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Thermal barrier coating material, thermal barrier coating, turbine member, and gas turbine

A thermal insulation coating, gas turbine technology, applied in the coating, metal material coating process, mechanical equipment, etc., can solve the problems of ceramic layer peeling, destabilization, durability reduction, etc.

Active Publication Date: 2011-09-14
MITSUBISHI POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] When coating the moving blades, vanes, etc. of a gas turbine with a thermal barrier coating material having a ceramic layer containing the above-mentioned YSZ, a part of the above-mentioned ceramic layer may be peeled off during the operation of the gas turbine under severe operating conditions exceeding 1500°C. , impaired heat resistance
In addition, YSZ destabilizes at a temperature exceeding 1200°C, and the durability will be greatly reduced.

Method used

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  • Thermal barrier coating material, thermal barrier coating, turbine member, and gas turbine
  • Thermal barrier coating material, thermal barrier coating, turbine member, and gas turbine
  • Thermal barrier coating material, thermal barrier coating, turbine member, and gas turbine

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Effect test

Embodiment 1

[0039] The sintered bodies of the respective compositions shown in Table 1 were produced by the normal pressure sintering method under the conditions of sintering temperature 1600° C. and sintering time 5 hours. Raw material powder uses Yb 2 o 3 、Sm 2 o 3 , ZrO 2 .

[0040] The fracture toughness value of the sintered body of each composition was measured based on JISR1607. The thermal conductivity was measured based on the laser flash method prescribed in JIS R 1611. The structural phase of the sintered body before and after heat treatment at 1300°C for 1000 hours was identified by powder X-ray diffraction.

Embodiment 2

[0055] The thermal spray powder of each composition shown in Table 1 with a particle diameter of 10-125 micrometers was manufactured using the spray drying method. Using the above-mentioned thermal spraying powder, a test piece on which a heat-barrier coating layer was formed was produced by the following method.

[0056] Alloy metal base material (manufacturer: INCO company, trade name: IN-738LC, chemical composition: Ni-16Cr-8.5Co-1.75Mo-2.6W-1.75Ta-0.9Nb-3.4Ti-3.4Al (mass. %))) a metal bonding layer with a film thickness of 100 μm was formed by a low-pressure plasma spraying method. The composition of the metal bonding layer was Ni: 32% by mass, Cr: 21% by mass, Al: 8% by mass, Y: 0.5% by mass, and Co: the remainder.

[0057] The above-mentioned sprayed powder was sprayed on the metal bonding layer by atmospheric pressure plasma spraying to form a film, and a sprayed film (ceramic layer 13 ) with a film thickness of 0.5 mm was formed. For thermal spraying, a thermal spray...

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Abstract

Provided is a thermal barrier coating material which has more excellent high-temperature crystal stability than that of YSZ, and which exhibits high toughness and thermal barrier effect. Also provided are a thermal barrier coating which has a ceramic layer formed using the thermal barrier coating material and which exhibits excellent durability in terms of heat cycle, and a turbine member and a gas turbine which are each provided with the thermal barrier coating. The thermal barrier coating material comprises, as the main component, ZrO2 which contains both Yb2O3 and Sm2O3 as stabilizers, thetotal contents of the stabilizers being 2 to 7mol% and the content of Sm2O3 being 0.1 to 2.5mol%.

Description

technical field [0001] The present invention relates to a material for a heat barrier coating having excellent durability, and more particularly to a ceramic layer used as an outer coat of a heat barrier coating. Background technique [0002] In recent years, as one of energy-saving measures, studies have been made to improve the thermal efficiency of thermal power generation. In order to improve the power generation efficiency of the gas turbine for power generation, it is effective to increase the gas inlet temperature, and this temperature may be set to about 1500°C. In order to increase the temperature of such a power generation device, it is necessary to configure the stator blades and rotor blades constituting the gas turbine, or the wall materials of the combustor and the like with heat-resistant materials. But the material of the turbine blade is a heat-resistant metal, and even then it cannot withstand such a high temperature. Therefore, a thermal barrier coating ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C26/00C23C4/10F01D5/28
CPCC23C4/105C23C28/00F05B2230/90C23C4/04C04B2235/9607C04B2235/96F05D2230/90F01D5/288C04B2235/3224C23C28/04C04B35/486C23C28/3215C23C28/345C23C28/3455C23C4/11Y10T428/12618C23C26/00C23C4/10F01D5/28
Inventor 鸟越泰治永野一郎冈田郁生塚越敬三高桥孝二冈岛芳史霞总司伊藤荣作森一刚
Owner MITSUBISHI POWER LTD
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