Parametric Analysis of a Two-Shaft Aeroderivate Gas Turbine of 11.86 MW

Entropy

R. Lugo-Leyte²  M. Salazar-Pereyra¹  H. D. Lugo Méndez²  I. Aguilar-Adaya²  J. J. Ambriz-Garc໚²  J. G. Vázquez Vargas³ 

[1] Tecnológico de Estudios Superiores de Ecatepec, División de Ingeniería Mecatrónica e Industrial, Av. Tecnológico Esq. Av. Hank González, Col. Valle de Anáhuac, 55210, Ecatepec, Estado de México, Mexico;Universidad Autónoma Metropolitana-Iztapalapa, Departamento de Ingeniería de Procesos e Hidráulica, Av. San Rafael Atlixco No. 186, Col. Vicentina, 09340, Iztapalapa, Ciudad de México, D.F., Mexico; E-Mails:;MAVAZCAR S.A. de C.V. Suministros, Servicios e Ingeniería, Manzana 36 casa 4, tercera etapa, Col. Lázaro Cárdenas del Río, 86600, Paraíso, Tabasco, Mexico; E-Mail:

关键词: aeroderivate gas turbine;    exergetic efficiency;    exergy;    irreversibility;   

DOI  :  10.3390/e17085829

来源: mdpi

【 摘 要 】

The aeroderivate gas turbines are widely used for power generation in the oil and gas industry. In offshore marine platforms, the aeroderivative gas turbines provide the energy required to drive mechanically compressors, pumps and electric generators. Therefore, the study of the performance of aeroderivate gas turbines based on a parametric analysis is relevant to carry out a diagnostic of the engine, which can lead to operational as well as predictive and/or corrective maintenance actions. This work presents a methodology based on the exergetic analysis to estimate the irrevesibilities and exergetic efficiencies of the main components of a two-shaft aeroderivate gas turbine. The studied engine is the Solar Turbine Mars 100, which is rated to provide 11.86 MW. In this engine, the air is compressed in an axial compressor achieving a pressure ratio of 17.7 relative to ambient conditions and a high pressure turbine inlet temperature of 1220 °C. Even if the thermal efficiency associated to the pressure ratio of 17.7 is 1% lower than the maximum thermal efficiency, the irreversibilities related to this pressure ratio decrease approximately 1 GW with respect to irreversibilities of the optimal pressure ratio for the thermal efficiency. In addition, this paper contributes to develop a mathematical model to estimate the high turbine inlet temperature as well as the pressure ratio of the low and high pressure turbines.

【 授权许可】

CC BY   
© 2015 by the authors; licensee MDPI, Basel, Switzerland.