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1 – 10 of over 2000
Article
Publication date: 30 March 2010

E. Vassilakis and G. Besseris

The purpose of this paper is to provide a relatively straightforward approach of implementing standard statistical process control (SPC) concepts while instituting…

1369

Abstract

Purpose

The purpose of this paper is to provide a relatively straightforward approach of implementing standard statistical process control (SPC) concepts while instituting problem‐solving intonations in aero‐engine maintenance processes.

Design/methodology/approach

The inspection workflow approach is presented in order to aid in collecting and monitoring critical aero‐engine data. Observed defects are categorized according to a Pareto analysis assisted by a cause‐and‐effect diagram. A binomial process capability analysis is performed on nonconforming aero‐engines based on operating curves produced specifically for this case study. The time frame for experimental analysis is reflected in a span of six months.

Findings

It is found that a significant number of aero‐engines may be benefited by entering a more progressive maintenance program relying on predictive maintenance on the way to establishing a more effective Total Productive Maintenance scheme.

Research limitations/implications

The case study showcases an approach to aero‐engine rejection statistical rates by accepting the fact that maintenance process may not be viewed as a process that may be limited to constant sampling.

Practical implications

For a long time, total quality management (TQM) tools have been deeply rooted in design, manufacturing and assembling of airliners and jet fighters alike. However, a comprehensive study focusing on the maintenance function of such complex machines may prove worthwhile now that an unstable global economy may prohibit extensive replacement of aging flying fleets.

Originality/value

With the lack of a prior practical unfolding in the field of genuine aero‐engine maintenance, this presentation aims to fill in the gap for engine rejection treatment. The variant operating curve notion introduced in the text is also a unique idea espoused for variable sampling situations when a binomial distribution is adopted.

Details

Journal of Quality in Maintenance Engineering, vol. 16 no. 1
Type: Research Article
ISSN: 1355-2511

Keywords

Article
Publication date: 20 April 2018

Shaohua Wang and Ping Zhang

Nowadays, a large amount of data related to aero engine in various types can be created in a single day and it is very important to well organize and store these data. The…

Abstract

Purpose

Nowadays, a large amount of data related to aero engine in various types can be created in a single day and it is very important to well organize and store these data. The paper aims to discuss this issue.

Design/methodology/approach

This paper puts forward the problem of data management with the fast development of aero engine and sets the compression system as an example to see the inner relationships of data from the initial design procedure to the final operation and maintenance part. There are five principles, namely digitization, accuracy, normative, integrality and validity, involved in managing the data effectively.

Findings

These data resources arranged according to the five principles can be well organized and better used.

Originality/value

At the end, the top design of aero engine data sharing platform is investigated and five layers including data layer, data access layer, communication layer, business logic layer and application layer are designed and presented to support the platform.

Details

Multidiscipline Modeling in Materials and Structures, vol. 14 no. 2
Type: Research Article
ISSN: 1573-6105

Keywords

Article
Publication date: 5 March 2018

Huibin Sun and Zhiyong Chang

The functionality and reliability of an overhauled aero-engine is determined by all configuration changes in the overhaul process. Identifying, recording, auditing…

Abstract

Purpose

The functionality and reliability of an overhauled aero-engine is determined by all configuration changes in the overhaul process. Identifying, recording, auditing, tracking and tracing of configuration modifications are significant and meaningful. Considering the barriers to these goals, this paper aims to put forward an approach to configuration management in the aero-engine overhaul process.

Design/methodology/approach

The overhaul configuration management model is proposed to describe an aero-engine’s configuration evolution trajectory in the overhaul process. The controlling and auditing procedures are put forward to control and audit parts’ return-to-zero statuses and overproof statuses. And some searching algorithms are also designed to enable tracking and tracing of the configuration status along the time coordinate, or get a snapshot of an aero-engine’s configuration at a certain time. The above model, procedures and algorithms have been implemented and adopted to fulfill the configuration management requirements in the aero-engine overhaul process.

