Bio yakıtla çalışan küçük gaz türbinli motor dönüşümü ve performans karşılaştırması

Download
2009
Akmandor, Sinan İbrahim
Uzol, Oğuz
Karaca, Mehmet
Since the flow and the combustion processes are continious, the limitations for fuel for gas turbines is much less when compared with other types of engines. Gas turbines enable the use of low calorific value biofuels. Gas turbines can use wide range of fuels from natural gas at cogeneration plants to Kerozene on aircraft engines. Nowadays, increase in the petrol prizes increase tendancy to use bio-fuels in gas turbines for energy generation. Bio-fuels has the potential to contribute a significant portion of the electricity consumed in Turkey. In addition it provides an alternative to fosil-fuel-based energy and creates a new market for agriculture. Multifuel useage capability will increase efficient reliable operations of gas turbine enginesCombined heat and power systems using biofuels will widely spread in the energy industry and greatly contribute to the economy of our country. The prior consideration in the project will be investigation of true air-fuel ratio, pressure and temperature on bio-fuel cobustion for high efficiecy. During the operation of the engine the property of the flow incoming to the combustion chamber varies. Ideal air to fuel ratios for various operating points will be obtained, and the results will be veifyed exğerimentally. Varying calorific value of the fuel will arise need for varying fuel flow rate for efficient combustion, to achieve efficient combustion using bio-fuels is one of the most important outcome of the work. At the end of the project, the results of the previously submitted thesis at the Aerospace Engineering Department will be used as to obtain performans characteristics of rotating components evaluating the measurments taken from the gas turbine. According to results obtained through the component performance estimation analysis, the modifications required to permit operation on Biofuel will be designed and applied to gas turbine.Finally, the system will be operated, and for comparing the efficiency and performance of the ststem with various types of fuel.

Suggestions

Surrogate model based system identification and control of gas turbine engines
Ekinci, Sinan; Yavrucuk, İlkay; Department of Aerospace Engineering (2019)
The focus of this thesis is on small low-cost turbojet engines where the fuel flow is provided by a gear-type fuel pump rather than a more traditional fuel metering unit. The incorporation of such type of fuel flow actuation devices introduces additional nonlinearities into the modeling and control of the small turbojet engines. As an alternative solution, this thesis presents and applies online/offline parameter estimation and adaptive control methods to such sub-class turbojet engines. For the simulation ...
Aerothermodynamics of turbine blade trailing edge cooling
Tunçel, Tuğba; Kahveci, Harika Senem; Department of Aerospace Engineering (2018)
It is known that the thermal efficiency of gas turbines strongly depends on the turbine entry temperature of the working fluid. This has resulted in increased turbine working temperatures, and peak temperatures in advanced gas turbines have been well above maximum allowable metal temperatures for quite some time. For turbine blades to survive while operating beyond these material temperature limits, internal and external cooling techniques have been developed. Due to structural and aerodynamic restrictions,...
Experimental investigation of the effects of tip geometry on the flow and loss characteristics in a linear turbine cascade
Alican, Ozan; Uzol, Oğuz; Department of Aerospace Engineering (2017)
In gas turbines, there are a number of factors causing efficiency decrease. When internal flow in turbomachines is considered, flow vortices are one of those factors. This study aims to investigate the main mechanisms behind the efficiency losses occurring due to Tip Leakage Vortex (TLV) in gas turbine rotor blades. Additionally, according to these mechanisms, two squealer tip geometries were applied to the turbine blades and the improvements were reported. This work is the experimental branch of an optimum...
Cooling performance investigation of a two-pass rib-roughened channel
Kavas, İsa; Kurtuluş, Dilek Funda; Yasa, Tolga; Department of Aerospace Engineering (2015)
The performance of the modern aero-engines is highly dependent on the turbine inlet gas temperature. The higher temperature leads to more compact and efficient machines. Additionally, specific fuel consumption of the engine is decreased for the same thrust rating. However, the turbine inlet temperatures of the today’s engines are already beyond the material structural limits. Hence, the turbine section must be cooled down to acceptable levels. Various types of cooling methods are typically applied to the ga...
The Influence of cooling configuration and tip geometry on gas turbine blade tip leakage flow and heat transfer
Sakaoğlu, Sergen; Kahveci, Harika Senem; Department of Aerospace Engineering (2019)
In gas turbine engines, an increase in the thermal efficiency and power output can be ensured by increasing the turbine inlet temperature. This causes the high-pressure turbine (HPT) blades to be exposed to extremely high temperatures that requires the introduction of cooling flow in order to keep the temperatures within the allowable material limits and to reduce the high thermal loads on the blade. However, cooling flow introduced around the blade tip region affects the blade tip leakage flow and blade tip he...
Citation Formats
S. İ. Akmandor, O. Uzol, and M. Karaca, “Bio yakıtla çalışan küçük gaz türbinli motor dönüşümü ve performans karşılaştırması,” 2009. Accessed: 00, 2020. [Online]. Available: https://app.trdizin.gov.tr/publication/project/detail/T1RjMk1qST0.