Papers by Keyword: Aero-Engine

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Authors: Liang He, Wan Lin Guo
Abstract: A kind of processing strategy of total life cycle of mechanical products was designed. A logistics model of total life cycle of mechanical products was established based on eight typical states of life cycle of mechanical products. The logistics analysis of total life cycle of a sort of aero-engine was carried out by using the model. The dynamic equivalent quantity of the aero-engines in different states of life cycle was obtained when times changed from the products were first put into production to the time when stable production capacity was reached. The model can also be used to predict logistics of other products rapidly. The results give references for production departments or enterprises which use life cycle methods to configure their production resources effectively and optimize production processes, and also provide a basis for further analysis of total life cycle analysis such as economic and environmental assessment.
402
Authors: Wen Zhu Sun, Jian Ling Qu, Yu Ping Zhou, Mei Jie Liu, Feng Gao
Abstract: A novel estimation method on Delta Engine Gas Temperature (DEGT) applicable for condition based maintenance of a certain military aero-engine was proposed in this paper to solve the problem that maintenance technique for national military aero-engine relatively fell behind. The application perspective of this proposed method in the condition monitor of military aero-engine was also discussed. The experiment analysis on a group of actual flight data indicated that the DEGT obtained via the proposed method was matched to the actual degeneration performance of the aero-engine, which could well reflect the condition of the aero-engine.
375
Authors: Yi Gang Sun, Lei Wang, Wei Xing Chen
Abstract: A system is designed to monitor fault of sensors for aircraft engine real-time. SCM C8051F120 is used to control sensor signal acquisition process, and after processing and storage, the data will be transferred to the data processing unit via Ethernet for analysis and detection. ARM9 embedded computer based on WinCE is used as a data processing core for the data processing unit, three layers BP neural network is used as a sensor fault detection algorithm and troubleshooting software with C++ is developed. It can handle large amounts of data and improve processing efficiency. It has a good interface as well. Compared with current systems, it has been greatly improved in real-time and accuracy. After verification, the system is accurate and strong real-time, and can monitor aircraft engine sensor faults correctly.
1470
Authors: Hai Bo Zhang, Ri Xian Wang, Yi Hui Lin, Yong Jin Li
Abstract: A class of multi-variable decoupling control algorithm for aero-engines is mainly studied In this paper. Firstly, the mechanism of ADRC decoupling control algorithm is elaborated and discussed in detail. Secondly, an ADRC controller for some turbofan engine's nonlinear component-level model is designed to solve two-loop control problem according to the basic principle of ADRC. Compared with ALQR (Augmented Linear Quadratic Regulator) controller in full flight envelope, enough numerical verification tests about ADRC controller have carried out. Finally, simulation results show that the closed-loop system based on the ADRC decoupling controller has better disturbance rejection capability than the ones based on ALQR controller.
7702
Authors: Kai Peng, Ding Fan, Ran Ran Wu, Yu Qiang Teng
Abstract: Active control of turbine blade tip clearance continues to be a concern in design and control of gas turbines. Ever increasing demands for improved efficiency and higher operating temperatures require more stringent tolerances on turbine tip clearance. In this paper, a turbine tip clearance control apparatus and a model of turbine tip clearance are proposed. The active clearance control (ACC) of aero-engine turbine tip clearance is evaluated in a lapse-rate take-off transient, along with the comparative and quantitative analysis. The results show that the resultant active tip clearance control system has favorable steady-state and dynamic performance and benefits of increased efficiency, reduced specific fuel consumption, and additional service life.
1531
Authors: Ling Ping Jiang
Abstract: In consideration of the problem in traditional aero-engine adaptive model, a new algorithm was proposed based on Recursive Reduced Least Squares Support Vector Regression (RRLSSVR). Feature Selection of model input and flight envelope divided was needed before the model established, then adaptive model was developed in every small envelope. Finally, an adaptive model was applied to validate the effectiveness and feasibility of the proposed feature selection algorithm and sparse model using RRLSSVR.
