Numerical solution of LOx flow in a liquid rocket engine additively manufactured cooling channel

dc.contributor.authorMonokrousos, Nikos
dc.contributor.authorKönözsy, László Z.
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorSozio, Ernesto
dc.contributor.authorRossi, Federico
dc.date.accessioned2024-10-30T15:20:13Z
dc.date.available2024-10-30T15:20:13Z
dc.date.freetoread2024-10-30
dc.date.issued2024-10-08
dc.date.pubOnline2024-10-08
dc.description.abstractThe present work has been conducted in the framework of the DemoP1 demonstrator for the design of a LOx/LNG aerospike engine carried out by Pangea Aerospace. The main objective of the demonstrator is to highlight the central features of the next generation booster-class engines such as reusability, the utilisation of cryogenic coolants and the benefits arising from the ever-growing field of Additive Manufacturing (AM) for high heat flux aerospace applications with increasing thermal load management demands. In the present study a numerical investigation of the cryogenic liquid oxygen coolant flow in an AM cooling channel of the DemoP1 engine is implemented. The simulations are performed on a three-dimensional curvilinear cooling channel of variable, rectangular cross-section of the aerospike engine. Different variations of the two-equation k − ω turbulence model are employed and assessed for the closure of the fluid flow governing equations and the identification of the efficient formulations for the accurate prediction of the spatial development of the primitive variables. The numerical solutions obtained for the characterisation of heat transfer and pressure drop in the AM cooling channel are compared against experimental data provided from Pangea Aerospace for the full-scale single-injector element hot-fire test campaign of the DemoP1 aerospike engine demonstrator.
dc.description.conferencename34th Congress of the International Council of the Aeronautical Sciences
dc.description.sponsorshipThe present research work was financially supported by the Centre for Propulsion and Thermal Power Engineering and the Cranfield Air and Space Propulsion Institute (CASPI) at Cranfield University, UK in collaboration with Pangea Aerospace, Spain.
dc.identifier.citationMonokrousos N, Konozsy L, Pachidis V, et al., (2024) Numerical solution of LOx flow in a liquid rocket engine additively manufactured cooling channel. ICAS Proceedings. 34th Congress of the International Council of the Aeronautical Sciences, 9-12 September 2024, Florence, Italyen_UK
dc.identifier.elementsID555408
dc.identifier.issn2958-4647
dc.identifier.urihttps://www.icas.org/ICAS_ARCHIVE/ICAS2024/data/papers/ICAS2024_0105_paper.pdf
dc.identifier.urihttps://www.icas.org/ICAS_ARCHIVE/ICAS2024/data/preview/ICAS2024_0105.htm
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23129
dc.language.isoen
dc.publisherInternational Council of the Aeronautical Sciencesen_UK
dc.publisher.urihttps://www.icas.org/ICAS_ARCHIVE/ICAS2024/data/preview/ICAS2024_0105.htm
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectaerospike engineen_UK
dc.subjectadditive manufacturingen_UK
dc.subjectcooling channelen_UK
dc.subjecttwo-equation k −ω turbulence modelen_UK
dc.titleNumerical solution of LOx flow in a liquid rocket engine additively manufactured cooling channelen_UK
dc.typeConference paper
dcterms.coverageFlorence, Italy
dcterms.dateAccepted2024-03
dcterms.temporal.endDate12 Sep 2024
dcterms.temporal.startDate9 Sep 2024

Files

Original bundle
Now showing 1 - 1 of 1
Loading...
Thumbnail Image
Name:
Numerical_solution_of_LOx flow-2024.pdf
Size:
2.09 MB
Format:
Adobe Portable Document Format
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.63 KB
Format:
Plain Text
Description: