A method for assembling a turbine engine includes assembling a heat exchanger assembly that includes at least a radially inner plate, a radially outer plate, and a heat exchanger coupled between the radially inner and outer plates, forming the heat exchanger assembly such that the heat exchanger assembly has a substantially arcuate shape, and coupling the heat exchanger to a fan casing such that the heat exchanger is positioned upstream or downstream from the fan assembly.

Method and apparatus for operating gas turbine engine heat exchangers

A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the airflow in the heat exchanger, and directing the cooled airflow into the engine casing to cool the casing.

Methods and apparatus for maintaining rotor assembly tip clearances

A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.

Interstage cooled turbine engine

A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger (34) disposed within a bypass duct (30) and accommodated by a sub passage (50) defined by a flow divider (48) affixed to an annular wall of the bypass duct (30). The sub-passage (50) defines an open upstream end (52) and an open downstream end (54) to direct a portion of the bypass air flow to pass therethrough.

Turbofan bypass duct air cooled fluid cooler installation

The present application provides a stoichiometric exhaust gas recovery turbine system. The stoichiometric exhaust gas recovery turbine system may include a main compressor for compressing a flow of ambient air, a turbine, and a stoichiometric exhaust gas recovery combustor. The stoichiometric exhaust gas recovery combustor may include a combustion liner, an extended flow sleeve in communication with the main compressor, and an extraction port in communication with the turbine. The extended flow sleeve receives the flow of ambient air from the main compressor so as to cool the combustion liner and then the flow of ambient air splits into an extraction flow to the turbine via the extraction port and a combustion flow within the combustion liner.

Stoichiometric Exhaust Gas Recirculation Combustor

The invention relates to a method of supplying cooling air to the hot portions of a turbojet that comprises, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor, in which method a flow of air is bled from the flow of air delivered by the compressor, the bled-off flow is cooled in a heat exchanger situated radially outside the combustion chamber, and is then directed radially inwards via the stationary blades of the distributor and used for cooling the moving wheel of the turbine, the method wherein the flow of cooling air is bled from the zone of the end of the combustion chamber that surrounds the diffuser, and wherein the stationary blades of the distributor are also cooled by a second flow of air bled from the diffuser.

Heat exchanger on a turbine cooling circuit

The cooling system (30) for an aircraft engine (10) comprises a channel (32) that draws off cold air in the secondary air flow (200), and a heat exchanger (34) located in the channel (32) and in which hot air circulates. The channel (32) comprises:- a supply pipe (322) and an evacuation pipe (326) fixed to the nacelle (324), - an intermediate box (324) located between the supply pipe (322) and the evacuation pipe (326), fixed to the engine (10), and in which the heat exchanger (34) is placed. Application to cooling of hot parts (22) in an aircraft engine (10).

Cooling system for hot parts of an aircraft engine, and aircraft engine equipped with such a cooling system

The invention concerns a housing (21) comprising an outer casing (22) provided with hooks (24) for supporting stator rings (26) and sealing rings (27); the hooks (24) are angularly discontinuous and assembled at the casing (22) by mortise-and tenon joints (28, 29). Thus the hooks and the casing can be of different constructions, that of the hooks being heat-resistant and the other being more amenable to machining and forming. Ventilation, clearance control and thermal protection are facilitated.

Gas turbine stator housing

The stator housing (39), comprising a casing with rings (41, 44) attached to its inner surface by hooks (40), has each hook made with two opposite slots (42, 43) to engage with two rings. The hooks are connected to the casing by tenon and mortise joints (47, 48), and the rings are in the form of seal rings alternating with fixed blade rings, fitted to certain hooks in a way that leaves the hooks partially exposed. Some of the hooks are one-sided and support fixed stator blade rings only.

Fixing stator elements in a turbomachine casing

In a succession of rotor disks, only the end disks are connected to a main structure by bolted extensions and the intermediate disks are suspended from rigid spacer pieces by centering and anti-rotation connections. The end disks are interconnected to clamp the assembly in the axial direction. There is no bolted connection between the successive disks. Assembly is very easy. The disks and the spacer pieces are stacked together in alternately, and the assembly is torsionally very rigid because of the use of a high number of claw-coupling teeth formed by protruding ends of the blade roots forming teeth that engage in spacer piece end rims.

Laurent Palmisano

Papers

Heat exchanger on a turbine cooling circuit

Cooling system for hot parts of an aircraft engine, and aircraft engine equipped with such a cooling system

Gas turbine stator housing

Fixing stator elements in a turbomachine casing

Turbomachine rotor arrangement