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

The turbine (10) has an impeller (18) rotatively mounted downstream of a distributor (16). Ring sectors (20) are circumferentially arranged in an end to end manner, and suspended to an outer casing (22) by an annular support (24). The distributor has an inner radial end including a fixation unit fixed on an inner casing. The distributor has an outer radial end that is in axial support on an annular plate (90), where the plate is suspended to the outer casing irrespective of the annular support of the ring sectors.

High-pressure turbine for e.g. turbojet engine, of airplane, has distributor with outer radial end that is in axial support on annular plate, where plate is suspended to outer casing irrespective of annular support of ring sectors

Etage de turbine pour une turbomachine, comprenant un distributeur (112) et une roue montee a l'interieur d'un anneau (118) sectorise porte par un carter (114), le distributeur etant accroche au carter et etant retenu axialement vers l'aval par appui sur un jonc annulaire (136), les secteurs d'anneau comprenant chacun a leurs extremites amont un organe (144) a section en C qui est engage sur le rail de carter et qui maintient radialement le jonc, caracterise en ce que la paroi radialement interne (148) de l'organe en C de chaque secteur d'anneau s'etend a l'interieur du jonc sur toute la dimension axiale de ce dernier et sa partie d'extremite amont est engagee dans au moins un evidement (160, 162) du distributeur.

Etage de turbine pour une turbomachine

Turbine haute-pression de turbomachine amelioree, secteur de distributeur et moteur d'aeronef associes

Module de turbomachine

Une entretoise (1) fixee a une portion principale de stator de
turboreacteur porte un anneau (5) par une paire de crochets (4,6) d'un
cote et des levres (7,8) de jonction de l'autre cote. L'etancheite est
realisee sur des faces planes (10,11) adjacentes aux levres par la
flexion elastique de pattes (13) repoussant une des levres (7). Les
pattes (13) peuvent aussi assurer le positionnement tangentiel de
l'anneau (5).

Alain Dominique Gendraud

Papers

High-pressure turbine for e.g. turbojet engine, of airplane, has distributor with outer radial end that is in axial support on annular plate, where plate is suspended to outer casing irrespective of annular support of ring sectors

Etage de turbine pour une turbomachine

Turbine haute-pression de turbomachine amelioree, secteur de distributeur et moteur d'aeronef associes

Module de turbomachine

Agencement de liaison d'un anneau de stator de turbine à une entretoise de support