CN113465768A - Gas temperature inversion method for aircraft engine - Google Patents

Gas temperature inversion method for aircraft engine Download PDF

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CN113465768A
CN113465768A CN202110698792.4A CN202110698792A CN113465768A CN 113465768 A CN113465768 A CN 113465768A CN 202110698792 A CN202110698792 A CN 202110698792A CN 113465768 A CN113465768 A CN 113465768A
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temperature
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fuel gas
aircraft engine
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CN113465768B (en
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吕金光
赵莹泽
梁静秋
王惟彪
秦余欣
陶金
郑凯丰
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Changchun Institute of Optics Fine Mechanics and Physics of CAS
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
    • G01K11/006—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using measurement of the effect of a material on microwaves or longer electromagnetic waves, e.g. measuring temperature via microwaves emitted by the object
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/02—Details or accessories of testing apparatus
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract

The invention provides an aircraft engine fuel gas temperature inversion method, which is characterized in that a spectrometer is used for measuring the fuel gas radiation spectrum in an aircraft engine in real time, iterative calculation is carried out according to the measured radiation spectrum and a dual-wavelength absorption coefficient ratio database, and when the difference between the calculated temperature of the fuel gas to be measured and the initially set temperature is within the calculation error, the temperature is the temperature of the fuel gas to be measured. The method does not need an active light source, inverts the gas temperature by measuring the internal radiation spectrum distribution of the aircraft engine during operation, has the advantages of good measurement real-time performance, simple modification on the existing engine, simple measurement device and the like compared with the traditional gas temperature measurement method, reduces the application cost, and improves the stability of the measurement system.

Description

Gas temperature inversion method for aircraft engine
Technical Field
The invention belongs to the technical field of spectrum temperature measurement, and particularly relates to a passive aero-engine-based fuel gas temperature inversion method.
Background
At present, the methods for measuring the gas temperature of the aircraft engine mainly comprise the following steps:
1. gas analysis thermometry: the method is used for calculating the gas temperature according to a gas combustion chemical equation by analyzing the content of various components in the gas. A mixture sample of fuel gas and fuel is extracted mainly through a probe, after quenching, the mixture sample is transmitted to a gas analyzer through a pipeline to carry out component and content analysis on the sample, and then combustion efficiency and a residual gas coefficient are calculated according to a combustion equation, so that the temperature of the fuel gas is calculated. The method is commonly used for measuring the distribution of the temperature field at the outlet of the combustion chamber during ground test of the aircraft engine. However, the gas temperature is measured by adopting a gas sampling mode, the structure of the sampling probe is complex, the sampling probe needs a huge water cooling mechanism to cool in order to prevent the sampling probe from being ablated by high-temperature gas, the volume structure is large, the sampling probe can only be used for an aircraft engine ground experiment platform, and the real-time gas temperature online measurement cannot be realized.
2. Tunable laser absorption spectroscopy: and the measurement of the gas temperature is realized by utilizing the characteristic that the gas absorption spectrum changes along with the temperature. The line intensity of a specific fuel gas absorption spectrum line has a functional relation with the fuel gas temperature, the absorption lines of the tunable laser absorption spectrum in two different wavelength absorption areas under the same absorption path are measured simultaneously, the ratio function corresponding relation of the line intensity of the spectrum corresponding to two wavelengths and the fuel gas temperature can be calculated based on the beer Lambert law, and the measured fuel gas temperature can be obtained. However, the measurement mode using active laser requires two engine casing wall openings at the transmitting end and the receiving end of the laser, which makes the modification of the existing engine difficult. The space inside the engine, which is very small, is limited, and the application of the active technology has a limitation. Meanwhile, the laser transmitting end and the laser receiving end are easily polluted by gas flow and carbon black particles during operation, so that the measurement precision is reduced.
