Definition of cycle based comprehensive efficiency of a cooled turbine

Ba, Wei; Wang, Xiaochen; Li, Xuesong; Ren, Xiaodong; Gu, Chen

doi:10.1016/j.energy.2018.11.137

Cited by 2 publications

(4 citation statements)

References 7 publications

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“…High-pressure cooling air is always extracted from the compressor, and the coolant fraction significantly influences the cycle performance. Therefore, the cyclebased comprehensive efficiency [15] is developed, which considers both the turbine aerodynamic performance and coolant requirement to evaluate the cooled-turbine comprehensive performance.…”

Section: Comprehensive Eflciencymentioning

confidence: 99%

“…where compressor inlet total enthalpy h t1 is included to consider the work added to the coolant to obtain high pressure. More details about the comprehensive efficiency of the cooled turbine can be found in the original paper [15], and the comprehensive efficiency is selected as the optimized objective in this study to evaluate turbines with different stator designs.…”

Section: Comprehensive Eflciencymentioning

confidence: 99%

“…Therefore, both aerodynamic efficiency and coolant-requirement fraction are important criteria for evaluating the cooledturbine comprehensive performance, which influence the gas-turbine cycle performance, and should be carefully considered during the turbine design. The cycle-based comprehensive efficiency of a cooled turbine [15] was developed as a method for evaluating the optimization design of cooled turbines, which considered the influence of changes in turbine aerodynamic performance and coolant fraction on the cycle efficiency. Therefore, maximum cooled-turbine comprehensive efficiency was considered as the optimized objective in the current research to improve the cycle performance [16,17], and the optimized designs were compared to demonstrate the importance of considering coolant-requirement change during turbine design.…”

Section: Introductionmentioning

confidence: 99%

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Three-dimensional optimal design of a cooled turbine considering the coolant-requirement change

Wang

et al. 2019

Open Physics

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Cooling technology is widely applied in modern turbines to protect the turbine blades, and extracting high-pressure cooling air from a compressor exerts a remarkable influence on the gas-turbine performance. However, the three-dimensional optimal design of a turbine in modern industrial practice is usually carried out by pursuing high component efficiency without considering possible changes in coolant requirement; hence, it may not exactly lead to improvement in the gas-turbine cycle efficiency. In this study, the turbine stator was twisted and leaned to achieve higher comprehensive efficiency, which is the cycle-based efficiency definition for a cooled turbine that considers both turbine aerodynamic performance and coolant requirement. First, the influence of twist and compound lean on turbine aerodynamic performance, considering stator-hub leakage, was investigated. Then, a method to predict the coolant requirement for turbines with different stator designs was applied, to evaluate coolant-requirement change at the design condition. The optimized turbines were finally compared to demonstrate the necessity of considering the coolant-requirement change in the optimal design. This indicated that proper twisting to open the throat area in the stator hub and compound lean to the pressure surface side could help improve the cooled-turbine comprehensive efficiency.

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Section: Comprehensive Eflciencymentioning

confidence: 99%

Section: Comprehensive Eflciencymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Three-dimensional optimal design of a cooled turbine considering the coolant-requirement change

Wang

et al. 2019

Open Physics

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“…Cooling of turbine have high influence on efficiency of engine, comparable to turbine aerodynamic performance [3][4][5][6][7][8][9] and should be taken into the account when optimizing the working process of gas turbine engine.…”

Section: Introductionmentioning

confidence: 99%

Estimation of cooling flow rate for conceptual design stage of a gas turbine engine

Filinov

Кузьмичев

Tkachenko

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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Development of a gas turbine engine starts with optimization of the working process parameters. Turbine inlet temperature is among the most influential parameters that largely determine performance of an engine. As typical turbine inlet temperatures substantially exceed the point where metal turbine blades maintain reasonable thermal strength, proper modeling of the turbine cooling system becomes crucial for optimization of the engine’s parameters. Currently available numerical models are based on empirical data and thus must be updated regularly. This paper reviews the published information on turbine cooling requirements, and provides an approximation curve that generalizes data on all types of blade/vane cooling and is suitable for computer-based optimization.

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Definition of cycle based comprehensive efficiency of a cooled turbine

Cited by 2 publications

References 7 publications

Three-dimensional optimal design of a cooled turbine considering the coolant-requirement change

Three-dimensional optimal design of a cooled turbine considering the coolant-requirement change

Estimation of cooling flow rate for conceptual design stage of a gas turbine engine

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