TED-AJ03-262 CYCLE ANALYSIS OF A MICRO GAS TURBINE WITH COMBUSTION PROCESS UNDER CONSTANT TOTAL TEMPERATURE

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概要

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• Since the adiabatic efficiencies of compressor and turbine of a micro gas turbine are not so high, one of the ways that improve the thermal efficiency is an increase of turbine inlet temperature (TI). However, in the conventional gas-turbine cycle, TIT which is restricted by endurance of material is attained just at the transient state from isobaric combustion to adiabatic expansion processes. Therefore, it is effective to utilize such a high temperature field throughout the process for converting thermal energy to mechanical work. From this point of view, if combustion is controlled just to compensate for the temperature drop in the expansion process, the resulting isothermal expansion process could increase the cycle efficiency under the allowable TIT. In order that the total temperature relating to the endurance of material is kept constant, the isothermal combustion should be executed in turbine rotor with energy conversion. In the present study, we analyzed the cycle which has the constant total-temperature expansion combustion process taking the relatively low adiabatic efficiencies of micro gas turbines into account. [figure] The cycle analysis that, under the condition that the adiabatic efficiencies are not high, the maximum temperature is relatively low and the regeneration of heat is conducted, the thermal efficiency is improved as a proportion of isothermal expansion combustion process increases. In other words, the isothermal expansion combustion throughout turbine is desirable. In case that the pressure ratio is three, the efficiency of the constant total temperature cycle has the gain of 5% over that of the conventional one. Furthermore, because the temperature at the exit of the constant total temperature turbine is identical with that at the turbine inlet and the heat of exhaust gas is regenerated, the part of isobaric combustion process is very small. Accordingly, the modified cycle in which an isobaric combustor is omitted and a slight temperature accent with combustion occurs in turbine is also proposed. This cycle has the high efficiency close to that of isothermal expansion combustion cycle, which is superior to the conventional micro gas turbine. [figure]

• 一般社団法人日本機械学会の論文

著者

• Echigo Ryozo

  Dept. Of Mechanical Engineering Shibaura Institute Of Technology

• Saito Motohiro

  Dept. Of Mechanical Engineering Kyoto University

• YOSHIDA Hideo

  Dept. of Mechanical Engineering, Kyoto University

• Yoshida Hideo

  Dept. Of Mechanical Engineering Kyoto University

関連論文

• TED-AJ03-262 CYCLE ANALYSIS OF A MICRO GAS TURBINE WITH COMBUSTION PROCESS UNDER CONSTANT TOTAL TEMPERATURE
• A108 CYCLE ANALYSIS OF ISOTHERMAL EXPANSION COMBUSTION GAS TURBINE(Advanced thermal system analysis-1)

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