3. Fourier transform spectroscopy: and calculating the temperature of the measured gas by establishing the relationship between the rotation constant and the temperature of the molecules based on the different rotation constants of the gas molecules in different waveband emission bands. Specifically, a Fourier transform spectrometer is used for measuring a spectrum absorption spectrum line of hot gas, and the temperature of the measured gas can be obtained by measuring gas radiation spectra of the gas at two different reference temperatures and acquiring a functional relation between a rotation constant and the temperature in a rotary vibration spectral band of the gas. However, due to the unique structure of the fourier transform spectrometer, the spectrum needs to be acquired by controlling the movement of the movable mirror, so the acquisition of the spectrum needs about 10s, which has the disadvantage of lagging the temperature measurement of the high-speed gas flow and cannot reflect the real-time temperature of the engine. Meanwhile, the Fourier transform spectrometer is usually used for measuring tail flames discharged by an engine in a remote measuring and measuring mode, the temperature of fuel gas in the engine cannot be measured, and the Fourier transform spectrometer and an aeroengine are difficult to integrate.
Disclosure of Invention
The invention provides an aircraft engine fuel gas temperature inversion method for overcoming the defects of the measurement method. When the aircraft engine works, a large amount of fuel gas is filled between the turbine blade and the optical probe, and the passive high-temperature fuel gas radiation transmission model is established by taking the gas layer radiation transmission model as a reference. When the aircraft engine works, fuel oil and air are mixed and then ignited in the combustion chamber, a large amount of high-temperature fuel gas (namely fuel gas to be tested) sprayed out from the rear of the combustion chamber is rectified by the static guide turbine blades to push the rotor turbine blades to rotate, and meanwhile, high-speed airflow of the high-temperature fuel gas sprayed out backwards generates forward thrust. The optical probe is placed between the guide turbine blade and the rotor turbine blade during measurement, and because the guide turbine blade does not rotate in the working process of the aero-engine, the temperature distribution of the surface is stable, the air flow between the guide turbine blade and the probe is stable, the distance between the probe and the guide turbine blade is small, and the gas flow field between the guide turbine blade and the measurement probe can be regarded as uniform distribution. Thus, the guide vane blades serve as a source of background radiation in the entire measurement model. And inverting the temperature of the fuel gas to be measured by a dual-wavelength absorption coefficient ratio temperature measurement method, thereby realizing real-time measurement of the fuel gas temperature of the aircraft engine. In order to achieve the purpose, the invention adopts the following specific technical scheme:
an aircraft engine fuel gas temperature inversion method comprises the following steps:
s1, calculating the temperature T of the gas to be measured according to the fitting function relation model of the formula (1)gas＝TaTime, two-band gas absorption coefficient ratio
Figure BDA0003128907930000031
Figure BDA0003128907930000032
Wherein, wj(j ═ 0,1,2, … n) is a fitting parameter of the polynomial;
λ1and λ2The wavelengths of two arbitrary characteristic absorption peaks in a characteristic absorption waveband of the fuel gas to be detected are measured;
s2, using the ratio of the two-waveband gas absorption coefficient of the formula (2) and the temperature T of the fuel gas to be measuredgasThe relationship model of (1) inverting the temperature T of the gas to be measuredgas：
Figure BDA0003128907930000033
Wherein, TbIs the temperature of the guide turbine blades;
Ltotalthe total spectral radiant energy received by the spectrometer;
L(λ1，Tgas),L(λ2,Tgas) The spectrum radiation energy of the fuel gas to be measured at different wavelengths received by the spectrometer;
s3, iterative operation is carried out on the results obtained in the steps S1 and S2 to enable | Ta-TgasIf is less than delta, obtaining the inverted gas temperature T to be measuredgasAnd δ is the set temperature calculation error.
Preferably, step S0 is further included before step S1, and step S0 is used for establishing the dual-band gas absorption coefficient ratio of the type (2) and the temperature T of the fuel gas to be measuredgasThe relationship model of (1).
Preferably, step S0 includes the steps of:
s01, establishing a spectral radiation energy transmission model of the guide turbine blade and the fuel gas to be detected:
Ltotal＝εgas(λi,Tgas)L(λi,Tgas)+τgas(λi,Tgas)Lb(λi,Tb) (3)
wherein, λ is the wavelength of the characteristic absorption peak of the fuel gas to be measured received by the spectrometer in the response band range;
εgas(λi,Tgas) The emissivity of the gas to be measured;
τgas(λi,Tgas) The transmittance of the fuel gas to be measured;
L(λi,Tgas) The radiation energy of the fuel gas to be detected;
Lb(λi,Tb) Radiant energy for a turbine blade;
Tbis the temperature of the guide turbine blades;
s02, determining characteristic wave absorption band of to-be-detected gas and inverting temperature T of to-be-detected gasgasWavelength lambda of the two characteristic absorption peaks required1And λ2And introducing the spectrum radiation energy transmission model to obtain:
Figure BDA0003128907930000041
s03, further reducing the formula (4) according to the lambert beer law to obtain the formula (2).
