Optimization Method for Installation Angle and Position of Multi-Channel Pyrometers in Aeroengines

Abstract

Optimization method for installation angle and position of multi-channel pyrometers in aero-engines. By reasonably abstracting evaluation indicators, the optimal installation angle and position can be obtained in advance before the equipment is put into use, which can ensure the reliable and effective operation of the multi-channel pyrometers to the greatest extent. The method includes the following steps: Step 1, determine the installation position parameters of the n-channel pyrometer, where n is an integer greater than 1, and the position parameters include the probe angle a, the front-back displacement b, and the left-right displacement c; Step 2, construct a geometric model of the measured turbine blade including the n-channel pyrometer and its installation position parameters, and perform ray tracing; Step 3, determine the evaluation indicators, and calculate the evaluation indicators using the ray tracing results; Step 4, use one or several comprehensive evaluation methods to conduct an evaluation to obtain the final score; Step 5, take the score as the optimization target, and use one or several optimization algorithms to optimize to obtain the position parameters that maximize the score.

Description

Technical Field

[0001] The present invention belongs to the technical field of turbine blade radiation temperature measurement, and particularly relates to an optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine. Background Art

[0002] Pyrometers based on the principle of radiation temperature measurement are widely used in the aerospace field due to their large temperature measurement range and high accuracy. One of the most important application scenarios in this field is to measure the surface temperature of turbine blades, so as to realize real-time monitoring of their health status and prevention of failure. The space near the turbine blades is narrow, and the blades are arranged closely, leaving very limited space for the installation or sampling of measuring devices. On the other hand, the radiation angle is an important factor affecting the temperature measurement accuracy of the pyrometer, which is not only related to the amount of radiation energy received by the pyrometer, but also related to the resolution of the temperature measurement target point of the pyrometer. A suitable installation angle and position can greatly reduce the temperature measurement error caused by the radiation angle. Therefore, the optimal selection of the installation angle and position of the pyrometer is crucial. Summary of the Invention

[0003] The present invention provides an optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine, which is particularly suitable for determining the installation angle and position of the pyrometer in industrial applications to achieve the best use effect.

[0004] The technical solution of the present invention is as follows:

[0005] An optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine, characterized by comprising the following steps:

[0006] Step 1, determining the installation position parameters of an n-channel pyrometer, where n is an integer greater than 1, and the position parameters include the probe angle a, the front-back displacement b, and the left-right displacement c;

[0007] Step 2, constructing a geometric model of the measured turbine blade including the n-channel pyrometer and its installation position parameters, and performing ray tracing;

[0008] Step 3, determining the evaluation index, and calculating the evaluation index by using the ray tracing result;

[0009] Step 4, adopting one or several comprehensive evaluation methods for evaluation to obtain the final score;

[0010] Step 5, taking the score as the optimization target, and adopting one or several optimization algorithms to optimize to obtain the position parameters that maximize the score.

[0011] The geometric model of the measured turbine blade in the step 2 includes at least two guide vanes and at least one moving vane, and the angle between the two guide vanes is The pyrometer is located between two guide vanes, namely the guide vane and the adjacent guide vane, and the moving blade is the moving blade to be measured; in the ray tracing process, the pyrometer emits rays, the rays are transmitted to the moving blade to be measured and frozen, and the moving blade to be measured rotates at an interval angle γ in the circumferential direction of the turbine.

[0012] In step 3, the following configurations of the geometric optics physical field are included: modify the "maximum number of secondary rays" in the geometric optics setting area to 0; modify the "vacuum wavelength" in the ray attribute setting area under the geometric optics node to the corresponding wavelength value; add the "wall" attribute, select all boundaries for the boundary, and set the "wall condition" to frozen; add the "ray detector attribute", select the surface of the blade to be measured for the boundary; add the "release from boundary" attribute, select the ray emission surface for the boundary, select "grid-based" for the initial position, and check "specify the tangential and normal vector components", and modify it to the direction vector of the actually required ray emission direction; add the "specular reflection" attribute according to the actual situation, and select the reflection surface for the boundary.

