Unlock instant, AI-driven research and patent intelligence for your innovation.

High temperature component with thermal barrier coating for gas turbine

A technology for gas turbines and high-temperature components, which is applied in the coating, engine components, and superimposed layers, etc., can solve problems such as reduction, achieve high-efficiency film cooling effect, and improve efficiency.

Inactive Publication Date: 2014-05-07
MITSUBISHI HITACHIPOWER SYST LTD
View PDF11 Cites 2 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although it varies depending on the conditions of use, in general, the substrate temperature can be reduced by 50 to 100°C by applying TBC

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • High temperature component with thermal barrier coating for gas turbine
  • High temperature component with thermal barrier coating for gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1）

[0029] As the substrate, prepare the gas turbine first-stage moving blade, which is made of nickel-based heat-resistant alloy IN738 (16%Cr-8.5%Co-3.4%Ti-3.4%Al-2.6%W-1.7%Mo-1.7%Ta-0.9 %Nb-0.1%C-0.05%Zr-0.01%B-the rest is Ni, wt%), with cooling air passages inside. In the moving blade, a plurality of cooling holes penetrating from the surface of the base body to the internal cooling passage are machined by electrical discharge machining. In addition, CoNiCrAlY alloy powder (Co-32%Ni-21%Cr-8%Al-0.5%Y, weight %) produced by a gas atomization method was prepared as a raw material powder having a substantially spherical shape and an average particle diameter of about 40 μm. The raw material powder is formed into a film on the surface of the combustion gas passage of the rotor blade using a cold spraying device. In terms of film forming conditions, nitrogen is used as the working gas, the gas pressure is 3 MPa, the gas temperature is 800° C., the powder supply rate is 20 g / min, and...

Embodiment 2）

[0033] figure 2 It is a schematic cross-sectional view of the main part of a gas turbine for power generation. The gas turbine includes, inside a gas turbine cylinder 48 : a rotating shaft (rotor) 49 located at the center; and a gas turbine unit 44 having moving blades 46 arranged around the rotating shaft 49 and stationary blades 45 supported on the cylinder 48 side. , and gas turbine shroud 47. The gas turbine includes: a compressor 50 connected to the gas turbine unit 44 , which sucks in atmospheric air to obtain compressed air for combustion and cooling medium; and a combustor 40 . The combustor 40 has a combustor nozzle 41 that mixes and injects the compressed air supplied from the compressor 50 and the supplied fuel (not shown), and combusts the mixed gas in the combustor flame tube 42 to generate high-temperature and high-pressure combustion gas. This combustion gas is supplied to the gas turbine 44 through a transition piece (transition piece) 43 , thereby causing a...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

PropertyMeasurementUnit
particle diameteraaaaaaaaaa
volume ratioaaaaaaaaaa
Login to View More

Abstract

The object of the present invention is to provide a high temperature component with a thermal barrier coating for a gas turbine. The most principal feature of the high temperature component having a thermal barrier coating and a cooling structure is as follows: micro passages are provided inside in an alloy bottom layer and a thermal insulation ceramic layer of the thermal battier coating, and are in communication from a substrate side to a surface side. Moreover, a partial amount of coolant of a coolant for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.

Description

technical field [0001] The present invention relates to high-temperature components for gas turbines, such as rotor blades, combustors, and shrouds of gas turbines, which have a heat-shielding coating excellent in heat resistance. Background technique [0002] The operating temperature of gas turbines increases year by year for the purpose of improving efficiency. In order to cope with the increase in operating temperature, high-temperature parts of gas turbines use materials with excellent heat resistance, and adopt a structure that cools the surface opposite to the surface exposed to combustion gas with a fluid coolant such as air or steam. In addition, for the purpose of relaxing the temperature environment, a thermal barrier coating (Thermal Barrier Coating: hereinafter referred to as TBC) made of ceramics with low thermal conductivity is applied to the surface. Although it varies depending on the usage conditions, in general, the substrate temperature can be lowered by...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): C23C24/04C23C4/10C23C4/12F01D5/18F01D9/02F01D25/08
CPCF01D5/288C23C4/085C23C24/087F01D5/186C23C28/3215F01D5/183C23C24/04C23C24/08C23C4/08C23C28/3455F01D5/18C23C4/073
Inventor 有川秀行儿岛庆享粕谷忠目幡辉市川国弘远藤宏之远藤孝夫
Owner MITSUBISHI HITACHIPOWER SYST LTD