Preferably, step S0 further includes the following steps for building a fitting functional relationship model of the type (1):
s04, calibrating the ratio of the absorption coefficients of the two-waveband gas based on the two characteristic absorption peaks at different temperatures
Figure BDA0003128907930000042
S05, discrete points of the measured ratio of the absorption coefficients of the dual-waveband gas at n different gas temperatures
Figure BDA0003128907930000043
And (4) carrying out polynomial fitting to obtain a fitting function relation model of the formula (1).
Preferably, j is 3.
The invention can obtain the following technical effects:
1. the invention is not limited to the type of spectrometer, and the method can be used for measuring the temperature of any gas in the response wave band of any spectrometer.
2. The invention can measure other kinds of gases in high-temperature fuel gas, such as water vapor, carbon monoxide, nitrogen oxide and the like, and can also replace carbon dioxide gas to realize inversion of fuel gas temperature.
Drawings
FIG. 1 is a flow chart of a method for inverting the gas temperature of an aircraft engine according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a high temperature gas measurement system of an aircraft engine gas temperature inversion method according to an embodiment of the invention;
FIG. 3 is a calibration curve diagram of the ratio of the two-band gas absorption coefficient to the CO gas temperature under different working conditions according to an embodiment of the present invention;
FIG. 4 shows a ratio of two-band absorption coefficient to CO at different operating conditions according to an embodiment of the present invention2Calibration curve diagram of gas temperature.
Reference numerals:
the device comprises a guide turbine blade 1, a gas to be detected 2, an optical system 3 and a spectrometer 4.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention.
The invention aims to provide an aircraft engine gas temperature inversion method, which can solve the problem of gas temperature monitoring during the operation of an aircraft engine, has the advantages of good measurement real-time performance, simple modification of the existing engine, simple measurement device and the like compared with the traditional high-temperature gas temperature measurement method, reduces the application cost, and improves the stability of a measurement system. The method for inverting the gas temperature of the aircraft engine provided by the invention will be described in detail through specific embodiments.
As shown in fig. 1, a flow chart of the inversion method for the temperature of the fuel gas to be measured calculates the ratio of the two-band gas absorption coefficients at different gas temperatures according to the spectral radiation curve of the fuel gas to be measured by the spectrometer and the band of the characteristic absorption peak of the corresponding gas, and fits and calibrates the functional relationship between the ratio of the two-band gas absorption coefficients and the temperature of the fuel gas to be measured. When calculating the inversion of the gas temperature to be measured, firstly setting the initial gas temperature TaAnd calculating the gas temperature as T according to the fitting function relation model (1)aThe corresponding two-waveband gas absorption coefficient ratio. Substituting the calculated ratio of the two-waveband gas absorption coefficient into the ratio of the two-waveband gas absorption coefficient and the temperature T of the gas to be measuredgasIn the relational model (2), the gas temperature value T corresponding to this time is calculatedgasIf at this time, | T is satisfieda-TgasWhen | < delta, the temperature calculation error is satisfied, and the temperature value is output as the temperature value of the fuel gas to be measured at the moment. When the relation is not satisfied, readjusting T according to the working conditionaThe calculation process is repeated until the temperature calculation error is met, and the corresponding gas temperature value at the moment is output.
Referring to the schematic diagram of the high-temperature gas measurement system shown in fig. 2, during the measurement process, the optical system 3 simultaneously receives the radiation energy of the gas 2 to be measured and the radiation energy (background radiation energy) from the turbine blades 1 of the turbine in the aircraft engine, which passes through the gas 2 to be measured, so that the total radiation energy received by the spectrometer 4 includes two parts: the radiation energy of the guide turbine blade 1 in the aircraft engine and the spectral radiation energy of the gas 2 to be measured establish the following spectral radiation energy transmission model:
Ltotal＝εgas(λi,Tgas)L(λi,Tgas)+τgas(λi,Tgas)Lb(λi,Tb) (3)
wherein, λ is the wavelength of the characteristic absorption peak of the fuel gas 2 to be measured in the response waveband range of the spectrometer 4;
εgas(λi,Tgas) The emissivity of the gas 2 to be measured;
τgas(λi,Tgas) The transmittance of the fuel gas 2 to be measured;
L(λi,Tgas) The radiation energy of the fuel gas 2 to be detected;
Lb(λi,Tb) Radiant energy for the guide turbine blades 1;
Tbis the temperature of the guide turbine blade 1.
