Abstract: In a gas turbine and a control method thereof, and a combined cycle plant, the gas turbine includes a compressor that compresses air, a combustor that mixes and combusts compressed air compressed by the compressor and fuel, a turbine that obtains rotational power using combustion gas generated by the combustor, a compressed air cooling heat exchanger that cools the compressed air to produce air for heat exchange, air temperature adjusting heat exchangers that exchange heat between the air and the compressed air, a heat exchange amount adjusting device that adjusts a heat exchange amount of each of the compressed air cooling heat exchanger and the air temperature adjusting heat exchangers, and a control device that controls the heat exchange amount adjusting device, in which the control device controls the heat exchange amount adjusting device based on a temperature of the air to be taken into the compressor.

Abstract: In a closed system that recirculates exhaust gas from a gas turbine engine, recirculated exhaust gas should be mixed into inlet gas in a manner that produces a uniform distribution within the mixed gas, while preventing an excessive pressure drop at the point of mixing, and without needing excessive duct length. Otherwise, the performance of the gas turbine engine may be detrimentally affected. Accordingly, a mixer box is disclosed that injects recirculated exhaust gas into a flow path of inlet gas in a uniform manner. The mixer box may comprise mixer(s) that extend the flow path of the recirculated exhaust gas into the flow path of the inlet gas along two axes. Each mixer may comprise surface apertures and/or interior channels designed to promote uniform ejection of the recirculated exhaust gas from the mixers into the flow path of inlet gas.

Abstract: A method comprising applying braze to a joint location of two work pieces and applying local heating to the joint location of the two work pieces until braze melting temperature is achieved to melt the braze while maintaining temperature of more remote portions of each work piece. The method includes reducing heating of the braze to form a braze joint joining the joint location of the two work pieces.

Abstract: A turbine includes a rotor including a rotation shaft that rotates around an axis and a blade row formed on an outer surface of the rotation shaft; a casing, which covers the rotor, has a casing inner surface being expanded radially outward approaching a downstream side of the casing in a direction of the axis; and an inner member body formed to line the casing inner surface of the casing such that an extraction port is formed between an upstream side end of the inner member body and the casing inner surface. A discharge port is formed between a downstream side end of the inner peripheral member body and the casing inner peripheral surface. The extraction port and the discharge port are formed in an annular shape centered on the axis. A flow path cross-sectional area of the discharge port is smaller than that of the extraction port.

Abstract: A first cylinder is configured to receive a gas turbine. A second cylinder surrounds an outer circumference of the first cylinder. Retainers extend from the second cylinder towards the first cylinder. Each of the retainers includes a central stalk that extends from the second cylinder towards the first cylinder and a branches extending radially from the central stalk.

Abstract: A tubular combustion chamber system for a gas turbine unit includes a plurality of annularly arranged transition lines, which are designed to be connected at the upstream ends thereof to respective burners and to conduct hot gas produced by the burners to a turbine. The tubular combustion chamber system has a hot gas distributor, which is designed to be connected to the turbine and defines a ring channel, which is open to the turbine and into which the downstream ends of the transition lines lead. A gas turbine unit includes a plurality of annularly arranged burners, a turbine and a tubular combustion chamber system which connects the burners to the turbine.

Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.

Abstract: A propulsion system assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an outer airflow inlet passage, an inner airflow inlet passage, an inlet structure and a center body structure. The outer airflow inlet passage is between the inlet structure and the center body structure. The inner airflow inlet passage is formed within the center body structure. The center body structure includes a valve configured to regulate air flow through the inner airflow inlet passage. The valve includes a first door configured to pivot between a closed position and an open position. The inlet duct is configured to receive air from the outer airflow inlet passage when the first door is in the closed position. The inlet duct is configured to receive air from the outer airflow inlet passage and the inner airflow inlet passage when the first door is in the open position.

Abstract: An acoustic attenuator comprises a first attenuation unit, a second attenuation unit, a welded section, and a communication part. A first acoustic damper is provided on an outer surface of a first acoustic liner, which faces toward a side opposite from an object, to form a first damper space that communicates with an internal space of the object. The second attenuation unit is attached to an outer surface of the object. The welded section is provided at least between the first acoustic damper and a second acoustic damper. The welded section secures the second attenuation unit to the first acoustic liner. The communication part is disposed in a position farther from an outer surface of the object than the welded section, allowing communication between the first damper space and a second damper space.

Abstract: An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.

Abstract: A combined cooling heating and power micro gas turbine device includes a micro gas turbine. The micro gas turbine includes a gas compressor, a turbine and a combustion chamber assembly. The combustion chamber assembly includes a combustion chamber, an air inlet cavity, an air inlet channel and an exhaust channel. The air inlet cavity includes an interior air inlet cavity and an exterior air inlet cavity that are integrated, an air outlet end of the exterior air inlet cavity is communicated with an air inlet end of the interior air inlet cavity, an air inlet end of the exterior air inlet cavity is communicated with the air inlet channel, the air inlet channel is communicated with the gas compressor, the combustion chamber is arranged between the interior air inlet cavity and the exterior air inlet cavity, and an air outlet of the combustion chamber is communicated with the exhaust channel.

Abstract: A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.

Abstract: A method is provided of controlling a cooled cooling air system for an aeronautical gas turbine engine. The method includes: receiving data indicative of an ambient condition of the aeronautical gas turbine engine, data indicative of a deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or a combination thereof; and modifying a cooling capacity of the cooled cooling air system in response to the received data indicative of the ambient condition of the aeronautical gas turbine engine, data indicative of the deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or the combination thereof.

Abstract: A heat shield assembly for use with an aircraft engine. The heat shield assembly includes a structural member, a heat shield panel adapted for exposure to aircraft engine exhaust, an index joint coupling the heat shield panel to the structural member in a fixed positional location, and a plurality of slip joints coupling the heat shield panel to the structural member. Each slip joint includes at least one wear buffer coupled to the heat shield panel, and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit. A gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.

Abstract: A fuel system for a turbomachine includes a fuel tank and a first fuel line in fluid communication with the fuel tank and one or more fuel injectors. The first fuel line includes a main fuel pump disposed on the first fuel line, and an electric metering system disposed on the first fuel line downstream of the main fuel pump configured for starting the turbomachine and metering fuel to the fuel injectors.

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.

Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.

Abstract: An acoustic treatment device for an aircraft turbojet engine nacelle forms an annular ring including several sections, each section having a sound absorption structure, an outer skin and two lateral skins attached to the inner air inlet shroud of such a nacelle by fasteners, and the sections being connected to each other by battens.

Abstract: A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.