A gas turbine engine includes an electrical device and a microchannel cooling system in communication with the electrical device to remove heat.

A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.

A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.

A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, characterized in that wherein said channels are formed, at least in part, inside said fins.

A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.

A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.

A method of making a light weight housing for an internal component is provided. The method including the steps of: forming a first metallic foam core into a desired configuration; forming a second metallic foam core into a desired configuration; inserting an internal component into the first metallic foam core; placing the second metallic foam core adjacent to the first metallic core in order to secure the internal component between the first metallic foam core and the second metallic foam core; applying an external metallic shell to an exterior surface of the first metallic foam core and the second metallic foam core; and securing an inlet fitting and an outlet fitting to the housing, wherein a thermal management fluid path for the internal component into and out of the housing is provided by the inlet fitting and the outlet fitting.

A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration; forming an inlet opening and an outlet opening in the external metallic shell in order to provide a fluid path through the metallic foam core; and injecting a thermoplastic material into the metallic foam core via the inlet opening.

A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; and applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration.

A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade. At least one of the pressure side cooling fluid passages may receive fresh cooling fluid from a cooling fluid inlet opening at the root end of the blade and direct the cooling fluid radially upwardly toward the tip end of the blade, across a top side of the bifurcating internal wall, and down through at least one of the plurality of suction side cooling fluid passages.