...Lorenzo Mazzei; Riccardo Da Soghe; Cosimo Bianchini It is well known from the literature that surface roughness significantly affects friction and heat transfer. This is even more evident for additive manufactured (AM) components, which are taking an increasingly important role in the gas turbine...

... cooling passages for modern gas turbine blade trailing edge. The Reynolds number range is 10,000–80,000, and the inlet rotation number range is 0–0.46. With the increase of Reynolds number, the enhancement of heat transfer performance of the channel with guiding pin fin arrays is significantly higher than...

...Nicolai Neumann; Arne Berthold; Frank Haucke; Dieter Peitsch; Panagiotis Stathopoulos Performance improvements of conventional gas turbines are becoming increasingly difficult and costly to achieve. Pressure gain combustion (PGC) has emerged as a promising technology in this respect, due...

... in Fig. 26 . The present study is one of preliminary experimental works under low-speed conditions for the determination of the best blade tip configuration suitable for 270 MW gas turbine for power generation. This paper presents detailed over-tip leakage loss data for a full squealer (FS) tip...

...Pingting Chen; Lang Wang; Xueying Li; Jing Ren; Hongde Jiang; Terrence Simon Film cooling technology is widely used in gas turbines. With the additive manufacturing anticipated in the future, there will be more freedom in film cooling hole design. Exploiting this freedom, the present authors tried...

... impingement repeatedly to remove powder until their weights did not change. Fig. 7 EOS M290 system and schematic figure of printing process 1 Corresponding author. Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the J OURNAL OF T URBOMACHINERY...

...S. M. Aminossadati; D. J. Mee 1 Corresponding author. Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the J OURNAL OF T URBOMACHINERY . Manuscript received December 8, 2010; final manuscript received January 5, 2012; published online March 25...

... channel flow Coriolis force gas turbines rotational flow turbulence gas turbine blade trailing edge cooling inclined pin-fins rotating channel Thermal efficiency and power output increase with increasing turbine inlet temperature. Therefore, an effective cooling strategy is necessary...

... to the square of the blade lift coefficient multiplied by 0.18 26 C D – sec = 0.18 C L – blade 2 07 09 2006 29 09 2006 07 09 2010 07 09 2010 gas turbines flow simulation computational fluid dynamics mechanical engineering computing compressors CAD...

... to predict changes in compressor stage characteristics, which, in turn, affect the inlet mass flow of the compressor. The test vehicle for calibration was a 50 Hz Alstom industrial gas turbine. Once calibrated, the code was successfully utilized to predict wet-compression effects for three additional like...

.... This lack of commercial use is the motivation for the current study. gas turbine tandem blade compressor rotor computational aerospace components aerospace engines blades compressors gas turbines numerical analysis rotors 29 09 2008 28 01 2009 25 03 2010 25 03...

... that contemporary CFD codes can be used as suitable means in the thermal design process. 03 06 2008 02 02 2009 11 09 2009 computational fluid dynamics cooling gas turbines jets linings mechanical engineering computing gas turbine heat shield impingement cooling TLC CFD...

...Bai-Tao An; Jian-Jun Liu; Hong-De Jiang This paper presents a detailed flow and heat transfer characteristic analysis on gas turbine first-stage turbine under hot streak inlet conditions. Two kinds of inlet total temperature conditions are specified at the turbine stage inlet. The first is uniform...

... 02 2009 aerodynamics blades computational fluid dynamics gas turbines rotors subsonic flow gas turbine tandem blade compressor cascade computational A major limitation on the pressure rise in a subsonic axial-flow compressor stage is boundary layer separation...

... blades computational fluid dynamics gas turbines heat transfer Mach number transonic flow turbulence gas turbine vane high turbulence Reynolds number heat transfer thin film gauge One way to increase the cycle efficiency of a gas turbine engine is to operate at higher turbine...

... in the squealer cavity. 13 08 2006 07 04 2007 12 02 2008 blades cooling gas turbines jet engines Mach number subsonic flow Some numerical investigations have also been carried out to study heat transfer and film-cooling effectiveness on blade tip. The effects of tip clearance...

... compression efficiency, aerodynamic breaking of water droplets etc. are investigated and discussed in this paper. Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Amsterdam, The Netherlands, June 3–6, 2002...