Findings

The approach is effective in identifying, recording, controlling, auditing, tracking and tracing configuration changes in the overhaul process.

Practical implications

The approach’s implementation and adoption present a practical example for aero-engines’ configuration management issue in the overhaul process.

Originality/value

The work proposes an original aero-engine configuration management solution for the overhaul process and enables a reliable and accurate configuration management mode.

Details

Aircraft Engineering and Aerospace Technology, vol. 90 no. 2
Type: Research Article
ISSN: 1748-8842

Keywords

Article
Publication date: 8 August 2016

Longbiao Li, Suyi Bi and Youchao Sun

– The purpose of this paper is to develop a method to predict the multi-failure risk of aero engine in service and to evaluate the effectiveness of different corrective actions.

Abstract

Purpose

The purpose of this paper is to develop a method to predict the multi-failure risk of aero engine in service and to evaluate the effectiveness of different corrective actions.

Design/methodology/approach

The classification of failure risk level, the determination of hazard ratio and the calculation of risk factor and the risk per flight have been proposed. The multi-failure risk assessment process of aero engine has been established to predict the occurrence of failure event and assess the failure risk level. According to the history aero engine failure data, the multi-failure risk, i.e., overheat, blade wounding, pump failure, blade crack, pipe crack and combustor crack, has been predicted considering with and without corrective action. Two corrective actions, i.e., reduce the maintenance interval and redesign the failure components, were adopted to analyze the decreasing of risk level.

Findings

The multi-failure risk of aero engine with or without corrective action can be determined using the present method. The risk level of combustor crack decreases from high-risk level of 1.18×1e−9 without corrective action to acceptable risk level of 0.954×1e−9 by decreasing the maintenance interval from 1,000 to 800 h, or to 0.912×1e−9 using the redesign combustor.

Research limitations/implications

It should be noted that probability of detection during maintenance actions has not been considered in the present analysis, which would affect the failure risk level of aero engine in service.

Social implications

The method in the present analysis can be adapted to other types of failure modes which may cause significant safety or environment hazards, and used to determine the maintenance interval or choose appropriate corrective action to reduce the multi-failure risk level of aero engine.

Originality/value

The maintenance interval or appropriate corrective action can be determined using the present method to reduce the multi-failure risk level of aero engine.

Details

Multidiscipline Modeling in Materials and Structures, vol. 12 no. 2
Type: Research Article
ISSN: 1573-6105

Keywords

Article
Publication date: 5 March 2018

Yasin Şöhret and T. Hikmet Karakoc

It is essential to develop more environment-friendly energy systems to prevent climate change and minimize environmental impact. Within this scope, many studies are…

Abstract

Purpose

It is essential to develop more environment-friendly energy systems to prevent climate change and minimize environmental impact. Within this scope, many studies are performed on performance and environmental assessments of many types of energy systems. This paper, different from previous studies, aims to prove exergy performance of a low-emission combustor of an aero-engine.

Design/methodology/approach

It is a well-known fact that, with respect to previous exergy analysis, highest exergy destruction occurs in the combustor component of the engine. For this reason, it is required to evaluate a low-emission aero-engine combustor thermodynamically to understand the state of the art according to the authors’ best of knowledge. In this framework, combustor has been operated at numerous conditions (variable engine load) and evaluated.

Findings

As a conclusion of the study, the impact of emission reduction on performance improvement of the aero-engine combustors exergetically is presented. It is stated that exergy efficiency of the low-emission aero-engine combustor is found to be 64.69, 61.95 and 71.97 per cent under various operating conditions.

Practical implications

Results obtained in this paper may be beneficial for researchers who are interested in combustion and propulsion technology and thermal sciences.

Originality/value

Different from former studies, the impact of operating conditions on performance of a combustor is examined from the viewpoint of thermodynamics.

