Evaluation of Aircraft Engine Diagnostic Methods Through ProDiMES

Koskoletos, Orestis A.; Aretakis, N.; Alexiou, A.; Romesis, C.; Mathioudakis, K.

doi:10.1115/gt2018-76647

Cited by 6 publications

(8 citation statements)

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“…The proposed AGCM is considered a zero-dimensional SS model, where no spatial and time-dependent variations in the thermodynamic properties of interest are considered; therefore, average thermodynamic properties at each station in Figure 1 are used. Aerothermodynamic zero-dimensional models show great capabilities and are widely used to address various GTEs problems: aircraft/engine optimization [23], specific engine matching [24], emissions assessment [25], engine diagnostics [26,27], etc.…”

Section: Model Descriptionmentioning

confidence: 99%

Improved Local Scale Generic Cycle Model for Aerothermodynamic Simulations of Gas Turbine Engines for Propulsion

Arrieta

Botez

2022

Designs

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A local scale Aerothermodynamic Generic Cycle Model (AGCM) is proposed. The AGCM accounts for several improvements not considered in similar models, such as compressor bleed extraction for aircraft Environmental Control System (ECS), parasitic shaft power extraction, and the enthalpy of the fuel entering the combustor. The AGCM is intended for steady-state Design Point (DP) and Off-Design (OD) performance analyses. The underlying physics is presented for the DP model. The turbomachinery component maps scaling and the system of nonlinear equations necessary to define the OD model are thoroughly discussed. The AGCM is compared with an equivalent model developed in the Numerical Propulsion System Simulation (NPSS). The comparisons were performed considering a DP envisioned to approximate a General Electric CF34-8C5B1 engine. The average errors found in these comparisons for the Specific Fuel Consumption (SFC) and net thrust were −0.111% and 0.193%, respectively. Finally, the predictions of the absolute levels of performance intended for the -8C5B1 engine are compared with empirical correlations derived from a comprehensive turbofan engine database. It was found that the predictions of the AGCM are in agreement with the empirical correlations; the errors found in SFC and net thrust at cruise flight condition were −0.43% and 2.06%, respectively.

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Section: Model Descriptionmentioning

confidence: 99%

Improved Local Scale Generic Cycle Model for Aerothermodynamic Simulations of Gas Turbine Engines for Propulsion

Arrieta

Botez

2022

Designs

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“…Ideally, the chosen method will help reduce the cost of operation and maintenance, and these savings are greater than the cost of monitoring, which generates profit. Expert sources are dominated by GPA methods developed for stationary gas turbines that have a relatively stable operating point (Yepifanov and Loboda, 2003; Putz, 2017; Koskoletos, 2018; Fentaye, 2019; Listou Ellefsen et al , 2019; Pérez-Ruiz, 2021). In our case, the operating point is strongly influenced by the flight parameters, and in addition, a limited number of operating parameters are available.…”

Section: Problem Descriptionmentioning

confidence: 99%

Engine condition monitoring on small single engine turboprop

Šplíchal

Červenka

Juračka

2023

AEAT

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Purpose This study aims to focus on verifying the possibility of monitoring the condition of a turboprop engine using data recorded by on-board avionics Garmin G1000. This approach has potential benefits for operators without the need to invest in specialised equipment. The main focus was on the inter-turbine temperature (ITT). An unexpected increase in temperature above the usual value may indicate an issue with the engine. The problem lies in the detection of small deviations when the absolute value of the ITT is affected by several external variables. Design/methodology/approach The ITT is monitored by engine sensors and stored by avionics 1× per second onto an SD card. This process generates large amount of data that needs to be processed. Therefore, an algorithm was created to detect the steady states of the engine parameters. The ITT value also depends on the flight parameters and surrounding environment. As a solution to these effects, the division of data into clusters that represent the usual flight profiles was tested. This ensures a comparison at comparable ambient pressures. The dominant environmental influence then remain at the ambient air temperature (OAT). Three OAT compensation methods were tested in this study. Compensation for the standard atmosphere, compensation for the standard temperature of the given flight level and compensation for the speed of the generator, where the regression analysis proved the dependence between the ambient temperature and the speed of the generator. Findings The influence of ambient temperature on the corrected ITT values is noticeable. The best method for correcting the OAT appears to be the use of compensation through the revolutions of the compressor turbine NG. The speed of the generator depends on several parameters, and can refine the corrected ITT value. During the long-term follow-up, the ITT differences (delta values) were within the expected range. The tested data did not include the behaviour of the engine with a malfunction or other damage that would clearly verify this approach. Therefore, the engine monitoring will continue. Practical implications This study presents a possible approach to turbine engine condition monitoring using limited on board avionic data. These findings can support the development of an engine condition monitoring system with automatic abnormality detection and low operating costs. Originality/value This article represent a practical description of problems in monitoring the condition of a turboprop engine in an aircraft with variable flight profiles. The authors are not aware of a similar method that uses monitoring of engine parameters at defined flight levels. Described findings should limit the influence of ambient air pressure on engine parameters.

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“…In another work, Kang [33] suggested a compressor map adaptation technique to enhance the accuracy of performance based diagnostics of a heavy-duty gas turbine. Comparison of different diagnostics approaches are studied in Koskoletos et al [34]. The authors performed a comparative analysis among: (1) probabilistic neural network (PNN); (2) k-nearest neighbours; (3) optimization; (4) combinatorial; (5) adaptive 2X2; and (6) combination of PNN and adaptive 2X2 method.…”

Section: Review On Performance Based Gas Path Diagnosticsmentioning

confidence: 99%

Diagnostics-Oriented Modelling of Micro Gas Turbines for Fleet Monitoring and Maintenance Optimization

Rahman

Zaccaria²,

Zhao³

et al. 2018

Processes

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The market for the small-scale micro gas turbine is expected to grow rapidly in the coming years. Especially, utilization of commercial off-the-shelf components is rapidly reducing the cost of ownership and maintenance, which is paving the way for vast adoption of such units. However, to meet the high-reliability requirements of power generators, there is an acute need of a real-time monitoring system that will be able to detect faults and performance degradation, and thus allow preventive maintenance of these units to decrease downtime. In this paper, a micro gas turbine based combined heat and power system is modelled and used for development of physics-based diagnostic approaches. Different diagnostic schemes for performance monitoring of micro gas turbines are investigated.

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Evaluation of Aircraft Engine Diagnostic Methods Through ProDiMES

Cited by 6 publications

References 0 publications

Improved Local Scale Generic Cycle Model for Aerothermodynamic Simulations of Gas Turbine Engines for Propulsion

Improved Local Scale Generic Cycle Model for Aerothermodynamic Simulations of Gas Turbine Engines for Propulsion

Engine condition monitoring on small single engine turboprop

Diagnostics-Oriented Modelling of Micro Gas Turbines for Fleet Monitoring and Maintenance Optimization

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