Coating structure, turbine part having the coating structure, and manufacturing method of the coating structure
A manufacturing method and coating technology, which is applied in the direction of combustion method, blade support components, engine components, etc., can solve the problems such as inability to improve heat resistance, and achieve the effect of improving heat resistance
Active Publication Date: 2022-03-01
MITSUBISHI HEAVY IND LTD
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- Description
- Claims
- Application Information
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Problems solved by technology
However, when the alloy is used for the adhesive coating film like this, there is a problem that the heat resistance cannot be improved
Method used
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[0033] Hereinafter, embodiments of the present invention will be described with reference to the drawings, but the present invention is not limited thereto. Requirements of the respective embodiments described below can be appropriately combined. Also, some of the constituent elements are not used in some cases. In addition, the constituent elements of the embodiments described below include elements that can be easily replaced by those skilled in the art, or elements that are substantially the same. For example, in this embodiment, a turbine part of a gas turbine is described as an example, but the coating structure and the high-temperature parts having the coating structure of this embodiment can also be used for parts for other purposes. The coating structure of this embodiment and the high-temperature parts having the coating structure can be used, for example, as parts of flying objects.
[0034] figure 1 It is a schematic diagram showing an example of the gas turbine ...
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Abstract
The invention provides a coating construction, a turbine part having the coating construction, and a method of manufacturing the coating construction. A coating construction is provided on a surface of a base including a ceramic matrix composite material, having: a bond coat layered on the surface of the base, formed of a rare earth silicate; and a top coat layered on the bond coat, adhering The residual stress of the coating is compressive residual stress, and the oxygen transmission coefficient is 10 when the oxygen partial pressure on the side with the higher oxygen partial pressure is 0.02 MPa or higher at 1200°C or higher. ‑9 kg·m ‑1 ·s ‑1 the following. Sometimes the bond coat also contains carbonitride particles or carbonitride whiskers.
Description
technical field [0001] The present invention relates to a coating structure, a turbine part having the coating structure and a method of manufacturing the coating structure. Background technique [0002] Aircraft and industrial gas turbines, flying objects, etc. have parts that reach a temperature of 1000°C or higher. A technique of using parts made of ceramic matrix composites (CMC: Ceramic Matrix Composites) for parts (high temperature parts) used in parts that reach temperatures above 1000°C is being studied. In addition, a method of forming an environment-resistant coating (EBC: Environmental Barrier Coating) or a thermal barrier coating (TBC: Thermal Barrier Coating) on the surface of ceramic matrix composites is being studied as a structure to improve water vapor corrosion resistance and heat insulation. ) structure. [0003] In Patent Document 1, as a coating structure provided on the surface of a base material including a ceramic matrix composite material, the fo...
Claims
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IPC IPC(8): C04B41/89F01D5/18F01D25/00F01D25/24F02C7/00F23R3/42
CPCF02C7/00F23R3/42C04B41/89C04B41/00F01D5/288C04B41/009C04B41/52C04B41/5024C23C28/042C04B41/5096C04B41/5042C04B2103/0021C04B35/565C23C28/04F05D2300/6033F05D2300/611F05D2300/609C04B35/80C04B41/4539C04B41/5066C04B41/5067C04B41/522C04B41/5061C04B41/5068C04B2103/0017C04B41/4527F01D5/18F01D25/00F23R3/007F01D25/24C04B35/16C04B41/4596F01D5/14
Inventor 栗村隆之松本峰明谷川秀次辻良史
Owner MITSUBISHI HEAVY IND LTD