The relation between the transmittance and the emissivity of the fuel gas can be obtained according to kirchhoff's law as follows: tau isgas(λi,Tgas)+εgas(λi,Tgas) 1, formula (3) can therefore be represented as:
Ltotal＝τgas(λi,Tgas)Lb(λi,Tb)+[1-τgas(λi,Tgas)]L(λi,Tgas) (6)
selecting any two characteristic absorption peaks lambda in the characteristic absorption wave band of the fuel gas 2 to be detected1And λ2Substituting into a spectral radiant energy transmission model to obtain:
Figure BDA0003128907930000061
from Lambert beer's law, τ is knowngas(λ1,Tgas)＝1-exp[-k(λ1)cgass]Therefore, formula (4) is rewritten as:
Figure BDA0003128907930000071
wherein, CgasThe concentration of the fuel gas 2 to be detected;
s is a measuring optical path;
further simplification of formula (7) yields:
Figure BDA0003128907930000072
as can be seen from equation (2): wavelength lambda of two characteristic absorption peaks in the characteristic absorption band of the gas 2 to be measured1And λ2Corresponding dual-band gas absorption coefficient ratio
Figure BDA0003128907930000073
Only with the total spectral radiant energy L received by the spectrometer 4total(λi) And the radiation energy L (lambda) of the gas 2 to be measuredi,Tgas) In relation to this, the concentration C of the gas 2 to be measuredgasThe parameters such as the measuring optical path S are irrelevant.
Therefore, the invention provides a calibration algorithm of the ratio of the two-waveband absorption coefficients, which is used for measuring the ratio of the two-waveband gas absorption coefficients of the gas 2 to be measured at the characteristic absorption peak under different gas temperatures to be measured according to the measured values
Figure BDA0003128907930000074
And the temperature T of the gas to be measuredgasFitting to obtain the ratio of the two-waveband gas absorption coefficient and the temperature T of the fuel gas to be measuredgasThe fitting function relation model is finally obtained through inversion calculation to obtain the temperature T of the fuel gas to be measuredgas。
The fitting function relation model establishment method comprises the following steps:
firstly, the discrete points of the ratio of the two-band gas absorption coefficients at different temperatures of the fuel gas to be measured are measured and can be expressed as:
Figure BDA0003128907930000075
wherein, T1，T2，…，TnRespectively represent different temperatures;
Figure BDA0003128907930000081
respectively, the temperature T obtained by the formula (2)1，T2，…，TnThe ratio of the corresponding two-band gas absorption coefficients;
secondly, fitting the obtained n discrete points into a polynomial by using a least square method, wherein the form of the polynomial is as follows:
Figure BDA0003128907930000082
wherein, wj(j ═ 0,1,2, … n) is a fitting parameter of the polynomial;
Ti(i ═ 1,2, …, j) denotes different temperatures;
the fitting functional relationship model is finally obtained as follows:
Figure BDA0003128907930000083
different fitting function relation models (1) can be obtained for different types of to-be-measured gas 2 according to data measured by experiments, and fitting parameters w corresponding to different polynomialsj(j＝0,1,2,…n)。
When the temperature of the fuel gas to be measured is inverted, the initial temperature of the fuel gas 2 to be measured is randomly selected to be TaCalculating the initial temperature T according to the fitting function relation model, namely the formula (1)aTime, corresponding dual-band gasRatio of bulk absorption coefficient
Figure BDA0003128907930000084
Then the corresponding two-waveband gas absorption coefficient ratio is compared
Figure BDA0003128907930000085
The ratio of the absorption coefficient of the gas brought into the dual-band and the temperature T of the gas to be measuredgasThe relation model of (2) is used for calculating the temperature T of the gas to be measured at the momentgas；
Finally, calculate TaAnd TgasIf | T is equal toa-TgasIf the value is less than delta, the calculation error is satisfied, and the initial temperature value T is usedaAnd obtaining the temperature of the fuel gas to be measured as inversion. When the relation is not satisfied, readjusting T according to the working conditionaThe calculation process is repeated until the set temperature calculation error value delta is met, and the corresponding gas temperature value T at the moment is outputa。
The temperature solving judgment principle is shown in Table 1, and the initial temperature value T is adjusted in the Case of Case 1 and Case 2aAnd (4) until the temperature calculation error delta is kept within the error allowable range, and finally reaching the Case of Case 3, and finishing the iterative calculation.
