Abstract: Provided is an abnormality response teaching system that estimates a factor of an abnormality and teaches a treatment for the factor. This abnormality response teaching system is provided with: an operation parameter acquisition unit for acquiring an operation parameter measured during operation of a device; a diagnosis information acquisition unit for acquiring diagnosis information indicating the result of a diagnosis of operation of a machine with which the device is provided, said diagnosis being executed prior to startup of the device; and a factor analysis unit for inputting the operation parameter and the diagnosis information to an FTA with which abnormality factors are analyzed, and thereby analyzing an abnormality factor, when an abnormality occurs in the device.

Abstract: A gas turbine startup method and device wherein low-pressure, medium-pressure, and high-pressure air bleed flow paths supply compressed air bled from low-pressure, medium-pressure, and high-pressure air bleed chambers, respectively, of a compressor as cooling air to a turbine. Low-pressure, medium-pressure, and high-pressure exhaust flow paths discharge the compressed air in the low-pressure, medium-pressure, and high-pressure air bleed flow paths, respectively to the turbine exhaust system, and the low-pressure, the medium-pressure, and the high-pressure exhaust flow paths are provided respectively with a low-pressure exhaust valve, a medium-pressure exhaust valve, and a high-pressure exhaust valve. When the gas turbine starts up, the high-pressure exhaust valve is opened before the startup state of the gas turbine reaches a region in which rotation stall occurs.

Abstract: A cooling system includes: a high pressure bleed line configured to bleed high pressure compressed air from a first bleed position of a compressor and to send the air to a first hot part; a low pressure bleed line configured to bleed low pressure compressed air from a second bleed position of the compressor and to send the air to a second hot part; an orifice provided in the low pressure bleed line; a connecting line configured to connect the high pressure bleed line and the low pressure bleed line; a first valve provided in the connecting line; a bypass line configured to connect the connecting line and the low pressure bleed line; and a second valve provided in the bypass line.

Abstract: A gas turbine startup method and device wherein low-pressure, medium-pressure, and high-pressure air bleed flow paths supply compressed air bled from low-pressure, medium-pressure, and high-pressure air bleed chambers, respectively, of a compressor as cooling air to a turbine. Low-pressure, medium-pressure, and high-pressure exhaust flow paths discharge the compressed air in the low-pressure, medium-pressure, and high-pressure air bleed flow paths, respectively to the turbine exhaust system, and the low-pressure, the medium-pressure, and the high-pressure exhaust flow paths are provided respectively with a low-pressure exhaust valve, a medium-pressure exhaust valve, and a high-pressure exhaust valve. When the gas turbine starts up, the high-pressure exhaust valve is opened before the startup state of the gas turbine reaches a region in which rotation stall occurs.

Abstract: A cooling system includes: a high pressure bleed line configured to bleed high pressure compressed air from a first bleed position of a compressor and to send the air to a first hot part; a low pressure bleed line configured to bleed low pressure compressed air from a second bleed position of the compressor and to send the air to a second hot part; an orifice provided in the low pressure bleed line; a connecting line configured to connect the high pressure bleed line and the low pressure bleed line; a first valve provided in the connecting line; a bypass line configured to connect the connecting line and the low pressure bleed line; and a second valve provided in the bypass line.

Abstract: Provided is a gas turbine plant that enables active clearance control for ensuring tip clearance of first-stage turbine rotor blades required during start-up and for achieving the minimum tip clearance during load operation. In a gas turbine plant including a cooler in an air system used for cooling second-stage turbine stator blades, a first-stage segmented ring and a second-stage segmented ring that oppose tips of first-stage turbine rotor blades and second-stage turbine rotor blades are supported by the same blade ring member, and a cooling-air for the second-stage turbine stator blades forms a cooling air flow cooling the blade ring, to control thermal expansion of the blade ring and to control the clearance with respect to the tips.

Abstract: Provided is a gas turbine plant that enables active clearance control for ensuring tip clearance of first-stage turbine rotor blades required during start-up and for achieving the minimum tip clearance during load operation. In a gas turbine plant including a cooler in an air system used for cooling second-stage turbine stator blades, a first-stage segmented ring and a second-stage segmented ring that oppose tips of first-stage turbine rotor blades and second-stage turbine rotor blades are supported by the same blade ring member, and a cooling-air for the second-stage turbine stator blades forms a cooling air flow cooling the blade ring, to control thermal expansion of the blade ring and to control the clearance with respect to the tips.

Abstract: A seal ring separating surface for a gas turbine, which sets a shape of an end portion in the separation surface to a cutting surface and reduces the leaking amount of sealing air. A seal ring holding ring (1) fixes brush seals (3, 4) on an upstream side of a stationary blade by bolts (5, 6) respectively, so as to form a seal with respect to a rotor disc (69). Further, the seal ring holding ring (1) fixes and supports a seal ring (2) on a downstream side by a bolt (7) so as to form a seal with respect to a seal portion (8) on the disc (69) side. The brush seals (3, 4) and the seal ring (2) are structured so as to have a circular ring shape and a separation construction, and each of the separation pieces has a gap, so that sealing air can leak to a downstream side from an upstream side through the gap.

Abstract: A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (51), which communicates with a seal tube (2). The seal tube (2) is inserted into the second air hole (51), and a spring (6) is arranged between a projection (4) of the tube (2) and a retaining portion (5) of the air hole (51) to removably secure the seal tube (2). Cooling air (54) flows through the first air hole (1) to cool the shrouds and the inside of a stator blade (31) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (36) so that a high pressure can be maintained without a pressure loss because the tube (2) is independent of the space (53) in the blade ring.

Abstract: A tip shroud (11) for a moving blade to be used at a downstream stage of a gas turbine. The tip shroud is extended in its creep lifetime by feeding it effectively with cooling air. In the tip shroud (11), there are cut-off portions (12, 13) which are passed by a hot combustion gas so that they are influenced by thermal stress. On the shroud faces, there are formed grooves (31, 32; 33, 34), and cooling guide covers (21, 22) are mounted in the grooves. The cooling guide covers (21, 22) are closed at one side with members (21a, 22a) and open at an end thereof. The covers function to cover the air holes (17) so that the cooling air is fed to the cut-off portions (12, 13) individually. The metal temperature rise at the cut-off portions (12, 13), as will be influenced by the hot combustion gas, can be suppressed so as to extend the creep lifetime of the tip shroud.

Abstract: An air separator for a gas turbine, in which cracks are prevented from occurring at a flange portion of the air separator due to fretting fatigue. The air separator (20) has a cylindrical split structure formed by two separator members (20-1 and 20-2), of which one of the separators (20-1) is mounted on a rotor (1) whereas the other separator member (20-2) is mounted on a disc portion (7) on a side of a moving blade (2) by bolts (28) extending through bolt holes (23) formed in a flange portion (22). Cooling air from a compressor enters a space (6) from a duct (5) and passes to a passage (32) from a clearance (33) so that it is fed to air feed holes (43) and radial holes (44) of the disc portion (7). Alternatively, air holes (50) are provided in the flange portion (22) in the form of circumferential slots for covering a plurality of radial holes to feed the cooling air homogeneously so that a prior art air separator of an existing plant can be replaced.