Köhler, J. ; Beer, Hans (1984)
Effectiveness Measurements for a Cooling Film Disrupted by a Row of Jets.
In: International Communications in Heat and Mass Transfer, 11 (6)
Artikel, Bibliographie
Kurzbeschreibung (Abstract)
The influence of cold air jet injection upon filmcooling of combustion chamber walls has been investigated by simulation. The experiments, in which a row of cold air jets is injected perpendicularly to the film cooled test chamber wall, show considerable decreases of the film cooling effectiveness downstream of the jet exit. The same behavior occurs in real combustion chambers of aircraft gas turbine engines. The tests are selected to represent combinations of geometries and flow variables (except the temperature ratios) which are pertinent to gas turbine combustor design. The present investigations cover effectiveness measurements for various combinations of the parameters: a) velocity ratio coolant film to mainstream b) velocity ratio jet to mainstream c) dimensionless distance between coolant film and jet exit d) spacing ratio e) ratio jet diameter to slot height f) ratio lip thickness to slot height.
| Typ des Eintrags: | Artikel |
|---|---|
| Erschienen: | 1984 |
| Autor(en): | Köhler, J. ; Beer, Hans |
| Art des Eintrags: | Bibliographie |
| Titel: | Effectiveness Measurements for a Cooling Film Disrupted by a Row of Jets |
| Sprache: | Englisch |
| Publikationsjahr: | 1984 |
| Titel der Zeitschrift, Zeitung oder Schriftenreihe: | International Communications in Heat and Mass Transfer |
| Jahrgang/Volume einer Zeitschrift: | 11 |
| (Heft-)Nummer: | 6 |
| URL / URN: | http://dx.doi.org/10.1016/0735-1933(84)90002-2 |
| Kurzbeschreibung (Abstract): | The influence of cold air jet injection upon filmcooling of combustion chamber walls has been investigated by simulation. The experiments, in which a row of cold air jets is injected perpendicularly to the film cooled test chamber wall, show considerable decreases of the film cooling effectiveness downstream of the jet exit. The same behavior occurs in real combustion chambers of aircraft gas turbine engines. The tests are selected to represent combinations of geometries and flow variables (except the temperature ratios) which are pertinent to gas turbine combustor design. The present investigations cover effectiveness measurements for various combinations of the parameters: a) velocity ratio coolant film to mainstream b) velocity ratio jet to mainstream c) dimensionless distance between coolant film and jet exit d) spacing ratio e) ratio jet diameter to slot height f) ratio lip thickness to slot height. |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet für Technische Thermodynamik (TTD) |
| Hinterlegungsdatum: | 26 Feb 2015 13:45 |
| Letzte Änderung: | 05 Aug 2019 13:27 |
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