IGTC-95 PERFORMANCE OF THERMAL BARRIER COATING FOR GAS TURBINE AIRFOIL IN ENGINE TEST(Session C-4 Material and Manufacturing I)

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概要

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• Effect and durability of thermal barrier coating (TBC) performed on the surface of a gas turbine high pressure first vane by plasma spraying was investigated in a 300 hour engine test. A 200 micron thick ZrO_2 ceramic layer was found to be effective as thermal barrier to give longer life to vane material which was under critical conditions during the test. No fatal TBC damage was observed after the test. TBC showed high durability to large strain induced by vane material deformation. To determine its durability further, a small tablet specimen thermal fatigue test was also performed. The role of the bond metal, which was arranged between ceramic layer and base metal, was emphasized for long range TBC durability.

• 公益社団法人日本ガスタービン学会の論文

著者

• Shimotori K.

  Toshiba Research And Development Center

• Takeda H.

  Toshiba Research and Development Center

• Baba H.

  Toshiba Turbine Works

• Suzuki T.

  Toshiba Research and Development Center

• Takahara K.

  National Aerospace Laboratory

• Yoshida T.

  National Aerospace Laboratory

関連論文

• IGTC-95 PERFORMANCE OF THERMAL BARRIER COATING FOR GAS TURBINE AIRFOIL IN ENGINE TEST(Session C-4 Material and Manufacturing I)
• IGTC-18 / ASME-83-GTJ-8 ON THE NATURE OF JETS ISSUING FROM A ROW OF HOLES INTO A LOW REYNOLDS NUMBER MAINSTREAM FLOW(Session A-5 Heat Transfer V (Film Cooling))
• IGTC-7 UNSTEADY TEMPERATURE ANALYSIS OF AIR-COOLED TURBINE VANES(Session A-2 Heat Transfer II (Unsteady))

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