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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.

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.

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

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.

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.

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.

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.

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

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

This paper was read before the World Petroleum Congress on July 19, 1933. Mr. Pye acted as chairman of a committee set up by the Institution of Petroleum Technologists to investigate the corelation of knock‐rating as determined in a test engine with the results obtained using aero‐engine cylinders. This paper prepared by him summarises the results of the committee's investigations

AIRCRAFT production is so much in everyone's mind at the present time that inevitably much discussion has arisen around its relationship to design. Schools of thought range from that which would subjugate design entirely to production to that which puts design for maximum performance before all other considerations. It is intended here to review the design and production of current types of aero‐engines primarily from the engine designer's point of view.

Spotlights that strategic alliances are widely used within the aerospace industry and the success of Europe’s Airbus Industrie consortium has been much publicized. Less well‐documented has been the success of some of Europe’s leading engineering companies, such as Rolls‐Royce, Daimler‐Benz and BMW, in supplying aero engines to the world’s airlines. Again collaborative ventures have played an important part in helping these firms to build market share within this highly competitive global market. Reviews the changes that have taken place within both the airframe and the engine sectors of the aerospace industry in recent years. Critically evaluates the part that strategic alliances have played in the increasing commercial success of the European Union in both sectors. Highlights differences in the nature and role of such alliances as well as their impact on the structure of each sector.

SUPERCHARGED aero engines are more or less a post‐war invasion into the practical side of aero‐engine design. The problem of power boosting for internal combustion engines, especially aero engines, has for several years engaged the attention of engine designers, with the result that to‐day quite a number of engines are produced with superchargers as an integral part of the standard equipment. Various types of superchargers have been tried, such as the reciprocating pump, Roots Blower, exhaust‐driven turbo compressor, and the gear‐driven centrifugal form of blower. The last‐named is the type most commonly used in this country at the present time.

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.

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.

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..

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.

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

I.—Historical IN this first lecture upon the origin and development of the heavy‐oil aero‐engine, to be delivered under the Akroyd‐Stuart foundation, it is appropriate to devote some space to the early history of oil engines generally, for it is certain that the aero‐engine of the future will claim a direct descent from some parent. The early history, moreover, of the heavy‐oil engine is of quite exceptional interest, both technical and personal.

The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamber performance.

The combustor geometry is designed using the reference area method and semi-empirical correlations. The three dimensional combustor model is made using a commercial software. The numerical modeling of the combustion process is performed by following Eulerian approach. The functional testing of combustor was conducted to evaluate the performance.

The results obtained by the numerical modeling provide a detailed understanding of the combustor internal flow dynamics. The transient flame structures and streamline plots are presented. The velocity profiles obtained at different locations along the combustor by numerical modeling mostly go in-line with the previously published research works. The combustor exit temperature obtained by numerical modeling and experiment are found to be within the acceptable limit. These results form the basis of understanding the design procedure and opens-up avenues for further developments.

Internal flow and combustion dynamics obtained from numerical simulation are not experimented owing to non-availability of adequate research facilities.

This study contributes toward the understanding of basic procedures and firsthand experience in the design aspects of combustors for aero-engine applications. This work also highlights one of the efficient, faster and economical aero gas turbine annular diffusion flame combustion chamber design and development.

The main novelty in this work is the incorporation of scoops in the dilution zone of the numerical model of combustion chamber to augment the effectiveness of cooling of combustion products to obtain the desired combustor exit temperature. The use of polyhedral cells for computational domain discretization in combustion modeling for aero engine application helps in achieving faster convergence and reliable predictions. The methodology and procedures presented in this work provide a basic understanding of the design aspects to the beginners working in the gas turbine combustors particularly meant for turbo shaft engines applications.

This study aims to investigate the aviation, energetic, exergetic, environmental, sustainability and exergoeconomic performances of a micro turbojet engine used in unmanned aerial vehicles at four different modes.

The engine data were collected from engine test cell. The engine performance calculations were performed for four different operation modes.

According to the results, maximum energy and exergy efficiency were acquired as 19.19% and 18.079% at Mode 4. Total cost rate was calculated as 6.757 $/h at Mode-1, which varied to 10.131 $/h at Mode-4. Exergy cost of engine power was observed as 0.249 $/MJ at Mode-1, which decreased to 0.088 $/MJ at Mode-4 after a careful exergoeconomic analysis.

The novelty of this work is the capability to serve as a guide for similar systems with a detailed approach in the thermodynamic, thermoeconomic and environmental assessments by prioritizing efficiency, fuel consumption and cost formation. This investigation intends to establish a design of the opportunities and benefits that the thermodynamic approach provides to turbojet engine systems.