IGTC-38 PVD-Overlay Coatings for Blades and Vanes of Advanced Aircraft Engines(Session B-6 AIRCRAFT ENGINES II)
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概要
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Gas turbine performance and fuel consumption are strongly dependent upon operating temperatures, which must be closely correlated to the properties of the superalloy materials used in fabricating turbine blades. Cooling blades by providing air ducts and employing directional solidification techniques to increase the abilities of blades to withstand high temperatures have allowed raising the operating temperatures of turbines equipped with nickel-base superalloy blades, with no significant changes in blade materials observed. The technological challenge presented by the coming generation of high-performance turbine engines lies in the need to develop new high-temperature materials and new or improved overlay coatings. Use of modern PVD coating methods in combination with new types of blade materials and optimized blade cooling systems allows increasing temperatures in gas turbine hot-gas sections by several hundred℃, significantly improving turbine operating efficiencies. Overlay coatings are currently deposited by plasma spraying both at atmospheric pressure and under vacuum, as well as by vacuum evaporation methods. EB vacuum evaporation has been shown to yield PVD coatings having excellent properties, particularly in the case of thermal-barrier coatings. This paper reviews EB-PVD and competing technologies for coating gas turbine blades and factors involved in EB-PVD coating blades on mass production scales. Using a fully automated EB-PVD system equipped for coating batches of 11 blades per deposition cycle as an example, we illustrate how critical processing requirements can be met for both MCrAlY and ceramic (YSZ) overlays.
- 公益社団法人日本ガスタービン学会の論文
著者
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Feuerstein A.
Engineering Coatings Department
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Lammermann H.
High-Rate Electron-Beam Evaporation Systems