Research of Aero-Engine Life Prediction Based on Take-Off EGTM

Life prediction is one important of area Engine research. Take-off EGTM is an important parameter to monitor Engine performance. Take-off EGTM have great influence on Engine life, Reducing EGT will help to extend Engine life on wing (LOW), thereby reducing operating costs. Aiming at aero-Engine condition monitoring, the definition of take-off EGT Margin is given, estimation methods and their application on Engine life prediction are discussed.

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Research of Engine Performance Control Based on EGTM

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.148-149.431 ◽

2011 ◽

Vol 148-149 ◽

pp. 431-436

Author(s):

Hong Bo Peng ◽

Min Dan

Keyword(s):

Condition Monitoring ◽

Life Prediction ◽

Great Influence ◽

Engine Performance ◽

Operating Costs ◽

Estimation Methods ◽

Performance Control ◽

Definition Of ◽

Engine Condition ◽

Engine Life

Life prediction is one important of Engine research. Take-off EGTM is an important parameter to monitor Engine performance. Take-off EGTM have great influence on Engine life, Reducing EGT will help to extend Engine life on wing (LOW), thereby reducing operating costs. Aiming at Engine condition monitoring, the definition of take-off EGT Margin is given, estimation methods and their application on Engine life prediction are discussed.

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Aero-Engine Condition Monitoring Based on Kalman Filter Theory

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.490-495.176 ◽

2012 ◽

Vol 490-495 ◽

pp. 176-181 ◽

Cited By ~ 1

Author(s):

You Gao ◽

Nan Wang

Keyword(s):

Kalman Filter ◽

Condition Monitoring ◽

Prediction Models ◽

Engine Performance ◽

Ar Model ◽

Performance Parameters ◽

Filter Theory ◽

Aero Engine ◽

Filter Approach ◽

Engine Condition

The maintenance and management of civil aero-engine require advanced monitor schemes to evaluate aero-engine health and condition in order to ensure safety of aircraft and increase life of aero-engine. In this paper, we adopted Kalman filter approach to monitor an aero-engine health and condition by building prediction models of main aero-engine performance parameters (EGT, N1, N2 and WF). The AR model is introduced into the Kalman filter equations, which is a helpful technique to improve the accuracy of monitoring models of performance parameters. When the relative error goes beyond ±0.3%, alarms will be given. The prediction results show that Kalman filter theory using for AR regression prognostic is an effective approach in aero-engine monitoring.

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Integration of 3D-CFD Component Simulation Into Overall Engine Performance Analysis for Engine Condition Monitoring Purposes

Volume 1: Aircraft Engine; Fans and Blowers; Marine ◽

10.1115/gt2018-75719 ◽

2018 ◽

Cited By ~ 2

Author(s):

C. Klein ◽

F. Wolters ◽

S. Reitenbach ◽

D. Schönweitz

Keyword(s):

Performance Analysis ◽

Condition Monitoring ◽

Guide Vane ◽

Engine Performance ◽

Operating Conditions ◽

Tip Clearance ◽

Inlet Guide Vane ◽

Cfd Model ◽

The Impact ◽

Engine Condition

For an efficient detection of single or multiple component damages, the knowledge of their impact on the overall engine performance is crucial. This knowledge can be either built up on measurement data, which is hardly available to non-manufacturers or –maintenance companies, or simulative approaches such as high fidelity component simulation combined with an overall cycle analysis. Due to a high degree of complexity and computational effort, overall system simulations of jet engines are typically performed as 0-dimensional thermodynamic performance analysis, based on scaled generic component maps. The approach of multi-fidelity simulation, allows the replacement of single components within the thermodynamic cycle model by higher-order simulations. Hence, the component behavior becomes directly linked to the actual hardware state of the component model. Hereby the assessment of component deteriorations in an overall system context is enabled and the resulting impact on the overall system can be quantified. The purpose of this study is to demonstrate the capabilities of multi fidelity simulation in the context of engine condition monitoring. For this purpose, a 0D-performance model of the IAE-V2527 engine is combined with a CFD model of the appropriate fan component. The CFD model comprises the rotor as well as the outlet guide vane of the bypass and the inlet guide vane of the core section. As an exemplarily component deterioration, the fan blade tip clearance is increased in multiple steps and the impact on the overall engine performance is assessed for typical engine operating conditions. The harmonization between both simulation levels is achieved by means of an improved map scaling approach using an optimization strategy leading to practicable simulation times.

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Design and Application of a Multidisciplinary Predesign Process for Novel Engine Concepts

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.4040750 ◽

2018 ◽

Vol 141 (1) ◽

Cited By ~ 7

Author(s):

Stanislaus Reitenbach ◽

Alexander Krumme ◽

Thomas Behrendt ◽

Markus Schnös ◽

Thomas Schmidt ◽

...

Keyword(s):

Data Model ◽

Structural Design ◽

Engine Performance ◽

Turbofan Engine ◽

Engine Model ◽

Modeling Techniques ◽

Aero Engine ◽

Open Rotor ◽

Definition Of ◽

Engine Components

The purpose of this paper is to present a multidisciplinary predesign process and its application to three aero-engine models. First, a twin spool mixed flow turbofan engine model is created for validation purposes. The second and third engine models investigated comprise future engine concepts: a counter rotating open rotor (CROR) and an ultrahigh bypass turbofan. The turbofan used for validation is based on publicly available reference data from manufacturing and emission certification. At first, the identified interfaces and constraints of the entire predesign process are presented. An important factor of complexity in this highly iterative procedure is the intricate data flow, as well as the extensive amount of data transferred between all involved disciplines and among different fidelity levels applied within the design phases. To cope with the inherent complexity, data modeling techniques have been applied to explicitly determine required data structures of those complex systems. The resulting data model characterizing the components of a gas turbine and their relationships in the design process is presented in detail. Based on the data model, the entire engine predesign process is presented. Starting with the definition of a flight mission scenario and resulting top level engine requirements, thermodynamic engine performance models are developed. By means of these thermodynamic models, a detailed engine component predesign is conducted. The aerodynamic and structural design of the engine components are executed using a stepwise increase in level of detail and are continuously evaluated in context of the overall engine system.

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