Deterioration Detection and Health Monitoring in Aircraft Jet Engines

2012 ◽  
Author(s):  
N. Daroogheh ◽  
A. Baniamerian ◽  
H. Nayyeri ◽  
K. Khorasani
Keyword(s):  
Performance Analysis ◽  
Statistical Method ◽  
Health Monitoring ◽  
Engine Performance ◽  
Jet Engines ◽  
Differential Analysis ◽  
Analysis Method ◽  
Jet Engine ◽  
Engine Model ◽  
Cumulative Sum Method

In this paper the problem of jet engine deterioration detection and health monitoring is investigated by utilizing two methods. The first method is based on the fusion of the modified CUSUM (CUmulative SUM) method with the differential analysis approach. An enhanced differential analysis method is developed through which the degradation is captured from the unsymmetrical performance analysis of both engines on an aircraft. This is achieved by considering the effects of minor maintenance actions that are not reported. In the second approach, a statistical method based on the Hotelling’s T2-test approach is utilized to detect gradual degradations in the engine performance. The performance of our proposed approaches is evaluated by implementing them on a dual spool engine model that is developed by using the GSP software.

Model Based Control Concepts for Jet Engines

2001 ◽  
Author(s):  
Klaus Lietzau ◽  
Andreas Kreiner
Keyword(s):  
Turbine Blades ◽  
Engine Performance ◽  
Current Control ◽  
Engine Control ◽  
Jet Engines ◽  
Jet Engine ◽  
Engine Model ◽  
Model Based ◽  
Safety Margins ◽  
Engine Life

Many jet engine variables cannot be measured in-flight or can only be measured with a complex, and hence unreliable, instrumentation system. This includes variables that are of imminent importance for the safe operation of the engine or for engine life, such as the temperature of the high pressure turbine blades or the surge margins of the turbo compressors, for instance. Current control systems therefore transform limits on these variables into limits on other variables measured by the engine’s sensors. This leads to increased safety margins and thus to non-optimal engine performance. An onboard engine model incorporated into the engine control system could provide information about all engine variables. This could enable further control and monitoring system optimisations leading to improved engine performance, reduced fuel consumption, increased safety and engine life. This paper explains the principle of model based engine control and gives an overview about possible applications for conventional and also thrust vectored jet engines. Modeling methods for real-time simulation as well as methods for online model adaptation are presented. The potential of model based jet engine control is analyzed and fortified by some prototype realizations.

Generation of Physically Based Analysis Factors to Improve Synthesis Models of Jet Engines

2005 ◽  
Author(s):  
Xavier Canalias ◽  
Frank Ko¨pf ◽  
Peter Sahm
Keyword(s):  
Engine Performance ◽  
Good Choice ◽  
Jet Engines ◽  
Analysis Method ◽  
Jet Engine ◽  
Analysis By Synthesis ◽  
Physically Based ◽  
The Common ◽  
Set Up ◽  
Definition Of

The ANalysis by SYNthesis (ANSYN) technique is a standard performance analysis method widely used in industry. It is currently used to evaluate engine performance from tests and to derive correcting factors (i.e. ANSYN factors) that modify certain parameters of the components’ characteristics in order to allow the reproduction of real engine behaviour by means of a synthesis calculation. Once they have been determined, these ANSYN factors can be implemented into the common synthesis tools to accurately predict the behaviour of the engine in non-tested conditions. The definition of how the engine synthesis will be modified to reproduce the measured cycle is called the “matching scheme”. It is the choice of the parameters that will not be modified, the ones that will be scaled and the ones that will be used as a reference. A good choice of the ANSYN factors and of the magnitudes used to tabulate them will make possible their physical interpretation and analysis, which can lead to the identification of inaccurate assumptions and phenomena that had not been accurately taken into account in the previous performance models. This understanding of their origin is a prerequisite for any improvement of the models and could lead to an enhanced process for the development of non-dimensional jet engine characteristics. In this study, a matching scheme for the RR-BR710 engine has been set up, implemented and applied. This method is an alternative to some of the currently used in the Rolls-Royce Deutschland ANSYN tools. The main goal of the present work has been the definition of a matching scheme that leads to the obtention of physically meaningful ANSYN factors. This allows their subsequent analysis and interpretation and can provide useful information on engine component operation and on the phenomena responsible for the observed deviations from predicted engine behaviour.

