WO2024045440A1 - 一种燃机叶片烧蚀程度确定方法 - Google Patents

一种燃机叶片烧蚀程度确定方法 Download PDF

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WO2024045440A1
WO2024045440A1 PCT/CN2022/141860 CN2022141860W WO2024045440A1 WO 2024045440 A1 WO2024045440 A1 WO 2024045440A1 CN 2022141860 W CN2022141860 W CN 2022141860W WO 2024045440 A1 WO2024045440 A1 WO 2024045440A1
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blade
ablated
model
ablation
complete
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French (fr)
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马伟
肖俊峰
高斯峰
刘全明
唐文书
高松
李永君
张炯
南晴
徐小卜
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Xian Thermal Power Research Institute Co Ltd
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Xian Thermal Power Research Institute Co Ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
    • G01B11/06—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/28—Measuring arrangements characterised by the use of optical techniques for measuring areas
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Definitions

  • the present application relates to the technical field of gas turbine generator sets, and in particular to a method for determining the degree of ablation of gas turbine blades.
  • the gas turbine combined cycle generator set is a circulation system composed of a gas turbine, a generator, a waste heat boiler, a steam turbine (condensing type) or a heating steam turbine (extraction type or back pressure type). It discharges the gas turbine after the work is done The high-temperature flue gas is converted into steam through the waste heat boiler and sent to the steam turbine to generate electricity, or part of the steam after power generation is used for heating.
  • Common forms include a single-shaft combined cycle in which a gas turbine and a steam turbine coaxially drive a generator, and a multi-shaft combined cycle in which a gas turbine and a steam turbine are combined with a generator respectively.
  • Gas turbine blades are an important component of a gas turbine; an internal combustion engine burning diesel or natural gas uses the gas produced after the fuel and air are mixed and burned to push the blades to do work.
  • gas turbine blades work under harsh conditions of high temperature and high pressure for a long time, so their service life will affect the service life of the gas turbine.
  • Temperature is important information when the blade is working. Once the coating on the blade falls off or is ablated and the local temperature of the blade increases, the strength of the blade will decrease and the probability of breakage will increase. Therefore, in order to better design, manufacture and manage service and life of gas turbine blades, it is necessary to evaluate the degree of ablation of gas turbine blades.
  • the thickness and volume of the blade ablation area are generally measured by visual inspection or using measuring tools.
  • some areas cannot be measured using measuring tools or visual inspection. Therefore, this method not only The measurement efficiency is low, and the measurement error value is large.
  • the purpose of this application is to provide a method for determining the degree of ablation of gas turbine blades; the method of this application can accurately obtain the thickness, length and missing area of the ablation area of gas turbine blades, etc., with high accuracy.
  • the error is small, and it is convenient and fast, which can provide a powerful reference for the research and development, design, manufacturing and service and life management of blades.
  • the method for determining the degree of ablation of gas turbine blades includes the following steps:
  • the scanning tool can scan out different graphic formats, such as stl, wrp and other formats.
  • the scanned files can be imported into the software to generate point cloud images.
  • the scanning tool used in this application is a flexible, simple and efficient scanning tool. It is oriented to engineering applications and is suitable for scanning large, complex and multi-curved objects. It can easily scan bright and black objects and is not affected by ambient light.
  • step 1) in order to avoid software lag caused by the large memory of the scanned point cloud image, the ablated blades need to be processed.
  • the specific processing process includes: cutting the ablated blades using tools in the software. Sections of the blade were cut with ablated areas; additionally, the process included operations such as deletion of extracorporeal points and noise reduction.
  • step 2) similarly, in order to avoid the software lag caused by the large memory of the scanned point cloud image, the complete blade needs to be processed.
  • the specific processing process includes: using the tools in the software to convert the complete blade.
  • the blade is sheared into a partial blade, which contains the blade part corresponding to the ablation area; in addition, the process also includes operations such as deleting extracorporeal points and reducing noise.
