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Experimental investigation of rotor tip film cooling at an axial turbine with swirling inflow consditions using pressure sensitive paint

Wilhelm, Manuel and Schiffer, Heinz-Peter (2019):
Experimental investigation of rotor tip film cooling at an axial turbine with swirling inflow consditions using pressure sensitive paint.
In: 13th European Turbomachinery Conference, Lausanne, Switzerland, April 8-12, 2019, [Online-Edition: http://www.euroturbo.eu/publications/proceedings-papers/etc2...],
[Conference or Workshop Item]

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.

Item Type: Conference or Workshop Item
Erschienen: 2019
Creators: Wilhelm, Manuel and Schiffer, Heinz-Peter
Title: Experimental investigation of rotor tip film cooling at an axial turbine with swirling inflow consditions using pressure sensitive paint
Language: English
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.

Divisions: 16 Department of Mechanical Engineering
16 Department of Mechanical Engineering > Institute of Gas Turbines and Aerospace Propulsion (GLR)
Event Title: 13th European Turbomachinery Conference
Event Location: Lausanne, Switzerland
Event Dates: April 8-12, 2019
Date Deposited: 15 Feb 2019 14:20
Official URL: http://www.euroturbo.eu/publications/proceedings-papers/etc2...
Identification Number: ETC2019-236
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