There is provided a system and method for detecting excess flow in an engine fluid system, the method comprising sensing a temperature of a fluid flowing in a fluid line of the fluid system, the fluid line located downstream of a fluid flow restrictor configured to receive the fluid from a source upstream thereof and to flow the fluid from the source into the fluid line downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line and outputting an excess flow indication accordingly.

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.

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.

A jig for assembling and extracting a blade root spring for fixing a rotor blade to a rotor includes: an extrusion mechanism for extruding the blade root spring or an extrusion rod pressed against the blade root spring; and a base plate to which the extrusion mechanism is fixed. The base plate is formed with a first groove for receiving a reaction force which is obtained when the extrusion mechanism extrudes the extrusion rod toward the blade root spring to extrude and assemble the blade root spring or to extract the blade root spring.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

A gas turbine storage container is composed of a horizontal cylindrical shell with openings at two opposite ends of the cylinder, outside is designed with frames to keep it fixed and has straps to install ropes when hoisting. The inside of the cylindrical shell is pumped with inert gas and contains desiccant. The engine is housed in a mount that can be fixed to the inside of the box, and has wheels to make it possible to move it out of the box. A sensor system that measures the temperature and humidity status inside the cylindrical shell can provide information about the quality of the gas stored in the cylindrical shell in real time without opening.

A gas turbine storage container is composed of a horizontal cylindrical shell with openings at two opposite ends of the cylinder, outside is designed with frames to keep it fixed and has straps to install ropes when hoisting. The inside of the cylindrical shell is pumped with inert gas and contains desiccant. The engine is housed in a mount that can be fixed to the inside of the box, and has wheels to make it possible to move it out of the box. A sensor system that measures the temperature and humidity status inside the cylindrical shell can provide information about the quality of the gas stored in the cylindrical shell in real time without opening.