Thermal performance analysis of gas turbine engines based on different compressor configurations

被引：1

作者：

Almutairi, Abdulrahman ^{[1
]}

Zedan, Mohamed ^{[1
]}

Alhajeri, Hamad M. ^{[1
]}

Alenezi, Abdulrahman ^{[1
]}

机构：

[1] Shuwaikh Educ, Coll Technol Studies Mech Power & Refrigerat Engn, POB 23167, Safat 13092, Kuwait

来源：

HEAT TRANSFER | 2020年 / 49卷 / 05期

关键词：

compressor; gas turbine; irreversibilities; power setting; reliability; POWER-PLANT; PARAMETRIC ANALYSIS; EXERGY ANALYSIS;

D O I：

10.1002/htj.21742

中图分类号：

O414.1 [热力学];

学科分类号：

摘要：

In this study, the performance of several gas turbine engines has been investigated using computational modelling based on the actual manufacturer's data. Further, the study focuses on evaluating the impact of varying the configuration of the compressor on overall engine performance based on the first and second laws of thermodynamics. The results confirm that the main source of irreversibilities occurs in the combustion chamber in all cases. The exergetic efficiency of the gas turbine engine significantly varies with compressor configurations, type of compressors, load variation, climatic condition, and isentropic efficiency. The engine capacity and high-pressure turbine inlet temperature govern the gas turbine performance, and higher values are more favourable. The gas turbine exergetic efficiency drops off when the power setting adjusted at part-load and at high ambient temperature. The most optimal gas turbine performance is located at the single axial compressor case, followed by the axial-centrifugal compressor and then the centrifugal-centrifugal compressor.

引用

页码：2717 / 2745

页数：29

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