Abstract: An encapsulated polymeric article is disclosed. The encapsulated polymeric article may include a polymer substrate and a metallic outer shell at least partially encapsulating the polymer substrate. The encapsulated polymeric article may be fabricated by a method comprising: 1) providing a mandrel in a shape of the encapsulated polymeric article, 2) shaping the metallic outer shell on the mandrel, 3) removing the mandrel from the metallic outer shell, and 4) molding the polymeric substrate into the metallic outer shell through a port formed in the metallic outer shell to provide the encapsulated polymeric article.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan has a bypass ratio of greater than 8.5. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

Abstract: In a featured embodiment, a fan rotor includes a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.

Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.

Abstract: A spinner for a gas turbine engine is disclosed. The spinner may include a body extending between a first and second end comprised of a cured chopped unidirectional fiber pre-impregnated material. The body may have a generally conical shape and may further be plated with a metal or metal alloy.

Abstract: A spinner for a gas turbine engine comprises an outer shell for defining an airflow path when mounted in a gas turbine engine. An inner surface is provided with a plurality of webs. A gas turbine engine and a fan section for a gas turbine engine are also disclosed.

Abstract: A gas turbine engine includes a gear assembly and a bypass flow passage that has an inlet. A fan is arranged within the bypass flow passage. A first turbine is coupled with a first shaft, which is coupled with the fan. A second turbine is coupled with a second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes 12 to 14 (N) of the fan blades, a solidity value (R) at tips of the fan blades that is greater than 0.85 and less than 1.1, and a ratio of N/R that is from 9 to 20.

Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.

Abstract: A gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.

Abstract: A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.

Abstract: A component comprises a non-metallic core having an outer surface, a first catalyst deposited onto at least a first portion of the outer surface of the non-metallic core, a second catalyst deposited onto at least a second portion of the outer surface of the non-metallic core, an electrical interface, and a metallic coating. The electrical interface is plated onto the first catalyst, and includes a first interface layer electroless plated onto the first catalyst. The metallic coating is plated onto the second catalyst.

Abstract: In a featured embodiment, a fan rotor comprises a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.

Abstract: An industrial product comprising a polymer substrate formed in a shape of the industrial product, and a metallic plating layer plated on at least one surface of the industrial product is described. The industrial product may be nuclear waste equipment, industrial equipment exposed to saline, a satellite or satellite component, or heating, ventilation, air-conditioning and refrigeration (HVACR) equipment.

Abstract: A gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.

Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber composite inlet guide vane for a gas turbine engine.

Abstract: A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.

Abstract: Aviation components comprising a polymeric substrate having an outer surface wherein a metal is plated onto the outer surface to form a plated layer are disclosed. A method to make aviation components comprising a polymeric substrate having an outer surface and where a metal is plated onto the outer surface is disclosed. An over-plated heating element for shedding ice from an aircraft component having a polymeric substrate with a pocket to receive a heating element, a metal deposited onto the substrate, a heating element positioned within the pocket and a covering layer deposited onto the heating element and the plated layer is disclosed.