A centrifugal compressor according to an embodiment includes a compressor impeller, a compressor housing, a suction-surface-side member disposed on a suction surface side of the compressor impeller, and a piezoelectric vibrator disposed in at least one of the compressor housing or the suction-surface-side member. The compressor housing and the suction-surface-side member have wall surfaces defining a space surrounded by the compressor housing and the suction-surface-side member. The wall surface of the at least one of the compressor housing or the suction-surface-side member is at least partially vibratable by operation of the piezoelectric vibrator.

One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator.

A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.

A centrifugal compressor according to an embodiment includes a compressor impeller, a compressor housing, a suction-surface-side member disposed on a suction surface side of the compressor impeller, and a piezoelectric vibrator disposed in at least one of the compressor housing or the suction-surface-side member. The compressor housing and the suction-surface-side member have wall surfaces defining a space surrounded by the compressor housing and the suction-surface-side member. The wall surface of the at least one of the compressor housing or the suction-surface-side member is at least partially vibratable by operation of the piezoelectric vibrator.

A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a fuel from a fuel supply and portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. Mixing a first portion of a compressed fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing a second portion of the compressed fuel to a second turbine for cooling, and flowing the reformed fuel through the second turbine to cool the reformed fuel.

An apparatus, system, and method for a gas turbine engine may include a sectioned heat exchanger. A heat exchanger may include an inlet manifold configured to receive a working fluid. A plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid. Each of the circuits may have a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve. The heat exchanger may further include an outlet manifold configured to pass the working fluid to an outlet. The heat exchanger may include a first sensor configured to measure of first parameter of the first circuit and a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit. A controller may be configured to selectively isolate at least one of the plurality of circuits based on a pressure difference between the first and second parameters.

A gas turbine engine includes a shaft having a first air compressor coupled thereto, a combustor positioned to receive compressed air from the first compressor, and a power source coupled to the shaft, the power source powered by a working fluid other than the compressed air.

One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator.