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首页> 外文会议>Symposium on Methods for the Assessment of Structural Integrity of Components and Structures; 20010425; Cambridge; GB >Structural Integrity in Aero Gas Turbine Engines
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Structural Integrity in Aero Gas Turbine Engines

机译：航空燃气涡轮发动机的结构完整性

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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，来自参与成员国的航空当局组成的联合航空当局联合会发布涵盖航空各个方面的要求。在航空发动机中具有特定应用的部分是JAR-E。 JAR-E中给出的规则设置了强度和余量的标准，所有发电厂必须满足民用航空的要求。航空燃气涡轮发动机中结构完整性的主要问题被认为是由于摄入物体，低周期性疲劳失效，裂纹扩展和裂纹合并而导致的行为。故障模式和影响分析可识别发动机中那些可能直接或间接导致危险影响的组件。有必要证明，此类关键组件的作用及其强度的变化以不会发生故障的方式结合在一起。描述了用于建立此类组件循环能力的方法。对于其他部件，尤其是叶片，可以通过在旋转台周围设置一个密闭壳来防止故障，这将防止单个叶片释放到发动机机舱之外。除此之外，还对发动机进行了测试，以证明其对包括燃烧室和涡轮叶片在内的高温区域的运行具有鲁棒性。然而，对于风扇叶片来说，这是第一阶段，因此更容易受到物体的吸收，因此有必要证明它们可以承受中小型鸟类的撞击，但仍保留其部分或全部推力。但是，对于大型鸟类的撞击，足以证明发动机可以安全关闭。如果风扇叶片脱落，则不平衡会导致发动机和发动机支座上的结构载荷增大。通常需要进行这样的测试：在发动机操作的最艰苦的时刻释放叶片，并展示安全壳系统和安全关闭发动机的能力。将发动机连接至机身的发动机支座可以设计成具有损伤容限，在承受最大应力的位置假定有裂纹，而在次要载荷路径中假定存在裂纹。在这种情况下，检查间隔与要从指定裂纹尺寸破裂的飞行周期数有关。壳体和燃烧室是用于燃气涡轮发动机的薄壳的两个示例，并且还描述了它们的结构完整性。

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