Patent application number | Description | Published |
20100111704 | TURBINE BLADE HAVING SQUEALER - A turbine blade of the invention includes an air foil including a plurality of cooling flow passages through which a cooling medium flows from a leading edge region to a trailing edge region, a top plate which forms the apex of the air foil, has a heat-resistant coating applied on the upper surface thereof, and includes a plurality of cooling holes, and a squealer which protrudes radially outward from the blade from the top plate, and is formed so as to extend from a leading edge end to a starting end of the trailing edge region along a suction-surface-side blade wall in a peripheral direction of the blade. | 05-06-2010 |
20110044805 | COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas. | 02-24-2011 |
20110107105 | MESSAGE SENDING/RECEIVING METHOD - Provided is a message sending method for sending a message by a process of a computer including a processor and a memory. The method includes the steps of: randomizing a signature generation key sk_s with a random number r to calculate a randomized signature generation key sk′_s=SigningKeyRandomize(sk | 05-05-2011 |
20110182724 | COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region which are disposed adjacent to the end portion on a rear side in a rotation direction, and cooling passages of a second region which are disposed on a farther front side in the rotation direction than the first-region cooling passages and have a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages. The first-region cooling passages are disposed adjacent to the second cooling passages of the neighboring segment body. | 07-28-2011 |
20110217180 | GAS TURBINE BLADE, MANUFACTURING METHOD THEREFOR, AND GAS TURBINE USING TURBINE BLADE - Provided are gas turbine blades in which it is possible to simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. In a gas turbine blade, cooling channels provided in the interior thereof include a plurality of straight channel-like base-side elongated holes that extend in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes that extend in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions that are interposed at connection portions between the two types of elongated holes to individually allow the two types of elongated holes to communicate with each other and that have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. In addition, the communicating hollow portions are formed so as to match the position of a platform portion of the turbine blade. | 09-08-2011 |
20110217181 | GAS TURBINE BLADE, MANUFACTURING METHOD THEREFOR, AND GAS TURBINE USING TURBINE BLADE - Provided are gas turbine blades in which it is possible to simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. In a gas turbine blade ( | 09-08-2011 |
20110255989 | Cooling system of ring segment and gas turbine - In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combustion gas than the openings on the upstream. | 10-20-2011 |
20120230838 | TURBINE BLADE AND GAS TURBINE - Provided is a turbine blade including: a platform; a blade body including a cooling flow channel including a meandering serpentine cooling flow channel; a fillet portion provided in a joint surface between the blade body and the platform; and a base portion including a cooling flow channel communicated with the serpentine cooling flow channel. The cooling flow channel includes a bypass flow channel that is branched off from a high-pressure part of the cooling flow channel, passes through along the inside of the fillet portion, and is connected to a low-pressure part of the cooling flow channel. | 09-13-2012 |
20120247125 | COMMUNICATING STRUCTURE BETWEEN COMBUSTOR AND TURBINE PORTION AND GAS TURBINE - In a communicating structure between combustors that generates combustion gas inside pipe pieces and a turbine portion that generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of turbine stator vanes and turbine rotor blades, at least some of the first-stage turbine stator vanes closest to the combustor among the turbine stator vanes are disposed downstream of sidewalls of one pipe piece and another pipe piece that are adjacent to each other, and the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the sidewalls of the pipe pieces to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the one pipe piece and an internal surface of the sidewall of the other pipe piece. | 10-04-2012 |
20120263603 | TURBINE BLADE AND GAS TURBINE - A turbine blade includes: a base portion fixed to a rotor; a platform that is fixed to the base portion and includes a cooling flow channel; a blade shape portion that extends from the platform to an outer side in a radial direction; and a fillet portion provided in a joint surface between the blade shape portion and the platform, and the turbine blade further includes: a main pipe that is branched off from the cooling flow channel and has an opening at a side end portion of the platform; and a branch pipe that is branched off from the main pipe, extends along the fillet portion so as to be close thereto on an inner side in the radial direction, and includes a film cooling hole opened on a surface of the platform. | 10-18-2012 |
20130074502 | TRANSITION PIECE OF COMBUSTOR, GAS TURBINE HAVING THE SAME, AND PRODUCING METHOD FOR TRANSITION PIECE - A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove. | 03-28-2013 |
20130209271 | GAS TURBINE BLADE, MANUFACTURING METHOD THEREFOR, AND GAS TURBINE USING TURBINE BLADE - Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade. | 08-15-2013 |
20130315725 | TURBINE VANE - In a turbine vane and a gas turbine, an outer shroud is fixed to one end of a vane body formed in a hollow shape, an inner shroud is fixed to the other end thereof, and a partition plate is fixed to the inner portions of the vane body, the outer shroud, and the inner shroud, so that a cavity is formed so as to be continuous between the partition plate and the group of the vane body, the outer shroud, and the inner shroud. Then, the vane body, the outer shroud, and the inner shroud are provided with a plurality of cooling holes, and the partition plate is provided with a plurality of penetration holes. Accordingly, since the vane structure or the end wall structure is evenly cooled, a deformation or damage may be suppressed. | 11-28-2013 |
20130339743 | MESSAGE SENDING/RECEIVING METHOD - Provided is a message sending method for sending a message by a process of a computer including a processor and a memory. The method includes the steps of: randomizing a signature generation key sk_s with a random number r to calculate a randomized signature generation key sk′_s=SigningKeyRandomize(sk_s, r); encrypting the random number r with a public encryption key pk_e to calculate an encrypted random number R=Enc(pk_e, r); signing a message m with the randomized signature generation key sk′_s to calculate a signed message s′=Sign(sk′_s, m); and sending the signed message s′ and the encrypted random number R to a recipient, where sk_s represents the secret signature generation key of a sender of the message m, pk_e represents the public encryption key of the recipient, r represents the random number, s represents a signature, Sign represents a signature generation function, s=Sign(sk_s, m) represents a signature for the message m, SigningKeyRandomize represents a function for randomizing the secret signature generation key sk_s, and Enc represents an encryption function. | 12-19-2013 |
20140234077 | COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas. | 08-21-2014 |
20140324834 | Providing Path-Level Access Control for Structured Documents Stored in a Database - An improved method and system for providing path-level access control to a structured document in a collection stored in a database, where the structured document includes a plurality of nodes is disclosed. The method includes the steps of providing an access control policy for the collection, where the access control policy comprises a plurality of access control rules, generating a path for each node of the plurality of nodes in the document, and generating for each path associated with a node a corresponding value expression based on at least one access control rule of the plurality of access control rules. According to the method and system of the present invention, the corresponding value expression is utilized during access control evaluation to determine whether a user is allowed to access a node in the structured document. | 10-30-2014 |