Details

Aircraft Engineering and Aerospace Technology, vol. 90 no. 2
Type: Research Article
ISSN: 1748-8842

Keywords

Article
Publication date: 28 September 2010

Qiang Liu and Chengen Wang

The paper aims to present a modified particle swarm optimization (MPSO) approach for automatic generation of near‐optimal pipe routes in constrained aero‐engine 3D…

Abstract

Purpose

The paper aims to present a modified particle swarm optimization (MPSO) approach for automatic generation of near‐optimal pipe routes in constrained aero‐engine 3D rotational space.

Design/methodology/approach

Pipe assembly for aero‐engine is formulated as searching for the optimal pipe paths meeting certain objectives in a constrained 3D rotational space. The routing space is first modelled by grid discretization in the cylindrical coordinate system, and then is simplified into several 2D planes by mapping development. The objective function is formulated to minimize the pipe lengths and the number of pipe turns, to place pipes next to the inner jacket as close as possible, and also to make pipe trajectories closely follow around obstacle contours while avoiding collisions. Then, an MPSO approach, which adopts a discrete operator and a fixed‐length encoding mechanism, is developed to seek optimal solutions to the objective function. The convergence of MPSO is theoretically proved. Finally, numerical computations of pipe‐routing examples are conducted by using Matrix Laboratory and Unigraphics NX 4.0 system, which demonstrates effectiveness and efficiency of the proposed method.

Findings

Results show that MPSO can quickly find the optimal pipe routes meeting certain engineering constraints, and also manifests better computation convergences.

Practical implications

The application of the MPSO approach in pipe routing for aero‐engines is demonstrated. MPSO is a general modified particle swarm optimization version that it is not restricted to the pipe‐routing problems, and the routing approach can also be applied in similar path‐planning problems such as robot path‐planning and very large‐scale integration design.

Originality/value

The paper develops a new formulation for aero‐engine pipe‐routing problems, and presents an MPSO approach to find the optimal pipe paths.

Details

Assembly Automation, vol. 30 no. 4
Type: Research Article
ISSN: 0144-5154

Keywords

Article
Publication date: 27 March 2009

E. Vassilakis and G. Besseris

Devoted to a description and evaluation of a selected maintenance process (assembly) at the aero‐engines maintenance unit of a large aerospace company by implementation of…

2425

Abstract

Purpose

Devoted to a description and evaluation of a selected maintenance process (assembly) at the aero‐engines maintenance unit of a large aerospace company by implementation of TQM tools, this paper attempts to identify the causes behind the defect observed and form the scientific platform for initiatives in a TQM‐governed enterprise and to broaden the principles of TQM for the selected process, prior to moving to a more structured plan that will include the entire unit.

Design/methodology/approach

Process monitoring and evaluation are organised by an application of control charts in order to provide vital information regarding the level of control in the selected process. Quality control data are contrasted with component specifications by employing control charts to provide a metric for the level of the process capability index. As a result a Fishbone diagram is constructed to identify existing interrelations between the causes responsible for the defect observed.

Findings

The maintenance process selected was the assembly process of an aero‐engine module (exhaust nozzle unit) at the aero‐engines maintenance unit of a large aerospace company. Process evaluation by means of multivariate control charts and tolerance analysis exhibited poor results. It was observed that certain measurement stations were out of control, whilst low actual capability index values were exhibited in others..

Research limitations/implications

Process monitoring and evaluation carried out for the purposes of the present study had the form of an off‐line tool. The paper shows that the aero‐engines maintenance unit had no infrastructure for an online process control and monitoring system. Consequently, performed analysis indicated that the implied assembly process was inadequately implemented. As a result, the maintained assembly units were out of stated specifications limits.

Originality/value

The study contributes to the literature on TQM in the aerospace maintenance business.

Details

Journal of Quality in Maintenance Engineering, vol. 15 no. 1
Type: Research Article
ISSN: 1355-2511

Keywords

Article
Publication date: 1 March 1993

BMW is a company that can look back on a long tradition in engine construction. This not only applies to developing innovative car engines, which were always a little…

Abstract

BMW is a company that can look back on a long tradition in engine construction. This not only applies to developing innovative car engines, which were always a little ahead of their time, but also to designing aero engines. It is now possible to present the public with a record of aero‐engine construction that was long believed to have been lost without trace: a BMW type 803 A aero engine built in 1944, comprising two 4‐cylinder double‐radial engines that together develop some 4,000 hp. This unique example is now being exhibited at the Deutsches Museum in Munich.

