温度场，获取径向温度分布因子和整体温度分布因子，以量化涡轮发动机燃烧室出口截面的温度不均匀性。
  15. 根据权利要求14所述的装置，所述重构模块还用于：基于皮尔逊相关系数评估所述重构的温度场的置信度。
  16. 根据权利要求14或15所述的装置，所述重构模块还用于：基于以下参数之一或任意组合评价所述重构的温度场的精确度：径向温度变化、整体温度变化、周向温度变化、周向平均径向温度分布参数。
PCT/CN2023/120425 2023-08-02 2023-09-21 评估涡轮发动机燃烧室的出口温度分布因子的方法及装置 Pending WO2025025317A1 (zh)

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