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期刊论文 13

年份

2022 1

2020 1

2019 2

2018 1

2016 1

2007 3

2003 1

2001 1

2000 1

1999 1

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关键词

航空发动机 3

发展和建议 1

可靠性 1

基础研究 1

多学科设计优化 1

寿命 1

总体优化 1

新技术 1

研制发展 1

科学决策 1

管理 1

航空发动机设计 1

航空喷气发动机 1

航空活塞发动机；高空模拟试验台；温度；仿真 1

部件级优化 1

零件级优化 1

预先研究 1

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Two-sided ultrasonic surface rolling process of aeroengine blades based on on-machine noncontact measurement

Shulei YAO, Xian CAO, Shuang LIU, Kaiming ZHANG, Xiancheng ZHANG, Congyang GONG, Chengcheng ZHANG

《机械工程前沿（英文）》 2020年第15卷第2期页码 240-255 doi: 10.1007/s11465-019-0581-7

摘要： As crucial parts of an aeroengine, blades are vulnerable to damage from long-term operation in harsh environments. The ultrasonic surface rolling process (USRP) is a novel surface treatment technique that can highly improve the mechanical behavior of blades. During secondary machining, the nominal blade model cannot be used for secondary machining path generation due to the deviation between the actual and nominal blades. The clamping error of the blade also affects the precision of secondary machining. This study presents a two-sided USRP (TS-USRP) machining for aeroengine blades on the basis of on-machine noncontact measurement. First, a TS-USRP machining system for blade is developed. Second, a 3D scanning system is used to obtain the point cloud of the blade, and a series of point cloud processing steps is performed. A local point cloud automatic extraction algorithm is introduced to extract the point cloud of the strengthened region of the blade. Then, the tool path is designed on the basis of the extracted point cloud. Finally, an experiment is conducted on an actual blade, with results showing that the proposed method is effective and efficient.

关键词： aeroengine blades on-machine noncontact measurement point cloud processing path planning surface strengthening

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Optimization model for rotor blades of horizontal axis wind turbines

LIU Xiong, CHEN Yan, YE Zhiquan

《机械工程前沿（英文）》 2007年第2卷第4期页码 483-488 doi: 10.1007/s11465-007-0084-9

摘要： This paper presents an optimization model for rotor blades of horizontal axis wind turbines. The model refers to the wind speed distribution function on the specific wind site, with an objective to satisfy the maximum annual energy output. To speed up the search process and guarantee a global optimal result, the extended compact genetic algorithm (ECGA) is used to carry out the search process. Compared with the simple genetic algorithm, ECGA runs much faster and can get more accurate results with a much smaller population size and fewer function evaluations. Using the developed optimization program, blades of a 1.3 MW stall-regulated wind turbine are designed. Compared with the existing blades, the designed blades have obviously better aerodynamic performance.

关键词： population extended algorithm developed optimization accurate

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Impact analysis of compressor rotor blades of an aircraft engine

Y B SUDHIR SASTRY, B G KIROS, F HAILU, P R BUDARAPU

《结构与土木工程前沿（英文）》 2019年第13卷第3期页码 505-514 doi: 10.1007/s11709-018-0493-3

摘要： Frequent failures due to foreign particle impacts are observed in compressor blades of the interceptor fighter MIG-23 aircraft engines in the Ethiopian air force, supplied by the Dejen Aviation Industry. In this paper, we made an attempt to identify the causes of failure and hence recommend the suitable materials to withstand the foreign particle impacts. Modal and stress analysis of one of the recently failed MIG-23 gas turbine compressor blades made up of the following Aluminum based alloys: 6061-T6, 7075-T6, and 2024-T4, has been performed, apart from the impact analysis of the rotor blades hit by a granite stone. The numerical results are correlated to the practical observations. Based on the modal, stress and impact analysis and the material properties of the three considered alloys, alloy 7075-T6 has been recommended as the blade material.

