Analysis of turbojet combustion chamber performances based on flow field simplified mathematical model

Rotaru, Constantin

doi:10.1063/1.4981987

Cited by 3 publications

(1 citation statement)

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“…Thus, during engine operation, a thrust force is created, Fig. 2, which is expressed in the following relationship [10,11,12] 𝐾 = 𝑚̇′𝑐 5 − 𝑚̇𝑐 1 (1) where: 𝑚̇air mass flow, 𝑚̇′mass flow of exhaust gases flowing from the engine, 𝑐 1air speed in the inlet, 𝑐 5velocity of exhaust gases flowing from the engine. Another very important parameter for comparing engine operation is specific fuel consumption.…”

Section: Fig 1 Gtm400 Mod Enginementioning

confidence: 99%

Stand characteristics of the GTM 400 MOD turbojet engine

Brodzik

2024

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Miniaturization of turbine jet engines not only enables testing of fuel mixtures but also opens up new possibilities for their use in smaller aircraft. In this work, measurements were carried out in the GTM 400 MOD engine in order to create the stand characteristics of unit thrust and specific fuel consumption. For both parameters, polynomials were determined describing their changes in the range of rotational speeds used. The work is the first stage of research under the rector's grant. Its goal is to create a hybrid turbojet engine powered by aviation kerosene and hydrogen. The reason for the research is to check the possibility of using hydrogen in turbomachinery engines. Hydrogen is one of the fuel additives approved for use by the European Union, which forces the aviation industry to reduce exhaust emissions into the atmosphere. Hydrogen can not only enrich aviation kerosene but also become an alternative fuel.

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