  • the shear edge of the ablated blade model is used as the benchmark to facilitate the fitting of the ablated blade model and the complete blade model.
  • step 3 use the alignment tool in the software to fit the ablated blade model and the complete blade model, or fix one of the models and move the three-dimensional coordinates of the other model to align the ablated blade model with the complete blade model.
  • Blade model fitting More specifically, during fitting, in order to increase the accuracy of fitting, you can choose N-point alignment or best-fit alignment, by selecting N points at the same position on the two blade models for alignment, and select The more points there are, the higher the accuracy of the fitting.
  • the ablated blade model and the complete blade model are represented by different colors.
  • ablation degree parameters include thickness, length, width and area.
  • the software is geomagic software.
  • This application can obtain the overall morphology of the blade by scanning the blade with a scanning tool, and then obtain the ablated blade model and the complete blade model through reverse modeling. Then, the ablated blade model and the complete blade model are fitted, and through the complete blade model, the ablated blade model and the complete blade model are fitted. By comparing the blade model, the ablation degree parameters of any ablated part can be obtained.
  • the method of this application has high measurement accuracy, small errors, is convenient and fast, and can not only accurately fit the two blade models during measurement, but also allows the two blade models to show different colors, allowing the blade ablation to be intuitively seen.
  • Changes in area and thickness, and in the established model, each point has a three-dimensional coordinate system, so that any thickness, length, width and missing area of the ablated part can be measured through the measurement of three-dimensional coordinates.
  • Figure 1 is a schematic flow chart of the method for determining the degree of ablation of gas turbine blades in this application.
  • Figure 2 is a model diagram of an ablation blade according to an embodiment of the present application.
  • Figure 3 is a complete blade model diagram of the embodiment of the present application.
  • Figure 4 is a fitting diagram of the ablation blade model and the complete blade model according to the embodiment of the present application.
  • the method for determining the degree of ablation of gas turbine blades in this embodiment includes the following steps:
  • the specific processing process is: use the tools in the software to cut the complete blade into partial blades, delete the in vitro points, and reduce the noise; the partial blade contains the corresponding The blade part of the ablation area; then package the processed point cloud image into a sheet to obtain a complete blade model, as shown in Figure 3; the complete blade model can completely cover the ablated blade model; and, in order to facilitate the ablation The ablated blade model and the complete blade model are fitted. When shearing the complete blade, the shear edge of the ablated blade model is used as the benchmark.
  • the measurement tool in the software uses the measurement tool in the software to measure the fitted model to obtain the ablation degree parameters of the ablation area of the ablated blade, including thickness, length, width, and missing area.
  • the overall width of the ablation area of the gas turbine blade is 116.22mm
  • the ablation height of the ablation area on the left includes 10.97mm and 10.48mm
  • the ablation height of the middle ablation area is 9.06mm.
