A method of cleaning a component within a turbine that includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the interior passageway from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component.

A method of cleaning a component within a turbine that includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the interior passageway from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A double turbine exhaust duct design and an inline V turbine exhaust duct design that both eliminate the need for the standard T-piece in a turbine exhaust duct assembly, substantially reducing the steam-side pressure drop, minimizing the sub-cooling in the steam cycle (the temperature difference between ACC condensate temperature out and turbine steam temperature), thus improving the overall efficiency of the steam cycle plant heat rate.

A double turbine exhaust duct design and an inline V turbine exhaust duct design that both eliminate the need for the standard T-piece in a turbine exhaust duct assembly, substantially reducing the steam-side pressure drop, minimizing the sub-cooling in the steam cycle (the temperature difference between ACC condensate temperature out and turbine steam temperature), thus improving the overall efficiency of the steam cycle plant heat rate.

A steam turbine 10 according to an embodiment includes rotor blades 22 implanted to a turbine rotor 21, stationary blades 26 making up a turbine stage together with the rotor blades 22, diaphragm outer rings 23 including an annular extending part 24 surrounding a periphery of the rotor blades 22, and supporting the stationary blades 26, and diaphragm inner rings 25 supporting the stationary blades 26. The steam turbine 10 further includes an annular slit 40 formed at an inner surface of the diaphragm outer ring 23 between the stationary blades 26 and the rotor blades 22 along a circumferential direction, and communication holes 50 provided in plural at an outer surface of the diaphragm outer ring 23 along the circumferential direction, communicated to the annular slit 40 from the outer surface side, and communicated to an exhaust chamber sucking water films via the annular slit 40.

A steam turbine 10 according to an embodiment includes rotor blades 22 implanted to a turbine rotor 21, stationary blades 26 making up a turbine stage together with the rotor blades 22, diaphragm outer rings 23 including an annular extending part 24 surrounding a periphery of the rotor blades 22, and supporting the stationary blades 26, and diaphragm inner rings 25 supporting the stationary blades 26. The steam turbine 10 further includes an annular slit 40 formed at an inner surface of the diaphragm outer ring 23 between the stationary blades 26 and the rotor blades 22 along a circumferential direction, and communication holes 50 provided in plural at an outer surface of the diaphragm outer ring 23 along the circumferential direction, communicated to the annular slit 40 from the outer surface side, and communicated to an exhaust chamber sucking water films via the annular slit 40.

An apparatus and method of reducing a flow of fluid and heat between a first space and a second space in a rotatable machine and an integral seal and heat shield device are provided. The device includes an annular flange configured to couple to the rotating member of the rotatable machine and a multi-walled seal shield member extending axially from the flange. The multi-walled seal shield member is formed integrally with the flange. The seal shield member includes a first wall including a plurality of surface features, a second wall spaced radially inwardly with respect to the first wall, and a cavity formed between the first and second walls. The integral seal and heat shield device also includes a cap end integrally formed and configured to seal the first and second walls. Each of the flange, the seal shield member, and the cap end are formed of a sintered metal.

An aircraft engine has a combustor supplied by a hydrogen fuel system and is configured to combust hydrogen and generate water vapor. A water vapor collector receives at least part of the water vapor. A condenser is in fluid communication with the water vapor collector to receive and cool in the condenser the at least part of the water vapor and thereby condense at least part of the at least part of the flow of water vapor. A spray nozzle is in fluid communication with the condenser and operable to spray the condensed part of the at least part of the flow of water vapor onto a component of the aircraft engine.