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INFLUENCE OF THERMAL BARRIER COATING ROUGHNESS ON THE BOUNDARY LAYER STATE OF A HIGH-PRESSURE TURBINE VANE WITH HIGH ACCELERATION CLOSE TO RELAMINARIZATION

Petersen, Anna and Hilfer, Michael and Brakmann, Robin (2022) INFLUENCE OF THERMAL BARRIER COATING ROUGHNESS ON THE BOUNDARY LAYER STATE OF A HIGH-PRESSURE TURBINE VANE WITH HIGH ACCELERATION CLOSE TO RELAMINARIZATION. Deutscher Luft- und Raumfahrtkongress 2022, Dresden.

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Abstract

This paper addresses how an engine relevant 7YSZ-thermal barrier coating (TBC) influences the boundary layer due to roughness. Experimental investigations on a NGV at the wind tunnel for straight cascades Göttingen (EGG) are conducted. The vane is modified so that the shape is not influenced by the thickness of the TBC. The roughness is expected to influence the location of the separation and transition. The effects that are influencing the transition next to the roughness are a positive and negative pressure gradient, separation and interacting shocks. The influence of the TBC will be discussed on the appearance of turbulent wedges, the position and the length of the separation bubble as well as the transition location. Together with previous investigations, this study creates a comprehensive picture of the aerothermodynamics of a turbine vane. Unsteady flow phenomena on a TBC coated NGV are investigated using ultra-fast-response temperature sensitive paint (iTSP). This data set will be used as a benchmark for innovative future turbine vane designs including TBC and extensive cooling. Additionally, the results will be used as a validation data set for numerical models and their improvement.

Item URL in elib:https://elib.dlr.de/190363/
Document Type:Conference or Workshop Item (Speech)
Title:INFLUENCE OF THERMAL BARRIER COATING ROUGHNESS ON THE BOUNDARY LAYER STATE OF A HIGH-PRESSURE TURBINE VANE WITH HIGH ACCELERATION CLOSE TO RELAMINARIZATION
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Petersen, AnnaUNSPECIFIEDhttps://orcid.org/0000-0003-4819-4994UNSPECIFIED
Hilfer, MichaelUNSPECIFIEDhttps://orcid.org/0000-0002-2881-7130UNSPECIFIED
Brakmann, RobinUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Date:2022
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:high pressure turbine stator; cascade; separation; transition; iTSP; SPOD; Infrared Technique
Event Title:Deutscher Luft- und Raumfahrtkongress 2022
Event Location:Dresden
Event Type:national Conference
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Clean Propulsion
DLR - Research area:Aeronautics
DLR - Program:L CP - Clean Propulsion
DLR - Research theme (Project):L - Advanced Materials and New Manufacturing Technologies
Location: Göttingen
Institutes and Institutions:Institute of Propulsion Technology > Turbine
Institute for Aerodynamics and Flow Technology > Experimental Methods, GO
Deposited By: Petersen, Anna
Deposited On:28 Nov 2022 09:55
Last Modified:08 Dec 2022 16:51

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