A denitration device comprising a duct (22) that leads and distributes exhaust gas from a turbine (56) of a gas turbine (50) including a compressor (52) and the turbine (56), an ammonia injection grid (24) that sprays, into the duct (22), an mixed gas in which ammonia gas and dilution air are mixed with each other, and a denitration catalyst (26) that is installed on a downstream side of flow of the exhaust gas of the ammonia injection grid in the duct (22), and there is provided an air bleeding line (76) that is connected to a low compression portion of the compressor (52) of the gas turbine (50) and supplies air bled of the compressor (52) into the ammonia injection grid (24) as the dilution air.

A denitration device comprising a duct (22) that leads and distributes exhaust gas from a turbine (56) of a gas turbine (50) including a compressor (52) and the turbine (56), an ammonia injection grid (24) that sprays, into the duct (22), an mixed gas in which ammonia gas and dilution air are mixed with each other, and a denitration catalyst (26) that is installed on a downstream side of flow of the exhaust gas of the ammonia injection grid in the duct (22), and there is provided an air bleeding line (76) that is connected to a low compression portion of the compressor (52) of the gas turbine (50) and supplies air bled of the compressor (52) into the ammonia injection grid (24) as the dilution air.

A diaphragm latch may comprise a housing, a diaphragm disposed in the housing, a pin coupled to the diaphragm, an opening in the housing, and a pin aperture disposed in the first side, wherein the pin extends from the pin aperture. The diaphragm may be configured to move in response to a pressure being communicated through the opening, and the pin may be configured to at least one of extend or retract from the pin aperture in response to the diaphragm moving. The diaphragm latch may passively couple an inner fixed structure (IFS) to an intermediate case (IMC) during an overpressure event.

A system for monitoring the state of health of a monitored aircraft engine comprises an anomaly detection unit which analyses engine operating parameters and raises an alarm if a result of the analysis of one of the engine operating parameters crosses a threshold, the alarm being associated with a probability of a given type of engine damage occurring. The system further comprises an engine operating conditions monitoring unit which determines a state of wear of the engine, and an alarm corroboration unit which weights the said probability of occurrence by the determined state of wear. The invention is applicable to the preventive maintenance of turbomachines.

A system for monitoring the state of health of a monitored aircraft engine comprises an anomaly detection unit which analyses engine operating parameters and raises an alarm if a result of the analysis of one of the engine operating parameters crosses a threshold, the alarm being associated with a probability of a given type of engine damage occurring. The system further comprises an engine operating conditions monitoring unit which determines a state of wear of the engine, and an alarm corroboration unit which weights the said probability of occurrence by the determined state of wear. The invention is applicable to the preventive maintenance of turbomachines.

Provided are a Ni-based heat resistant superalloy for aircraft engine cases excellent in high-temperature characteristic such as tensile characteristics and low-cycle fatigue characteristics in a high-temperature range and also excellent in workability, and an aircraft engine case formed of the same. The Ni-based heat resistant superalloy has composition containing, by mass, Co: 4.0 to 11.0%, Cr: 12.0 to 17.0%, Al: 2.0 to 4.0%, Ti: 2.0 to 4.0%, Al+Ti: 4.6 to 6.7%, Mo: more than 5.5 to 10.0%, W: more than 0 to 4.0%, B: 0.001 to 0.040%, C: 0.02 to 0.06%, Zr: 0 to 0.05%, Mg: 0 to 0.005%, P: 0 to 0.01%, Nb: 0 to 1.0%, Ta: 0 to 1.0%, and Fe: 0 to 2.0%, and the balance of Ni with inevitable impurities, and is suitable for aircraft engine cases.

Provided are a Ni-based heat resistant superalloy for aircraft engine cases excellent in high-temperature characteristic such as tensile characteristics and low-cycle fatigue characteristics in a high-temperature range and also excellent in workability, and an aircraft engine case formed of the same. The Ni-based heat resistant superalloy has composition containing, by mass, Co: 4.0 to 11.0%, Cr: 12.0 to 17.0%, Al: 2.0 to 4.0%, Ti: 2.0 to 4.0%, Al+Ti: 4.6 to 6.7%, Mo: more than 5.5 to 10.0%, W: more than 0 to 4.0%, B: 0.001 to 0.040%, C: 0.02 to 0.06%, Zr: 0 to 0.05%, Mg: 0 to 0.005%, P: 0 to 0.01%, Nb: 0 to 1.0%, Ta: 0 to 1.0%, and Fe: 0 to 2.0%, and the balance of Ni with inevitable impurities, and is suitable for aircraft engine cases.

A gas turbine apparatus includes a turbine configured to be driven by a combustion gas from a combustor, an exhaust passage, an extraction line configured to extract a fluid from a combustor casing, a cooling part disposed in the extraction line and configured to cool the fluid, a return line for returning the fluid from the cooling part to an inside of the combustor casing, the return line being connected to the extraction line downstream of the cooling part, a bypass line for introducing the fluid from the cooling part to the exhaust passage by bypassing the turbine, the bypass line branching from the return line, and a communication state switching part for controlling a communication state between the extraction line and the combustor casing via the return line, and a communication state between the extraction line and the exhaust passage via the bypass line.

By melting a shaping material in which a metal powder and a binder are mixed and by carrying out injection molding (primary shaping) in an injection mold, an injection molded body, or an intermediate shaped body are produced. The injection molded body or the intermediate shaped body is placed by a transfer mold and is subjected to a gravity shaping (secondary shaping) with a transformation. A sintered body is manufactured by carrying out debindering and sintering to the injection molded body.

By melting a shaping material in which a metal powder and a binder are mixed and by carrying out injection molding (primary shaping) in an injection mold, an injection molded body, or an intermediate shaped body are produced. The injection molded body or the intermediate shaped body is placed by a transfer mold and is subjected to a gravity shaping (secondary shaping) with a transformation. A sintered body is manufactured by carrying out debindering and sintering to the injection molded body.