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Structural Integrity in Aero Gas Turbine Engines

机译：航空燃气轮机的结构完整性

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In Western Europe, the Joint Aviation Authorities, a consortium of aviation authorities from participating member states, publish requirements covering all aspects of aviation. The part which has specific application to aero engines is JAR-E. The rules given in JAR-E set standards of strength and margins which must be met by all power plant for civil aviation usage. The main concerns for structural integrity in aero gas turbine engines are identified as behaviour as a result of ingested objects, low cyclic fatigue failures, crack growth and coalescence of cracks. A failure modes and effects analysis identifies those components in the engine whose failure may lead directly or indirectly to hazardous effects. It is necessary to demonstrate that the duty of such Critical components and the variation in their strength combine in such a way that failures cannot occur. The approaches used to establish the cyclic capability of such components are described. With other components, notably blades, failure is designed against by providing a containment shell around the rotating stage which will prevent the release of a single blade outside the engine nacelle. As well as this, the engine is tested to demonstrate robustness in operation for the hot sections including combustors and turbine blades. With fan blades, however, which are the first stage and therefore more likely to be subjected to ingested object damage, it is necessary to show that they can sustain impacts by small and medium birds but still retain part or all of their thrust capability. For impact with large birds, however, it is simply enough to show that the engine can be shut down safely. In the event of a fan blade becoming detached, the imbalance causes large structural loads on the engine and engine mounts. A test is generally required in which a blade is released at the most arduous point in the engine operation and both the containment system and the ability to shut the engine down safely is demonstrated. Engine mounts, which connect the engine to the airframe, may be designed with damage tolerance where a crack is assumed in the most highly stressed location and, where applicable, another is assumed in the secondary load path. In such cases the inspection interval is related to the number of flight cycles to burst from the specified crack sizes. Casings and combustors are two examples of thin shells used in gas turbine engines and their structural integrity is also described.
机译：在西欧，联合航空权当局是来自参与会员国的航空权威机构，发布涵盖航空各方面的要求。对Aero发动机具有特定应用的部分是JAR-E。 jar-e设定了强度和边缘标准的规则，必须由所有电厂进行民用航空使用情况。由于摄入物体，低循环疲劳失败，裂纹生长和裂缝聚结的结果，在航空燃气轮机发动机中结构完整性的主要问题被识别为行为，裂缝的低循环疲劳失败，裂纹生长和聚结。失败模式和效果分析识别发动机中的那些组件，其失效可能直接或间接地延伸到危险效果。有必要证明这种关键部件的占空比和其强度的变化以使失败不能发生的方式组合。描述了用于确定这些组分的循环能力的方法。利用其他部件，特别是刀片，通过在旋转级周围提供容纳壳体来设计故障，这将防止在发动机机舱外释放单个刀片。除此之外，测试发动机以展示在包括燃烧器和涡轮机叶片的热部分的操作中的鲁棒性。然而，与风扇叶片，这是第一阶段，因此更有可能受到摄入的物体损坏，有必要表明他们可以通过中小鸟类维持影响，但仍然保持部分或全部推力能力。然而，对于大型鸟类的影响，它简单地表明发动机可以安全地关闭。如果发生扇形叶片的拆卸，则失衡导致发动机和发动机支架上的大结构载荷。通常需要测试，其中刀片在发动机操作中最艰难的点处释放，并且证明了安全系统和安全性地关闭发动机的能力。将发动机连接到机身的发动机支架可以设计有损坏公差，其中在最高压力的位置假设裂缝，并且在适用的情况下，在二次负载路径中假设另一个。在这种情况下，检查间隔与从指定的裂缝尺寸突发的飞行循环的数量有关。壳体和燃烧器是用于燃气涡轮发动机中使用的薄壳的两个例子，并且还描述了它们的结构完整性。

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