Temperature-dependent solid material properties of GRCop-42 for an additively manufactured liquid rocket engine LOx cooling channel

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dc.contributor.authorMonokrousos, Nikos
dc.contributor.authorKönözsy, László
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorSozio, Ernesto
dc.contributor.authorRossi, Federico
dc.date.accessioned2025-03-21T15:42:25Z
dc.date.available2025-03-21T15:42:25Z
dc.date.freetoread2025-03-21
dc.date.issued2024-11-06
dc.date.pubOnline2024-11-06
dc.descriptionXXXІI International Scientific and Practical Conference “Information Technologies: Science, Engineering, Technology, Education, Health (MicroCAD-2024)” 22-25 May 2024, Kharkiv, Ukraine
dc.description.abstractRecent technological developments in the field of Additive Manufacturing (AM) provide a number of opportunities for the utilisation of high-performance copper alloys for aerospace applications. The additively manufactured LOx/LNG DemoP1 aerospike engine demonstrator designed by Pangea Aerospace is a characteristic example based on the Direct Metal Laser Sintering (DMLS) technology. The aerospike engine thrust chamber and LOx cooling channels are manufactured using GRCop-42 material powder, a Cu-Cr-Nb based copper alloy developed by the National Aeronautics and Space Administration (NASA) for the regenerative cooling technology of high thermal demand thrust chambers and nozzles. In the current work temperature-dependent correlations are derived for the density, specific heat capacity at constant pressure and thermal conductivity of the GRCop-42 material. The correlations for the solid material properties are then introduced into the ANSYS Fluent 2023 R2 Computational Fluid Dynamics (CFD) package and their capabilities are investigated for the characterisation of the flow-field characteristics of the LOx flow in the cooling channel. The numerical solution of the coolant flow in the AM cooling channel is compared against experimental data of the DemoP1 engine demonstrator. The main objective of this study is to provide a realistic physical description of the temperature-dependent properties of the AM solid material in high heat flux applications where the material properties are mostly considered as constant in previous studies.
dc.description.journalNameMultidiszciplináris Tudományok (Multidisciplinary 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.format.extentpp. 92-113
dc.identifier.citationMonokrousos N, Könözsy L, Pachidis V, et al., (2024) Temperature-dependent solid material properties of GRCop-42 for an additively manufactured liquid rocket engine LOx cooling channel. In: MultiScience - microCAD International Multidisciplinary Scientific Conference - Special Issue Part II, November 2024, pp. 92-113
dc.identifier.eissn2786-1465
dc.identifier.elementsID561012
dc.identifier.issn2062-9737
dc.identifier.issueNo3
dc.identifier.urihttps://doi.org/10.35925/j.multi.2024.3.9
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23658
dc.identifier.volumeNo14
dc.language.isoen
dc.publisherUniversity of Miskolc
dc.publisher.urihttps://ojs.uni-miskolc.hu/index.php/multi/article/view/3186
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectAerospike engine
dc.subjectAdditive Manufacturing
dc.subjectLOx cooling channel
dc.subjectGRCop-42 copper alloy
dc.subjectMaterial properties
dc.titleTemperature-dependent solid material properties of GRCop-42 for an additively manufactured liquid rocket engine LOx cooling channel
dc.typeArticle
dcterms.dateAccepted2024

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