The effect of effusion holes inclination angle on the adiabatic film cooling effectiveness in a three-sector gas turbine combustor rig with a realistic swirling flow

Andreini, Antonio; Becchi, Riccardo; Facchini, Bruno; Picchi, Alessio; Peschiulli, Antonio

doi:10.1016/j.ijthermalsci.2017.07.003

Cited by 43 publications

(9 citation statements)

References 39 publications

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“…Downstream the dilution, the average level of film effectiveness is enhanced by the film superposition and the jet traces are more elongated. Upstream the first row of holes the average effectiveness level presents values above zero: this behaviour can be attributed to the recirculation of effusion flow in the corner region as already underlined in the open literature [8].…”

Section: Adiabatic Film Cooling Effectiveness Resultssupporting

confidence: 55%

“…Thus imply a severe impact on the performance of the liner cooling system and attest the importance of investigations under realistic swirling conditions. This aspect was fully remarked by the thorough experimental analysis conducted by Wurm et al [4,5] and by Andreini et al [6,7,8]. Both research groups carried out several measurement campaigns on atmospheric enlarged-scale rigs, replicating three sectors of a combustion chamber in a planar arrangement.…”

Section: Introductionmentioning

confidence: 99%

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A New Test Facility for Investigating Thermal Behaviour of Effusion Cooling Test Plates for RQL Combustors

Picchi

Andreini

Becchi

et al. 2020

Volume 7A: Heat Transfer

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In aero engines the combustors are subjected to critical thermal conditions in terms of high temperatures and corrosive environment, which could affect the service life of the entire system. As well known, Thermal Barrier Coatings (TBC) and above all cooling systems represents the state-of-the-art in the nowadays protecting methods: the maximization of this beneficial effect is achieved by defining an optimal cooling arrangement and developing suitable manufacturing technologies for these systems. In modern aero-engine combustors, one of the most effective cooling scheme for liners is composed by an effusion perforation coupled with a slot system to start the film cooling. The cooling performances are deeply influenced by the mutual interactions between swirling and cooling flows. In addition, for typical Rich-Quench-Lean (RQL) combustor architectures, the injection of air provided to promoting the local break-down of the flame mixture fraction, deeply interacts with the swirled flow, generating recirculating structures capable of affecting the development of film cooling and making the design of cooling systems very challenging. A new test facility for testing effusion test plates for RQL combustors applications has been developed with the final aim of comparing different cooling strategies and at the same time to collect data for numerical model validation. The experimental set-up consists of a non-reactive planar sector rigs with 5 engine-scale swirlers fed with air up to 250 °C and 3 bar. The rig was equipped with outer/inner dilution ports, and a simple inner liner cooling scheme composed of effusion and a slot system: all these features, fed with air at ambient temperature, can be independently controlled in terms of mass flow. Using dedicated optical accesses, InfraRed (IR) camera tests were performed to retrieve overall effectiveness data imposing a temperature difference between swirling and cooling flows. To better understand those results, Pressure Sensitive Paint (PSP) technique was used to obtain reliable film effectiveness data decoupling the contribution of slot and effusion flows. The thermal characterization was supported by Particle Image Velocimetry (PIV) investigations on the median plane. Tests were performed at different pressure drops across swirler and varying the mass flows of slot and inner/outer liners. The analysis of the data highlighted the influences of the swirling flow on the overall thermal performance and the behaviour of the film cooling system.

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Section: Adiabatic Film Cooling Effectiveness Resultssupporting

confidence: 55%

Section: Introductionmentioning

confidence: 99%

A New Test Facility for Investigating Thermal Behaviour of Effusion Cooling Test Plates for RQL Combustors

Picchi

Andreini

Becchi

et al. 2020

Volume 7A: Heat Transfer

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show abstract

“…The classical criteria proposed by Sellers is here used [28], which assumes a perfect overlapping of consecutive film layers produced by effusion jets. As observed in previous investigations carried out by the same research group, the presence of a highly three-dimensional flow field produced by the swirling jet issued by the burner may greatly affect the flow field in the near-wall region, with local flow structures impinging on the film layer and therefore significantly limit the superposition process [29]. Specific sensitivity to the uncertainty related to the superposition criteria may point out this problem but this type of detailed analysis was out of the scope of the present work.…”

Section: Bc Analysismentioning

confidence: 74%

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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“…Additionally, it is characterized by lower weight and complexity compared to double-wall schemes, in addition to being less prone to dust clocking. This cooling technique has been widely investigated, both experimentally and numerically, on flat plate, standard mainstream conditions [ 5 , 6 , 7 , 8 ], as well as under the influence of swirling flows [ 9 , 10 , 11 , 12 , 13 , 14 , 15 ].…”

Section: Introductionmentioning

confidence: 99%

Prediction of Liner Metal Temperature of an Aeroengine Combustor with Multi-Physics Scale-Resolving CFD

Bertini

Mazzei

Andreini

2021

Entropy

Self Cite

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Computational Fluid Dynamics is a fundamental tool to simulate the flow field and the multi-physics nature of the phenomena involved in gas turbine combustors, supporting their design since the very preliminary phases. Standard steady state RANS turbulence models provide a reasonable prediction, despite some well-known limitations in reproducing the turbulent mixing in highly unsteady flows. Their affordable cost is ideal in the preliminary design steps, whereas, in the detailed phase of the design process, turbulence scale-resolving methods (such as LES or similar approaches) can be preferred to significantly improve the accuracy. Despite that, in dealing with multi-physics and multi-scale problems, as for Conjugate Heat Transfer (CHT) in presence of radiation, transient approaches are not always affordable and appropriate numerical treatments are necessary to properly account for the huge range of characteristics scales in space and time that occur when turbulence is resolved and heat conduction is simulated contextually. The present work describes an innovative methodology to perform CHT simulations accounting for multi-physics and multi-scale problems. Such methodology, named U-THERM3D, is applied for the metal temperature prediction of an annular aeroengine lean burn combustor. The theoretical formulations of the tool are described, together with its numerical implementation in the commercial CFD code ANSYS Fluent. The proposed approach is based on a time de-synchronization of the involved time dependent physics permitting to significantly speed up the calculation with respect to fully coupled strategy, preserving at the same time the effect of unsteady heat transfer on the final time averaged predicted metal temperature. The results of some preliminary assessment tests of its consistency and accuracy are reported before showing its exploitation on the real combustor. The results are compared against steady-state calculations and experimental data obtained by full annular tests at real scale conditions. The work confirms the importance of high-fidelity CFD approaches for the aerothermal prediction of liner metal temperature.

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The effect of effusion holes inclination angle on the adiabatic film cooling effectiveness in a three-sector gas turbine combustor rig with a realistic swirling flow

Cited by 43 publications

References 39 publications

A New Test Facility for Investigating Thermal Behaviour of Effusion Cooling Test Plates for RQL Combustors

A New Test Facility for Investigating Thermal Behaviour of Effusion Cooling Test Plates for RQL Combustors

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

Prediction of Liner Metal Temperature of an Aeroengine Combustor with Multi-Physics Scale-Resolving CFD

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