218
Authors: Phill Doorbar, Mark Dixon, Amit Chatterjee
Abstract: The aero-engine has provided the major drive for the development of new improved titanium alloys in recent years. This paper covers these developments from the workhorse alloy Titanium 6/4 and it’s higher temperature stable mates through to the more exotic intermetallic materials and on to their reinforcement with ceramics. The use of Ti6/4 alloy is now widespread throughout the aero space industry providing a good combination of strength at moderate temperatures (~300°C) a relatively low density and a wide range of processing options ranging from castings to forgings to powder HIP and diffusion bonding. Alloy development for the aero-engine essentially concentrated on either increasing the temperature capability and creep resistance or increasing the strength at intermediate temperatures. Alloys such as Ti 6242 and IMI 834 were aimed at compressor disc applications with operation up to around 600°C. Improvements resulted from compositional control and thermal processing to optimize the microstructure for creep and fatigue. High strength intermediate temperature capability (~500°C) alloys were also developed (Ti6246) where higher levels of molybdenum balance the alpha strengthening additions. The drive for lighter weight led to the development of titanium intermetallic systems. Alloys such as 45-2-2XD and Alloy 7 have been the subject of much research and manufacturing development over the last 20 years, demonstrating that they are capable of operating at temperatures well above those of conventional titanium. More recently, alloys with higher additions of Nb and Ta have shown improved mechanical properties and offer promise to extend the application of TiAl above 700°C. In parallel with intermetallic developments combining titanium alloys with the extreme high strength of ceramic fibres has proved irresistible and many ways to produce titanium composites have been developed. The majority of application development has focused on Ti6/4 alloy as the matrix although other matrix alloys have been investigated and tested in U.S. engine demonstrators. Recently a combination of Ti-22Al-26Nb disks reinforced with orthorhombic MMC ran for over 100 hours in an engine test. However, none of these niche composite systems has yet made the transition into large volume production and the fibre reinforced Ti6/4 system probably offers the greatest potential for implementation. The main barrier to the take up of both advanced intermetallics and titanium composites is the cost of raw materials and processing. The challenge still exists to produce net shape components and provide weight savings at an acceptable cost. This will be the key to future exploitation.
127
Authors: Tao Xu, Yan Jin, Jin Xu
Abstract: Because of the complicated structure of rollers, it is very difficult to diagnosis aero-engine vibration fault. Harmonic wavelet method is proposed target towards whole-body vibration of aero-engine in this paper. To implement vibration fault diagnosis of Aero-engine, vibration signals are presented with time-frequency and spectrum of coefficients after harmonic wavelet transform. The designed method overcome noise disturbance and energy leakage and possesses better performance for aero-engine vibration analysis compared with traditional wavelet analysis method. With the vibration data from whole-body vibration experiment, the effectiveness of the designed method is illustrated and it could identify three classical vibration faulty modes accurately, which provides a better method for whole-body vibration fault diagnosis of Aero-engine.
218
Authors: Y.Y. Li, G.Y. Tan, Y.L. Cheng, F.C. Cheng
Abstract: Through the analysis of typical aero-engine fault, the function parameters under different throttle openings of the aero-engine are presented, and the fault characteristic learning as the training set are studied using the RBF neural network. An aero-engine function evaluation model is proposed in this work by comparing the test set with the expected value of the training set, and the decay degree of engine function are determined. The proposed method is validated to be an effective method of diagnosing and identifying the aero-engine fault accurately and timely by testing large amount of recorded flight data from each of various types of aero-engines. It makes it possible for early and successful diagnosis and prediction of the health condition of aero-engines.
560
Authors: Chang Zheng Li, Chao Lin, Yong Lei
Abstract: Aero engine running is complex mechanical experiments. In the last two decades, many computer aided testing (CAT) systems were developed and employed in aero engine running. Traditionally, the main role of a CAT system is data acquisition, which developed with the client/server (C/S) architecture. Now, a CAT system plays more and more important roles in information management, such as measurement channels management, experiment design and management, data analysis and report management, and so on. Users may work on local place or on remote. So, it is not only a data acquisition system, but also an information system. In this paper, we introduce hybrid architecture of C/S and browser/server (B/S) to take advantages of both of them. For local users, clients are realized to provide local monitor and operation. For remote users, browsers provide not only real-time measurement data, but also querying and management of the history data. It demonstrates that the CAT system meets the requirement of aero engine running.
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