DESAIN AWAL RUANG BAKAR PREMIXED UNTUK TURBIN GAS ULTRA MIKRO (TGUM) DENGAN MENGGUNAKAN PENDEKATAN TEMPERATUR ADIABATIK

Authors

  • Muhamad Maris Al Gifari UPI
  • Firman Hartono
  • Prihadi Setyo Darmanto
  • Iman Kartolaksono Reksowardojo

DOI:

https://doi.org/10.21776/jrm.v15i3.1613

Keywords:

Combustion Chamber Preliminary Design, Reference Diameter, Flame speed, Equivalence Ratio

Abstract

The need to develop ultra-micro gas turbine (TGUM) applications is getting higher, especially as a portable energy source. Many applications whose energy requirements cannot be met by current batteries but can be handled by TGUM. The energy density of kerosene is 45 times greater than that of current batteries. The development of ultra-micro gas turbines has been carried out for more than 20 years. The challenge faced in the TGUM development process was manufacturing technology, but manufacturing developments continue to advance over time, meaning that one day high-speed bearing technology may be achieved. The development of an ultra-micro gas turbine can be started from the design of the combustion chamber. The basic concept of determining the initial size of the diameter as the initial reference length is widely available and established, but this reference is only for combustion chambers with non-premixed combustion. No one has discussed the determination of the size of the premixed combustion chamber. The basis for the initial determination of the combustion chamber in this article is the determination of the adiabatic temperature, and the energy balance equation which is simplified to become Black's Principle. This method describes the relationship between the diameter of the combustion chamber, airflow dilution portion and the flame propagation speed that must be met. This method also determines the value of the equivalence ratio, and also length of combustion chamber based on SHR (Space Heating Rate) that must be taken. The results of this method when entering the condition of the combustion chamber inlet 379 K, 2.05 bar, and outlet 879 K, 1.79 bar produce a reference decision of 5 cm diameter, flame speed of 6 m/s, equivalent ratio of 0.8 and 74% cooling portion for a gas turbine mass flow rate of 85.7 g/s.

References

S. Yuasa, K. Oshimi, H. Nose, and Y. Tennichi, “Concept and combustion characteristics of ultra-micro combustors with premixed flame,” Proc. Combust. Inst., vol. 30, no. 2, pp. 2455–2462, Jan. 2005, doi: 10.1016/j.proci.2004.08.207.

D. Reynaerts, P. H. R. Braembussche, and M. Baelmans, “Development of a gas turbine with a 20 mm rotor: review and perspectives,” Dec. 2006.

Roberto Capata and Giampaolo Saracino, “The Ultra-Micro Gas Turbine Generator project at UDR1: experimental assessment of the compressor map and of the regenerative combustion chamber efficiency,” Sep. 2009.

A. I. Komara, A. Mahmudah, A. S. Lestari, and J. C. J. Hasibuan, “DESAIN DAN PENGEMBAN-GAN MESIN MICRO-PRESS PEMBENTUK KOMPONEN MIKRO,” J. Rekayasa Mesin, vol. 13, no. 3, pp. 751–762, Dec. 2022, doi: 10.21776/jrm.v13i3.1140.

T. Nagashima, “Learnt from the Ultra-Micro Gas Turbine Development at University of Tokyo,” 2005.

M. Janovec, J. Čerňan, F. Škultéty, and A. Novák, “Design of Batteries for a Hybrid Propulsion Sys-tem of a Training Aircraft,” Energies, vol. 15, no. 1, p. 49, Dec. 2021, doi: 10.3390/en15010049.

H. Löbberding et al., “From Cell to Battery System in BEVs: Analysis of System Packing Efficiency and Cell Types,” World Electr. Veh. J., vol. 11, no. 4, p. 77, Dec. 2020, doi: 10.3390/wevj11040077.

M. Schneider et al., “Development of a Gas Turbine Concept for Electric Power Generation in a Com-mercial Hybrid Electric Aircraft,” in Volume 1: Aircraft Engine; Fans and Blowers; Marine; Honors and Awards, Phoenix, Arizona, USA: American Society of Mechanical Engineers, Jun. 2019, p. V001T01A028. doi: 10.1115/GT2019-92065.

