Development of 25N oxygen-kerosene thruster

2021 ◽  
Author(s):  
V.L. Salich
Keyword(s):  
Oxygen Supply ◽  
Rocket Engine ◽  
Experimental Chamber ◽  
Internal Cooling ◽  
Cylindrical Section

The paper introduces the scientific and technical groundwork obtained by the author and used as a basis for the development of an oxygen-kerosene rocket engine with a thrust of 25 N. This groundwork represents the results of research carried out on an experimental chamber developed by the author. The design of the chamber made it possible to study the effect of the configuration of the mixing element on its characteristics, the number of holes of oxygen supply to the internal cooling curtain, the length of the cylindrical section behind the curtain belt. The results of tests of various variants of the chamber and their analysis are presented. The results of tests of the developed engine, in which one of the camera variants is implemented, are given as well.

Laser Ignition of Liquid-Oxygen–Gaseous-Hydrogen Fuel in a Large-Scale Combustion Chamber

2019 ◽  
pp. 104-114
Author(s):  
S.G. Rebrov ◽  
V.A. Golubev ◽  
Y.P. Kosmachev ◽  
V.P. Kosmacheva
Keyword(s):  
Combustion Chamber ◽  
Large Scale ◽  
Rocket Engine ◽  
Laser System ◽  
Optical Breakdown ◽  
Gaseous Hydrogen ◽  
Liquid Oxygen ◽  
Research Centre ◽  
Laser Ignition ◽  
Experimental Chamber

The article presents a review of the results of studies of laser ignition of a cryogenic mixture (gaseous hydrogen and liquid oxygen) in an experimental combustion chamber, carried out at the bench testing facility of KBKhA (Voronezh). A laser ignition module specially designed at the Keldysh Research Centre and with parameters optimized for use in the rocket engine launch system was used during the experiments. Fuel ignition by the laser system occurred directly in the experimental chamber without the use of an ignition device or pre-chamber. To implement this ignition method, inflammation of the fuel in the chamber was carried out by focusing the laser radiation into the mixture, with the initiation of a spark of optical breakdown in the selected area with conditions favorable for the start of combustion. The results of the experiments confirmed the efficiency of the laser module during both standalone and firing tests, including multiple launches of the propulsion unit operated on a cryogenic mixture (gaseous hydrogen and liquid oxygen).

Consideration of pre-cooling sequence of the liquid oxygen supply system for rocket engine

2018 ◽  
Vol 2018 (0) ◽  
pp. OS14-10
Author(s):  
Inaho YOSHIKAWA ◽  
Daisuke NAKATA ◽  
Ryojiro MINATO ◽  
Hiromitsu YAGIHASHI ◽  
Koki ARIMATSU ◽  
...  
Keyword(s):  
Oxygen Supply ◽  
Rocket Engine ◽  
Supply System ◽  
Liquid Oxygen

Study on Pulsed Linear MHD Accelerator using Model Rocket Engine

2012 ◽  
Vol 132 (12) ◽  
pp. 1140-1145 ◽  
Author(s):  
Yuichi Takai ◽  
Yuhki Naganuma ◽  
Sho Takayanagi ◽  
Toru Sasaki ◽  
Takashi Kikuchi ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Model Rocket Engine

Recent Studies in Turbine Blade Internal Cooling

2010 ◽  
Vol 41 (8) ◽  
pp. 803-828 ◽  
Author(s):  
Michael Huh ◽  
Je-Chin Han
Keyword(s):  
Turbine Blade ◽  
Internal Cooling

FLOW FIELD AND HEAT TRANSFER ANALYSIS IN AMON/MMH BIPROPELLANT ROCKET ENGINE

2017 ◽  
Vol 16 (3) ◽  
pp. 263-280 ◽  
Author(s):  
Yu Daimon ◽  
Hideyo Negishi ◽  
Hiroumi Tani ◽  
Yoshiki Matsuura ◽  
Shigeyasu Iihara ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Flow Field ◽  
Rocket Engine ◽  
Heat Transfer Analysis
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