Design of a film cooled dual-bell nozzle

Stark, Ralf; Génin, Chloe; Mader, Christian; Maier, Dietmar H.; Schneider, Dirk; Wohlhüter, Michael

doi:10.1016/j.actaastro.2018.05.056

Cited by 9 publications

(2 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Using an already-existing LOX/GH2 thrust chamber, Stark et al, [13] evaluated the design of a film-cooled dual-bell nozzle before introducing it as a part of a thrust chamber assembly. The nozzle is a scaled-down version of an existing TIC nozzle that includes the injection of a gaseous hydrogen cooling layer.…”

Section: Literature Surveymentioning

confidence: 99%

Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method

Vinayaka Nagarajaiah,

Sara Solomon Raj,

Ayampalayam Nanjappan Swaminathen

et al. 2024

ARFMTS

View full text Add to dashboard Cite

A nozzle is a tubular structure designed to facilitate the flow of hot gases. Rocket nozzle designs typically consist of a stationary convergent section and a stationary divergent section. The term "CD" is an abbreviation for "convergent-divergent" and is used to refer to this specific nozzle type. Upgrades are being made to nozzles and other engine components in order to enhance performance and optimise thrust delivery. Application-specific improvements will be made to rocket nozzles and other current combustion expansion systems. An instance of such progress is the implementation of the bell and twin bell nozzle. This study conducted a comparative analysis of two kinds of nozzles, namely bell and conical, at different Mach speeds to ascertain which one yields the most optimal flow. Subsequently, the flow parameters were modelled with computational fluid dynamics (CFD). Ensuring optimal pressure thrust integral throughout the supersonic zone of the nozzle surface while taking the base pressure into account was the aim of the problem formulation. The research focused on irrotational flow, taking into consideration the impacts of boundary layers.

show abstract

Section: Literature Surveymentioning

confidence: 99%

Optimization of Process Parameters for Flow Nozzle with Different Geometry using Computational Fluid Dynamics Method

Vinayaka Nagarajaiah,

Sara Solomon Raj,

Ayampalayam Nanjappan Swaminathen

et al. 2024

ARFMTS

View full text Add to dashboard Cite

show abstract

“…The second part of the base nozzle was cooled with GH2 flowing through cooling channels that accelerated and injected the flow as a cooling film for the extension nozzle. Preparatory works to the test campaign are presented in more details in [18,20].…”

Section: Dual-bell Nozzle Film Coolingmentioning

confidence: 99%

Dual-Bell Nozzle Design

Génin

Schneider

Stark

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

Self Cite

View full text Add to dashboard Cite

The dual-bell nozzle is an altitude adaptive nozzle concept that offers two operation modes. In the framework of the German Research Foundation Special Research Field SFB TRR40, the last twelve years have been dedicated to study the dual-bell nozzle characteristics, both experimentally and numerically. The obtained understanding on nozzle contour and inflection design, transition behavior and transition prediction enabled various follow-ups like a wind tunnel study on the dual-bell wake flow, a shock generator study on a film cooled wall inflection or, in higher scale, the hot firing test of a thrust chamber featuring a film cooled dual-bell nozzle. A parametrical system study revealed the influence of the nozzle geometry on the flow behavior and the resulting launcher performance increase.

show abstract