In one embodiment, the system includes one or more electrical components associated with turbomachinery, and the one or more electrical components are disposed within two or more interior compartments of an electrical enclosure. The system also includes a cooling system coupled to the electrical enclosure. The cooling system includes one or more air ducts configured to direct a cooling air to each interior compartment of the two or more interior compartments. The cooling system also includes a controller configured to route cooling air to each interior compartment via the one or more air ducts. The controller is configured to independently regulate a thermal environment for each interior compartment of the two or more interior compartments.

Various embodiments include a heat transfer device, a turbomachine casing and a related storage medium. In some cases, the device includes: a body having an outer surface and an inner cavity within the outer surface; at least one aperture extending through the body, the at least one aperture positioned to direct fluid from the inner cavity through the body to the outer surface; a first lip proximate a first end of the body, and a second lip proximate a second end of the body, the first lip and the second lip each extending radially outward from the outer surface relative to a direction of flow of the fluid through the inner cavity; and a plug coupled with the body, the plug for obstructing an end of the inner cavity, the plug positioned to redirect flow of the fluid from a first direction to a second, distinct direction.

A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a turbine casing. A combustor assembly, including at least one combustor, fluidically connects the compressor portion and the turbine portion. At least one of the compressor portion, turbine portion and combustor assembly includes a sensing cavity. A passive clearance control system is operatively arranged in the turbomachine. The passive clearance control system includes at least one passive flow modulating device mounted in the sensing cavity, and at least one cooling channel extending from the sensing cavity through the casing. The at least one passive flow modulating device selectively passes the fluid from the sensing cavity through the at least one cooling channel to adjust a clearance between stators and rotating airfoils in the turbine portion.

A gas passage that is connected to an exhaust passage and a water passage that is connected to a water jacket are formed in a turbine housing. The water passage and the gas passage are arranged adjacent to each other in an exhaust gas-introducing side joint part of the turbine housing, and a mating face in which the water passage opens and a mating face in which the gas passage opens are formed not to connect smoothly to each other. The turbine housing is attached to the cylinder head with an O-ring that prevents leakage of coolant interposed between the mating face and the cylinder head, and a seal member that prevents leakage of exhaust gas interposed between the mating face and the cylinder head.

A gas passage that is connected to an exhaust passage and a water passage that is connected to a water jacket are formed in a turbine housing. The water passage and the gas passage are arranged adjacent to each other in an exhaust gas-introducing side joint part of the turbine housing, and a mating face in which the water passage opens and a mating face in which the gas passage opens are formed not to connect smoothly to each other. The turbine housing is attached to the cylinder head with an O-ring that prevents leakage of coolant interposed between the mating face and the cylinder head, and a seal member that prevents leakage of exhaust gas interposed between the mating face and the cylinder head.

Described is a heat-protection element (50) for a gas turbine (10), in particular an aircraft gas turbine, the heat-protection element (50) being adapted to at least partially surround a bearing chamber (60) of the gas turbine (10) and having at least one connecting portion (52) which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element (54) of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion (58) which is disposed in an axially central region (MB) and adapted to support the heat-protection element (50) radially on the bearing chamber (60), an end portion (64) which is disposed in an axially rearward region (HB) and forms a free end (66) of the heat-protection element (50) and which is configured such that the end portion surrounds (64) the bearing chamber (60) in a contactless manner.

A method of assembling a turbocharger having a vaned turbine nozzle includes first forming a sub-assembly of a center housing, shaft, bearings, compressor wheel, turbine wheel, and vane assembly. The vane assembly is held captive in attachment to the center housing by an annular heat shield that includes prongs or the like at its inner and outer peripheries for respectively engaging a first catch formed on the center housing and a second catch formed on the nozzle ring of the vane assembly. The heat shield forms a snap fit to the center housing and nozzle ring, thereby connecting the cartridge to the center housing. The whole sub-assembly is then joined to the turbine housing, in the process axially compressing the heat shield and a spring shroud for exerting an axial biasing force on the nozzle ring.

A turbocharger includes a turbine housing, a compressor housing, and a bearing housing. Each of the housings includes a passage for cooling inside. The turbocharger further includes a switching valve and a controller that switches a valve position of the switching valve. The switching valve is adapted to switch the circulation state of coolant in each passage such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing or such that the coolant is supplied from another passage to the passage of the bearing housing. The controller switches the valve position of the switching valve such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing until a predetermined amount of time passes after starting of the engine.

A turbocharger includes a turbine housing, a compressor housing, and a bearing housing. Each of the housings includes a passage for cooling inside. The turbocharger further includes a switching valve and a controller that switches a valve position of the switching valve. The switching valve is adapted to switch the circulation state of coolant in each passage such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing or such that the coolant is supplied from another passage to the passage of the bearing housing. The controller switches the valve position of the switching valve such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing until a predetermined amount of time passes after starting of the engine.

A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.