Change search
ReferencesLink to record
Permanent link

Direct link
Radiative heat transfer in film-cooled liquid rocket engine nozzles
KTH, Superseded Departments, Energy Technology.
2003 (English)In: Journal of thermophysics and heat transfer, ISSN 0887-8722, Vol. 17, no 1, 29-34 p.Article in journal (Refereed) Published
Abstract [en]

A radiation model has been implemented in a Navier-Stokes flow solver to investigate the importance of thermal radiation in film-cooled liquid hydrogen/liquid oxygen rocket engine thrust chambers. Two running conditions were computed: high-altitude and sea-level conditions. For high altitudes, the smalls are heated by radiation approximately 3 K, and the flow is not influenced. At sea level, the flow separates from the nozzle walls and a Mach disk is formed inside the nozzle. This extra source of radiation is clearly observable and, combined with the cold atmospheric air pocket created behind the separation, contributes importantly to the wall temperatures. An increase of up to 140 K is observed in the zone after the separation. Moreover, the position of the shock is slightly affected by radiative transfer. It is shown that radiative heat transfer does play an important role in the case of a shocked film-cooled nozzle. In the unshocked case, its effects are noticeable, but may be neglected.

Place, publisher, year, edition, pages
2003. Vol. 17, no 1, 29-34 p.
Keyword [en]
URN: urn:nbn:se:kth:diva-22204ISI: 000180594900003OAI: diva2:340902
QC 20100525Available from: 2010-08-10 Created: 2010-08-10Bibliographically approved

Open Access in DiVA

No full text

Search in DiVA

By author/editor
Fransson, Torsten H.
By organisation
Energy Technology
In the same journal
Journal of thermophysics and heat transfer

Search outside of DiVA

GoogleGoogle Scholar
The number of downloads is the sum of all downloads of full texts. It may include eg previous versions that are now no longer available

Total: 65 hits
ReferencesLink to record
Permanent link

Direct link