关键词： axial flow compressor rotor and stator blades aircraft engine stress and impact analysis aluminum alloys

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An Exploration of Surface Integrity Remanufacturing for Aeroengine Components

Qiao Xiang,Yong He,Ting-hong Hou

《工程管理前沿（英文）》 2016年第3卷第2期页码 107-114 doi: 10.15302/J-FEM-2016025

摘要： Surface integrity is the major factor impacting on the operation quality, service life and reliability of the aeroengine components. The surface integrity of aeroengine component is damaged by the failures such as crack, deformation, oxidation, corrosion, erosion, and microstructural degeneration. It adopts advanced remanufacturing technologies to restore or improve the surface integrity and regenerate these high value parts. This paper firstly puts forward the concept, namely surface integrity remanufacturing for aeroengine components, and its connotation. The key remanufacturing technologies have been developed to repair the components with surface damages. Ultimately, some application examples of surface integrity remanufacturing technologies as well as their effects in aeroengine maintenance are introduced. The discarded components have been reused and their service lives have been extended and their reliability has been increased by implementing surface integrity remanufacturing. It has realized “The Repaired Components Outpacing the New Ones”, material saving, energy saving, and emission reduction.

关键词： aeroengine component surface integrity remanufacturing surface integrity remanufacturing

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Novel casting processes for single-crystal turbine blades of superalloys

Dexin MA

《机械工程前沿（英文）》 2018年第13卷第1期页码 3-16 doi: 10.1007/s11465-018-0475-0

摘要：

This paper presents a brief review of the current casting techniques for single-crystal (SC) blades, as well as an analysis of the solidification process in complex turbine blades. A series of novel casting methods based on the Bridgman process were presented to illustrate the development in the production of SC blades from superalloys. The grain continuator and the heat conductor techniques were developed to remove geometry-related grain defects. In these techniques, the heat barrier that hinders lateral SC growth from the blade airfoil into the extremities of the platform is minimized. The parallel heating and cooling system was developed to achieve symmetric thermal conditions for SC solidification in blade clusters, thus considerably decreasing the negative shadow effect and its related defects in the current Bridgman process. The dipping and heaving technique, in which thin-shell molds are utilized, was developed to enable the establishment of a high temperature gradient for SC growth and the freckle-free solidification of superalloy castings. Moreover, by applying the targeted cooling and heating technique, a novel concept for the three-dimensional and precise control of SC growth, a proper thermal arrangement may be dynamically established for the microscopic control of SC growth in the critical areas of large industrial gas turbine blades.

关键词： superalloy investment casting Bridgman process directional solidification single crystal turbine blade

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航空发动机技术的发展和建议

刘大响

《中国工程科学》 1999年第1卷第2期页码 24-29

摘要：

自40年代初燃气涡轮发动机问世以来，飞机的速度、飞行高度和机动性发生了历史性飞跃，并跨入了超声速飞行的新时代。到21世纪初，战斗机及其发动机大致经历4次更新换代。目前现役主力机种是第三代，发动机的推重比为8一级，还在不断改进改型；第四代推重比10一级发动机已进入首飞，预计2003年前后装备部队；第五代推重比15～20一级发动机，可望在2020年研制成功。世界航空发动机技术呈加速发展态势。面对21世纪和知识经济时代，本文对如何抓住机遇、加快发展，提出了几点看法和建议。

关键词：航空发动机新技术发展和建议

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Timing decision-making method of engine blades for predecisional remanufacturing based on reliability

Le CHEN, Xianlin WANG, Hua ZHANG, Xugang ZHANG, Binbin DAN

《机械工程前沿（英文）》 2019年第14卷第4期页码 412-421 doi: 10.1007/s11465-019-0551-0

摘要： A timing decision-making method for predecisional remanufacturing is presented. The method can effectively solve the uncertainty problem of remanufacturing blanks. From the perspective of reliability, this study analyzes the timing decision-making interval for predecisional remanufacturing of mechanical products during the service period and constructs an optimal timing model based on energy consumption and cost. The mapping relationships between time and energy consumption are predicted by using the characteristic values of performance degradation of products combined with the least squares support vector regression algorithm. Application of game theory reveals that when the energy consumption and cost are comprehensively optimal, this moment is the best time for predecisional remanufacturing. Used engine blades are utilized as an example to demonstrate the validity and effectiveness of the proposed method.

