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Autor(en):
N. Kuen, L. Stecher Alonso Lillo, C. Helcig, V. Gümmer
Zusammenfassung:
This paper investigates the influence of different design parameters of a pneumatic system used to spin-up the gas generator of a helicopter turboshaft gas turbine. The system uses supersonic nozzles to impinge air on the outer section of the compressors radial end-stage. After identifying the relevant variables, Design of Experiments is used to vary and investigate their effects on the performance systematically and to discover possible interactions. The results of static experiments show good accordance with analytical calculations, however, acceleration experiments revealed interesting non-linear effects. The nozzle exit Mach number was identified as the most critical parameter. The Mach number is linked with the supply pressure and is, therefore, the reason for a design conflict. Prediction models are derived to get a data base for the redesign of the impingement system.
Veranstaltung:
Deutscher Luft- und Raumfahrtkongress 2021
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2021
Medientyp:
Conference Paper
Sprache:
englisch
Format:
21,0 x 29,7 cm, 11 Seiten
URN:
urn:nbn:de:101:1-2021100811265527816374
DOI:
10.25967/550175
Stichworte zum Inhalt:
experimental, design of experiments, impingement nozzle
Verfügbarkeit:
Kommentar:
Zitierform:
Kuen, N.; Stecher Alonso Lillo, L.; et al. (2021): Experimental Investigation of Design Parameters in an Impingement Starting System for Turboshaft Engines. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/550175. urn:nbn:de:101:1-2021100811265527816374.
Veröffentlicht am:
08.10.2021