Full-length visualisation of liquid oxygen disintegration in a single injector sub-scale rocket combustor-Reference-Cited by-同舟云学术

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Full-length visualisation of liquid oxygen disintegration in a single injector sub-scale rocket combustor

Published:2019-03 Issue: Volume:86 Page:444-454
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Suslov Dmitry I.,Hardi Justin S.^ORCID,Oschwald Michael

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference16 articles.

1. Mixing and combustion of cryogenic oxygen–hydrogen shear-coaxial jet flames at supercritical pressure;Oefelein;Combust. Sci. Technol.,2006

2. Large-eddy simulation of transcritical flows;Schmitt;C. R. Méc.,2009

3. Unsteady high-order simulation of a liquid oxygen/gaseous hydrogen rocket combustor;Lempke;J. Propuls. Power,2015

4. Exploration of combustion instability triggering using large eddy simulation of a multiple injector liquid rocket engine;Urbano;Combust. Flame,2016

5. An efficient multi-fluid-mixing model for real gas reacting flows in liquid propellant rocket engines;Banuti;Combust. Flame,2016

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1. Numerical Investigation of Flame-Acoustic Interaction at Resonant and Non-Resonant Conditions in a Model Combustion Chamber;Aerospace;2024-07-05

2. Experimental and numerical investigation on thermochemical erosion and mechanical erosion of carbon-based nozzles in hybrid rocket motors;Aerospace Science and Technology;2024-05

3. Flame dynamics of an injection element operated with LOX/H₂, LOX/CNG and LOX/LNG in a sub- and supercritical rocket combustor with large optical access;International Journal of Spray and Combustion Dynamics;2023-05-19

4. Flame Characteristics and Response of a High-Pressure LOX/CNG Rocket Combustor with Large Optical Access;Aerospace;2022-07-29

5. Flame characteristics of a high-pressure LOX/H2 rocket combustor with large optical access;Case Studies in Thermal Engineering;2021-12

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