Clocking and Potential Effects in Combustor–Turbine Stator Interactions

Flaszyński, Paweł; Piotrowicz, Michal; Bacci, Tommaso

doi:10.3390/aerospace8100285

Cited by 4 publications

(2 citation statements)

References 19 publications

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“…As a result, the blade thermal load predictions were significantly affected, while the stage expansion was not affected. Flaszynski et al [12] used the Spalart-Allmaras and explicit algebraic Reynolds stress turbulence models for a combustor-turbine system with different clocking positions. They observed that whilst the vane potential effect is weak, the clocking significantly affects the van temperature and flow conditions.…”

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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“…Rokicki et al [4] proposed inductive sensor for measuring blade vibration in high pressure compressors and turbines and used a rotor rig and turbojet to validate it at elevated temperatures (200-1000 • C). Flaszynski et al [5] discussed turbine stator's potential effect on flow in a combustor and the clocking effect on temperature distribution in a nozzle guide vane (NGV). It was shown that the NGV potential effect on flow distribution at the combustor-turbine interface located at 42.5% of the axial chord is weak.…”

mentioning

confidence: 99%