共查询到20条相似文献,搜索用时 78 毫秒
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中铁十九局乌努格吐山铜钼矿项目部拥有大型进口矿用设备36台套,其发动机的型号和数量为:cumminsk38-1050c25台、VOLVOD12D5台、VOLVOD16E5台、五十铃AH-6WGlXYSA-31台。发动机的维修和大修全部是自己完成,首次大修已经完成,维修效果良好,未出现因大修发动机而引起的机械故障。在完成这些进口发动机的大修后总结出来一些经验,现浅谈一下,愿与技术人员探讨。 相似文献
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通过对火箭发动机试车台工作原理及性能的研究,对试车台轴向推力、推力偏心、发动机外壁壁温等参数模块化校准。本文主要介绍轴向推力校准模块、推力偏心校准模块、发动机外壁壁温校准模块,实现试车台多参数的原位校准。 相似文献
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航天飞机尾部有三台以液氢液氧为推进剂的液体火箭发动机,称之为主发动机。三台主发动机的结构是完全一样的。发动机具有两个预燃室,涡轮泵输出的大部分燃料和小部分氧化剂在预燃室内进行富燃料燃烧(氧:氢约为0.8),燃气温度在600~700℃左右,用来驱动涡轮,然后排入主燃烧室与其余的氧化剂进行补充燃烧,形成高温高压燃气从燃烧室喷口排出。三台主发动机合起来可以提供600多吨的推力。发动机中氢系统和氧系统的工作环境是极其恶劣的,这就对其材料提出了特殊而苛刻的 相似文献
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大型多功能热声发动机的研制及初步实验 第二部分:热声发动机的初步实验 总被引:13,自引:5,他引:13
行波热声发动机在回热器中进行的是可逆热声转换过程,理论上可以更高效地产生和传输声功,因而具有广阔的研究应用前景.对自行研制的大型多功能热声发动机进行了初步实验,着重研究了系统的起振、消振过程及压力波动情况.实验结果表明,该热声发动机比纯驻波型热声发动机具有更低的起振温度、更大的压比及更高的热声转换效率.以氮气为工质,在充气压力为9×105 Pa的条件下,该热声发动机最大压比达1.21,工作频率为25 Hz,这是当前国际上处于前列的实验结果. 相似文献
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首先对燃料电池发动机反应堆进行初步设计,然后建立燃料电池发动机反应堆悬置系统振动力学模型,同时对反应堆悬置系统进行振动特性分析,最后采用移频减振原理对燃料电池发动机反应堆悬置刚度和阻尼进行优化设计;设计方法可以达到对燃料电池发动机反应堆进行隔振的设计要求。 相似文献
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国内的低速柴油机制造厂 ,船舶设计部门、造船厂和船东好象已经有一种共识 :艉机舱推进轴系使用低速五缸柴油机作主机时 ,都要用扭振减振器。但是 ,只要在设计时合理选用柴油机转速 ,并采用高强度低合金钢来制造中间轴 ,这类轴系大部分是不需要扭振减振器的。 相似文献
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随着飞机适航审定关于噪声要求的逐年提高,预测部件飞行噪声声压级可以为飞机的适航审定工作提供依据,也可以为发动机的减噪设计提供参考。通过对发动机部件噪声进行预测,可以有效确定发动机的部件特性。以核心机噪声为突破口,通过对发动机核心机的静态噪声进行预测,然后经过从静态到飞行状态相关映射因素声源移动效应、声衰减等的修正,最后得到飞机在边线时的噪声值。同时可以用文中的方法预测其他部件的噪声值,整合预测出整机的噪声,可作为适航审定的依据,从而大量减少适航审定过程的投入成本。 相似文献
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内燃机表面辐射噪声源识别技术初探 总被引:1,自引:0,他引:1
通过测量某内燃机表面振动速度的方法对其进行表面辐射噪声源的识别研究。首先,确定出该内燃机各主要噪声辐射部件,并分别测量其表面振动速度,分析各部件的振动特性,通过表面振动速度计算出各部件辐射的声功率和它们对总噪声的贡献量比值,从而识别出该内燃机的主要表面噪声源。最后提出为改善内燃机整体噪声辐射水平应采取的降噪措施。 相似文献
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Feng Xue Piero Bonissone Anil Varma Weizhong Yan Neil Eklund Kai Goebel 《Journal of Failure Analysis and Prevention》2008,8(2):199-206
Under customer service agreements (CSA), engine operational data are collected and stored for monitoring and analysis. Other
data sources provide damage assessments that are either provided post-maintenance or analytically assessed. This paper takes
advantage of these data and investigates local fuzzy models to determine the remaining useful life (RUL) of an engine or engine
component. Local fuzzy models are related to both kernel regressions and locally weighted learning. The particular local models
described in this paper are not based on individual models that consider the track history of a specific engine nor are they
based on a global average model that would consider the collective track history of all the engines. Instead, for a given
engine or component, this local fuzzy model defines a cluster of peers in which each of these peers is a similar instance
to this given engine with comparable operational characteristics; the RUL prediction for this given engine is obtained by
a fuzzy aggregation of its peers’ RUL. We combine the fuzzy instance-based approach with an evolutionary framework for model
tuning and maintenance. This evolutionary tuning process is repeated periodically to automatically update and improve the
fuzzy models such that they can be updated to date with the latest collection of data. This fuzzy instance-based approach
is applied to predicting the RUL of a commercial engine validated with post-maintenance assessment.
Reprinted with permission from Integration of Machinery Failure Prevention Technologies into Systems Health Management, Proceedings of the 61st Meeting of
the Society for Machinery Failure Prevention Technology, Society for Machinery Failure Prevention Technology, 2007, on CD-ROM.
This work was done while the author was with GE Global Research. 相似文献
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Yixuan Ye Yu Zhang Tao Huang Shikun Zou Yalin Dong Han Ding Vijay K. Vasudevan Chang Ye 《Advanced Engineering Materials》2023,25(16):2201451
Many aviation accidents are caused by the failure of aircraft engine components, and engine blades are especially vulnerable to high-cycle fatigue fracture in severe working environments as well as to impact damage caused by foreign objects. To address this problem, the United States took the lead and has been successful in implementing laser shock peening (LSP) as a surface treatment for aircraft engine components to enhance their fatigue performance. This review provides an overview of the development of LSP for use in treating aircraft engine components over the past three decades, with a brief introduction to the development of high-energy pulsed lasers for LSP. A particular focus of this review is on the limitations and challenges associated with the application of LSP for treating critical aircraft engine components. It is hoped that this review serves as a reference for future research and development that can lead to better performance of these components. 相似文献