Abstract
Inlet temperature is vital to the thermal efficiency of gas turbines, which is becoming increasingly important in the context of structural changes in power supplies with more intermittent renewable power sources. Blade cooling is a key method for gas turbines to maintain high inlet temperatures whilst also meeting material temperature limits. However, the implementation of blade cooling within a gas turbine—for instance, thermal barrier coatings (TBCs)—might also change its heat transfer characteristics and lead to challenges in calculating its internal temperature and thermal efficiency. Existing studies have mainly focused on the materials and mechanisms of TBCs and the impact of TBCs on turbine blades. However, these analyses are insufficient for measuring the overall impact of TBCs on turbines. In this study, the impact of TBC thickness on the performance of gas turbines is analyzed. An improved mathematical model for turbine flow passage is proposed, considering the impact of cooling with TBCs. This model has the function of analyzing the impact of TBCs on turbine geometry. By changing the TBCs’ thickness from 0.0005 m to 0.0013 m, its effects on turbine flow passage are quantitatively analyzed using the proposed model. The variation rules of the cooling air ratio, turbine inlet mass flow rate, and turbine flow passage structure within the range of 0.0005 m to 0.0013 m of TBC thicknesses are given.
Highlights
Introduction a Gas TurbineEnergies 2022, 15, 85.For high thermal efficiencies, modern gas turbines require significantly high turbine inlet temperatures, which have approached 1600 ◦ C in the latest H-class and J-class gas turbines used for power generation [1]
El-Masri carried out a second law analysis of gas turbine combined cycles [2] and a detailed thermodynamic analysis of cooling turbines in single cycles [3] and combined cycles [4], which laid the foundation for later researchers to develop more detailed thermodynamic models to analyze the performance of cooling turbines
24.221 (21)of cooling air and thermal barrier coatings (TBCs) based on the calculation of aerothermodynamics, which is closer to
Summary
Inturbines turbines with with cooling cooling technologies, technologies, the the cooling cooling air air is is fed fed into into the the turbine turbine stage-bystage-byIn stage. The application of TBCs enhances cooling effect, which reduces need the of cooling cooling air to maintain constant bladetemperature—but substrate temperature—but to what extent do air to maintain a constantablade substrate to what extent do TBCs affect. The length of the last stage blade, the length of the first stage blade, and turbine flow passage, respectively
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