  • the ablation height of the ablation area on the right is 39.18mm
  • the ablation width includes 38.92mm and 30.8mm from top to bottom.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

一种燃机叶片烧蚀程度确定方法，包括如下步骤：通过扫描工具对烧蚀的叶片进行扫描，获得烧蚀叶片的点云图；将烧蚀叶片的点云图导入软件中进行处理，并将处理后的点云图封装成片状，得到烧蚀叶片模型；通过扫描工具对完整的叶片进行扫描，获得完整叶片的点云图；将完整叶片的点云图导入软件中进行处理，并将处理后的点云图封装成片状，得到完整叶片模型；将烧蚀叶片模型和完整叶片模型同时导入软件中，对两个模型进行拟合，通过测量工具对拟合后的模型进行测量，得到烧蚀叶片的烧蚀区的烧蚀程度参数。该方法可以准确获得燃机叶片烧蚀区域的烧蚀程度参数，测量精度较高，误差较小，且方便快捷。

Description

一种燃机叶片烧蚀程度确定方法
相关申请的交叉引用
本申请要求在2022年8月31日提交中国国家知识产权局、申请号为202211057398.3、发明名称为“一种燃机叶片烧蚀程度确定方法”的中国专利申请的优先权，其全部内容通过引用的方式并入本文中。
技术领域
本申请涉及燃机发电机组技术领域，特别涉及一种燃机叶片烧蚀程度确定方法。
背景技术
燃气轮机联合循环发电机组是燃气轮机、发电机与余热锅炉、蒸汽轮机(凝汽式)或供热式蒸汽轮机(抽汽式或背压式)共同组成的循环系统，它是将燃气轮机作功后排出的高温烟气通过余热锅炉回收转换为蒸汽，送入蒸汽轮机发电，或者将部分发电作功后的蒸汽用于供热。常见形式有燃气轮机、蒸汽轮机同轴推动一台发电机的单轴联合循环，也有燃气轮机、蒸汽轮机各分别与发电机组合的多轴联合循环。
燃气轮机叶片是燃气轮机的重要部件；燃烧柴油或天然气的内燃机利用燃料与空气混合燃烧后产生的气体推动叶片做功。燃机叶片作为燃气轮机的重要组成部分，由于长时间在高温高压的恶劣的情况下工作，因此其寿命将会影响燃气轮机的使用时间。温度是叶片工作时的重要信息，一旦叶片上的涂层脱落或者烧蚀、叶片局部温度升高，会导致叶片强度下降、增加断裂几率。因此，为了更好的进行燃机叶片的设计、制造以及服役、寿命等的管理，需要对燃机叶片的烧蚀程度进行评估。
现有技术中，一般通过目测的方式或利用测量工具对叶片烧蚀区域的厚度、体积进行测量，但是由于叶片结构较为复杂，有些区域无法用测量工具或目测的方式进行测量，因此该方法不仅测量效率较低，而且测量的误差值 较大。
发明内容
为解决上述技术问题，本申请的目的在于提供一种燃机叶片烧蚀程度确定方法；本申请的方法可以准确获得燃机叶片烧蚀区域的厚度、长度以及缺失的面积等，精度较高，误差较小，且方便快捷，能够为叶片的研发、设计、制造以及服役、寿命的管理提供有力参考。
为实现上述技术目的，达到上述技术效果，本申请通过以下技术方案实现：
燃机叶片烧蚀程度确定方法，包括如下步骤：
1)通过扫描工具对烧蚀的叶片进行扫描，扫描文件经软件生成从而获得烧蚀叶片的点云图；将烧蚀叶片的点云图导入软件中进行处理，并将处理后的点云图封装成片状，得到烧蚀叶片模型；
2)通过扫描工具对完整的叶片进行扫描，扫描文件经软件生成从而获得完整叶片的点云图；将完整叶片的点云图导入软件中进行处理，并将处理后的点云图封装成片状，得到完整叶片模型；该完整叶片模型能够完全覆盖所述烧蚀叶片模型；
3)将烧蚀叶片模型和完整叶片模型同时导入软件中，对两个模型进行拟合；
