Journal
INTERNATIONAL JOURNAL OF TURBOMACHINERY PROPULSION AND POWER
Volume 4, Issue 3, Pages -Publisher
MDPI
DOI: 10.3390/ijtpp4030023
Keywords
combustor-turbine interaction; rotor blade tip; swirl; film cooling; pressure sensitive paint
Categories
Funding
- Federal Republic of Germany, Ministry for Economic Affairs and Energy [FKZ: 03ET7021K]
- Rolls-Royce Deutschland GmbH
- Ansaldo Energia Switzerland AG
- Euroturbo Association
Ask authors/readers for more resources
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 into a gain in eta.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available