Patent application number | Description | Published |
20080261069 | HIGH TEMPERATURE COMPONENT WITH THERMAL BARRIER COATING - 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. | 10-23-2008 |
20090117282 | DIFFUSION ALUMINIDE COATING PROCESS - A method of applying a diffusion aluminide coating partially to a selective region more simply and conveniently, the method including a step of forming a metal aluminum film onto a selective region of the heat-resistant alloy substrate to be treated; and a step of applying a heat treatment to the heat-resistant alloy substrate on the selective region of which the metal aluminum film is formed and diffusing and penetrating aluminum in the metal aluminum film into the heat-resistant alloy substrate. | 05-07-2009 |
20090311103 | ROTOR FOR STEAM TURBINE AND METHOD OF MANUFACTURING THE SAME - A steam turbine rotor shaft and a method of manufacturing the same are provided wherein the sliding characteristics of a journal are improved, and the journal is free from welding cracks and does not need a post heat treatment. The low alloy steel coating layer having a better sliding characteristics than 9 to 13% Cr heat resisting steel and a area rate of defects including pores and oxides in a range of 3 to 15% is formed by a high velocity flame spray coating method on a sliding surface of the journal. | 12-17-2009 |
20100278645 | Seal Structure and Control Method Therefor - Provided are a seal structure and a control method therefor that can improve sealing performance between a rotating portion and a fixed portion, smoothly start up a steam turbine, and suppress the temperature rise of the rotating portion even if the rotating portion is continuously rotated for a long period of time. | 11-04-2010 |
20100330391 | HIGH-TEMPERATURE RESISTANT COMPONENT AND GAS TURBINE HOT PART - A high-temperature resistant component for a gas turbine hot part and so on is provided, which has durability and reliability enough to withstand a corrosive environment with use of the low-grade oil. The high-temperature resistant component includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance. | 12-30-2010 |
20110014035 | HIGH-RELIABILITY TURBINE METAL SEALING MATERIAL - A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant. | 01-20-2011 |
20110182720 | GAS TURBINE SHROUD WITH CERAMIC ABRADABLE COATINGS - There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas turbine ceramic abradable coating includes a bond layer, a thermal barrier ceramic layer, and a porous ceramic abradable layer (hardness may be RC15Y: 80±3). A slit groove is provided in the porous ceramic abradable layer by machining. A width of a rectangular section of the ceramic abradable layer divided by the slit groove may be set to a range of 2 to 7 mm. | 07-28-2011 |
20120084981 | METHOD OF WORKING COOLING HOLE OF TURBINE BLADE - In a method of working a film cooling hole which communicates with an internal cooling passage of a turbine blade from an outer surface, in the turbine blade which has a heat shield coating and the internal cooling passage, there is employed a method of working a cooling hole of a turbine including a step of executing a bond coat on a blade base material a step of piercing a cooling hole in accordance with an electric discharge machining, a step of executing a top coat, and a step of removing the top coat in accordance with a mechanical method with respect to a band-like region including a row of cooling holes, by using an abrasive blasting, a water jet method or the like. Accordingly, an occlusion of the cooling hole, and a damage of the TBC due to the piercing are hardly generated. | 04-12-2012 |
20120102966 | OPERATION CONTROL METHOD FOR GAS TURBINE AND OPERATION CONTROLLER FOR GAS TURBINE - An operation control method for a gas turbine comprising the steps of: making a molten salt map in a liquid phase state by calculating a dew point and a solidus temperature of molten salt for causing high-temperature corrosion on high-temperature components of the turbine due to impurities using a thermodynamic equilibrium calculation on the basis of the impurities contained in low-quality fuel and operation data of the gas turbine, indicating a surface temperature and a pressure of the high-temperature components of the turbine on the molten salt map to determine a superposition state thereof on a region of molten salt in a liquid phase, predicting a lifetime of the high-temperature components of the gas turbine by estimating a corrosion rate thereof, and controlling the flow rate of the low-quality fuel supplied to a combustor on the basis of the prediction of the lifetime of the high-temperature components so that an area of surface temperature and pressure regions of the high-temperature components superposing on the region of molten salt in the liquid phase on the molten salt map is reduced. | 05-03-2012 |
20120107103 | GAS TURBINE SHROUD WITH CERAMIC ABRADABLE LAYER - A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (hardness RC15Y: 80±3), the porous ceramic abradable layer is provided with slit grooves by machining work, and a slit groove width is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved. | 05-03-2012 |
20120159952 | GAS TURBINE COMPONENT HAVING THERMAL BARRIER COATING AND A GAS TURBINE USING THE COMPONENT - The present invention provides gas turbine components having durability and reliability for use in a corrosive environment such as a turbine employing a low grade fuel, and also provides a gas turbine equipped with the components. One of the components is a gas turbine bucket/nozzle comprising a substrate made from an alloy containing Ni, Co, or Fe, a bonding layer made from an alloy and disposed over the substrate, and a thermal barrier coating disposed over the bonding layer. The thermal barrier coating includes a thermal barrier layer of porous ceramics, an environmental barrier layer containing silica, and an impregnation layer having a silica-containing material in the pores of the porous ceramics. | 06-28-2012 |
20140064939 | HIGH-RELIABLITY TURBINE METAL SEALING MATERIAL - A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant. | 03-06-2014 |