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

scholarly journals Early detection of thermoacoustic instabilities in a cryogenic rocket thrust chamber using combustion noise features and machine learning

2021 ◽  
Vol 31 (6) ◽  
pp. 063128
Author(s):  
Günther Waxenegger-Wilfing ◽  
Ushnish Sengupta ◽  
Jan Martin ◽  
Wolfgang Armbruster ◽  
Justin Hardi ◽  
...  
Keyword(s):  
Machine Learning ◽  
Early Detection ◽  
Combustion Noise ◽  
Thermoacoustic Instabilities ◽  
Thrust Chamber ◽  
Rocket Thrust

scholarly journals Injector-coupled thermoacoustic instabilities in an experimental LOX-methane rocket combustor during start-up

2020 ◽  
Vol 12 (2) ◽  
pp. 267-279
Author(s):  
Sebastian Klein ◽  
Michael Börner ◽  
Justin S. Hardi ◽  
Dmitry Suslov ◽  
Michael Oschwald
Keyword(s):  
Combustion Chamber ◽  
High Amplitude ◽  
Acoustic Properties ◽  
Two Phase ◽  
Close Coupling ◽  
Thermoacoustic Instabilities ◽  
Thrust Chamber ◽  
Start Up ◽  
Rocket Thrust ◽  
Lox Methane

AbstractThis paper reports the investigation of acoustic combustion instability experienced during repetitive ignition testing of a sub-scale LOX-methane rocket thrust chamber. The occurrence of resonant coupling between the LOX injectors and the combustion chamber acoustic modes was assessed from the experimental data recorded during the highly transient phase of operation from ignition up to around 2 s. A method was developed to model the evolution of acoustic properties in both the combustion chamber and the injectors during the transient period. For the LOX injectors, the Woods equation was used to estimate the speed of sound in the two-phase flow. The models were used to identify the corresponding mode frequencies in the unsteady pressure measurements, and show that the high-amplitude instability occurred when they intersected. Very close coupling of less than 3% frequency difference is required for high amplitudes to be observed. However, the condition was necessary but not sufficient for high amplitudes to be reached.

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

Numerical Investigation on Radiative Heat Loads in Liquid Rocket Thrust Chambers

2019 ◽  
Vol 35 (5) ◽  
pp. 930-943 ◽  
Author(s):  
Giuseppe Leccese ◽  
Daniele Bianchi ◽  
Francesco Nasuti
Keyword(s):  
Numerical Investigation ◽  
Radiative Heat ◽  
Rocket Thrust ◽  
Liquid Rocket ◽  
Heat Loads

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.

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