The technical field of the invention is steam turbines including a steam feed circuit based on a functional steam generator set that may be nuclear- or fossil-fuel powered, and in particular a steam feed circuit (1) of a turbine (2), comprising n main steam lines (3) and n steam admission lines (4) to the turbine, the number n of steam admission lines (4) to the turbine being strictly greater than the number n of main steam lines (3), characterized in that there are n direct steam admission lines (5) to the turbine linking the as main steam lines (3) directly to the steam admission lines (4) to the turbine.

A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0.

An engine has spherical pressure vessels attached to a continuous vertical conveyor. Each spherical pressure vessel has an operating pressure sufficient to hold gas at a pre-defined pressure. At least one gas compressor is in communication with each spherical pressure vessel, and the gas compressor is capable of compressing a gas in each pressure vessel to the pre-defined pressure. A pressure relief mechanism is in communication with each spherical pressure vessel. The pressure relief mechanism is capable of returning the gas in each vessel to atmospheric pressure. A plurality of reciprocating electrical generators is disposed in each spherical pressure vessel to convert the heat generated during pressurization to electrical power.

An engine has spherical pressure vessels attached to a continuous vertical conveyor. Each spherical pressure vessel has an operating pressure sufficient to hold gas at a pre-defined pressure. At least one gas compressor is in communication with each spherical pressure vessel, and the gas compressor is capable of compressing a gas in each pressure vessel to the pre-defined pressure. A pressure relief mechanism is in communication with each spherical pressure vessel. The pressure relief mechanism is capable of returning the gas in each vessel to atmospheric pressure. A plurality of reciprocating electrical generators is disposed in each spherical pressure vessel to convert the heat generated during pressurization to electrical power.

A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0.

A fluid motor is disclosed employed in a turbocharger to spin-up the turbocharger turbine independently of the existing exhaust gas pressure on the exhaust turbine wheel. A fluid turbine wheel is fixedly attached to the rotary mounted shaft of the turbocharger. Fixedly mounted nozzles directed at the fluid turbine wheel present fluid from a controlled source of pressurized fluid. A fixedly mounted collector receiving exhausted fluid from the fluid turbine wheel. The fluid is recycled from the collector to the controlled source of pressurized fluid and then back to the fixedly mounted. The fluid turbine wheel exhausts the fluid with residual energy to the collector. The controlled source of pressurized fluid includes a gear pump with an accumulator and a solenoid valve.

A fluid motor is disclosed employed in a turbocharger to spin-up the turbocharger turbine independently of the existing exhaust gas pressure on the exhaust turbine wheel. A fluid turbine wheel is fixedly attached to the rotary mounted shaft of the turbocharger. Fixedly mounted nozzles directed at the fluid turbine wheel present fluid from a controlled source of pressurized fluid. A fixedly mounted collector receiving exhausted fluid from the fluid turbine wheel. The fluid is recycled from the collector to the controlled source of pressurized fluid and then back to the fixedly mounted. The fluid turbine wheel exhausts the fluid with residual energy to the collector. The controlled source of pressurized fluid includes a gear pump with an accumulator and a solenoid valve.

Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

A turbine exhaust case (28) comprises a fairing (120) defining an airflow path through the turbine exhaust case, and a multi-piece frame (100) disposed through and around the fairing to support a bearing load. The multi-piece frame comprises an inner ring (104), an outer ring (102), and a plurality of strut bosses (106). The outer ring is disposed concentrically outward of the inner ring, and has open bosses (126) at strut locations. The plurality of radial struts pass through the vane fairing, are secured to the inner ring via radial fasteners (108), and are secured via non-radial fasteners (114) to the open boss.