Abstract
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.
Highlights
Gas turbines are used successfully to power aircraft as well as to generate power in industrial applications
A two-shaft aeroderivate gas turbine is conformed by a gas generator and a free power turbine known as low pressure turbine (LPT), as depicted in the schematic diagram of Figure 1a
A simple methodology has been presented in this paper to estimate the values of the pressure ratio and the high pressure turbine inlet temperature for the operation of an aeroderivate gas turbine
Summary
Gas turbines are used successfully to power aircraft as well as to generate power in industrial applications. There exist aero-derivate gas turbines of low and medium power, and their maximum capacity of generation is of 65 MW, depending on their compressor pressure ratio, high pressure turbine inlet temperature and of their shaft number [1,2]. A two-shaft aero-derivate gas turbine is composed by a gas generator and a free power turbine known as a low pressure turbine. The gas generator turbine provides power for the air compressor and the free power turbine generates the useful power output. Improvements in the design and operation of gas turbines have come along with advances in aerodynamics, thermodynamics and metallurgy has made possible for today’s gas turbines to withstand temperatures in the 1415 °C range, compressor pressure ratios up to 34:1 and overall thermal efficiency up to 42% [4,5]
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