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Heat-resistant component with heat insulation coating

A technology of covering layer and heat insulation layer, which is applied in the direction of plating of superimposed layers, supporting elements of blades, coating, etc., can solve the problems of reduced mechanical properties of heat-resistant alloy matrix materials, low strength of metamorphic layers, etc., and achieve reliability Excellent, sufficient durability, and the effect of realizing high temperature

Active Publication Date: 2008-10-22
MITSUBISHI POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0011] Since the metamorphic layer usually produced by this interdiffusion is brittle and also has low strength, it is possible that the mechanical properties of the heat-resistant alloy base material will be reduced

Method used

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  • Heat-resistant component with heat insulation coating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0075] As the test piece base material, a disc-shaped Ni-based heat-resistant alloy with a diameter of 25 mm and a thickness of 5 mm (by weight, C: 0.03% to 0.20%, B: 0.004% to 0.050%, Hf: 0.01% to 1.50% % or less, Zr: 0% to 0.02%, Cr: 1.5% to 16.0%, Mo: 0.4% to 6.0%, W: 2% to 12%, Re: 0.1% to 9.0%, Ta: 2% to 12%, Nb: 0.3% to 4.0%, Al: 4.0% to 6.5%, Ti: 0% to 0.4%, Co: 0.5% to 9.0%, and the rest are basically Ni; Specifically, by weight, C: 0.11%, B: 0.025%, Hf: 0.75%, Zr: 0.01%, Cr: 7.5%, Mo: 2.8%, W: 6%, Re: 4.5%, Ta: 6.5%, Nb: 2.1%, Al: 5.2%, Ti: 0.2%, Co: 4.5% and the rest are basically single crystal materials of Ni), using NiCrAl alloy (Ni-22wt%Cr-10wt% The Al) powder was formed into a bonding layer by plasma spraying in a reduced-pressure atmosphere, and a heat treatment at 1121° C. for 4 hours in vacuum was performed as a diffusion heat treatment.

[0076] The thickness of the bonding layer is about 100 μm. Then, yttria is used to partially stabilize zirconia (ZrO ...

Embodiment 2

[0084] Using the same test piece base material as in Example 1, use the NiCrAl alloy (Ni-22wt%Cr-10wt%Al) powder and NiCrAlSi alloy (Ni-22wt%Cr-10wt%Al-1wt%Al) powder of the present embodiment on its surface %Si) powder, form a bonding layer by plasma spraying in a reduced-pressure atmosphere, and perform a heat treatment at 1121° C. for 4 hours in vacuum as a diffusion heat treatment.

[0085]The thickness of the bonding layer is about 100 μm. Then, the following four methods are used to form yttria partially stabilized zirconia (ZrO 2 -8wt%Y 2 o 3 ) insulation layer.

[0086] The first method is to form a heat insulating layer with a porosity of about 10% by plasma spraying in the atmosphere.

[0087] The second method is to form a porous heat insulating layer with a porosity of about 20% by plasma spraying in the atmosphere.

[0088] The third method: form a heat insulating layer with longitudinal cracks by plasma spraying in the atmosphere.

[0089] The fourth method...

Embodiment 3

[0102] A rotor blade of a gas turbine equipped with a TBC according to the present embodiment was produced. Figure 4 A perspective view showing the overall structure of a rotor blade of a gas turbine is shown.

[0103] Figure 4 In this gas turbine, the rotor blade is a single crystal material of a Ni-based heat-resistant alloy (the composition of which is the same as that shown in Example 1), for example, as the primary Rotating blades are used, having a blade part 61 , a platform part 62 , a body part 63 , sealing tabs 64 , chip pockets 65 , mounted on a disc by means of dovetail slots 66 .

[0104] In addition, the blade portion 61 of the rotor blade of the gas turbine has a length of 100 mm, and the length below the platform portion 42 is 120 mm. The gas turbine rotor blade is passed through a refrigerant for cooling from the inside, especially for allowing air or water vapor to pass through. Cooling holes (not shown) leading from the dovetail groove 66 to the blade por...

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Abstract

A ceramic top coat is formed over a heat resistant alloy including Ni as a main component through a bond coat which contains Ni essentially as a main component, Cr, and Al. The alloy for the bond coat can include Si in the range from 0 to 10 wt.%. As a result, in a long time operation, the spalling damage of a ceramic top coat is not easily created and the deterioration of the mechanical properties is small.

Description

technical field [0001] The present invention relates to a heat-resistant member for a gas turbine with a heat-insulating coating, in particular to a heat-resistant member for a gas turbine with a heat-insulating coating whose heat-resistant alloy base material includes a Ni-based heat-resistant superalloy containing Ni as a main component. Background technique [0002] The operating temperature of gas turbines is increasing year by year for the purpose of improving efficiency. In order to cope with such high temperature, castings of various Ni-based superalloys with excellent high-temperature strength are used for some parts of gas turbines. In addition, in order to improve the high-temperature strength of castings, in addition to ordinary casting materials, directionally solidified materials are also used. Columnar crystal materials and single crystal materials (for example, refer to Patent Document 1). [0003] In addition, for the purpose of reducing the temperature of g...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B15/04B32B9/00B32B33/00C22C19/05F01D25/00
CPCY02T50/671C23C28/00F05D2300/12C23C28/3215C22C19/05Y02T50/67F05D2300/132C23C4/18C23C28/3455F05C2201/0466C23C4/105F01D5/288C23C4/085F05D2300/21C23C30/00C23C28/325C23C4/11C23C4/073Y10T428/12535Y10T428/12611Y02T50/60
Inventor 有川秀行目幡辉儿岛庆享市川国弘
Owner MITSUBISHI POWER LTD
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