| Patent application number | Description | Published |
|---|
| 20080289341 | Combustor of Gas Turbine - A combustor | 11-27-2008 |
| 20090202339 | PLATFORM COOLING STRUCTURE FOR GAS TURBINE MOVING BLADE - A platform cooling structure for a gas turbine moving blade is provided which is capable of improving cooling performance of a platform and of improving reliability of a moving blade in such a manner that a portion in the vicinity of a side edge of the platform which is away from moving blade cooling passageways and is easily influenced by thermal stress caused by high-temperature combustion gas, that is, an upper surface of the side edge is effectively cooled by guiding high-pressure cooling air, flowing to the moving blade cooling passageways, to a discharge opening formed in a surface of the platform in the vicinity of the side edge of the platform without particularly attaching an additional member such as a cover plate to the platform. A moving blade cooling passageway | 08-13-2009 |
| 20100047065 | BLADE STRUCTURE OF GAS TURBINE - To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section | 02-25-2010 |
| 20100196154 | TURBINE BLADE CASCADE ENDWALL - Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade. | 08-05-2010 |
| 20100217540 | METHOD FOR ESTIMATING PHYSICAL PROPERTY OF CERAMIC, METHOD FOR ESTIMATING PHYSICAL PROPERTY OF THERMAL BARRIER COATING, METHOD FOR ESTIMATING REMAINING LIFETIME OF THERMAL BARRIER COATING, METHOD FOR ESTIMATING REMAINING LIFETIME OF HIGH-TEMPERATURE MEMBER, AND PHYSICAL PROPERTY ACQUIRING APPARATUS - A method is provided by which physical properties, in particular, the Young's modulus and thermal conductivity of a ceramic layer of a thermal barrier coating formed on a high-temperature member are accurately estimated in a short period of time. A method for estimating a physical property of a ceramic includes a step of calculating the Larson-Miller parameter from the time for which and the temperature at which the ceramic is heated; a step of acquiring the porosity of the ceramic corresponding to the calculated Larson-Miller parameter, based on the calculated Larson-Miller parameter and a diagram correlating the Larson-Miller parameter and the porosity obtained from samples having the same composition as the ceramic; and a step of acquiring the physical property of the ceramic corresponding to the acquired porosity, based on the acquired porosity and a diagram correlating the porosity and the physical property obtained from samples having the same composition as the ceramic. | 08-26-2010 |
| 20100284818 | TURBINE BLADE CASCADE ENDWALL - Provided is a turbine blade cascade endwall that is capable of reducing crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, therefore being capable of achieving enhanced turbine performance. A convex portion ( | 11-11-2010 |
| 20110262770 | THERMAL BARRIER COATING MATERIAL, THERMAL BARRIER COATING, TURBINE MEMBER, AND GAS TURBINE - A thermal barrier coating material that exhibits superior high-temperature crystal stability to YSZ, as well as a high degree of toughness and an excellent thermal barrier effect. Also provided are a thermal barrier coating, which has a ceramic layer formed using the thermal barrier coating material and exhibits excellent durability to heat cycling, and a turbine member and a gas turbine which are each provided with the thermal barrier coating. The thermal barrier coating material comprises mainly ZrO | 10-27-2011 |
| 20120014832 | Ni-BASED SINGLE CRYSTAL SUPERALLOY - The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass,
| 01-19-2012 |
