A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.

An air turbine starter device comprises a rotor arranged in a cavity of a housing, a first manifold having a cavity with a port operative to direct compressed air to the rotor, a second manifold having a cavity with a port operative to direct compressed air to the rotor, wherein the first manifold is larger than the second manifold.

A nacelle is disclosed. The nacelle may comprise, in various embodiments, a drag link fitting mounted to an Inner Fixed Structure (IFS) and pivotally attached to an end of a drag link, and a vent defining a passageway through the IFS to bring cooling air through the IFS. The drag link fitting may be aerodynamically associated with the vent such that the drag link fitting helps direct air into the vent.

A cooling system configured to reduce a temperature within a gas turbine engine in a shutdown mode of operation includes a first gas turbine engine including a compressor having a bleed port. In a first operating mode of the gas turbine engine, the compressor bleed port is configured to channel a high pressure flow of air from the compressor. During a shutdown mode of operation, the compressor bleed port is configured to channel an external flow of cooling air into the compressor. The cooling system also includes a source of cooling air and a conduit coupled in flow communication between the compressor bleed port and the source of cooling air. The source of cooling air configured to deliver a flow of cooling air into the compressor through the compressor bleed port.

A device for circulation of air for a turbomachine, the device including an inlet provided to receive incident airflow, air circulation ducts connected to the inlet, a central part including side walls, peripheral walls arranged at a distance from the central part, so as to form the air circulation ducts, each duct being arranged between one of the side walls of the central part and one of the peripheral walls, each peripheral wall including an upstream end portion delimiting with one of the side walls an inlet orifice of one of the ducts and a downstream end portion delimiting with one of the side walls an outlet orifice of one of the ducts, at least one member mobile in translation relative to the peripheral walls, the at least one mobile member being formed in the central part and arranged so that its displacement varies a section of each of the inlet orifices and a section of at least one of the outlet orifices.

A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.

A method of transferring a fluid flow from a static component to a rotor of a gas turbine engine and a modulated flow transfer system are provided. The modulated flow transfer system includes an annular inducer configured to accelerate the fluid flow in a substantially circumferential direction in a direction of rotation of the rotor. The system further includes a first fluid flow supply including a compressor bleed connection, a feed manifold formed of bendable tubing, and a feed header extending between the compressor bleed connection and the feed manifold. The feed header includes a modulating valve configured to control an amount of fluid flow into the feed manifold. The system also includes a flow supply tube that extends between the feed manifold and the inducer and is couplable to at least one of the plurality of first fluid flow inlet openings through a sliding piston seal.

Embodiments of hot streak alignment for gas turbine durability include structures and methods to align hot streaks with the leading edges of aligned first stage nozzle vanes in order to improve mixing of the hot streaks with cooling air at a stator nozzle of a first stage turbine and reduce usage of cooling air at first stage non-aligned stator nozzle vanes disposed adjacent to the aligned stator vanes.

An apparatus is provided for a powerplant. The apparatus includes a heat pipe extending axially along an axis from a first end of the heat pipe to a second end of the heat pipe. The heat pipe extends circumferentially around the axis. The heat pipe includes an evaporator region, a condenser region and a plurality of fluid passages. The evaporator region is disposed at the second end of the heat pipe. The condenser region is disposed at the first end of the heat pipe. The condenser region is disposed radially inboard of the evaporator region. The fluid passages are axially between and fluidly couple the evaporator region and the condenser region.

An apparatus is provided for a powerplant. The apparatus includes a heat pipe extending axially along an axis from a first end of the heat pipe to a second end of the heat pipe. The heat pipe extends circumferentially around the axis. The heat pipe includes an evaporator region, a condenser region and a plurality of fluid passages. The evaporator region is disposed at the second end of the heat pipe. The condenser region is disposed at the first end of the heat pipe. The condenser region is disposed radially inboard of the evaporator region. The fluid passages are axially between and fluidly couple the evaporator region and the condenser region.