Apparatus and method are provided for facilitating pumped, immersion-cooling of an electronic subsystem having multiple different types of components to be immersion-cooled. The apparatus includes a container sized to receive the electronic subsystem, and a coolant inlet port and a coolant outlet port for facilitating ingress and egress of coolant through the container. The apparatus further includes a coolant pump assembly coupled in fluid communication with the coolant inlet and outlet ports of the container for facilitating active pumping of coolant through the container. When the electronic subsystem is operatively inserted into the container and coolant is pumped through the container, the multiple different types of components of the electronic subsystem are immersion-cooled by the coolant. In one embodiment, a filler element is disposed within the container, and is sized to reduce the amount of coolant within the container, while still maintaining the components of the electronic subsystem immersion-cooled.

Apparatus and method for facilitating pumped immersion-cooling of an electronic subsystem

A cooling system and method are provided for facilitating cooling of a liquid-cooled electronics rack. The cooling system includes a coolant flow controller, a modular cooling unit and a pressure controller. The flow controller is associated with a respective electronics rack and controls flow of coolant through that electronics rack based on its changing cooling requirements. The cooling unit includes an adjustable coolant pump for facilitating supply of coolant to the rack. The pressure controller is associated with the cooling unit for controlling pressure of coolant at an output of the cooling unit via control of pump speed of the pump. Responsive to adjusting coolant flow through the electronics rack, the pressure controller automatically adjusts pump speed of the adjustable pump to maintain pressure about a constant coolant pressure set point at an output of the cooling unit, thereby conserving power while still cooling the liquid-cooled electronics rack.

Cooling system and method minimizing power consumption in cooling liquid-cooled electronics racks

A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.

Blade outer air seal

Liquid-cooled electronics racks are provided which include: immersion-cooled electronic subsystems; a vapor-condensing heat exchanger to condense dielectric fluid vapor egressing from the immersion-cooled electronic subsystems; a dielectric fluid vapor return coupling in fluid communication the vapor outlets of the immersion-cooled electronic subsystems and the vapor-condensing heat exchanger; a reservoir for holding dielectric fluid; a gravity drain line coupled to drain dielectric fluid condensate from the vapor-condensing heat exchanger to the reservoir; an immersed, sub-cooling heat exchanger disposed within the reservoir; a dielectric fluid supply manifold coupling in fluid communication the reservoir and the dielectric fluid inlets of the immersion-cooled electronic subsystems; and a pump for supplying under pressure dielectric fluid from the reservoir to the dielectric fluid supply manifold for maintaining dielectric fluid in a liquid state within the immersion-cooled electronic subsystems.

Liquid-cooled electronics rack with immersion-cooled electronic subsystems

Apparatus and method are provided for facilitating liquid cooling of a plurality of blades of an electronic system chassis. The apparatus includes a chassis-level manifold assembly with a first coolant path and a plurality of second coolant paths. The first coolant path is isolated from the plurality of second coolant paths by a heat exchanger. The heat exchanger facilitates transfer of heat from coolant within the second coolant paths to coolant within the first coolant path. Each second coolant path is isolated from the other second coolant paths, and coolant passing therethrough facilitates cooling of a respective blade. When operational, each second coolant path forms a portion of a respective closed loop coolant path extending between the manifold assembly and the electronic system chassis, and in one embodiment, each blade is an immersion-blade, with multiple components thereof immersion-cooled by coolant flowing through the respective second coolant path.

Liquid cooling apparatus and method for cooling blades of an electronic system chassis

A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the casing in order to modify the temperature thereof. A tubular air manifold is disposed around the air flow duct(s). There are also disposed an air feed tube to supply the tubular air manifold with air and an air pipe opening in the tubular air manifold and opening out into the air flow duct(s). The air pipe is provided with a balancing diaphragm for balancing the air flowing through the pipe.

Device for tuning clearance in a gas turbine, while balancing air flows

A device for controlling the clearance between the tips of rotary blades and a stationary ring assembly of a gas turbine, the device comprising a circular control box having at least two annular air circulation strips that are spaced apart from each other in the axial direction, each having a plurality of perforations in order to modify the temperature of the stationary ring assembly by discharging air, an annular air feed channel radially spaced from the air circulation strip, at least one air duct for feeding the feed channel with air, and a plurality of hollow distribution spacers connecting the air feed channel to the air circulation strips in order to feed the strips with air while enabling the air that has been discharged against the stationary ring assembly to flow between the feed channel and the circulation strips in order to be evacuated therefrom.

Device for controlling clearance in a gas turbine

This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element. The means of intervention offers a means of controlling the clearance of the labyrinth seal clearance.

Labyrinth seal device for gas turbine engine

Dispositif de pilotage de jeu en sommet d'aubes mobiles d'un rotor de turbine a gaz, comportant au moins une rampe annulaire de circulation d'air (14) montee circonferentiellement sur un carter annulaire (12) d'un stator de la turbine et destinee a decharger de l'air sur ledit carter (12) afin d'en modifier la temperature. Un tube collecteur d'air (20) est dispose autour de la ou des rampes de circulation d'air (14). On dispose egalement un tube d'alimentation en air (22) pour alimenter en air le tube collecteur d'air (20) et une conduite d'air (24) s'ouvrant dans le tube collecteur d'air (20) et debouchant dans la ou les rampes de circulation d'air (14). La conduite d'air (24) est pourvue de moyens (30) pour equilibrer le debit d'air la traversant.

Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air

FIELD: mechanical engineering; gas turbines. ^ SUBSTANCE: device for adjusting clearance between heads of working blades and stationary ring unit of gas turbine contains circular adjusting unit enclosing stationary ring unit. Adjusting unit has at least two circulating air ring channels spaced in axial direction. Each channel is provided with holes to change temperature of stationary ring unit by air blowing. Device to adjust clearance contains also ring channel to deliver air into circulating air ring channels, and at least one air duct supplying air to air delivery channel. Ring air delivery channel is spatially separated in radial direction from circulating air ring channels. Adjusting unit contains additionally hollow distributing bridges connecting air delivery channel with circulating air channels to feed air into said channels with provision of possibility for air supplied for blowing stationary ring unit to flow in axial direction between air delivery channel and circulating air channels with subsequent discharge of air from stationary ring unit. ^ EFFECT: provision of high degree of equality of temperature in stationary ring unit, no interferences of discharge and blowing air flows. ^ 9 cl, 4 dwg

Delphine Roussin

Papers

Device for tuning clearance in a gas turbine, while balancing air flows

Device for controlling clearance in a gas turbine

Labyrinth seal device for gas turbine engine

Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air

Device for adjusting radial clerance of gas turbine