Design of a Non-Reactive Warm Rig With Real Lean-Premix Combustor Swirlers and Film-Cooled First Stage Nozzles

Cubeda, Simone; Bacci, Tommaso; Mazzei, Lorenzo; Salvadori, Simone; Facchini, Bruno; Fiorineschi, Lorenzo; Volpe, Yary

doi:10.1115/1.0002550v

Cited by 3 publications

(5 citation statements)

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“…The comparison can then be extended to the blade load curves at a certain span section of the airfoil, which, per the mid-span, is reported in FIGURE 7. The experimental curves indicate a significant measurement noise, due to the low sensitivity of the measurement technique to pressure measurements [24]. CFD results bring a satisfactory match with measurements, if focusing on the central vane passage, i.e.…”

Section: Boundary Conditionsmentioning

confidence: 83%

“…The nozzle guide vanes (NGV) cascade is composed by two vanes and three passages. The module was designed in the early stage of the project [24] via CFD as per a design of experiments approach. Through this, the sidewalls were built in order to replicate the target conditions of a periodic simulation on the central vane passage, also considering that there was not a 1:1 ratio between swirler and nozzle real components.…”

Section: Test Rig Design and Characteristicsmentioning

confidence: 99%

“…The operating conditions of the rig, used for stationary, probe traversing tests on Plane 40 and 41 are derived from the nominal ones [24], which were scaled from real engine conditions in order to conserve the Mach number. By contrast, it was not possible to simultaneously fulfill the Reynolds number similitude due to facility constraints, yet the rig achieves representative conditions for secondary flows and pressure loss mechanisms, although heat transfer rates are slightly reduced.…”

Section: Test Rig Design and Characteristicsmentioning

confidence: 99%

“…Lastly, the necessity for increasing the knowledge on combustor-turbine interaction and improving standard design practices for industrial applications has led to the design and installation of a new test rig representative of a heavy-duty configuration and hosting real components. The steps taken during the design of such rig were described by Cubeda et al [24], who made use of both steady and unsteady simulations.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Numerical Prediction of Heat Transfer Coefficient and Adiabatic Effectiveness on a Nozzle Guide Vane With Representative Combustor Outflow

Tomasello

Andreini

Bacci

et al. 2022

Volume 6A: Heat Transfer — Combustors; Film Cooling

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The employment of lean-premix combustors in modern gas turbines allows to reduce NOx emissions by controlling the flame temperature at the expense of highly unsteady and strongly non-uniform flow fields which are necessary to stabilize the flame. This highly complex swirled flow field characterized by evident temperature distortions alters the aerodynamics and heat transfer in the first high pressure turbine stator with potential detrimental consequences on engine life and efficiency. From a numerical point of view, the mutual combustor-turbine interaction has been studied by using standard turbulence modeling approaches, as commonly employed during the design phase, even if more advanced scale-resolving methods have been proven more reliable and benchmarked against various experimental findings. From the experimental perspective, film-cooling adiabatic effectiveness and heat transfer coefficient (HTC) measurements on the external surface of the nozzle guide vanes, in the presence of representative combustor outflow characteristics, are not common since the relevant temperature distortions that are present make such kind of measurements really challenging to perform. For this reason, very limited assessment of such approaches regarding this aspect is available in literature. In this study, an experimental test case with a combustor simulator and a nozzle cascade, where both adiabatic effectiveness and HTC measurements have been carried out, is investigated by carrying out a systematic computational study, through RANS calculations of the combustor-cascade integrated domain. The film cooling system performance has been predicted by meshing the whole vane internal cooling system, while the heat transfer coefficient is calculated using the conventional two-point method, normally adopted for heat transfer calculations in gas turbines. The comparison between numerical predictions and experimental results was exploited to assess the capability of traditional modeling approaches in the characterization of both adiabatic effectiveness and heat transfer coefficient. This evaluation represents an effective means to assess if conventional/industrial approaches can be reliably used, when representative and highly unsteady combustor outflows are considered, or advanced and more time-consuming methods shall be adopted.

