Abstract: A gas turbine moving blade steam cooling system in which leakage of steam for cooling a moving blade is prevented and thermal stress at a blade root end portion is mitigated. Each end portion of a blade root portion (3) of the moving blade (1) is projected so as to form a projection portions (4a, 4b). A steam passage 5 is provided between the projection portions (4a, 4b) and a steam supply port 5a and a steam recovery port (5b) are provided downwardly with the respect to the steam passage 5. The steam supply port (5a) connects to a steam supply passage (20) and the steam recovery port (5b) connects to a steam recovery passage (21). Steam is supplied from the steam supply port (5a) into a blade interior and is recovered through the steam recovery port (5b). Side surface seal plates (6, 7 and 8) are provided for preventing steam leakage.

Abstract: A gas turbine shroud and platform seal system, which is constructed so that the flow of sealing air does not disturb a combustion gas flow, and thus any aerodynamic loss is reduced. The leaking air (60) leaks from between a platform (2) of moving blade (1) and an inside shroud (12) in a stationary blade (11). At a front or upstream side of the moving blade (1), the leaking air (60) flows along a S-shaped path within a space (8, 17) formed by a projecting end portion (12b) of the shroud, a honeycomb seal (14) and a projecting portion (4) of the platform. The air eventually flows out in the same flow direction as that of the combustion gas (50) along a surface of the platform (2). At a rear side of the moving blade (1), the leaking air (60) flows along an S-shaped path within a space (6, 9) formed by a projecting end portion (2b) of the platform, a projecting end portion (12b) of the shroud, a honeycomb seal (13) and a seal plate (3).

Abstract: A gas turbine stationary blade, having a simple structure in which sufficient cooling is achieved and the drop in pressure of cooling vapor is decreased so that the turbine efficiency is prevented from lowering. The shape of a vapor passage is simplified to prevent the drop in pressure because an outer shroud (3) of the stationary blade and a blade unit (2) are cooled with vapor, while an inner shroud (4) is cooled with the air supplied from another system.

Abstract: A turbine cooling apparatus comprising a turbine disk having a plurality of moving blades, a torque tube coupled coaxially to one surface side of the turbine disk and having a thick stepped inner wall portion in the central portion thereof, an air separator fitted on the torque tube with the inner surface thereof in contact with the outer surface of the torque tube so that a passage through which cooling air is supplied to the moving blades via the turbine disk is defined between the air separator and the torque tube, and a torque tube cooling hollow portion provided along and in the vicinity of the outer surface of the thick stepped wall portion of the torque tube.

Abstract: A gas turbine moving blade in which the moving blade operating in a high temperature operating gas is cooled from its interior by steam and the steam after being used for the cooling is recovered, by use of a simple structure. A supply side passage (10), through which steam (6) is supplied directly into a cooling passage (51) of a blade leading edge side (11), is provided within a blade root portion (2) and a pocket (19). One end of the pocket is connected to the supply side passage and the other end of which is connected to a cooling passage (52) of a blade trailing edge side (12). The pocket is covered with a plate, which extends in a blade chord direction on an outer peripheral side face of the blade root portion between a blade platform and a rotor plate. Thus, efficiency of the gas turbine can be effectively enhanced.

Abstract: Disclosed is a gas turbine rotor (5) having multi-stage moving blades, each fitted to a disc (12), characterized in comprising: an inner cavity (9) and an outer cavity (8) provided between each disc (12); a blade cooling passage (6) of each moving blade except a rearmost stage moving blade (4); a cooling steam supply passage (13) extending from a rear portion of the rearmost stage moving blade (4) to a leading edge portion of a foremost stage moving blade (1) in the rotor (5); a bifurcation passage (16) provided in the disc (12) portion of the foremost stage so as to connect at its proximal end to the cooling steam supply passage (13) and to bifurcate at its distal end so that one bifurcation thereof (16a) connects to one end of the blade cooling passage (6) and the other bifurcation (16b) connects to the outer cavity (8); a blade return passage (17) connecting at its proximal end to the other end of the blade cooling passage (6) and at its distal end to the inner cavity (9); a cavity connecting passage (20)

Abstract: Provided is a blow-molded article which can be readily formed with good Gloss and with substantially no surface unevenness, even without application of surface coating, and which can be used as a finished product without further treatment. The blow-molded article has a base layer and a surface layer. The base layer is formed from a thermoplastic resin material having a melt index (MI) of about 0.05-2.0 and a flexural modulus of 1,470 MPa (15,000 kgf/cm.sup.2) or more. The surface layer is formed from a colored or transparent thermoplastic resin material having an MI of about 1-30 provided that it is higher than that of the base layer, and excellent weather resistance. The thermoplastic resins used to form the base and surface layers should be resins of the same family.