[0013] The evaluation indexes in step 3 include the angular factor A, the overall variance B, the working distance C, the guide vane distance D, and the resolution error E; the single angular factor is defined as where θ is the incident angle of a single ray, then the angular factor where m is a positive integer, and the smaller the angular factor A, the higher the evaluation score; the smaller the overall variance B, the higher the evaluation score; the closer the working distance C is to the designed working distance, the higher the evaluation score; the guide vane distance D refers to the distance between the pyrometer and one of the guide vanes, and the closer the position of the pyrometer is to the middle of the two guide vanes, the higher the evaluation score; the resolution error E is expressed as where S r is the actual resolution area of the temperature measurement target point, and S d is the designed resolution area of the temperature measurement target point, and the smaller the resolution error E, the higher the evaluation score.

[0014] In step 4, the evaluation methods include the analytic hierarchy process, the fuzzy evaluation method, the rank sum ratio method, the comprehensive analysis method and / or the Topsis method.

[0015] In step 5, the optimization algorithms include the Newton method, the gradient descent method, the simulated annealing method, the genetic algorithm, the ant colony algorithm and / or the particle swimming method.

[0016] The technical effects of the present invention are as follows: The present invention discloses an optimization method for the installation angle and position of a multi-channel pyrometer in an aeroengine, which is related to the determination of the installation position of the pyrometer in industrial applications, including: determining the installation position parameters of the n-channel pyrometer; constructing a geometric model of the pyrometer and the measured turbine blade, and performing ray tracing; determining evaluation indexes, and calculating the evaluation indexes by using the ray tracing results; adopting one or several comprehensive evaluation methods for evaluation to obtain the final score; taking the score as the optimization target, and adopting one or several optimization algorithms to optimize to obtain the position parameters that maximize the score.

[0017] Compared with the prior art, the advantages of the present invention are as follows: 1. The optimization method for the installation angle and position of a multi-channel pyrometer in an aeroengine according to the present invention can pre-obtain the optimal installation angle and position before the equipment is put into use by reasonably abstracting evaluation indexes, which can ensure the reliable and effective operation of the multi-channel pyrometer to the greatest extent. 2. The optimization method for the installation angle and position of a multi-channel pyrometer in an aeroengine according to the present invention has an accurate and efficient analysis process without complex equipment and structures. 3. The optimization method for the installation angle and position of a multi-channel pyrometer in an aeroengine according to the present invention has a clear optimization target, and any intermediate step can provide strong support for the error evaluation and analysis of the subsequent high-temperature radiometer. Description of the Drawings

[0018] Figure 1 is a schematic flow chart of implementing the optimization method for the installation angle and position of a multi-channel pyrometer in an aeroengine according to the present invention. Figure 1 It includes Step 1 of determining the installation position parameters of the n-channel pyrometer, where n is an integer greater than 1; Step 2 of constructing a geometric model of the pyrometer and the measured turbine blade, and performing ray tracing; Step 3 of determining evaluation indexes, and calculating the evaluation indexes by using the ray tracing results; Step 4 of adopting one or several comprehensive evaluation methods for evaluation to obtain the final score; Step 5 of taking the score as the optimization target, and adopting one or several optimization algorithms to optimize to obtain the position parameters that maximize the score. The position parameters include the probe angle, the front-back displacement, the left-right displacement, etc. The evaluation indexes include the angle factor, the overall variance, the working distance, the guide vane distance, the resolution error, etc. The evaluation methods include the analytic hierarchy process, the fuzzy evaluation method, the rank sum ratio method, the comprehensive analysis method, the Topsis method, etc. (Topsis, Technique for Order Preference by Similarity to an Ideal Solution, the method for ranking by approaching the ideal solution). The optimization algorithms include: the Newton method, the gradient descent method, the simulated annealing method, the genetic algorithm, the ant colony algorithm, the particle swimming method, etc. The n-channel pyrometer is the multi-channel pyrometer, for example, n = 5.

[0019] Figure 2 is a schematic diagram of the geometric model of the turbine blade in a reference embodiment of the present invention.

[0020] The descriptions of the reference numerals are as follows: 1 - the measured moving blade; 2 - the guide vane; 3 - the adjacent guide vane; 4 - the pyrometer. Detailed implementation manners

[0021] The present invention will be described below in conjunction with the accompanying drawings ( Figure 1 - Figure 2 ).) and embodiments.

