Technology Application to MHPS Large Flame F Series Gas Turbine

Abstract

The development of gas turbines, Mitsubishi Hitachi Power Systems, Ltd. (MHPS) has continued to pursue and contribute to society in terms of global environmental conservation and stable energy supply. MHPS leverages its abundant gas turbine operation experience and takes advantage of its extensive advanced technologies research on the Japanese National Project. MHPS has been participating in this project since 2004. Recent years’ achievements include the demonstration of a gas turbine combined cycle (GTCC) efficiency in excess of 62% created by increasing the turbine inlet temperature to the 1,600°C class in the M501J in 2011. The Latest M701F incorporates “J” gas turbine technologies, already applied to actual equipment, for efficiency improvement. It also applies air-cooled combustor technologies successfully validated in the G class, for increased flexibility. The 1st unit started commercial operation in 2015 and currently 4 units has accumulated more than 46,000 actual operating hours collectively. MHPS is making the upgrading program for existing F-series gas turbines. The proven technology verified in the M501J and developed in the National project increases efficiency and reliability. This paper explains the features and development status of Latest M701F gas turbine, and explains upgrade program for existing F-series gas turbines.

Test-Rig Simulation on Hybrid Thermal Barrier Coating Assisted with Cooling Air System for Advanced Gas Turbine under Prolonged Exposures—A Review

“…Advanced gas turbine can be described as upgrading the standard gas turbine to improve its reliability in terms of prolonging design life, efficiency in terms of improved power output, and durability in terms of enhanced operational flexibility [14][15][16]. The upgraded works include the use of upgraded superalloys, improved cooling holes configuration in both external film cooling and internal cooling, the application of TBC, and the use of an upgraded combustion system.…”

“…The differences in temperature reduction by different TBC thicknesses and number of cooling holes have also been elaborated in the study, and the summary is shown in Figure 7. Fujimoto et al have discussed the upgrading works that have been conducted to optimize the hybrid TBC-assisted cooling air by increasing the TBC thickness and modifying the shape of the cooling hole [16]. Taniguchi et al in their work modified the turbine blade cooling holes to improve the cooling performance [31].…”