关键词： predecisional remanufacturing reliability least squares support vector regression (LS-SVR) game theory

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发人深省的航空喷气发动机发祥史——兼谈预先研究的基础作用

吴大观

《中国工程科学》 2000年第2卷第1期页码 77-80

摘要：

文章对鲜为后人详知的航空喷气发动机在世界上发祥的历史，作了简要介绍。美国、前苏联和旧中国，在40年代都买得英国喷气发动机的专利，50多年以后的今天，前两国在世界上形成两个航空大国，而我国却远不能与其相比拟。经过对比分析，事实证明狠抓发动机预先研究，是发展发动机行业的关键条件之一。文章还为我国今后如何重视预先研究提出了改进的有效措施和意见。

关键词：航空喷气发动机基础研究预先研究

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航空活塞发动机高空模拟试验台温度系统研究

袁领双,刘猛,王浚

《中国工程科学》 2007年第9卷第12期页码 53-56

摘要：在航空活塞发动机高空模拟试验中，模拟温度低、温度范围跨度大，高空模拟试验台（简称高空台）上应用了空气制冷和电加热两种调温措施，控制难度较大。将模拟温度划分为高温、常温、低温三个温度段，分别应用三种不同的调节方式进行温度控制；在系统数学建模和温度变化动态特性分析基础上，对高空台温度系统的调节过程进行了仿真研究，结果表明该方法能够满足温度的调节速度和控制精度要求。为了满足带涡轮增压器的航空活塞发动机对进气温度的要求，建立了涡轮增压器与中冷器之间的数学换热关系，以稳态时的发动机进气温度为例进行了仿真计算，结果与

关键词：航空活塞发动机；高空模拟试验台；温度；仿真

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军用航空发动机可靠性和寿命管理

徐可君,江龙平

《中国工程科学》 2003年第5卷第1期页码 82-88

摘要：

以西方军用航空发动机可靠性和寿命管理为蓝本，阐述了可靠性和寿命管理的基本要素，并结合我国航空发动机可靠性和寿命管理的现状，讨论了我国航空发动机可靠性和寿命管理工作存在的差距和误区，指出了我国航空发动机可靠性寿命管理工作落后的根源在于管理观念落后、管理体制不健全、基础工作薄弱、标准不完善。参照西方国家的管理理念，构建和完善我国航空发动机可靠性和寿命管理是必要的，但完全照搬西方标准并不可取。正确做法是结合我国的现状，走出一条合乎国情的道路。

关键词：航空发动机可靠性寿命管理

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科学决策是航空发动机研制成功的关键

温俊峰

《中国工程科学》 2001年第3卷第1期页码 31-35

摘要：

首先论述了现代管理决策理论对我国航空发动机研制发展的重要意义和科学决策的关键作用。通过国内外航空新机研制发展的成败实例，分析总结在决策与管理上的经验与教训，并进一步阐述了在决策航空发动机的研制发展时，必须从我国实际出发正确处理好几个关系。为了我国航空发动机更好、更快地发展，当务之急是实施决策科学化和民主化。最后对我国新机研制发展科学决策提出了几点建议。

关键词：航空发动机研制发展科学决策

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Creep life assessment of aero-engine recuperator based on continuum damage mechanics approach

《机械工程前沿（英文）》 2022年第17卷第4期 doi: 10.1007/s11465-022-0702-6

摘要： The creep life of an aeroengine recuperator is investigated in terms of continuum damage mechanics by using finite element simulations. The effects of the manifold wall thickness and creep properties of brazing filler metal on the operating life of the recuperator are analyzed. Results show that the crack initiates from the brazing filler metal located on the outer surface of the manifold with the wall thickness of 2 mm and propagates throughout the whole region of the brazing filler metal when the creep time reaches 34900 h. The creep life of the recuperator meets the requirement of 40000 h continuous operation when the wall thickness increases to 3.5 mm, but its total weight increases by 15%. Decreasing the minimum creep strain rate with the enhancement of the creep strength of the brazing filler metal presents an obvious effect on the creep life of the recuperator. At the same stress level, the creep rupture time of the recuperator is enhanced by 13 times if the mismatch between the minimum creep rate of the filler and base metal is reduced by 20%.

关键词： creep life assessment brazed joint continuum damage mechanics aeroengine recuperator

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航空发动机多学科设计优化技术研究

尹泽勇,米栋,吴立强,肖根升,刘飞春,李立君

《中国工程科学》 2007年第9卷第6期页码 1-10

摘要：

多学科设计优化（MDO）是为实现复杂产品设计方法升级换代的最佳技术途径。针对先进航空发动机设计面临的各学科间耦合关系复杂、指标冲突严重等困难，按零件、部件和总体方案设计３个阶段对MDO的各项关键技术开展了研究、开发及应用工作，提出了基于MDO技术的航空发动机一体化设计方法。给出的５个工程应用实例表明，该方法与传统设计方法相比，能大幅提高航空发动机设计水平，具有广泛的工程应用前景。

关键词：航空发动机设计多学科设计优化零件级优化部件级优化总体优化