[0022] Figure 1 is a schematic flow chart of an optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine according to the present invention. Figure 2 is a schematic diagram of a geometric model of a turbine blade of a reference embodiment of the present invention. Refer to Figures 1 to 2 As shown, the present invention discloses an optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine. By reasonably abstracting evaluation indexes, the optimal installation angle and position can be obtained in advance before the equipment is put into use, which can ensure the reliable and effective operation of the multi-channel pyrometer to the greatest extent. The method includes the following steps: Step 1, determining the installation position parameters of an n-channel pyrometer, where n is an integer greater than 1, and the position parameters include the probe angle a, the front-back displacement b, and the left-right displacement c; Step 2, constructing a geometric model of the measured turbine blade including the n-channel pyrometer and its installation position parameters, and performing ray tracing; Step 3, determining the evaluation indexes, and calculating the evaluation indexes by using the ray tracing results; Step 4, adopting one or several comprehensive evaluation methods to evaluate and obtain the final score; Step 5, taking the score as the optimization target, and adopting one or several optimization algorithms to optimize and obtain the position parameters that maximize the score.

[0023] The present invention provides an optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine, which is particularly suitable for determining the installation angle and position of the pyrometer in industrial applications to achieve the best use effect.

[0024] An optimization method for the installation angle and position of a multi-channel pyrometer of an aero-engine, the flow chart of which is as Figure 1 shown, includes the following steps:

[0025] Step L1, determining the installation position parameters of an n-channel pyrometer;

[0026] Step L2, constructing a geometric model of the pyrometer and the measured turbine blade, and performing ray tracing;

[0027] Step L3, determining the evaluation indexes, and calculating the evaluation indexes by using the ray tracing results;

[0028] Step L4, adopting one or several comprehensive evaluation methods to evaluate and obtain the final score;

[0029] Step L5, taking the score as the optimization target, and adopting one or several optimization algorithms to optimize and obtain the position parameters that maximize the score.

[0030] Taking a turbine blade including one moving blade under test and two adjacent guide vanes as an example, the geometric model is as shown in Figure 2 shown below.

[0031] In the embodiment of the present invention, the position parameters of the pyrometer 4 in step L1 include but are not limited to: the probe angle a, the front-back displacement b, and the left-right displacement c.

[0032] In the embodiment of the present invention, the geometric model of the turbine blade under test in step L2 includes two guide vanes and one moving blade, and the angle between the guide vane 2 and the adjacent guide vane 3 is The pyrometer 4 has 5 channels and is located between the guide vane 2 and the adjacent guide vane 3; in the ray tracing process, the pyrometer 4 emits rays, the rays are transmitted to the blade and frozen, and the moving blade 1 under test rotates at an interval angle γ = 1° in the circumferential direction of the turbine.

[0033] In the embodiment of the present invention, the evaluation indexes in step L3 include but are not limited to the angle factor A, the overall variance B, the working distance C, the guide vane distance D, and the resolution error E; the single angle factor is defined as where θ is the incident angle of a single ray, then the angle factor where That is, m = 30, the smaller the angle factor A, the higher the evaluation score; the smaller the overall variance B, the higher the evaluation score; the closer the working distance C is to the designed working distance, the higher the evaluation score; the guide vane distance D refers to the distance between the pyrometer and one of the guide vanes, and the closer the pyrometer is to the middle of the two guide vanes, the higher the evaluation score; the resolution error E can be expressed as where S r is the actual resolution area of the temperature measurement target point, S d is the designed resolution area of the temperature measurement target point, and the smaller the resolution error E, the higher the evaluation score.

[0034] The configuration of the geometric optical physical field in step 3 includes but is not limited to: modifying the "maximum number of secondary rays" in the geometric optical setting area to 0; modifying the "vacuum wavelength" in the ray attribute setting area under the geometric optical node to the corresponding wavelength value; adding the "wall" attribute, with the boundary selected as all boundaries and the "wall condition" set to freeze; adding the "ray detector attribute", with the boundary selected as the surface of the blade under test; adding the "release from boundary" attribute, with the boundary selected as the ray emission surface, the initial position selected as "grid-based", and checking "specify tangent and normal vector components", and modifying it to the direction vector of the actual required ray emission direction; adding the "specular reflection" attribute according to the actual situation, with the boundary selected as the reflection surface.

