Computational Study on Fully Coupled Combustor–Turbine Interactions

Miki, Kenji; Wey, Thomas; Moder, Jeffrey P.

doi:10.2514/1.b38501

Cited by 2 publications

(2 citation statements)

References 23 publications

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“…They observed that whilst the vane potential effect is weak, the clocking significantly affects the van temperature and flow conditions. Miki et al [13] compared the sequential single-component simulation method against the fully coupled simulation method for a combustor-turbine system. Although the mean combustor flowfields were similar between the two methods, there was a significant difference in the hot-streak distributions.…”

Section: Introductionmentioning

confidence: 99%

Fully Coupled Whole-Annulus Investigation of Combustor–Turbine Interaction with Reacting Flow

Wang,

Luo

2024

Energies

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Micro-gas turbines are used for power generation and propulsion in unmanned aerial vehicles. Technological advancements to enhance their efficiency and fuel adaptability are continuously sought out. As part of a comprehensive study focused on understanding the fundamental performance and emission characteristics of a micro gas turbine model, with the aim of finding ways to enhance the operation of micro gas turbines, the current study uses a fully coupled whole-annulus simulation approach to systematically explore the combustor–turbine interaction without compromising the accuracy due to domain truncation. The numerical model is highly complex, spanning aerothermodynamics, fuel vaporization, combustion, and multi-species flow transport. Coupled with the realistic geometries of a representative micro-gas turbine, the proposed numerical model is highly accurate with the capability to capture the complex interaction between the flowfield and the aerothermodynamics and emission performances. The results show that unburnt gaseous Jet-A fuel is carried into the turbine domain through vortical flow structures originating from the combustion chamber. Notably, combustion processes persist within the turbine, leading to rapid Jet-A fuel concentration decay and linearly increasing soot concentration across the turbine domain. The relative circumferential positioning of the combustion chamber and turbine vane (i.e., clocking effects) profoundly influences micro-gas turbine aerothermodynamics and pollutant emissions. Leading-edge impingement hot-streak configurations enhance aerodynamic efficiency, while mid-passage hot-streak configurations mitigate aerothermal heat load and soot emissions. Clocking effects impact all parameters, indicating a complex interplay between the flowfield, aerothermal performance, and pollutant emissions. However, turbine vane heat load exhibits the most significant variations.

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Section: Introductionmentioning

confidence: 99%

Fully Coupled Whole-Annulus Investigation of Combustor–Turbine Interaction with Reacting Flow

Wang,

Luo

2024

Energies

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“…Results from that analysis were discussed in Section 3.1. Miki et al [205] compared results obtained from the fully coupled and the decoupled simulations of the "Energy Efficient Engine" combustor [206] and turbine [207], and an integrated simulation using high-fidelity methods. Results obtained with the decoupled simulation were considered inaccurate, while fully coupled methods demonstrated their superior ability to capture flow physics, although only the integrated simulation individuated a low-pressure region downstream of the first-stage vane.…”

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confidence: 99%

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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Computational Study on Fully Coupled Combustor–Turbine Interactions

Cited by 2 publications

References 23 publications

Fully Coupled Whole-Annulus Investigation of Combustor–Turbine Interaction with Reacting Flow

Fully Coupled Whole-Annulus Investigation of Combustor–Turbine Interaction with Reacting Flow

Unsteady Flows and Component Interaction in Turbomachinery

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