Preliminary Research on Future Smart Engine Architecture

2020 ◽  
Author(s):  
Yudong Liu ◽  
Min Chen ◽  
Hailong Tang
Keyword(s):  
Aerospace Industry ◽  
Research Projects ◽  
Engine Design ◽  
Engine Component ◽  
Aero Engine ◽  
The Future ◽  
Component Matching ◽  
Matching Mechanism ◽  
Preliminary Research ◽  
Aero Engines

Abstract Aero engines that fit the future have now increasingly attracted the attention of aerospace industry and academia. With this trend, many research projects have been carried out to explore future aero engine technologies. This paper focuses on engine design field, and aims to satisfy the future flight missions that may be unpredictably varying. However, the intrinsic strong coupling of engine component matching mechanism blocks acceleration of engine design. Under this condition, this paper comes up with the concept of smart engine architecture that via a series of engine decoupling strategies, the components can be decoupled to an extent that by properly selecting and assembling them, an engine that satisfies certain flight mission can be designed, this is named mission-oriented pluggable design mode in this paper. Following this idea, a multi-purpose engine design scheme is presented to demonstrate the potential of this engine design mode, and further value of smart engine architecture is discussed.

Lionel Haworth. 4 August 1912 — 12 April 2000

2005 ◽  
Vol 51 ◽  
pp. 195-220
Author(s):  
G. B. R. Feilden
Keyword(s):  
Civil Aviation ◽  
Initial Training ◽  
Chief Designer ◽  
Hands On ◽  
The World ◽  
Aero Engine ◽  
The Future ◽  
Aero Engines

Lionel Haworth was one of the leading aero engine designers in the world. After initial training in 1934 to 1936 with the Associated Equipment Company of Southall–the builders of London's buses—he moved to Rolls–Royce, Derby, where he worked until 1963 when he transferred to the Bristol Siddeley engine company, which merged with Rolls–Royce in 1966. Throughout his career he was very much a 'hands on' engineer who insisted in keeping close to work on any new engine for which he was responsible. He worked on Rolls–Royce engines for aircraft ranging from the Meteor to Concorde, his crowning achievement in Derby being the Dart engine, which was an extremely successful, admirably simple turboprop that powered the Vickers Viscount and 11 other aircraft and had a wide influence on the future of civil aviation around the world. In Bristol, as Chief Designer, he took overall responsibility for the Concorde, Harrier and Tornado as well as all other aero engines being developed and built by Rolls–Royce, Bristol, between 1963 and 1977.

A Review of the Relative Merits of Petrol Injection and Carburettors for Aero Engines

1939 ◽  
Vol 43 (347) ◽  
pp. 837-874
Author(s):  
J. E. Ellor ◽  
F. M. Owner
Keyword(s):  
Fuel Injection ◽  
The Other ◽  
Design And Development ◽  
Amount Of Information ◽  
Engine Design ◽  
Aero Engine ◽  
The Subject ◽  
Aero Engines

The subject of the carburettor as opposed t o fuel injection is one which has created much controversy in aero engine design and development. Current opinions both in this country and abroad are many and varied and it would be presumptuous to forecast which will eventually predominate. The object of this paper is to present an unbiased review in the hope of provoking a useful interchange of opinions and experiences.It might be argued that claims for one system can be countered by claims for the other and to be impartial it is necessary, therefore, to be familiar with as many facts and as much published information as possible. Owing to the meagre amount of information available on fuel injection, the paper is not as complete a review as the authors would wish, but it is hoped that sufficient material has been presented to be helpful to those who are interested in the subject.

The Origin and Development of Heavy—Oil Aero Engines

1931 ◽  
Vol 35 (244) ◽  
pp. 265-298
Author(s):  
D. R. Pye
Keyword(s):  
Power Generation ◽  
Heavy Oil ◽  
Early History ◽  
Aero Engine ◽  
The Future ◽  
History Of ◽  
Aero Engines

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 terrestrial parent. The early history moreover, of the heavy oil engine is of quite exceolional interest, both technical and personal.Herbert Akroyd—Stuart was born in 1864.His father, Charles Stuart, owned a small engineering works at Fenny Stratford, and it was here that the son gained his training as an engineer. Between 1885 and 1890 he took out several patents for the improvement of oil engines, which appear to have been the outcome of his experience with a “ Spiel ” petroleum engine used for power generation at his father's works.

Electromagnetic Propulsion Aero-Engine Design Based on Ampere Theorem

2013 ◽  
Vol 411-414 ◽  
pp. 1773-1778
Author(s):  
Shu Sheng Bi ◽  
Shi Xing Fang ◽  
Shi Hao Wang
Keyword(s):  
Magnetic Field ◽  
Plant Design ◽  
Innovative Design ◽  
Engine Design ◽  
Potential Market ◽  
Working Medium ◽  
Aero Engine ◽  
Late Model ◽  
Aero Engines ◽  
Electromagnetic Propulsion

This paper means to provide an innovative design of aero-engine after investigating existing aero-engines. It is a late model power plant design which is based on the watercraft electromagnetic propulsion technology and the theory that in electromagnetic field magnetic field generates Ampere force to current flow and in combination with specific structures of aero-engines. The design principle of this engine is that when the air working medium with high conductivity goes through an arc generator, it will ionize and produce plasma, which actions in the magnetic field that produced by built-in superconducting magnetic and generates forward push. This design will provide a theoretical reserve for future development of aero-engines and has potential market prospects.