[0035] In the embodiment of the present invention, the evaluation methods in step L4 include, but are not limited to, the analytic hierarchy process, the fuzzy evaluation method, the rank sum ratio method, the comprehensive analysis method, and the Topsis method. As a possible implementation, the Topsis method is used to calculate the score.

[0036] In the embodiment of the present invention, the optimization algorithms in step L5 include, but are not limited to, the Newton method, the gradient descent method, the simulated annealing method, the genetic algorithm, the ant colony algorithm, and the particle swarm optimization method. As a possible implementation, the particle swarm optimization method is used to optimize the position parameters.

[0037] The content not described in detail in the specification of the present invention belongs to the prior art well-known to those skilled in the art. It is hereby pointed out that the above description helps those skilled in the art to understand the present invention, but does not limit the protection scope of the present invention. Any implementation that makes equivalent replacements, modifications, improvements, and / or simplifies the above description without departing from the substantial content of the present invention falls within the protection scope of the present invention.

Claims

1. Optimization method for installation angle and position of multi-channel pyrometers in aeroengines, characterized in that, It includes the following steps: Step 1: Determine the installation position parameters of the n-channel pyrometer, where n is an integer greater than 1, and the position parameters include the probe angle a, the front-back displacement b, and the left-right displacement c; Step 2: Construct a geometric model of the measured turbine blade including the n-channel pyrometer and its installation position parameters, and perform ray tracing; Step 3: Determine the evaluation index, and calculate the evaluation index using the ray tracing results; Step 4: Use one or several comprehensive evaluation methods to evaluate and obtain the final score; Step 5: Take the score as the optimization objective, and use one or several optimization algorithms to optimize and obtain the position parameters that maximize the score; In the said step 2, the geometric model of the turbine blade to be measured includes at least two guide vanes and at least one moving blade, and the angle between two guide vanes is The pyrometer is located between two guide vanes, which are respectively the guide vane and the adjacent guide vane, and the moving blade is the moving blade to be measured; in the ray tracing process, the pyrometer emits rays, the rays are transmitted to the moving blade to be measured and frozen, and the moving blade to be measured rotates at an interval angle γ in the circumferential direction of the turbine; The evaluation indicators in step 3 include the angle factor A, the overall variance B, the working distance C, the guide vane distance D, and the resolution error E; the single angle factor is defined as where θ is the incident angle of a single ray, then the angle factor where m is a positive integer, and the smaller the angle factor A, the higher the evaluation score; the smaller the overall variance B, the higher the evaluation score; the closer the working distance C is to the designed working distance, the higher the evaluation score; the guide vane distance D refers to the distance between the pyrometer and one of the guide vanes, and the closer the pyrometer is to the middle of the two guide vanes, the higher the evaluation score; the resolution error E is expressed as where S r is the actual resolution area of the temperature measurement target point, S d is the designed resolution area of the temperature measurement target point, and the smaller the resolution error E, the higher the evaluation score.

2. The optimization method for the installation angle and position of a multi-channel pyrometer of an aeroengine according to claim 1, characterized in that The following configurations of the geometric optical physical field are included in Step 3: Modify the "maximum number of secondary rays" in the geometric optical settings area to 0; Modify the "vacuum wavelength" in the ray attribute settings area under the geometric optical node to the corresponding wavelength value; Add the "wall" attribute, select all boundaries for the boundary, and set the "wall condition" to frozen; Add the "ray detector attribute", select the surface of the measured blade for the boundary; Add the "release from boundary" attribute, select the ray emission surface for the boundary, select "based on grid" for the initial position, and check "specify the tangent vector and normal vector components", and modify it to the direction vector of the actual required ray emission direction; Add the "specular reflection" attribute according to the actual situation, and select the reflection surface for the boundary.

3. The optimization method for the installation angle and position of the multi-channel pyrometer of an aero-engine according to claim 1, characterized in that In Step 4, the evaluation methods include the analytic hierarchy process, the fuzzy evaluation method, the rank sum ratio method, the comprehensive analysis method, and / or the topsis method.

4. The optimization method for the installation angle and position of the multi-channel pyrometer of an aero-engine according to claim 1, characterized in that, In Step 5, the optimization algorithms include the Newton method, the gradient descent method, the simulated annealing method, the genetic algorithm, the ant colony algorithm, and / or the particle swimming method.

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