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

A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Turbine ring assembly

The invention concerns a shroud stay sector (14) for minimising working clearances (J) between the summit of the blades (3) and the ring (12) of the high-pressure turbine and mounting clearances of the shroud stay sectors (14) on the high-pressure turbine housing (1). Each shroud stay sector (14) has upstream a tab (20) comprising an end (21) supported on the inner wall (1l) of the high-pressure turbine housing (1) thereby producing a close contact between the parts fixing said shroud stay sector (14) with the corresponding parts of the high-pressure turbine. The invention is applicable to gas turbine engines equipping aircraft.

Stay sector of stator shroud of the high-pressure turbine of a gas turbine engine with clearance control

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

An arrangement for adjusting the diameter of a gas turbine stator includes a casing having a main portion and rings bordering a vein of a gas flow and located in front of respective levels of mobile blades of a rotor, and communication passages of a gas flow under pressure. The rings are surrounded by the casing and fixed thereto by circular groups of spacers. The rings include a wall extending from the casing to one of the rings and separating two chambers. The wall includes an outside edge curved into a spacer hook and engaged between the main portion of the casing and a respective appendage curved into a casing hook associated with the spacer hook. The communication passages of the gas flow under pressure exist between the chambers. At least one of the communication passages is realized by cavities through a junction of hooks.

Arrangement for adjusting the diameter of a gas turbine stator

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.

Alain Dominique Gendraud

Papers

Turbine ring assembly

Stay sector of stator shroud of the high-pressure turbine of a gas turbine engine with clearance control

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

Arrangement for adjusting the diameter of a gas turbine stator

Device for controlling clearance in a gas turbine