4)通过软件中的测量工具对拟合后的模型进行测量，得到烧蚀叶片的烧蚀区的烧蚀程度参数。
步骤(1)和步骤(2)中，扫描工具可以扫描出不同的图形格式，例如stl、wrp等格式，扫描文件导入到软件中可生成点云图。本申请所使用的扫描工具为灵活简便高效的扫描工具，面向于工程应用，适合扫描大型、结构复杂的多曲面物体，可轻松扫描物体的亮色和黑色，且不受环境光的影响。
进一步的，步骤1)中，为避免扫描得到的点云图内存较大所导致的软件卡顿现象，需要对烧蚀叶片进行处理，具体的处理过程包括：通过软件中的工具将烧蚀叶片剪切成具有烧蚀区域的部分叶片；此外，该处理过程还包括删除体外点以及减少噪音等操作。
进一步的，步骤2)中，同样的，为避免扫描得到的点云图内存较大所导 致的软件卡顿现象，需要对完整叶片进行处理，具体的处理过程包括：通过软件中的工具将该完整叶片剪切成部分叶片，该部分叶片包含对应烧蚀区域的叶片部分；此外，该处理过程还包括删除体外点以及减少噪音等操作。
更进一步的，在对完整叶片进行剪切时，以烧蚀叶片模型的剪切边缘为基准，以便于进行烧蚀叶片模型和完整叶片模型的拟合。
进一步的，步骤3)中，通过软件中的对齐工具将烧蚀叶片模型和完整叶片模型进行拟合，或者将其中一个模型固定，通过移动另一模型的三维坐标，使烧蚀叶片模型和完整叶片模型拟合。更具体的，在拟合时，为增加拟合的精确性，可以选用N点对齐方式或最佳拟合对齐方式，通过在两个叶片模型上的同一位置选取N个点进行对齐，且选取的点越多，拟合的精确性越高。
进一步的，烧蚀叶片模型和完整叶片模型采用不同颜色表示。
进一步的，所述烧蚀程度参数包括厚度、长度、宽度以及面积。
进一步的，所述软件为geomagic软件。
本申请的有益效果：
本申请通过扫描工具扫描叶片可得到叶片的全体形貌，再通过逆向建模可以获得烧蚀叶片模型和完整叶片模型，再通过对烧蚀叶片模型和完整叶片模型进行拟合，并通过与完整叶片模型进行比对，可以获得任意烧蚀部分的烧蚀程度参数。
本申请方法测量精度较高，误差较小，方便快捷，在测量时不仅能使两个叶片模型进行准确拟合，且由于两个叶片模型呈现出不同颜色，能直观的看出叶片烧蚀的区域以及厚度的变化，并且在所建立的模型中，每一个点均有一个三维坐标系，即可通过三维坐标的测量就可测出烧蚀部分的任意厚度、长度、宽度以及缺失的面积。
附图说明
图1为本申请的燃机叶片烧蚀程度确定方法的流程示意图。
图2为本申请实施例的烧蚀叶片模型图。
图3为本申请实施例的完整叶片模型图。
图4为本申请实施例的烧蚀叶片模型与完整叶片模型的拟合图。
具体实施方式
下面结合附图对本申请的较佳实施例进行详细阐述，以使本申请的优点和特征能更易于被本领域技术人员理解，从而对本申请的保护范围做出更为清楚明确的界定。
实施例
如图1所示，该实施例的燃机叶片烧蚀程度确定方法，包括如下步骤：
1)通过扫描工具对某燃机烧蚀的叶片进行扫描，扫描文件导入软件生成点云图，从而获得烧蚀叶片的点云图；将烧蚀叶片的点云图导入geomagic软件中，为避免扫描得到的点云图内存较大所导致的软件卡顿现象，需要对烧蚀叶片进行处理，具体的处理过程为：通过软件中的工具将烧蚀叶片剪切成具有烧蚀区域的部分叶片，并删除其中的体外点，以及降低噪音；再将处理后的点云图封装成片状，得到烧蚀叶片模型，如图2所示。
