TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ
Thermal Barrier Coatings (TBCs) are multi-layer protective coatings used in the hot section components such as combustor and turbine of advanced gas turbine engines to protect them from degrading affects of hot gases. Today, due to lack of a reliable life time assessment, the potential of these co...
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| Format: | Article |
| Language: | English |
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Turkish Air Force Academy
2009-07-01
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| Series: | Havacılık ve Uzay Teknolojileri Dergisi |
| Subjects: | |
| Online Access: | http://www.jast.hho.edu.tr/JAST/index.php/JAST/article/view/206/195 |
| _version_ | 1797910438901448704 |
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| author | Serdar Dalkılıç A. Akide Tanatmış |
| author_facet | Serdar Dalkılıç A. Akide Tanatmış |
| author_sort | Serdar Dalkılıç |
| collection | DOAJ |
| description | Thermal Barrier Coatings (TBCs) are multi-layer protective coatings used in the hot section components such as
combustor and turbine of advanced gas turbine engines to protect them from degrading affects of hot gases.
Today, due to lack of a reliable life time assessment, the potential of these coatings cannot be fully used.
Understanding of damage mechanisms of thermal barrier coatings is the key factor to increase durability and
reliability.
In this paper TBCs are shortly introduced and then damages resulting from high temperature low cycle fatigue
tests and their probable reasons have been explained. Inconel 100, a directionally solidified nickel based
superalloy as a substrate, approximately 120 μm thick NiCoCrAlY bond coat and approximately 200 μm thick 7
wt % Yttria Stabilized Zirconia ceramic top coat have been used. Both layers are deposited by EB-PVD
technique. The results of the tests show that number and the size of the cracks changes with the strain range.
Cracks initiate in the TGO/BC interface and propagate into the substrate perpendicularly to the loading axes.
Ceramic thermal barrier coating retards the formation of cracks. On the surfaces of the specimens having only
bond coat, rumpling which is a typical service damage of turbine blades has been detected. |
| first_indexed | 2024-04-10T11:24:21Z |
| format | Article |
| id | doaj.art-4ba8c2dd443249b6b010247fcf29ba43 |
| institution | Directory Open Access Journal |
| issn | 1304-0448 1304-0448 |
| language | English |
| last_indexed | 2024-04-10T11:24:21Z |
| publishDate | 2009-07-01 |
| publisher | Turkish Air Force Academy |
| record_format | Article |
| series | Havacılık ve Uzay Teknolojileri Dergisi |
| spelling | doaj.art-4ba8c2dd443249b6b010247fcf29ba432023-02-15T16:18:27ZengTurkish Air Force AcademyHavacılık ve Uzay Teknolojileri Dergisi1304-04481304-04482009-07-01421527TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİSerdar Dalkılıç0A. Akide Tanatmış1Anadolu UniversityAnadolu UniversityThermal Barrier Coatings (TBCs) are multi-layer protective coatings used in the hot section components such as combustor and turbine of advanced gas turbine engines to protect them from degrading affects of hot gases. Today, due to lack of a reliable life time assessment, the potential of these coatings cannot be fully used. Understanding of damage mechanisms of thermal barrier coatings is the key factor to increase durability and reliability. In this paper TBCs are shortly introduced and then damages resulting from high temperature low cycle fatigue tests and their probable reasons have been explained. Inconel 100, a directionally solidified nickel based superalloy as a substrate, approximately 120 μm thick NiCoCrAlY bond coat and approximately 200 μm thick 7 wt % Yttria Stabilized Zirconia ceramic top coat have been used. Both layers are deposited by EB-PVD technique. The results of the tests show that number and the size of the cracks changes with the strain range. Cracks initiate in the TGO/BC interface and propagate into the substrate perpendicularly to the loading axes. Ceramic thermal barrier coating retards the formation of cracks. On the surfaces of the specimens having only bond coat, rumpling which is a typical service damage of turbine blades has been detected.http://www.jast.hho.edu.tr/JAST/index.php/JAST/article/view/206/195Gas turbineThermal Barrier CoatingLow Cycle Fatigue |
| spellingShingle | Serdar Dalkılıç A. Akide Tanatmış TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ Havacılık ve Uzay Teknolojileri Dergisi Gas turbine Thermal Barrier Coating Low Cycle Fatigue |
| title | TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ |
| title_full | TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ |
| title_fullStr | TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ |
| title_full_unstemmed | TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ |
| title_short | TERMAL BARİYER KAPLAMA SİSTEMLERİNDE YÜKSEK SICAKLIKTA DÜŞÜK ÇEVRİMLİ YORULMA ŞARTLARI ALTINDA OLUŞAN HASARLARIN İNCELENMESİ |
| title_sort | termal bariyer kaplama sistemlerinde yuksek sicaklikta dusuk cevrimli yorulma sartlari altinda olusan hasarlarin incelenmesi |
| topic | Gas turbine Thermal Barrier Coating Low Cycle Fatigue |
| url | http://www.jast.hho.edu.tr/JAST/index.php/JAST/article/view/206/195 |
| work_keys_str_mv | AT serdardalkılıc termalbariyerkaplamasistemlerindeyukseksicakliktadusukcevrimliyorulmasartlarialtindaolusanhasarlarinincelenmesi AT aakidetanatmıs termalbariyerkaplamasistemlerindeyukseksicakliktadusukcevrimliyorulmasartlarialtindaolusanhasarlarinincelenmesi |