航空發(fā)動(dòng)機(jī)葉片熱障涂層技術(shù)aircraft_enginer_tbc_benchmark(更新版)
【正文】 ct areas, transfers a small quantity of the electrode to the work piece to form a strong metallurgical bonding. 15 / Confidential/ 5/30/2022 Tech Roadmap 16 / Confidential/ 5/30/2022 Appendix 17 / Confidential/ 5/30/2022 Operating Condition of Turbine Blades Journey through a jet engine Fan LPC HPC HPT LPT 18 / Confidential/ 5/30/2022 Data for Turbine Blades ?High Temperature: ~1400oC ?High Pressure: ~40atm ?High Rotating Speed: ~11,000rpm ?Centrifugal force, airflow impact and vibration ?Oxidation and erosion ?Thermal Mechanical Cycling HPT blade lifetime: ?Currently: 16,000 hours (2~3years) ?Expected: 30,000+ hours Rough estimate of cost: ?A set of blades for HPT: gbp ?Refurbishment: to 1M gbp 19 / Confidential/ 5/30/2022 Mat paraamp。m Material Technique TBC top coat Thermally insulating Low k, high CTE, porous morphology 100~ 400 YSZ APS, EBPVD TGO Oxidation resistance Dense alumina 110 Al2O3 Bond Coat Aluminide, Solid adhesion, transition Gradient layer, Phase stability 50100 NiAl PtAl MCrAlY CVD,PackCem Plating, CVD VPS,HVOF,EB ? Rupture: CTE mismatch, sharp thermal gradient, thermomechanical cycling ? Delamination: TGO, degradation of bond coating, ? Incipient crack nucleateamp。 Failure Layer Function Requirement t/181。phase diagram ▲ Plot of k vs. CTE ? YttriaZirconia Phase Diagram 20 / Confidential/ 5/30/2022 Comparison of morphology
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