Wilhelm, Manuel ; Schiffer, Heinz-Peter (2019)
Experimental investigation of rotor tip film cooling at an axial turbine with swirling inflow consditions using pressure sensitive paint.
13th European Turbomachinery Conference. Lausanne, Switzerland (April 8-12, 2019)
Konferenzveröffentlichung, Bibliographie
Kurzbeschreibung (Abstract)
Rotor tip film cooling is investigated at the Large Scale Turbine Rig, which is a 1.5-stage axial turbine rig operating at low speeds. Using pressure sensitive paint, the film cooling effectiveness eta at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on eta is examined in comparison to an axial inflow baseline case. Coolant-to-mainstream injection ratios are varied between 0.45 and 1.74. for an engine-realistic coolant-to-mainstream density ratio of 1.5. It is shown that inlet swirl causes a reduction in eta for low injection ratios by up to 26 %, with the trailing edge being especially susceptible to swirl. For injection ratios greater than 0.93 however, eta is increased by up to 11%for swirling inflow, while for axial inflow a further increase in coolant injection does not transfer to a gain in eta.
| Typ des Eintrags: | Konferenzveröffentlichung |
|---|---|
| Erschienen: | 2019 |
| Autor(en): | Wilhelm, Manuel ; Schiffer, Heinz-Peter |
| Art des Eintrags: | Bibliographie |
| Titel: | Experimental investigation of rotor tip film cooling at an axial turbine with swirling inflow consditions using pressure sensitive paint |
| Sprache: | Englisch |
| Publikationsjahr: | 8 April 2019 |
| Veranstaltungstitel: | 13th European Turbomachinery Conference |
| Veranstaltungsort: | Lausanne, Switzerland |
| Veranstaltungsdatum: | April 8-12, 2019 |
| URL / URN: | http://www.euroturbo.eu/publications/proceedings-papers/etc2... |
| Kurzbeschreibung (Abstract): | Rotor tip film cooling is investigated at the Large Scale Turbine Rig, which is a 1.5-stage axial turbine rig operating at low speeds. Using pressure sensitive paint, the film cooling effectiveness eta at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on eta is examined in comparison to an axial inflow baseline case. Coolant-to-mainstream injection ratios are varied between 0.45 and 1.74. for an engine-realistic coolant-to-mainstream density ratio of 1.5. It is shown that inlet swirl causes a reduction in eta for low injection ratios by up to 26 %, with the trailing edge being especially susceptible to swirl. For injection ratios greater than 0.93 however, eta is increased by up to 11%for swirling inflow, while for axial inflow a further increase in coolant injection does not transfer to a gain in eta. |
| ID-Nummer: | ETC2019-236 |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet für Gasturbinen, Luft- und Raumfahrtantriebe (GLR) |
| Hinterlegungsdatum: | 15 Feb 2019 14:20 |
| Letzte Änderung: | 06 Mär 2020 07:20 |
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