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Section: Boundary Conditionsmentioning

confidence: 83%

Section: Test Rig Design and Characteristicsmentioning

confidence: 99%

Section: Test Rig Design and Characteristicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Prediction of Heat Transfer Coefficient and Adiabatic Effectiveness on a Nozzle Guide Vane With Representative Combustor Outflow

Tomasello

Andreini

Bacci

et al. 2022

Volume 6A: Heat Transfer — Combustors; Film Cooling

View full text Add to dashboard Cite

show abstract

“…To face these problems, a thorough CFD activity was carried out by Cubeda et al (2020), for the fluid-dynamic design. The resulting fluid domain geometry to be reproduced by the test rig is reported in Figure 1.…”

Section: Methodsmentioning

confidence: 99%

Non-reactive test rig for combustor-turbine interaction studies in industrial gas turbines

Fiorineschi

Bacci

Frillici

et al. 2021

JEDT

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Purpose This paper aims to present the design of a particular non-reactive test rig for combustion swirlers and first stage turbine nozzles. The test rig is required for important experimental activities aimed at the optimization of a specific class of gas turbines. Design/methodology/approach A multi-disciplinary team performed the design process by following a tailored design approach, which has been developed for the specific case. The design outcomes allowed to build a fully functional test rig to be introduced in a test cell and then to perform preliminary experiments about the fluid dynamic behaviour of the turbine elements. Findings The followed design approach allowed to efficiently perform the task, by supporting the information exchange among the different subjects involved in both the conceptual and the embodiment design of the test rig. Additionally, the performed experiments allowed to achieve a final configuration that makes the test rig a valuable test case for combustor-turbine interaction studies. Research limitations/implications The study described in this paper is focused on the design of a specific test rig, used for first validation tests. However, the achieved results (both in terms of design and test) constitutes the underpinning of the in-depth investigations to be performed in the next steps of the experimental campaign. Originality/value To the best of the authors’ knowledge, the present paper is the first one that comprehensively describes the design activity of an experimental test rig for turbine application, also providing indications about the specific methodological procedure used to manage the process.

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Unsteady Flows and Component Interaction in Turbomachinery

Salvadori,

Insinna,

Martelli

2024

IJTPP

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Unsteady component interaction represents a crucial topic in turbomachinery design and analysis. Combustor/turbine interaction is one of the most widely studied topics both using experimental and numerical methods due to the risk of failure of high-pressure turbine blades by unexpected deviation of hot flow trajectory and local heat transfer characteristics. Compressor/combustor interaction is also of interest since it has been demonstrated that, under certain conditions, a non-uniform flow field feeds the primary zone of the combustor where the high-pressure compressor blade passing frequency can be clearly individuated. At the integral scale, the relative motion between vanes and blades in compressor and turbine stages governs the aerothermal performance of the gas turbine, especially in the presence of shocks. At the inertial scale, high turbulence levels generated in the combustion chamber govern wall heat transfer in the high-pressure turbine stage, and wakes generated by low-pressure turbine vanes interact with separation bubbles at low-Reynolds conditions by suppressing them. The necessity to correctly analyze these phenomena obliges the scientific community, the industry, and public funding bodies to cooperate and continuously build new test rigs equipped with highly accurate instrumentation to account for real machine effects. In computational fluid dynamics, researchers developed fast and reliable methods to analyze unsteady blade-row interaction in the case of uneven blade count conditions as well as component interaction by using different closures for turbulence in each domain using high-performance computing. This research effort results in countless publications that contribute to unveiling the actual behavior of turbomachinery flow. However, the great number of publications also results in fragmented information that risks being useless in a practical situation. Therefore, it is useful to collect the most relevant outcomes and derive general conclusions that may help the design of next-gen turbomachines. In fact, the necessity to meet the emission limits defined by the Paris agreement in 2015 obliges the turbomachinery community to consider revolutionary cycles in which component interaction plays a crucial role. In the present paper, the authors try to summarize almost 40 years of experimental and numerical research in the component interaction field, aiming at both providing a comprehensive overview and defining the most relevant conclusions obtained in this demanding research field.

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Design of a Non-Reactive Warm Rig With Real Lean-Premix Combustor Swirlers and Film-Cooled First Stage Nozzles

Cited by 3 publications

References 0 publications

Numerical Prediction of Heat Transfer Coefficient and Adiabatic Effectiveness on a Nozzle Guide Vane With Representative Combustor Outflow

Numerical Prediction of Heat Transfer Coefficient and Adiabatic Effectiveness on a Nozzle Guide Vane With Representative Combustor Outflow

Non-reactive test rig for combustor-turbine interaction studies in industrial gas turbines

Unsteady Flows and Component Interaction in Turbomachinery

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