Correlations of Soot Formation in Turbojet Engines and in Laboratory Flames

1984 ◽  
Author(s):  
R. J. Gill ◽  
D. B. Olson ◽  
H. F. Calcote
Keyword(s):  
Soot Formation ◽  
Dominant Role ◽  
Engine Performance ◽  
Smoke Point ◽  
Jet Engines ◽  
Fuel Property ◽  
Jet Engine ◽  
Related Data ◽  
Polycyclic Aromatic ◽  
Engine Testing

Smoke related performance of both jet engine and research combustors has been correlated with several fuel properties. The smoke related data included: smoke number, liner temperature rise, and radiation flux to the combustor wall; fuel parameters included: percent hydrogen, percent aromatic, percent polycyclic aromatic, smoke point, and the threshold soot index, TSI. The research combustor results correlated best with the threshold sooting index. While some correlations with engine performance were excellent, no single fuel property was generally useful in evaluating smoke related performance, mainly because of insufficient data on the fuels tested in the jet engine programs, e.g., percent aromatics specifies a class of fuels which span > 50% of the possible range of sooting tendencies. It is, however, demonstrated that fuel composition plays a dominant role in determining smoke related engine parameters. It is recommended that fuels used for engine testing programs be chemically analyzed in greater detail or be made available for laboratory measurements of soot thresholds and soot yields until a sufficient data base is available to establish a laboratory technique of predicting relative smoke related performance of fuels in jet engines.

The Selective Bleed Variable Cycle Engine

1991 ◽  
Author(s):  
Marco A. R. Do Nascimento ◽  
Pericles Pilidis
Keyword(s):  
Performance Analysis ◽  
Engine Performance ◽  
Performance Characteristics ◽  
Variable Geometry ◽  
Jet Engine ◽  
Fuel Savings ◽  
Operating Modes ◽  
Low Weight ◽  
Bypass Ratio ◽  
Aircraft Propulsion

A new concept in aircraft propulsion is described in this paper. A variable cycle jet engine is being investigated for a supersonic STOVL aircraft. The engine is the selective bleed turbofan, a two shaft three compressor engine. At low flight speeds this engine operates as a medium bypass turbofan, and for the supersonic cruise condition it operates as a low bypass ratio turbofan in the dry mode. In this paper, the performance of the engine and some of the components is analysed. Off-design engine performance characteristics are explained, compressor running lines are shown, and variable geometry requirements are described. The performance analysis shows that fuel savings are significant, thus reducing aircraft take-off weight. The major advantage of this engine is that all the components are employed all the time, for all operating modes, thus incurring low weight penalties.

New Approach of Whole Engine Structural System Design

2014 ◽  
Author(s):  
Masaharu Andoh ◽  
Tatsuhito Honda ◽  
Kikuo Takamatsu
Keyword(s):  
Engine Performance ◽  
Design Approach ◽  
Jet Engines ◽  
Structural System ◽  
New Approach ◽  
Jet Engine ◽  
Conventional Design ◽  
Engine Design ◽  
Current Design ◽  
And Performance

Fuel-efficient jet engines are developed by many companies. In the conventional design approach of a jet engine, many parameters are investigated independently. Consequently, a developed jet engine by this approach meets conventional design criteria but there is still room for improvement of engine performance. In this research, the new design approach of a jet engine that integrates these design objectives is developed and performance of a jet engine is evaluated. The goal is to develop the design approach of a fuel-efficient and robust jet engine. In current design, a jet engine is developed with a focus on not only performance improvement but also robustness. Therefore, Taguchi method is adopted in order to assess robustness. By this method, a jet engine is optimized based on the analysis that minimizes deterioration and variation of SFC. As a result, more efficient engine design is realized with the new design approach that directly deals with SFC.

Use of Computer Simulation Techniques to Assess Thrust Rating as a Means of Reducing Turbo-Jet Life Cycle Costs

1994 ◽  
Author(s):  
B. Devereux ◽  
R. Singh
Keyword(s):  
Computer Simulation ◽  
Life Cycle ◽  
High Performance ◽  
Engine Performance ◽  
Simulation Technique ◽  
Life Cycle Costs ◽  
Clear Understanding ◽  
Jet Engines ◽  
Jet Engine ◽  
Baseline Values

This paper investigates the concept of thrust rating as a means towards reducing the life cycle costs of turbo-jet engine ownership. Towards this end, the concepts of life usage and thrust rating will be discussed to provide a clear understanding of the goals and methods involved in this investigation. In general, all “serviceable” engines will experience varying levels of performance above baseline values. Thrust rating ideally seeks to limit engine performance to baseline values, thereby converting performance into life. In particular, this paper will present a general computer simulation technique that may be applied to any turbo-jet engine to quantify the life cycle savings resulting from the adoption of thrust rating techniques. The inter-relationships that exist between thrust rating and many practical in-service aspects of turbo-jet usage including performance degradation, operational roles and maintenance practices and policies will be investigated. Some strengths and limitations of the simulation technique will also be identified. This paper will discuss general guidelines for investigating the feasibility of performing thrust rating on various turbo-jet engines. While this technique is likely to be of greatest interest to users of high performance military turbo-jet engines, its principles can be adapted for other gas turbine uses.

