Pressure losses in combustion chamber fuel system of the natural gas running gas turbine engine

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles

DOI: 10.34759/vst-2020-2-157-168


Baklanov A. V.

Kazan National Research Technical University named after A.N. Tupolev, KNRTU-KAI, 10, Karl Marks str., Kazan, 420111, Russia



Pressure losses computing in the fuel system of the stationary gas turbine engine is an integral part for solving a number of engineering and operational tasks. For example, such calculation is necessary to determine a minimum required gas pressure at the inlet of the engine to ensure the engine reaching its operational modes. Likewise, this calculation may come in handy at the fuel gas composition changing, since gas properties change, which means the pressure loss change too that can require to make changes in control equipment. It is well known that fuel nozzles are carbonized while a combustion chamber operation process. Very often, it leads to the resistance increasing of the fuel system, and therefore the of pressure losses rising. Besides, any discrepancies in the dosing equipment can be detected by a hydraulic calculation.

The article considers a fuel system of a stationary converted aircraft engine intended for driving the gas pumping unit supercharger. The pressure losses computing technique for the fuel system of such engine is presented in the article. A relevance of the topic and the necessity of such techniques forming are disclosed. To check the adequacy of the developed technique the NK-16ST engine rig test was performed with pressure measuring in the fuel supply pipelines to the nozzles and in the gas doser. The results of the studies revealed that the gas fuel pressure level measured in the eight gas-extraction from collector to nozzles pipelines differed insignificantly, which confirmed the fuel distribution uniformity along the pipelines. Experimental results comparison with the computational studies confirms that their discrepancy does not exceed 6%.


Pressure losses in combustion chamber fuel system of the natural gas running gas turbine engine


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