Email this article Comparison of two methods for determining the thrust characteristics of model jet engine
- Authors: Lukashevich S.V.1, Shiplyuk A.N.1,2
-
Affiliations:
- S. A. Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences
- Novosibirsk State Technical University
- Issue: Vol 15, No 3 (2022)
- Pages: 46-50
- Section: Articles
- URL: https://journals.rcsi.science/2305-9117/article/view/286548
- DOI: https://doi.org/10.30826/CE22150305
- EDN: https://elibrary.ru/ITPDJK
- ID: 286548
Cite item
Open Access
Access granted
Subscription Access
Abstract
In the study of combustion processes in the combustion chambers of air-jet engines, the main attention is paid to determining their thrust characteristics. The main way to determine the thrust characteristics is the direct measurement of the thrust generated by the combustion chamber or a charge of solid fuel. Another way to determine the thrust characteristics is to define the momentum of the jet flowing through the sonic nozzle according to the known flow parameters at the nozzle exit (pressure, temperature, and gas composition). Depending on the task at hand, it is convenient to use one of the indicated methods. In this paper, the results of determining the thrust characteristics of a model combustion chamber have been compared in two ways under the conditions of one experiment.
About the authors
Sergey V. Lukashevich
S. A. Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences
Author for correspondence.
Email: lukashevich@itam.nsc.ru
Candidate of Science in physics and mathematics, research scientist
Russian Federation, NovosibirskAlexander N. Shiplyuk
S. A. Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences; Novosibirsk State Technical University
Email: shiplyuk@itam.nsc.ru
Corresponding Member of the Russian Academy of Sciences, director; professor
Russian Federation, Novosibirsk; NovosibirskReferences
- Aleksandrov, V. Yu., K. K. Klimovskiy, and A. N. Prokhorov. 2013. Sposob opredeleniya polnoty sgoraniya toplivnoy smesi v kamere sgoraniya sverkhzvukovogo pryamotochnogo vozdushno-reaktivnogo dvigatelya [Method for determining the combustion efficiency of the fuel mixture in the combustion chamber of a supersonic ramjet engine]. Patent RF 2495270 C1.
- Arkhipov, V. A., A. B. Kiskin, V. E. Zarko, and A. G. Korotkikh. 2014. Laboratory method for measurement of the specific impulse of solid propellants. Combust. Explo. Shock Waves 50(5):622–624. doi: 10.1134/ S0010508214050177.
Supplementary files
