Sensitivity Analysis of an Aircraft Engine Model Under Consideration of Dependent Variables

Salomon, Julian; Göing, Jan; Lück, Sebastian; Broggi, Matteo; Friedrichs, Jens; Beer, Michael

doi:10.1115/gt2021-58905

Cited by 4 publications

(4 citation statements)

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“…The simulation of the engine steady-state performance is carried out using a performance synthetic calculation algorithm which was developed by Goeing et al (2020) and Salomon et al (2021). The steady-state operating points are computed based on the engine matching technique.…”

Section: Methodology Engine Performance and Boundary Conditionsmentioning

confidence: 99%

Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine

Ignatidis¹,

Nghiem²,

Goeing³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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Malfunctions in the combustion chamber of aircraft engines influence downstream turbines. If individual burners vary in their performance, cold or hot streaks can enter and propagate through the turbine section and alter the temperature distribution in the exhaust of the engine. Analysing the variances in the temperature distribution of the exhaust jet provides information on the failure modes of the combustor. This can be used to identify damage to the aircraft engine, accelerate the inspection process and reduce maintenance cost. To investigate the influence of combustor failure on the temperature distribution, CFD simulations of a defined defect are carried out in this paper for a real size gasturbine engine. For this purpose, the total failure of one fuel nozzle in the combustion chamber, which results in a cold gas streak entering the turbine, is simulated. The cold streak is analysed by performing a turbine simulation for which the combustor exit profile is used on as an inlet condition. The simulations were performed using two different techniques. A frozen-rotor approach was used for the steady-state method to estimate the geometric influence on the mixing. The influence of the blade rotation is considered via unsteady simulation. The disturbance width and propagation were determined for both methods. The mixing and dispersion processes are found to be strong in the high pressure part of the turbine and are strongly influenced by the engine rotational speed.

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Section: Methodology Engine Performance and Boundary Conditionsmentioning

confidence: 99%

Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine

Ignatidis¹,

Nghiem²,

Goeing³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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“…In conjunction with the CFD simulations of the HPT, the NLGPA and, thus, the virtual process allow a combination of the overall aircraft engine performance with the local effect of deterioration. This analysis is presented by the schematic flow chart illustrated in Figure 6 and is implemented in Matlab (Kurzke and Halliwell, 2018;Salomon et al, 2021).…”

Section: Performance Simulation Of the Overall Aircraft Enginementioning

confidence: 99%

Virtual process for evaluating the influence of real combined module variations on the overall performance of an aircraft engine

Goeing

Seehausen

Stania

et al. 2023

J. Glob. Power Propuls. Soc.

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The effects of real combined variances in components and modules of aero engines, due to production tolerances or deterioration, on the performance of an aircraft engine are analysed in a knowledge-based process. For this purpose, an aero-thermodynamic virtual evaluation process that combines physical and probabilistic models to determine the sensitivities in the local module aerodynamics and the global overall performance is developed. Therefore, an automatic process that digitises, parameterises, reconstructs and analyses the geometry automatically using the example of a real turbofan high-pressure turbine blade is developed. The influence on the local aerodynamics of the reconstructed blade is investigated via a computational fluid dynamics (CFD) simulations. The results of the high-pressure turbine (HPT) CFD as well as of a Gas-Path-Analysis for further modules, such as the compressors and the low-pressure turbine, are transferred into a simulation of the performance of the whole aircraft engine to evaluate the overall performance. All results are used to train, validate and test several deep learning architectures. These metamodels are utilised for a global sensitivity analysis that is able to evaluate the sensitivities and interactions. On the one hand, the results show that the aerodynamics (especially the efficiency <inline-formula><mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" display="inline" overflow="scroll"><mml:msub><mml:mi>η</mml:mi><mml:mrow><mml:mi>H</mml:mi><mml:mi>P</mml:mi><mml:mi>T</mml:mi></mml:mrow></mml:msub></mml:math></inline-formula> and capacity <inline-formula><mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" display="inline" overflow="scroll"><mml:msub><mml:mrow><mml:mover><mml:mi>m</mml:mi><mml:mo>˙</mml:mo></mml:mover></mml:mrow><mml:mrow><mml:mi>H</mml:mi><mml:mi>P</mml:mi><mml:mi>T</mml:mi></mml:mrow></mml:msub></mml:math></inline-formula>) are particularly driven by the variation of the stagger angle. On the other hand, <inline-formula><mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" display="inline" overflow="scroll"><mml:msub><mml:mi>η</mml:mi><mml:mrow><mml:mi>H</mml:mi><mml:mi>P</mml:mi><mml:mi>T</mml:mi></mml:mrow></mml:msub></mml:math></inline-formula> is significantly related to exhaust gas temperature (Tt5), while specific fuel consumption (SFC) and mass flow <inline-formula><mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" display="inline" overflow="scroll"><mml:msub><mml:mrow><mml:mover><mml:mi>m</mml:mi><mml:mo>˙</mml:mo></mml:mover></mml:mrow><mml:mrow><mml:mi>H</mml:mi><mml:mi>P</mml:mi><mml:mi>T</mml:mi></mml:mrow></mml:msub></mml:math></inline-formula> are related to HPC exit temperature (Tt3). However, it can be seen that the high-pressure compressor has the most significant impact on the overall performance. This novel knowledge-based approach can accurately determine the impact of component variances on overall performance and complement experience-based approaches.

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“…The next step is to check whether this correct cycle also achieves the required thrust. If this does not happen, the rotational speed n 2 is varied using the Newton-Raphson method [23,36]. If both criteria are satisfied, the required cycle is achieved.…”

Section: Jet Engine Performance Simulationmentioning

confidence: 99%

Environmental Noise Assessment of Holding Approach Procedures Using a Multi-Level Simulation Framework

et al. 2022

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Computational models of sufficient quality are indispensable to quantitatively assess aircraft noise reduction measures. Within this study, a multi-level simulation framework is established in order to predict the environmental noise of holding approach procedures by coupling simulation models from three different domains: flight performance calculation employing the base of aircraft data (BADA), jet engine performance using the software Gasturb and aircraft noise simulations based on the software sonAIR. Two different concepts of holding approach procedures are investigated, namely, the vertical holding stack and the linear hold point merge. The study is conducted considering generic air traffic scenarios at a single-runway airport. Thereby, the investigated air traffic is based on a statistical analysis of traffic data at existing airports and thus assumed to be representative. As the aircraft’s noise emission depends on both the aircraft and the engine performance, reliable results can be expected only if all individual challenges and interdependencies are accounted for simultaneously. Addressing this challenge is the main contribution of the presented work. The presented results show the plausibility of the proposed multi-level simulation framework, thus supporting its use to investigate the environmental noise impact of air traffic scenarios.

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Sensitivity Analysis of an Aircraft Engine Model Under Consideration of Dependent Variables

Cited by 4 publications

References 0 publications

Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine

Mixing Behaviour and Propagation of Combustion Chamber Defects in an Aircraft Engine

Virtual process for evaluating the influence of real combined module variations on the overall performance of an aircraft engine

Environmental Noise Assessment of Holding Approach Procedures Using a Multi-Level Simulation Framework

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