Computer Based Optimisation and Automation of Analysis and Design Processes in Aero Engine Development

2002 ◽  
Author(s):  
Alexander Karl ◽  
Roland Hansen ◽  
Michael Pfitzner
Keyword(s):  
Loose Coupling ◽  
Analysis And Design ◽  
Repetitive Tasks ◽  
Engine Design ◽  
Aero Engine ◽  
Computer Based ◽  
Aero Engines ◽  
Engine Components ◽  
Engine Development

Many variants of designs of different engine components have to be analysed in detail during the design and subsequent optimisation of modern aero engines. This often involves repetitive tasks and even today this process still contains a considerable amount of manual work for the majority of the tasks in the design process. Experts from different technical disciplines are involved and several different analysis tools are used. An automation of this process not only saves a lot of time during the design phase; it also increases the quality of the design since many more design variants can be screened. In the present paper the integration of different analysis codes and optimisation tools into an automated process using off-the-shelf software is described. A mix of commercial and in-house codes is integrated in a loose coupling way. Several applications from different areas of aero engine design are described. It is shown that in all cases the computer based optimisation and the process automation yields results of equal or better technical quality compared to the original hand optimised ones or improves the understanding of the design space. In addition, the necessary wall-clock time to reach the results was in all cases a fraction of that of the manual process.

Safety Design Methods for Rotor-Bearing System and Dynamic Analysis in Aero-Engines

2018 ◽  
Author(s):  
Jie Hong ◽  
Tianrang Li ◽  
Zhichao Liang ◽  
Dayi Zhang ◽  
Yanhong Ma ◽  
...  
Keyword(s):  
Engine Design ◽  
Safety Design ◽  
Aero Engine ◽  
Rotor Bearing ◽  
Response Peak ◽  
Aero Engines ◽  
Stiffness Loss ◽  
Optimal Stiffness ◽  
Bearing System ◽  
Peak Value

One typical fusing structure (fused device or load reduction device, a variable supporting stiffness structure used in bearing supporting in aero-engine design) was introduced in this paper. Based on the rotor-bearing system simulation model, a dynamic calculation under the condition of variable supporting stiffness was conducted aimed at providing data for the rotor system safety design. Results showed that: rotor working in supercritical state had a benefit to the dynamic characteristics, as when the supporting stiffness suddenly lost, transient excessively increasing vibration was restrained, steady vibration also remained at a low level. Transient response peak value and impact response increased with the increase of stiffness loss, steady vibration ratio decreased with the increase of stiffness loss. Therefore, a compromise on the choosing of an optimal stiffness loss value was necessary. We also got some other significant conclusions that are instructive for further engineering applications.

Lifing Requirement Based Turbine Airfoil Mass Estimation Method in Conceptual Aero-Engine Design

2011 ◽  
Author(s):  
Stefan Bretschneider ◽  
Hermann Klingels ◽  
Fabian Donus ◽  
Meinrad Weisser
Keyword(s):  
Mechanical Design ◽  
Turbine Blades ◽  
Estimation Method ◽  
Engine Design ◽  
Area Distribution ◽  
Aero Engine ◽  
Aero Engines ◽  
Airfoil Cascade ◽  
Cooling Air ◽  
Material Temperature

The presented paper describes a method developed by MTU Aero Engines to estimate the mass of turbine blades during multi-disciplinary conceptual design studies based on a prescribed airfoil lifetime [1, 2]. For a given material, the target lifetime can be translated into a maximally allowable material temperature and stress level. While the latter has to be maintained by an appropriate mechanical design of the turbine blades, the material temperature needs to be established by sufficient cooling air. The predominant life-limiting effects are taken into account to determine the allowable temperatures and stresses as an accumulation of the varying operating condition over a flight cycle. The applicable stress levels are then used to calculate the necessary radial area distribution of the airfoil and by this a prediction of its mass is possible. Furthermore, the methodology estimates the required amount of cooling air per airfoil cascade from the computed material temperatures. Example calculations are presented and discussed which illustrate design trends and the benefits which are gained from the proposed method.

scholarly journals SUSTAINABILITY ASSESSMENT OF COMPOSITES IN AERO-ENGINE COMPONENTS

2020 ◽  
Vol 1 ◽  
pp. 1989-1998
Author(s):  
P. L. Y. Léonard ◽  
J. W. Nylander
Keyword(s):  
Sustainability Assessment ◽  
Aerospace Industry ◽  
Environmental Issues ◽  
New Materials ◽  
Environmental Consequences ◽  
Complex Processes ◽  
Aero Engine ◽  
Aero Engines ◽  
Sustainability Challenges ◽  
Engine Components

AbstractEnvironmental issues such as climate change are leading to sustainability challenges for the aerospace industry. New materials such as composites allow significant weight reduction, which leads to a lower fuel consumption. However, composites involve complex processes and there is a lack of knowledge on their social and environmental consequences. Through two cases based on real aero-engines components, this paper shows that the weight savings provided by composites reduce significantly the CO2 emissions during flight which compensates the environmental drawbacks from production and recycling.

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