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探讨了航空氢发动机中轴承面临的典型问题，重点分析了氢脆、氢致开裂/剥落、氢鼓泡、应力腐蚀等氢损伤行为对轴承性能的影响，以及临氢/涉氢轴承的材料选择、设计参数、润滑方式和工况适应性等技术挑战。 本文作者针对某型涡轴发动机滚子轴承 (以下简称某滚子轴承)的环下润滑结构，通过试验研究了转速、供油压力、喷嘴与锁紧螺母轴向距离等对供油效率的影响，验证其轴向收油以及输油结构的有效性。 针对该问题，结合摩擦生热模型、两相流模型和多重坐标系法建立了航空发动机三点接触球轴承环下润滑流固耦合传热模型，分析了滚动体自转、轴承转速、供油速度和保持架结构参数对轴承热特性的影响. 结果表明：轴承转速较低时，滚动体自转会降低腔内油相体积，而轴承转速较高时则与之相反，且滚动体自转会显著降低其自身温度；随轴承转速的增大，内外圈平均温度显著上升；随供油速度的增大，内外圈平均温度先降低后升高；随保持架宽度的增加，内圈平均温度升高，外圈平均温度略微降低；随保持架兜孔直径的增加，内外圈平均温度略有升高；随保持架厚度的增加，内圈平均温度先降低后显著升高，外圈平均温度变化较小. 研究结果为降低环下润滑高速球轴承的温升提供了依据.
本发明可在高收油效率下实现滑油的定量分配，满足高速滚动轴承的润滑和冷却需求，提高轴承的安全性和可靠性。 1、本发明提供了一种轴向环下润滑结构及具有其的航空发动机，以解决现有润滑方式存在的使发动机滑油系统流路布置更为复杂，且增加了滑油泵的负载和重量的技术问题。 以航空发动机主轴承环下供油润滑系统为研究对象,考虑气液两相对润滑介质流态及润滑性能的影响,基于有限体积法建立了润滑介质在分相流动状态下的计算模型.采用SIMPLEC方法,得出了分相流动情况下两相的分布情况以及含气率,喷嘴喷射流量和系统转速等工况.
本文围绕航空发动机主轴轴承的高效润滑冷却技术,对比了典型润滑方式,系统梳理并总结了环下润滑技术的发展现状,讨论了环下润滑轴承的润滑冷却效果,对航空发动机主轴高速轴承润滑冷却技术的未来发展趋势进行了展望,为航空轴承高效润滑冷却和精细化热管理提供参考。
针对航空发动机主轴轴承内部流场特征不明确的问题开展了研究，构建了主轴轴承在典型单元间隙最小平面域流体动力学模型。 本文为满足航空发动机的发展需求，系统分析了国内外航空轴承技术现状及差距，基于航空发动机未来发展趋势，梳理出需要迫切解决和发展的航空轴承技术方向，希望为航空轴承技术发展提供参考。
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