Uncertainty quantification of an aeronautical combustor using a 1-D approach

Gamannossi, Andrea; Amerini, Alberto; Poggiali, Matteo; Elmi, Carlo Alberto; Mazzei, Lorenzo; Andreini, Antonio

doi:10.1063/1.5138816

Cited by 3 publications

(2 citation statements)

References 14 publications

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“…In this approach, the range of each input random variable is divided into intervals with equal probability. The methodology has been extensively used in a wide range of applications [17,18,19,20,21], including rotorcraft conceptual design [22] and uncertainty analysis with NASA rotorcraft sizing design tools [23]. Even with improved stratified sampling for uncertainty propagation, the MC approach with direct model evaluations is a computationally expensive process especially if high-fidelity simulations govern the solver.…”

Section: A Monte Carlo Approachmentioning

confidence: 99%

Uncertainty Quantification of the ONERA 7A Rotor Performance and Spanwise Structural Loads using a Surrogate-Based Approach

Khurana,

Yeo

2023

Preprint

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The study demonstrates the role of uncertainty quantification for rotorcraft aeromechanics using the ONERA 7A rotor. The uncertainties in blade properties including torsion, flap, and lag stiffness on rotorcraft performance and spanwise structural loads are quantified. To support this effort, a stochastic-based computational framework is developed using a surrogate of the rotorcraft comprehensive analysis code with artificial neural networks. Statistical analysis is undertaken to quantify system uncertainties with probabilities and a qualitative approach with parallel coordinate plots is used for a visual interpretation of the trends between uncertain inputs and response outputs. It is shown that the stochastic-based approach will aid intelligent data driven decisions to follow as a design window with quantifiable probabilities of failure due to high loads and/or excessive power requirements are identifiable.

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Section: A Monte Carlo Approachmentioning

confidence: 99%

Uncertainty Quantification of the ONERA 7A Rotor Performance and Spanwise Structural Loads using a Surrogate-Based Approach

Khurana,

Yeo

2023

Preprint

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“…Regarding the PC approach, only the optimum method is here reported: the graphs will show the MC in comparison with the Quadrature order (1 st order) and the total order (2 nd order) approximation only. Additional orders were previously studied [25] but the results proved how these methods are the most computational costeffective method with an optimum grade of accuracy for the results. The stochastic collocation has not been included since the results are the same as the QO method.…”

Section: Geometrical Analysismentioning

confidence: 99%

Application of Uncertainty Quantification Methods to the Prediction of Effusion Cooled Combustor Liner Temperature

Gamannossi¹,

Andreini²,

Poggiali³

et al. 2021

Preprint

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As far as the preliminary thermal design of gas turbine components is concerned, 1-D codes are still widely used in standard industrial practice. Among the different components, the combustor is one of the most critical ones and its thermal design still greatly affects the reliability and life of the entire engine. During the initial phases of the design process, parameters are often roughly known. For this preliminary phase, a low-order approach is preferred instead of a high-fidelity simulation: the exploration of the whole space is extremely important to better understand the behavior of the system and to focus on the design objectives. Uncertainty quantification (UQ) methods, mainly developed in recent years and applied in many fields, are useful tools for the preliminary design phase and provide support during the whole design process. The objective of this work is to estimate the main sources of uncertainties in the design phase of an aeroengine effusion cooled combustor. The test case is based on a full annular lean-burn combustor, tested during the LEMCOTEC (Low EMissions COre-engine TEChnologies) European project. Among the test points investigated in the experimental campaign, the Approach condition is here analyzed. The inner liner is taken into consideration to investigate the metal temperature. Therm-1D, a 1-D in-house simulation code, is used to model the combustor and the open-source tool DAKOTA is adopted for the uncertainty quantification analysis. The baseline case of the combustor is studied and several uncertainty analyses are investigated. They are divided into 3 main groups: geometrical, tuning modelling parameters and thermal loads. For each group, the most relevant parameters are considered as a source of input uncertainty. In particular, a classical Monte Carlo approach is compared with four innovative polynomial-chaos approaches for each group: Gauss quadrature, total order with LHS sampling, stochastic

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Uncertainty Quantification of the ONERA 7A Rotor Performance and Loads Using Comprehensive Analysis

Khurana

Din

Yeo

2023

Journal of Aircraft

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Quantification of blade stiffness uncertainties and sensitivities on rotor power and structural loads for the ONERA 7A rotor is established using the U.S. Army and ONERA rotorcraft comprehensive analysis tools. A stochastic-based approach is implemented to generate probabilistic bounds of the response outputs, including rotor performance and loads due to uncertainties in blade stiffness using 1) a Monte Carlo approach coupled directly with U.S. Army’s rotorcraft comprehensive toolset, and 2) a surrogate of ONERA’s rotorcraft comprehensive analysis solver using polynomial chaos expansions to efficiently predict the response outputs. The analysis showed that uncertainties in blade torsion, flap, and lag stiffnesses impact the predicted rotor power by a quantifiable amount. Significant uncertainties in peak torsion, flap, and chord bending moments are also confirmed. The sensitivities of the stiffness properties on response outputs using Sobol indices are also studied. The results show that total required power is exclusively sensitive to variability in torsion stiffness with no interaction effects with flap and lag stiffnesses. Sensitivities due to independent parameter effects and by combining with other parameters on peak structural loads are also examined. The analysis demonstrates the merits of integrating a stochastic, data-driven approach for uncertainty and sensitivity analyses in rotorcraft aeromechanics predictions.

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Uncertainty quantification of an aeronautical combustor using a 1-D approach

Cited by 3 publications

References 14 publications

Uncertainty Quantification of the ONERA 7A Rotor Performance and Spanwise Structural Loads using a Surrogate-Based Approach

Uncertainty Quantification of the ONERA 7A Rotor Performance and Spanwise Structural Loads using a Surrogate-Based Approach

Application of Uncertainty Quantification Methods to the Prediction of Effusion Cooled Combustor Liner Temperature

Uncertainty Quantification of the ONERA 7A Rotor Performance and Loads Using Comprehensive Analysis

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