TANGGAPAN WAJIB PAJAK TERHADAP KUALITAS PELAYANAN DILIHAT DARI TINGKAT KEPENTINGAN DAN KINERJA PADA KANTOR PELAYANAN PAJAK KOTA BOGOR

2018 ◽  
Vol 2 (01) ◽  
pp. 14
Author(s):  
Eddy Supardi
Keyword(s):  
Performance Analysis ◽  
Service Quality ◽  
Descriptive Analysis ◽  
Good Work ◽  
Satisfaction Level ◽  
Quality Service ◽  
Analysis Method ◽  
And Performance ◽  
Personal Tax

The Tax Payer obidience in fulfiling their taxation obligation will be influenced a lot by the satisfaction level toward the service fiscus. The aim of this observation is to know the response of Tax Payer toward service quality through importance and performance. The population which become the object of this observation is the personal Tax Payer registered in Bogor Tax Service Office and the number of respondents taken as the sample are 100 respondents with Slovin formula. The analysis method used is descriptive analysis and importance-performance analysis.   The result of this observation will be able to be used as one of the input to Bogor Tax Service Office in improving the quality service and for the following observation, especially those who take the same object as the observation in order to improve the quality service to the Tax Payer based on the service of its working way which is felt less. Otherwise it is important for The Tax Payer, maintaining the good work or balancing the service quality based on the working way which is evaluated less important by The Taxe Payer, but has been done reasonably well or very well by The Service Office

KINERJA PROSES PELELANGAN IKAN DI PASAR ARUMBAI KOTA AMBON

2017 ◽  
Vol 1 (2) ◽  
pp. 58-66
Author(s):  
Frendly Matulessy ◽  
Dionisius Bawole
Keyword(s):  
Performance Analysis ◽  
Gap Analysis ◽  
Primary Data ◽  
Satisfaction Level ◽  
Questionnaire Data ◽  
Analysis Method ◽  
Value For Money ◽  
Qualitative Descriptive ◽  
Market Needs ◽  
Descriptive Method

This study aims to measure the performance of fish auction process in Arumbai Market in Ambon. Primary data were collected from 43 respondents through observation and direct interview based on questionnaire. Data was analysed by qualitative descriptive method, importance performance analysis method (IPA) and gap analysis, and value for money method. The results show that: 1). There are three auction process activities namely pre auction, auction, and post auction; 2). Fisherman's satisfaction level is 67% and merchant satisfaction is 81%; and 3). The auction performance of the economic aspect is less economical, with the final value of 83%, while the fish auction performance from the efficiency aspect is less efficient with the value of 76%. For that, it needs additional officers to manage fish auction place (TPI) in Arumbai Market. In addition, the fish auction facilities (TPI) in Arumbai Market needs to be improved.

scholarly journals Axial Compressor Mean-Line Analysis: Choking Modelling and Fully-Coupled Integration in Engine Performance Simulations

2021 ◽  
Vol 6 (1) ◽  
pp. 4
Author(s):  
Ioannis Kolias ◽  
Alexios Alexiou ◽  
Nikolaos Aretakis ◽  
Konstantinos Mathioudakis
Keyword(s):  
Axial Compressor ◽  
Engine Performance ◽  
Engine Model ◽  
Multi Stage ◽  
Transient Simulations ◽  
Full Knowledge ◽  
Compressor Performance ◽  
First Time ◽  
Performance Calculation ◽  
Fully Coupled

A mean-line compressor performance calculation method is presented that covers the entire operating range, including the choked region of the map. It can be directly integrated into overall engine performance models, as it is developed in the same simulation environment. The code materializing the model can inherit the same interfaces, fluid models, and solvers, as the engine cycle model, allowing consistent, transparent, and robust simulations. In order to deal with convergence problems when the compressor operates close to or within the choked operation region, an approach to model choking conditions at blade row and overall compressor level is proposed. The choked portion of the compressor characteristics map is thus numerically established, allowing full knowledge and handling of inter-stage flow conditions. Such choking modelling capabilities are illustrated, for the first time in the open literature, for the case of multi-stage compressors. Integration capabilities of the 1D code within an overall engine model are demonstrated through steady state and transient simulations of a contemporary turbofan layout. Advantages offered by this approach are discussed, while comparison of using alternative approaches for representing compressor performance in overall engine models is discussed.

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