TABLE 1 Dual band absorption coefficient ratio algorithm temperature solving judgment principle
Figure BDA0003128907930000091
TABLE 2 characteristic absorption band of common gases
Figure BDA0003128907930000092
In a preferred embodiment of the present invention, taking the gas 2 to be measured as CO and the spectrometer 4 as a common near infrared fiber spectrometer as an example, it can be known from table 2 that at a wavelength band near a characteristic absorption peak of CO of 2.3 μm, the spectral radiation energy received by the spectrometer 4 includes radiation energy from the background and radiation energy of CO.
According to Table 2, a selection of lambda around 2.3 μm was chosen1＝2334nm(4285cm-1) And λ2＝2319nm(4312cm-1) Two wavelengths are taken as two characteristic absorption peaks of CO gas, and the ratio of the two-waveband gas absorption coefficient at the temperature of 700-1500K is calibrated according to a HITEMP high-temperature spectrum database as shown in FIG. 3
Figure BDA0003128907930000093
The distribution curve of (2) shows that the ratio of the dual-waveband gas absorption coefficient and the gas temperature are in positive correlation change, and the ratio of the dual-waveband gas absorption coefficient is gradually increased along with the increase of the gas temperature.
Under this condition, a higher fitting accuracy can be achieved by using a third-order fitting polynomial j equal to 3, and therefore, the fitting function relationship model is as follows:
Figure BDA0003128907930000101
obtaining a polynomial fitting equation by using a least square method as follows:
Figure BDA0003128907930000102
performing iterative operation on the formula (1-1) and the formula (2) until the gas temperature T to be measured corresponding to the ratio of the two-waveband gas absorption coefficients calibrated by the formula (1-1) is simultaneously satisfiedgasAnd T calculated by the formula (2)gasThe corresponding temperature error value is within the set temperature calculation error delta, and the corresponding gas temperature T to be measured in the formula (1-1)gasNamely the temperature of the fuel gas 2 to be measured obtained by inversion.
In another preferred embodiment of the invention, the fuel gas 2 to be measured is CO2The spectrometer 4 is a common near infrared fiber spectrometer with response bands, as shown in Table 2, where CO is present at 1.4 μm, 1.6 μm and 2.0 μm2Absorption peak of (2) in CO2At the characteristic absorption peak of (1), spectrometer4 the received spectral radiant energy comprises radiant energy from the background and CO2Of the radiation energy of (1).
According to Table 2, λ is selected1＝2028nm(4930cm-1) And λ2＝2022nm(4945cm-1) As CO2Two characteristic absorption peaks of gas, with reference to the ratio of two-band gas absorption coefficients at the temperature of 600-1500K calibrated according to HITEMP high temperature spectrum database as shown in FIG. 4
Figure BDA0003128907930000103
The distribution curve of (2) shows that the ratio of the dual-waveband gas absorption coefficient and the gas temperature are in positive correlation change, and the ratio of the dual-waveband gas absorption coefficient is gradually increased along with the increase of the gas temperature.
Taking a measurement working condition of 5atm as an example, a higher fitting accuracy can be achieved by using a third-order fitting polynomial j equal to 3, and therefore, a fitting function relation model is as follows:
Figure BDA0003128907930000104
obtaining a polynomial fitting equation by using a least square method as follows:
Figure BDA0003128907930000111
performing iterative operation on the above formula (1-2) and the formula (2) until the gas temperature T to be measured corresponding to the ratio of the two-waveband gas absorption coefficients calibrated by the formula (1-2) is simultaneously satisfiedgasAnd T calculated by the formula (2)gasThe corresponding temperature error value is within the set temperature calculation error delta, and the corresponding gas temperature T to be measured in the formula (1-2)gasNamely the temperature of the fuel gas 2 to be measured obtained by inversion.