L. Badum, B. Leizeronok, and B. Cukurel, “New Insights From Conceptual Design of an Additive Manufactured 300 W Microgas Turbine Toward Unmanned Aerial Vehicle Applications,” J. Eng. Gas Turbines Power, vol. 143, no. 2, p. 021006, Feb. 2021, doi: 10.1115/1.4048695.

M. Gerendás and R. Pfister, “Development of a Very Small Aero-Engine,” in Volume 1: Aircraft Engi-ne; Marine; Turbomachinery; Microturbines and Small Turbomachinery, Munich, Germany: American Society of Mechanical Engineers, May 2000, p. V001T04A006. doi: 10.1115/2000-GT-0536.

Z. Turkeli-Ramadan, R. N. Sharma, and R. R. Raine, “Experimental Study on Flat Flame Combustion for Ultra Micro Gas Turbine Applications,” Combust. Sci. Technol., vol. 189, no. 8, pp. 1307–1325, Aug. 2017, doi: 10.1080/00102202.2017.1294588.

D. Mohaddes, C. T. Chang, and M. Ihme, “Thermodynamic cycle analysis of superadiabatic matrix-stabilized combustion for gas turbine engines,” Energy, vol. 207, p. 118171, Sep. 2020, doi: 10.1016/j.energy.2020.118171.

M. M. Noor, A. P. Wandel, and T. Yusaf, “Design and Development of MILD Combustion Burner,” J. Mech. Eng. Sci., vol. 5, pp. 662–676, Dec. 2013, doi: 10.15282/jmes.5.2013.13.0064.

M. T. Schobeiri, Gas Turbine Design, Components and System Design Integration. Cham: Springer International Publishing, 2018. doi: 10.1007/978-3-319-58378-5.

M. J. Moran, Ed., Fundamentals of engineering thermodynamics, 8th ed. Hoboken, N.J: Wiley, 2014.

Direktorat Jendral Minyak dan Gas Bumi, “Komposisi LPG Tidak Berubah.” [Online]. Available: https://migas.esdm.go.id/post/read/Komposisi-LPG-Tidak-Berubah

M. A. Nemitallah, A. A. Abdelhafez, and M. A. Habib, Approaches for Clean Combustion in Gas Turbines, vol. 122. in Fluid Mechanics and Its Applications, vol. 122. Cham: Springer International Publishing, 2020. doi: 10.1007/978-3-030-44077-0.

E. Mach and B. McGuinness, Principles of the Theory of Heat: Historically and Critically Elucidated. Dordrecht: Springer Netherlands, 1986.

I. Wierzba and G. A. Karim, “The Flammability of Fuel Mixtures in Air Containing Propane and Buta-ne,” J. Energy Resour. Technol., vol. 111, no. 2, pp. 100–103, Jun. 1989, doi: 10.1115/1.3231403.

D. R. Ballal and A. H. Lefebvre, “The influence of flow parameters on minimum ignition energy and quenching distance,” Symp. Int. Combust., vol. 15, no. 1, pp. 1473–1481, Jan. 1975, doi: 10.1016/S0082-0784(75)80405-X.

B. Aravind, Velamati Ratna Kishore, and Akram Mohammad, “Combustion characteristics of the effect of hydrogen addition on LPG–air mixtures,” Int. J. Hydrog. Energy, vol. 40, pp. 16605–16617, 2015.

Muller, “Patent Application Publication ULTRA-MCRO GAS TURBINE.” United States Patent Ap-plication Publication, 2008.

R. Capata, “Ultra Micro Gas Turbines,” in Efficiency, Performance and Robustness of Gas Turbines, V. Konstantin, Ed., InTech, 2012. doi: 10.5772/37829.

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Published

2024-12-15

How to Cite

Al Gifari, M. M., Hartono, F., Darmanto, P. S., & Reksowardojo, I. K. (2024). DESAIN AWAL RUANG BAKAR PREMIXED UNTUK TURBIN GAS ULTRA MIKRO (TGUM) DENGAN MENGGUNAKAN PENDEKATAN TEMPERATUR ADIABATIK. Jurnal Rekayasa Mesin, 15(3), 1319–1329. https://doi.org/10.21776/jrm.v15i3.1613

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