Wilhelm, Manuel ; Schiffer, Heinz-Peter (2021)
Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint.
In: International Journal of Turbomachinery, Propulsion and Power, 2019, 4 (3)
doi: 10.26083/tuprints-00019089
Artikel, Zweitveröffentlichung, Verlagsversion
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 η at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on η 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 η 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, η is increased by up to 11% for swirling inflow, while for axial inflow a further increase in coolant injection does not transfer into a gain in η.
| Typ des Eintrags: | Artikel |
|---|---|
| Erschienen: | 2021 |
| Autor(en): | Wilhelm, Manuel ; Schiffer, Heinz-Peter |
| Art des Eintrags: | Zweitveröffentlichung |
| Titel: | Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint |
| Sprache: | Englisch |
| Publikationsjahr: | 2021 |
| Publikationsdatum der Erstveröffentlichung: | 2019 |
| Verlag: | MDPI |
| Titel der Zeitschrift, Zeitung oder Schriftenreihe: | International Journal of Turbomachinery, Propulsion and Power |
| Jahrgang/Volume einer Zeitschrift: | 4 |
| (Heft-)Nummer: | 3 |
| Kollation: | 19 Seiten |
| DOI: | 10.26083/tuprints-00019089 |
| URL / URN: | https://tuprints.ulb.tu-darmstadt.de/19089 |
| Zugehörige Links: | |
| Herkunft: | Zweitveröffentlichungsservice |
| 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 η at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on η 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 η 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, η is increased by up to 11% for swirling inflow, while for axial inflow a further increase in coolant injection does not transfer into a gain in η. |
| Status: | Verlagsversion |
| URN: | urn:nbn:de:tuda-tuprints-190892 |
| Sachgruppe der Dewey Dezimalklassifikatin (DDC): | 600 Technik, Medizin, angewandte Wissenschaften > 620 Ingenieurwissenschaften und Maschinenbau |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet für Gasturbinen, Luft- und Raumfahrtantriebe (GLR) |
| Hinterlegungsdatum: | 02 Jul 2021 12:30 |
| Letzte Änderung: | 06 Jul 2021 05:29 |
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| Suche nach Titel in: | TUfind oder in Google |
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