Mixture ratio distribution - Its impact on rocket thrust chamber performance.

1967 ◽  
Vol 4 (6) ◽  
pp. 786-789 ◽  
Author(s):  
J. L. PlEPER ◽  
L. E. DEAN ◽  
R. S. VALENTINE
Keyword(s):  
Ratio Distribution ◽  
Mixture Ratio ◽  
Thrust Chamber ◽  
Rocket Thrust

Wall Heat Loads in a Cryogenic Rocket Thrust Chamber During Thermoacoustic Instabilities

2021 ◽  
pp. 1-11
Author(s):  
Thomas Govaert ◽  
Wolfgang Armbruster ◽  
Justin S. Hardi ◽  
Dmitry Suslov ◽  
Michael Oschwald ◽  
...  
Keyword(s):  
Thermoacoustic Instabilities ◽  
Thrust Chamber ◽  
Rocket Thrust ◽  
Heat Loads

Injector-Driven Flame Dynamics in a High-Pressure Multi-Element Oxygen–Hydrogen Rocket Thrust Chamber

2019 ◽  
Vol 35 (3) ◽  
pp. 632-644 ◽  
Author(s):  
Wolfgang Armbruster ◽  
Justin S. Hardi ◽  
Dmitry Suslov ◽  
Michael Oschwald
Keyword(s):  
High Pressure ◽  
Thrust Chamber ◽  
Flame Dynamics ◽  
Rocket Thrust

A Comparison of Analytical and Experimental Local Heat Fluxes in Liquid-Propellant Rocket Thrust Chambers

1962 ◽  
Vol 84 (1) ◽  
pp. 19-28 ◽  
Author(s):  
William E. Welsh ◽  
Arvel B. Witte
Keyword(s):  
Heat Flux ◽  
Flow Characteristics ◽  
Heat Fluxes ◽  
Chamber Pressure ◽  
Liquid Propellant ◽  
Nitrogen Tetroxide ◽  
Thrust Chamber ◽  
Experimental Heat ◽  
Rocket Thrust ◽  
Propellant Rocket

Experimental data are presented showing heat-flux distributions measured calorimetrically with several liquid-propellant rocket thrust-chamber configurations. Thrust levels of the experimental chambers were from 300 to 5000 lb. Enzian-type and axial-stream showerhead propellant injectors were utilized with hydrazine (N2H4) and nitrogen tetroxide (N2O4) propellants. Nozzle-contraction-area ratios of 8 to 1, 4 to 1, and 1.64 to 1 were tested, each having a 5-in. inlet diameter. Characteristic chamber lengths ranged from 16.95 to 62.8 in. The comparison between the experimental heat flux and the analytical heat flux using the method of Bartz [1] was found to be closest in the nozzle-expansion region. The experimental heat-flux measurements ranged between 80 per cent above and 45 per cent below the analytical estimates at the nozzle throat, however. These differences were dependent upon thrust-chamber configuration, injector type, and chamber pressure, and apparently resulted from nonideal combustion and flow characteristics. It is concluded that a priori determination of heat-flux distribution along the thrust-chamber length was possible only to a first approximation for the conditions of these tests.

Optimization of Length of Mixing Zone in GH2-GO2 Based Torch Igniter, Applying Numerical Techniques

2014 ◽  
Vol 592-594 ◽  
pp. 1692-1696
Author(s):  
A. Anoop ◽  
M.P. Assiz ◽  
M. John Manu
Keyword(s):  
Quality Criteria ◽  
Main Stage ◽  
Mixing Zone ◽  
Numerical Techniques ◽  
Ratio Distribution ◽  
Mixture Ratio ◽  
Scramjet Engine ◽  
New Challenges ◽  
Torch Igniter ◽  
Hypergolic Propellants

Initiation of chemical reactions liberating thermal energy in non hypergolic propellants require ignition systems which are reliable as well as robust in nature. This necessitates the igniter and its subsystems be on par or exceed every quality criteria required for the main stage. The ignition systems which provide pilot action and flame holding in supersonic environment adds new challenges in its structural and thermal stability. The paper aims to conduct a numerical analysis of the Augmented Spark Torch igniter required for an air breathing rocket (SCRAMJET) engine with the emphasis on the optimization of the mixing length ratio required to achieve a uniform mixture ratio distribution in the zone of the igniter combustion chamber. Nomenclature

Sign in / Sign up

Export Citation Format

Share Document