Abstract: An anti-ice arrangement for a gas turbine engine may comprise an engine static structure, a fan blade housed for rotation within the engine static structure, and a magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade.

Abstract: A power takeoff and gearbox system of a multi-spool gas turbine engine includes a low rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, and a high rotor towershaft operably connected to and driven by a second spool of the gas turbine engine. The high rotor towershaft and the low rotor towershaft are concentric and extend to a common gearbox housing.

Abstract: Disclosed is a method for machining a component, comprising: installing the component on a fixture, causing a medium of the fixture to solidify to encase a first portion of the component, applying a toolset to a second portion of the component that is outside of the solidified medium, and subsequent to applying the toolset, extracting the component from the fixture when the medium is in one of a liquid state or a semi-liquid state, where the medium has a melting-point temperature that is less than 500 degrees Fahrenheit. Disclosed is a fixture for machining a component, comprising: a medium configured to encase a first portion of the component when the medium is in a solidified state, and a toolset configured to be applied to a second portion of the component that is outside of the solidified medium, the medium having a melting-point temperature that is less than 500 degrees Fahrenheit.

Abstract: An anti-ice system for a gas turbine engine may comprise a power generating device and a first thermally conductive applique comprising a first heating circuit. The power generating device may comprise a first component configured to rotate about an axis and generate a current. A first conductive layer may electrically couple the first heating circuit and the first component of the power generating device.

Abstract: A gas turbine engine has an engine static structure and at least one component rotatable relative to the engine static structure about an engine axis of rotation. A fan is coupled to at least one component for rotation about the engine axis of rotation. An actuator is mounted to the engine static structure, wherein the actuator is activated to prevent the fan from rotation and is inactivated to allow the fan to rotate. A method for preventing rotation of a fan in a gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.

Abstract: A gas turbine engine including a compressor has a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine includes a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. The first shaft includes at least one magnetic section. An electromagnet is disposed radially outward of the first shaft at an axial location of the at least one magnetic section, relative to an axis defined by the gas turbine engine.

Abstract: A compressor case for a gas turbine engine includes an annular body that extends circumferentially around a center axis and extends axially along the center axis. A first bleed manifold is formed on an outer surface of the annular body and encloses a first plenum. A second bleed manifold is formed on the outer surface of the annular body and is axially aft of the first bleed manifold. The second bleed manifold encloses a second plenum. A bleed inlet extends through the annular body and into the first bleed manifold. Cooling passages are formed in the annular body, and each of the cooling passages extends from the first plenum to the second plenum and fluidically connects the first plenum to the second plenum.

Abstract: A gas turbine engine includes a joint and a flexible strip wrapped circumferentially around the joint. The flexible strip includes a lock operable to fasten the flexible strip about the joint. A thermochromatic layer is attached to a surface of the flexible strip and is operable to change color responsive to a change in temperature.

Abstract: An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.

Abstract: A method for forming a sheet structure includes providing a tool having a formation surface corresponding to a shape of the sheet structure. The method also includes depositing at least one layer of material on the formation surface using a cold-spray deposition technique. The method also includes removing the at least one layer of material from the formation surface to create the sheet structure.

Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

Abstract: A method for forming a metallic structure having multiple layers includes providing a main tool having a main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing the first layer of material on the main formation surface using a cold-spray deposition technique. The method also includes positioning a secondary tool having a secondary formation surface in a portion of a first volume defined by a first surface of the first layer of material. The method also includes depositing a second layer of material on the secondary formation surface using the cold-spray deposition technique. The method also includes removing the secondary tool such that the first volume is positioned between the first layer of material and the second layer of material.

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.

Abstract: A variable-pitch vane system for a gas turbine engine includes a plurality of vanes and a synchronization ring assembly operably connected to the plurality of vanes. The synchronization ring assembly includes a first synchronization ring, a second synchronization ring and a bridge bracket connecting the first synchronization ring to the second synchronization ring. The bridge bracket includes a first face sheet, a second face sheet, a honeycomb core located between the first face sheet and the second face sheet, a first attachment feature located at a first end of the bridge bracket at which the first synchronization ring is secured, and a second attachment feature located at a second end of the bridge bracket at which the second synchronization ring is secured.

Abstract: 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.

Abstract: A gas turbine engine includes an engine case along an engine axis, a conformal accessory drive gearbox housing mounted to the engine case, and at least one accessory mounted to the conformal housing

Abstract: A gas turbine engine includes a high pressure compressor disposed about a central longitudinal axis, a combustor, and a diffuser case. The diffuser case includes an outer ring providing a first platform and an inner ring providing a second platform. The first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis. A plurality of circumferentially spaced struts extend radially from the first platform to the second platform and each include first and second circumferential sides. A plurality of heat shields are disposed on a leading edge defined at a forward end of a respective one of the plurality of struts.

Abstract: A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

Abstract: A thermal management system for a gas turbine engine includes an additively manufactured outer engine duct structure, at least a portion of an internal surface of the additively manufactured outer engine duct structure forming an additively manufactured heat exchanger