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Effusion Cooled Combustor Liner Tiles with Modern Cooling Concepts: A Comparative Experimental Study

Jackowski, Thomas and Schulz, Achmed and Bauer, Hans-Jörg and Gerendas, Miklos and Behrendt, Thomas (2016) Effusion Cooled Combustor Liner Tiles with Modern Cooling Concepts: A Comparative Experimental Study. In: Proceedings of the ASME Turbo Expo, pp. 1-13. ASME. ASME Turbo Expo 2016, 13.-17. Juni 2016, Seoul, Südkorea. DOI: 10.1115/GT2016-56598

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Abstract

Advanced combustion techniques in aero engines require highly effective cooling schemes of combustor liners. One Parameter affecting the cooling performance is the geometry of the cooling holes themselves. So far, the freedom in the design of cooling holes was limited due to the manufacturing techniques. With emerging additive manufacturing methods, e.g. Direct Metal Laser Sintering, however, the geometry of the cooling holes is virtually unlimited. Especially the entrance and the curvature of the cooling holes determines the through-flow of the hole and consequently the cooling performance of the ejected cooling film. In this study a set of combustor liner tiles with two innovative and four traditional cooling hole geometries will be analyzed and compared to each other in terms of cooling performance. The innovative geometries have bent cooling holes with a nearly horizontal outlet. All specimens have the same cooling hole pattern. The cooling performance is determined by comparing the total cooling effectiveness for a given pressure difference across the combustor liner tiles. The coolant mass flow rate is gained from experimentally determined discharge coefficients for the respective pressure difference. The first set of measurements is conducted in an atmospheric open-loop test rig at reduced temperatures but realistic density ratios between hot gas and coolant. The specimen with the best cooling performance has been selected for an investigation in a high pressure test rig at realistic combustor conditions (pressure, temperature) including fluctuations of the cooling air to simulate combustion instabilities. The cooling performance again is determined by the total cooling effectiveness for a given pressure difference across the combustor liner tiles.

Item URL in elib:https://elib.dlr.de/104947/
Document Type:Conference or Workshop Item (Speech)
Title:Effusion Cooled Combustor Liner Tiles with Modern Cooling Concepts: A Comparative Experimental Study
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Jackowski, ThomasKIT, Institut für thermische StrömungsmaschinenUNSPECIFIED
Schulz, AchmedKIT, Institut für thermische StrömungsmaschinenUNSPECIFIED
Bauer, Hans-JörgKIT, Institut für thermische StrömungsmaschinenUNSPECIFIED
Gerendas, MiklosRolls-Royce DeutschlandUNSPECIFIED
Behrendt, ThomasThomas.Behrendt (at) dlr.dehttps://orcid.org/0000-0002-4154-3277
Date:13 June 2016
Journal or Publication Title:Proceedings of the ASME Turbo Expo
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI :10.1115/GT2016-56598
Page Range:pp. 1-13
Publisher:ASME
Series Name:Turbo Expo Proceedings
Status:Published
Keywords:Gas turbine, combustor, cooling
Event Title:ASME Turbo Expo 2016
Event Location:Seoul, Südkorea
Event Type:international Conference
Event Dates:13.-17. Juni 2016
Organizer:ASME
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Combustion Chamber Technologies
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Combustor
Deposited By: Behrendt, Dr.-Ing. Thomas
Deposited On:12 Jul 2016 12:42
Last Modified:05 Feb 2018 11:08

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