2)通过扫描工具对完整的叶片进行扫描，扫描文件导入软件生成点云图，从而获得完整叶片的点云图；将完整叶片的点云图导入geomagic软件，为避免扫描得到的点云图内存较大所导致的软件卡顿现象，需要对完整叶片进行处理，具体的处理过程为：通过软件中的工具将该完整叶片剪切成部分叶片，并删除其中的体外点，以及降低噪音；该部分叶片包含对应烧蚀区域的叶片部分；再将处理后的点云图封装成片状，得到完整叶片模型，如图3所示；该完整叶片模型能够完全覆盖所述烧蚀叶片模型；并且，为了便于对烧蚀叶片模型和完整叶片模型进行拟合，在对完整叶片进行剪切时，以烧蚀叶片模型的剪切边缘为基准。
3)将烧蚀叶片模型和完整叶片模型同时导入软件中，通过软件中的对齐工具将烧蚀叶片模型和完整叶片模型进行拟合，或者将其中一个模型固定，通过移动另一模型的三维坐标，使烧蚀叶片模型和完整叶片模型拟合；在拟合时，为增加拟合的精确性，可以选用N点对齐方式或最佳拟合对齐方式，通过在两个叶片模型上的同一位置选取N个点进行对齐。如图4所示，拟合后，烧蚀叶片模型的剪切边与完整叶片模型的剪切边重合；拟合时，烧蚀叶片模型和完整叶片模型采用不同颜色表示。
4)通过软件中的测量工具对拟合后的模型进行测量，得到烧蚀叶片的烧蚀区的烧蚀程度参数，包括厚度、长度、宽度以及缺少面积等。如图4所示， 该燃机叶片的烧蚀区域的总体宽度为116.22mm，左边的烧蚀区域的烧蚀高度包括10.97mm和10.48mm，中间的烧蚀区域的烧蚀高度为9.06mm，右边的烧蚀区域的烧蚀高度为39.18mm，烧蚀宽度从上至下包括38.92mm和30.8mm。
以上所述仅为本申请的实施例，并非因此限制本申请的专利范围，凡是利用本申请说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本申请的专利保护范围内。

Claims (8)

  1. 燃机叶片烧蚀程度确定方法，其特征在于，包括如下步骤：
    1)通过扫描工具对烧蚀的叶片进行扫描，获得烧蚀叶片的点云图；将烧蚀叶片的点云图导入软件中进行处理，并将处理后的点云图封装成片状，得到烧蚀叶片模型；
    2)通过扫描工具对完整的叶片进行扫描，获得完整叶片的点云图；将完整叶片的点云图导入软件中进行处理，并将处理后的点云图封装成片状，得到完整叶片模型；该完整叶片模型能够完全覆盖所述烧蚀叶片模型；
    3)将烧蚀叶片模型和完整叶片模型同时导入软件中，对两个模型进行拟合；
    4)通过软件中的测量工具对拟合后的模型进行测量，得到烧蚀叶片的烧蚀区的烧蚀程度参数。
  2. 根据权利要求1所述的燃机叶片烧蚀程度确定方法，其特征在于，步骤1)中，对烧蚀叶片的处理过程包括：通过软件中的工具将烧蚀叶片剪切成具有烧蚀区域的部分叶片。
  3. 根据权利要求2所述的燃机叶片烧蚀程度确定方法，其特征在于，步骤2)中，对完整叶片的处理过程包括：通过软件中的工具将该完整叶片剪切成部分叶片，该部分叶片包含对应烧蚀区域的叶片部分。
  4. 根据权利要求3所述的燃机叶片烧蚀程度确定方法，其特征在于，在对完整叶片进行剪切时，以烧蚀叶片模型的剪切边缘为基准。
  5. 根据权利要求1所述的燃机叶片烧蚀程度确定方法，其特征在于，步骤3)中，通过软件中的对齐工具将烧蚀叶片模型和完整叶片模型进行拟合，或者将其中一个模型固定，通过移动另一模型的三维坐标，使烧蚀叶片模型和完整叶片模型拟合。
  6. 根据权利要求1所述的燃机叶片烧蚀程度确定方法，其特征在于，烧蚀叶片模型和完整叶片模型采用不同颜色表示。
  7. 根据权利要求1所述的燃机叶片烧蚀程度确定方法，其特征在于，所述烧蚀程度参数包括厚度、长度、宽度以及面积。
  8. 根据权利要求1所述的燃机叶片烧蚀程度确定方法，其特征在于，所述软件为geomagic软件。
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