A method for operating a gas turbine engine (10), including a first compressor (14), a second compressor (16), and a turbine (20), coupled together in serial flow arrangement. The method includes channeling compressed airflow (53) discharged from the first compressor through an intercooler (50) having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet (26,30) of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Methods and apparatus for operating gas turbine engines

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 turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Mounting apparatus for low-ductility turbine shroud

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

Agencement de reglage de diametre d'un stator de turbine a gaz

Ensemble a anneau fixe d'une turbine a gaz

FIELD: machine building.SUBSTANCE: gas turbine engine module comprising a movable wheel rotatably mounted inside the crankcase of the module and surrounded by segmented O-ring (18), which comprises an annular row of ring sectors, wherein each sector of the ring comprises at least one circumferential hook configured to interact with the crankcase annular fixing guide, wherein the module further comprises a segmented annular protective spacer (50) which is mounted between the ring sectors and the crankcase guide hooks and comprises an annular row of spacer sectors, characterized in that edges (60) of the gating sectors circumferential ends are not aligned with circumferential ends (58) edges ring sectors along module longitudinal axis.EFFECT: invention allows better protection of crankcase guide, since gases that could pass between edges of circumferential ends of ring sectors are retained by sectors of laying (due to their angular displacement relative to ring sectors) and cannot reach crankcase guide.10 cl, 10 dwg

Gas turbine engine module

Procede d'assemblage d'elements sectorises (14, 24) d'un stator annulaire
(10) d'une turbine haute-pression de turbomachine autour d'un axe
longitudinal (X-X) de ladite turbine, procede selon lequel, on definit un
motif de repartition angulaire des elements du stator pour un secteur
angulaire predetermine ( Ψ ), le motif de repartition etant defini de facon a
eviter un alignement radial entre des zones inter-secteurs (14a, 24a) des
elements du stator (14, 24) definies entre deux secteurs adjacents d'un
meme element du stator, et a repeter ledit motif de repartition sur toute la
circonference du stator.

Stator de turbine haute-pression de turbomachine et procédé d'assemblage

L'invention concerne une amelioration apportee aux turbines haute pression (10) de turbomachine, telle qu'un turboreacteur, dans lesquelles est prevu un boitier de pilotage (40) des jeux radiaux d'aubes rotatives (18). Selon l'invention, on prevoit un element annulaire (5) a flexibilite determinee dont l'une des extremites (51) est fixee a un support annulaire (24) et dont l'autre extremite (52) est en appui simple axial avec une pression donnee contre l'amont (401) du boitier de pilotage (40). On evite ainsi les sollicitations vibratoires genantes au niveau des points de fixation (45, 46) du boitier de pilotage avec le carter externe (22) des turbines, et par la, le risque d'apparition de criques.

Alain Dominique Gendraud

Papers

Agencement de reglage de diametre d'un stator de turbine a gaz

Ensemble a anneau fixe d'une turbine a gaz

Gas turbine engine module

Stator de turbine haute-pression de turbomachine et procédé d'assemblage

Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles.