Abstract: Devices, systems, and techniques are described to detect when a power transmitting and receiving system is in an inefficient position, which may cause a thermal response that less desirable than a more efficient position. The system may power transmitting device configured to wirelessly transfer electromagnetic energy to a power receiving device. Processing circuitry of the system may compute a target output power deliverable by the power transmitting device for a first duration and control the power transmitting device to output the target output power based in part on a heat limit. The processing circuitry may further calculate an energy transfer efficiency to the power receiving unit, update an adjustment factor based on the calculated energy transfer efficiency, and apply the adjustment factor to the heat limit for a subsequent duration.

Abstract: Devices, systems, and techniques are described to detect when a power transmitting and receiving system is in an inefficient position, which may cause a thermal response that less desirable than a more efficient position. The system may power transmitting device configured to wirelessly transfer electromagnetic energy to a power receiving device. Processing circuitry of the system may compute a target output power deliverable by the power transmitting device for a first duration and control the power transmitting device to output the target output power based in part on a heat limit. The processing circuitry may further calculate an energy transfer efficiency to the power receiving unit, update an adjustment factor based on the calculated energy transfer efficiency, and apply the adjustment factor to the heat limit for a subsequent duration.

Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.

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: The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment. The nosecap may have bolt holes surrounded by bolt pockets that are asymmetric about a plane passing through a geometric center of the nosecap and passing through and dividing the bolt hole in an embodiment.

Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Abstract: A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub. A platform is removably secured to the hub and is arranged adjacent to the fan blade. The platform has a body with lateral sides that each include a channel. A seal is removably received in each of the channels, with one of the seals abutting the fan blade. A method of repairing the fan blade platform includes the steps of removing a nose cone to provide access to a hub, detaching a platform from the hub, and pulling the seal from a groove in the platform.

Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.

Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.

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: The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment. The nosecap may have bolt holes surrounded by bolt pockets that are asymmetric about a plane passing through a geometric center of the nosecap and passing through and dividing the bolt hole in an embodiment.

Abstract: A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.

Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.

Abstract: A fan assembly includes a first fan blade with a rib extending therealong and a first fairing platform mounted on and supported from the first fan blade. The first fairing platform has a flange with a groove that mates with the rib.

Abstract: A method, performed by a computer device, may include scanning a network of digital cross connect devices to identify an open port and determining that the identified open port has been designated as unavailable in a provisioning database. The method may further include determining that the identified open port corresponds to a recoverable port and recovering the identified open port by designating the identified open port as available in the provisioning database, in response to determining that the identified open port corresponds to a recoverable port.

Abstract: A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.

Abstract: A fan assembly includes a first fan blade with a rib extending therealong and a first fairing platform mounted on and supported from the first fan blade. The first fairing platform has a flange with a groove that mates with the rib.

Abstract: A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub. A platform is removably secured to the hub and is arranged adjacent to the fan blade. The platform has a body with lateral sides that each include a channel. A seal is removably received in each of the channels, with one of the seals abutting the fan blade. A method of repairing the fan blade platform includes the steps of removing a nose cone to provide access to a hub, detaching a platform from the hub, and pulling the seal from a groove in the platform.

Abstract: A method, performed by a computer device, may include scanning a network of digital cross connect devices to identify an open port and determining that the identified open port has been designated as unavailable in a provisioning database. The method may further include determining that the identified open port corresponds to a recoverable port and recovering the identified open port by designating the identified open port as available in the provisioning database, in response to determining that the identified open port corresponds to a recoverable port.