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首页> 外文会议>ASME turbo expo: turbine technical conference and exposition >DETERMINATION OF ALLOWABLE FOD DEFECTS SIZES ON THE SURFACE OF GAS-TURBINE ENGINE STATOR PARTS BASED ON STRESS-CONCENTRATION FACTORS
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DETERMINATION OF ALLOWABLE FOD DEFECTS SIZES ON THE SURFACE OF GAS-TURBINE ENGINE STATOR PARTS BASED ON STRESS-CONCENTRATION FACTORS

机译：基于应力集中因素的燃气轮机定子零件表面允许的缺陷尺寸确定

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Requirements for reliability and safety of modern aircraft engines are constantly growing. Among these requirements is periodic inspection of the engine condition and condition of its individual parts during operation, for the purpose of evaluation of the risk to operation. This is to ascertain possible damage to various engine parts in the course of operation and progressive wear. Damage can occur for a variety of reasons: ingestion of foreign matter in the engine gas path, operation in extreme and off-design conditions, wear, etc. To trace the engine parts condition and detect various damage on the engine parts, periodic inspection is provided. In case of any damage or deviations on parts, the question of their performance and possibility to break during operation are addressed. There are two ways of answering this question: 1 - experimental demonstration of the required strength of parts with damage; 2 - computational demonstration of the required strength of parts with damage. The first way requires a good deal of time and money for carrying out the experiments. It is efficient only with enough operational experience in typical parts with various surface damage. While developing a new engine (having no prototypes) it is more reasonable to use computational methods. To determine the allowable damage of gas-turbine engine parts, a special procedure has been developed. Its main principles consist of the following: 1. classification of the typical parts damage by foreign object ingestion; 2. determination of the stress concentration factors (Kt) due to damage for various defect sizes; 3. determination of strength factors of safety and life for various zones of parts without damage; 4. determination of Kt values with which minimum allowable values of strength safety factor and life are attained; 5. determination of allowable sizes of various types of damage for all zones of each part based on previously defined Kt dependencies on typical damage sizes. This methodology is proposed for determination of allowable damage on the surface of gas-turbine engines stator parts caused by foreign object ingestion in order to ensure the required reliability and safety; its experimental verification is foreseen for the future.
机译：对现代飞机发动机的可靠性和安全性的要求正在不断提高。在这些要求中，包括定期检查发动机的运行状况以及运行过程中各个零件的运行状况，以评估运行风险。这是为了确定在运行过程中和逐渐磨损过程中可能损坏各个发动机部件。损坏的发生可能有多种原因，包括：在发动机气体通道中吸入异物，在极端和非设计条件下运行，磨损等。要跟踪发动机部件的状况并检测发动机部件上的各种损坏，请定期进行检查。假如。如果零件有任何损坏或偏差，则应解决其性能以及在操作过程中可能断裂的问题。有两种方法可以回答这个问题：1-实验证明需要的零件有损坏的强度; 2-具有损坏零件所需强度的计算演示。第一种方法需要大量的时间和金钱来进行实验。它只有在具有各种表面损坏的典型零件中具有足够的操作经验时才有效。在开发新引擎（没有原型）时，使用计算方法更为合理。为了确定燃气涡轮发动机零件的允许损坏，已经开发了一种特殊程序。其主要原理包括以下内容：1.对异物吞咽造成的典型零件损坏进行分类; 2.确定由于各种缺陷尺寸的损坏而引起的应力集中系数（Kt）; 3.确定各部分区域的安全性和使用寿命的强度因子，无损坏; 4.确定Kt值，通过该值可达到强度安全系数和寿命的最小允许值; 5.根据先前定义的对典型损伤尺寸的Kt依赖性，确定每个零件所有区域的各种类型的损伤的允许尺寸。为了确保所需的可靠性和安全性，建议使用此方法来确定由于异物吸入而引起的燃气轮机定子零件表面允许的损坏。预计将在未来进行实验验证。

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