Details

Aircraft Engineering and Aerospace Technology, vol. 65 no. 3
Type: Research Article
ISSN: 0002-2667

Article
Publication date: 30 September 2022

Fernando Tejero, David MacManus, Josep Hueso-Rebassa, Francisco Sanchez-Moreno, Ioannis Goulos and Christopher Sheaf

Aerodynamic shape optimisation is complex because of the high dimensionality of the problem, the associated non-linearity and its large computational cost. These three…

Abstract

Purpose

Aerodynamic shape optimisation is complex because of the high dimensionality of the problem, the associated non-linearity and its large computational cost. These three aspects have an impact on the overall time of the design process. To overcome these challenges, this paper aims to develop a method for transonic aerodynamic design with dimensionality reduction and multifidelity techniques.

Design/methodology/approach

The developed methodology is used for the optimisation of an installed civil ultra-high bypass ratio aero-engine nacelle. As such, the effects of airframe-engine integration are considered during the optimisation routine. The active subspace method is applied to reduce the dimensionality of the problem from 32 to 2 design variables with a database compiled with Euler computational fluid dynamics (CFD) calculations. In the reduced dimensional space, a co-Kriging model is built to combine Euler lower-fidelity and Reynolds-averaged Navier stokes higher-fidelity CFD evaluations.

Findings

Relative to a baseline aero-engine nacelle derived from an isolated optimisation process, the proposed method yielded a non-axisymmetric nacelle configuration with an increment in net vehicle force of 0.65% of the nominal standard net thrust.

Originality/value

This work investigates the viability of CFD optimisation through a combination of dimensionality reduction and multifidelity method and demonstrates that the developed methodology enables the optimisation of complex aerodynamic problems.

Details

International Journal of Numerical Methods for Heat & Fluid Flow, vol. ahead-of-print no. ahead-of-print
Type: Research Article
ISSN: 0961-5539

Keywords

Article
Publication date: 1 June 2022

Jun Wu, Hong-Zhong Huang, Yan-Feng Li, Song Bai and Ao-Di Yu

Aero-engine components endure combined high and low cycle fatigue (CCF) loading during service, which has attracted more research attention in recent years. This study…

Abstract

Purpose

Aero-engine components endure combined high and low cycle fatigue (CCF) loading during service, which has attracted more research attention in recent years. This study aims to construct a new framework for the prediction of probabilistic fatigue life and reliability evaluation of an aero-engine turbine shaft under CCF loading if considering the material uncertainty.

Design/methodology/approach

To study the CCF failure of the aero-engine turbine shaft, a CCF test is carried out. An improved damage accumulation model is first introduced to predict the CCF life and present high prediction accuracy in the CCF loading situation based on the test. Then, the probabilistic fatigue life of the turbine shaft is predicted based on the finite element analysis and Monte Carlo analysis, where the material uncertainty is taken into account. At last, the reliability evaluation of the turbine shaft is conducted by stress-strength interference models based on an improved damage accumulation model.

Findings

The results indicate that predictions agree well with the tested data. The improved damage accumulation model can accurately predict the CCF life because of interaction damage between low cycle fatigue loading and high cycle fatigue loading. As a result, a framework is available for accurate probabilistic fatigue life prediction and reliability evaluation.

Practical implications

The proposed framework and the presented testing in this study show high efficiency on probabilistic CCF fatigue life prediction and can provide technical support for fatigue optimization of the turbine shaft.

Originality/value

The novelty of this work is that CCF loading and material uncertainty are considered in probabilistic fatigue life prediction.

Details

Aircraft Engineering and Aerospace Technology, vol. ahead-of-print no. ahead-of-print
Type: Research Article
ISSN: 1748-8842

Keywords

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