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Degradation study of 7YSZ TBCs on Aero-engine Combustion Chamber parts due to Infiltration by different CMAS variants

Naraparaju, Ravisankar and Schulz, Uwe and Mechnich, Peter and Döbber, Philipp and Seidel, Frank (2014) Degradation study of 7YSZ TBCs on Aero-engine Combustion Chamber parts due to Infiltration by different CMAS variants. ICMCTF 2014, 28.April-02.May 2014, San Diego, USA.

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Abstract

At temperatures above 1200°C, ingested sand and debris particles melt on the TBC surfaces of aero-engine combustion chamber parts and form calcium-magnesium-alumino silicate (CMAS) deposits. The composition and melting point of CMAS vary according to the source and location of the sand and debris. A damage assessment of TBC coated combustion chamber parts of aero-engines after service in CMAS loaded areas was performed in this study. Parts from different aero-engines were investigated by SEM and the extent of damage of the 7YSZ plasma-sprayed TBC due to CMAS deposition and infiltration was estimated. With the help of SEM and EDS, CMAS chemical composition was analyzed and two different typical chemical compositions of CMAS were derived. These model CMAS compositions were synthesized in laboratory and their melting behaviour was determined by means of DSC. Both CMAS variants were subsequently deposited on air plasma sprayed yttria stabilized zirconia (APS-7YSZ) TBC specimens. Samples were subjected to isothermal heat treatments in air at temperatures ranging from 1200°C to 1250°C for times between 10 h and 100 h. The phase formations and microstructural changes were examined by SEM and XRD. Results from the CMAS/TBC interaction experiments could duplicate with the damage patterns on the real combustion chamber parts. Furnace cycle tests (FCT) were conducted at 1135°C on TBC coated buttons with and without CMAS. The extent of TBC damage strongly correlates to the CMAS composition. The presence of Ca-sulfate (CaSO4, anhydrite) in the CMAS plays a large role in damaging the 7YSZ and infiltration depth of CMAS. With raising temperature, the depth of infiltration increases rapidly and the CMAS has penetrated completely throughout the TBC thickness at 1250°C. In addition, the time to failure of the TBCs strongly depended on the type of CMAS deposited. The life time of the samples with CaSO4 containing CMAS was found to be the lowest compared to the samples without CMAS and with the CaSO4 free CMAS variant.

Item URL in elib:https://elib.dlr.de/95288/
Document Type:Conference or Workshop Item (Speech)
Additional Information:This work is reviewd
Title:Degradation study of 7YSZ TBCs on Aero-engine Combustion Chamber parts due to Infiltration by different CMAS variants
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Naraparaju, Ravisankarravisankar.naraparaju (at) dlr.deUNSPECIFIED
Schulz, Uweuwe.schulz (at) dlr.deUNSPECIFIED
Mechnich, Peterpeter.mechnich (at) dlr.deUNSPECIFIED
Döbber, Philippphilip.doebber (at) mtu.deUNSPECIFIED
Seidel, Frankfrank.seidel (at) mtu.deUNSPECIFIED
Date:1 May 2014
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:CMAS, APS 7YSZ
Event Title:ICMCTF 2014
Event Location:San Diego, USA
Event Type:international Conference
Event Dates:28.April-02.May 2014
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 - Turbine Technologies
Location: Köln-Porz
Institutes and Institutions:Institute of Materials Research > High Temperature and Functional Coatings
Deposited By: Naraparaju, Dr Ravisankar
Deposited On:09 Apr 2015 13:29
Last Modified:23 Sep 2015 13:56

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