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

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

L'invention porte sur une turbine (10) d'un moteur a turbine a gaz comprenant au moins un distributeur de turbine (25) et un rotor de turbine (1 1 ), ledit distributeur de turbine (25) comprenant au moins une plate-forme annulaire interne (26), ladite plate-forme interne (26) comprenant une paroi radiale (30) menageant au moins une cavite (31 a, 31 b) entre le distributeur de turbine (25) et le rotor de turbine (1 1 ), turbine (10) caracterisee en ce que le rotor de turbine (1 1 ) comprend au moins un element allonge (40, 42) dispose substantiellement axialement et definissant une chicane d'etancheite dans ladite cavite (31 a, 31 b) et en ce que le distributeur de turbine (25) comprend au moins un element en materiau abradable (44) apte a cooperer avec ledit element allonge (40, 42) du rotor de turbine (1 1 ) de maniere a former un joint d'etancheite a labyrinthe.

Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz

The paddle wheel (1) has a rotor disk (2) equipped with mounting slots (3) of blade roots (4). Paddles (9) comprise platforms (11) internally defining an annular fluid flow duct. A piece (15) is returned back on an upstream face (16) of the rotor disk at an external periphery. An annular spoiler (17) extends axially toward upstream at a level of the platforms, and limits a passage of fluid outside the fluid flow duct. Sealing units i.e. joints (26), are arranged between the piece and upstream ends (28) of the platforms of the paddles. An independent claim is also included for a turboshaft engine.

Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles

L'invention concerne une roue mobile de turbomachine a aubes en materiau composite, comportant un flasque de montage (4), une pluralite d'aubes (16) en materiau composite montees sur le flasque de montage, chaque aube ayant un talon (20) en sommet muni de lechettes (22), un disque d'orientation (28) fixe coaxialement autour du flasque de montage et comprenant a sa peripherie exterieure une pluralite de fentes axiales ouvertes a une extremite, chaque fente presentant une section transversale adaptee a la section transversale d'un pied (18) d'aube afin de le maintenir angulairement par cooperation de forme, et un anneau ressort a diametre variable (38) loge en partie dans une encoche axiale (26) formee dans chaque pied d'aube et faisant saillie axialement par rapport a celui-ci, l'anneau ressort etant apte a venir en butee radiale contre une surface interne (34a) du disque d'orientation lors d'un deplacement radial des aubes vers l'exterieur du flasque de montage.

Roue mobile de turbomachine a aubes en materiau composite munie d'un anneau ressort

A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.

Alain Dominique Gendraud

Papers

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

Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz

Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles

Roue mobile de turbomachine a aubes en materiau composite munie d'un anneau ressort

Turbine stage for a turbine engine