Wall Heat Flux Mapping of Liquid Rocket Thrust Chamber with Dual Impinging GH2/GO2 Jets

2017 ◽  
Author(s):  
Vigneshwaran Sankar ◽  
Aravind A ◽  
Giridharan D ◽  
Pavithra Murugesh ◽  
VR Sanal Kumar
Keyword(s):  
Heat Flux ◽  
Wall Heat Flux ◽  
Thrust Chamber ◽  
Rocket Thrust ◽  
Liquid Rocket ◽  
Flux Mapping

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.

scholarly journals Consequences of modeling demands on numerical rocket thrust chamber flow simulation tools

2019 ◽  
Author(s):  
O. Knab ◽  
H. Riedmann ◽  
B. Ivancic ◽  
C. Höglauer ◽  
M. Frey ◽  
...  
Keyword(s):  
Flow Simulation ◽  
Time Frame ◽  
Computational Effort ◽  
Full Scale ◽  
Test Cases ◽  
Thrust Chamber ◽  
Simulation Tools ◽  
Rocket Thrust ◽  
Liquid Rocket ◽  
Model Features

Numerical simulation of liquid rocket thrust chamber flows is a challenging task which requires a comprehensive tool validation strategy encompassing laboratory- to full-scale test cases. While the former are widely used as the first step to verify advanced numerical schemes and thermochemical models, the latter can often no more be simulated in a reasonable time frame due to the extreme computational effort necessitated by the enlarged dimensions and configurational changes. Conclusions drawn from tools with such limitations are only of little help for a thrust chamber designer and, hence, ill-posed to adequately tackle the simulation challenges of such a device. This paper discusses the modeling demands for numerical thrust chamber flow simulation tools and outlines the indispensable validation approach from laboratory- via subto full-scale configurations using consistent model features throughout the test cases. Consequences of this obligation are exposed to drive the tool setup. Exemplarily, the Airbus DS thrust chamber flow simulation philosophy is presented.

Wall Heat Flux Evaluation in Regeneratively Cooled Rocket Thrust Chambers

2021 ◽  
Vol 35 (1) ◽  
pp. 127-141
Author(s):  
Nikolaos Perakis ◽  
Lukas Preis ◽  
Oskar J. Haidn
Keyword(s):  
Heat Flux ◽  
Wall Heat Flux ◽  
Rocket Thrust
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