Patent application number | Description | Published |
20110027102 | COOLING STRUCTURE OF TURBINE AIRFOIL - A cooling structure of a turbine airfoil cools a turbine airfoil ( | 02-03-2011 |
20120201694 | TURBINE BLADE - Disclosed is a turbine blade capable of being cooled by a coolant gas supplied to a hollow region, wherein a plurality of meandering flow paths that guide the coolant gas between the suction wall surface and the pressure wall surface while causing the coolant gas to repeatedly meander are continuously arranged from the hub side toward the tip side of the turbine blade, and the meandering flow paths adjacent to each other cause the coolant gas to meander in different repetitive patterns. | 08-09-2012 |
20140003962 | TURBINE BLADE | 01-02-2014 |
20140020393 | COMBUSTOR FOR GAS TURBINE ENGINE AND GAS TURBINE - A combustor for gas turbine engine, wherein: a plurality of impingement-cooling holes are opened passing through an external wall of a liner for cooling air to blow out towards the outer surface of an internal wall of the liner; a plurality of pin-fins are formed on the outer surface of the internal wall of the liner; a plurality of effusion cooling holes are opened passing through the internal wall of the liner for cooling air to blow out along the inner surface of the internal wall of the liner. The top surface of each pin-fin is not in contact with the inner surface of the external wall of the liner and the ratio of the height of the pin-fin to the equivalent diameter of the impingement-cooling hole is set to be 1.0-3.0. | 01-23-2014 |
20140234121 | FILM COOLING STRUCTURE AND TURBINE BLADE - The film cooling structure includes: a wall surface along which a heating medium flows; and at least one pair of film cooling holes that open at the wall surface and that blow a cooling medium. The pair of film cooling holes are arranged to be adjacent to each other in a main flow direction of the heating medium. In addition, perforation directions of the pair of film cooling holes are set such that directions of swirls of the cooling medium formed by blowing are opposite to each other, a swirl of the cooling medium on a downstream side in the main flow direction is mixed and merged with another swirl of the cooling medium on an upstream side in the main flow direction, and the merged cooling medium flows along the wall surface in a direction intersecting with the main flow direction. | 08-21-2014 |
20140238028 | IMPINGEMENT COOLING MECHANISM, TURBINE BLADE, AND COMBUSTOR - It has a flat impingement hole ( | 08-28-2014 |
20140238031 | COMBUSTOR LINER - The invention is a combustor liner ( | 08-28-2014 |
20140271229 | TURBINE BLADE - The present invention is a turbine blade ( | 09-18-2014 |
20140290256 | IMPINGEMENT COOLING MECHANISM, TURBINE BLADE AND COMBUSTOR - The present invention relates to an impingement cooling mechanism that ejects a cooling gas toward a cooling target ( | 10-02-2014 |
20140290257 | IMPINGEMENT COOLING MECHANISM, TURBINE BLADE AND CUMBUSTOR - The present invention relates to an impingement cooling mechanism ( | 10-02-2014 |
20140294598 | TURBINE BLADE - The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole. | 10-02-2014 |
20140366545 | GAS TURBINE ENGINE - In a gas turbine engine ( | 12-18-2014 |