Therefore, when the gas temperature is measured, the method can realize the temperature T of the gas to be measured only by calibrating the absorption coefficient ratio of the gasgasAnd can be implemented in any response band of the spectrometer 4And measuring the temperature of the fuel gas to be measured.
The high-temperature gas measurement method in the prior art is limited by the response range of the spectrometer 4 and can only measure water vapor and carbon dioxide, and the aero-engine gas temperature inversion method provided by the invention can invert the temperature of any gas in the high-temperature gas by only having the absorption peak of the gas component gas in the response range of the spectrometer without limiting the type of the spectrometer.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
The above embodiments of the present invention should not be construed as limiting the scope of the present invention. Any other corresponding changes and modifications made according to the technical idea of the present invention should be included in the protection scope of the claims of the present invention.

Claims (5)

1. An aircraft engine fuel gas temperature inversion method is characterized by comprising the following steps:
s1, calculating the temperature T of the gas to be measured according to the fitting function relation model of the formula (1)gas＝TaTime, two-band gas absorption coefficient ratio
Figure FDA0003128907920000011
Figure FDA0003128907920000012
Wherein, wj(j ═ 0,1,2, … n) is a fitting parameter of the polynomial;
λ1and λ2The wavelengths of any two characteristic absorption peaks in a characteristic absorption waveband of the fuel gas to be detected are obtained;
s2, utilizing the ratio of the two-waveband gas absorption coefficient of the formula (2) to the temperature T of the fuel gas to be measuredgasThe relationship model of (1) inverting the temperature T of the gas to be measuredgas：
Figure FDA0003128907920000013
Wherein, TbIs the temperature of the guide turbine blades;
Ltotalthe total spectral radiant energy received by the spectrometer;
L(λ1，Tgas)，L(λ2，Tgas) The spectral radiant energy of the fuel gas to be detected at different wavelengths received by a spectrometer;
s3, iterative operation is carried out on the results obtained in the steps S1 and S2 to make | Ta-TgasIf is less than delta, obtaining the inverted temperature T of the fuel gas to be measuredgasAnd δ is the set temperature calculation error.
2. The aircraft engine gas temperature inversion method according to claim 1, further comprising a step S0 before the step S1, wherein the step S0 is used for establishing the dual-band gas absorption coefficient ratio of the type (2) and the measured gas temperature TgasThe relationship model of (1).
3. The aircraft engine gas temperature inversion method according to claim 2, wherein the step S0 includes the steps of:
s01, establishing a vertical (3) spectral radiation energy transmission model of the guide turbine blade and the fuel gas to be detected:
Ltotal＝εgas(λi,Tgas)L(λi,Tgas)+τgas(λi,Tgas)Lb(λi,Tb)(3)
wherein λ is the wavelength of the characteristic absorption peak of the gas to be measured received by the spectrometer within the response band range;
εgas(λi,Tgas) The emissivity of the gas to be measured is obtained;
τgas(λi,Tgas) The transmittance of the fuel gas to be detected is adopted;
L(λi,Tgas) The radiant energy of the fuel gas to be detected is obtained;
Lb(λi,Tb) Radiant energy for the flow directing turbine blades;
Tbis the temperature of the guide turbine blade;
s02, determining the characteristic wave absorption band of the gas to be detected and inverting the temperature T of the gas to be detectedgasWavelength lambda of the two characteristic absorption peaks required1And λ2And substituting the spectral radiant energy transmission model with:
Figure FDA0003128907920000021
s03, further reducing the formula (4) according to the lambert beer law to obtain the formula (2).
4. The aircraft engine gas temperature inversion method according to claim 3, wherein the step S0 further comprises the steps of establishing the fitted functional relationship model of the vertical type (1):
s04, calibrating the ratio of the absorption coefficients of the two bands of gas based on the two characteristic absorption peaks at different temperatures
Figure FDA0003128907920000022
S05, discrete points of the measured ratio of the absorption coefficients of the dual-band gas at n different gas temperatures
Figure FDA0003128907920000023
And (4) carrying out polynomial fitting to obtain a fitting function relation model of the formula (1).
5. The aircraft engine gas temperature inversion method of claim 4, wherein j is 3.
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