Fault-tolerant radial flux rotary electric machines are provided. One such machine comprises: a permanent magnet rotor having fourteen poles; and an alternate-wound stator having sixteen slots and four coil pairs, each coil pair forming part of one of four independent electrical phases.

A flow combiner is provided for a gas turbine engine. The flow combiner includes an outlet duct, a compressor bleed inlet duct coupled to the outlet duct, and a ventilation inlet duct coupled to the outlet duct. The compressor bleed inlet duct is configured to receive a bleed flow from a compressor of the gas turbine engine. The ventilation inlet duct is configured to receive a ventilation flow from an enclosure surrounding the gas turbine engine. The bleed flow and the ventilation flow are combined as an outlet flow through the outlet duct.

Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine , a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.

A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine , a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. A plurality of dispensers is included. Each dispenser of the plurality of dispensers is positioned facing the open surface of the plurality of blades and directs discharged fluid toward the open surface of the plurality of blades to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser. A plurality of exhaust pipes is coupled to the housing and extends away from the shaft directing the discharged fluid out of the housing. Each exhaust pipe corresponds to a respective dispenser of the plurality of dispensers. A controller is in communication with the plurality of dispensers and is configured to control the plurality of dispensers.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. A plurality of dispensers is included. Each dispenser of the plurality of dispensers is positioned facing the open surface of the plurality of blades and directs discharged fluid toward the open surface of the plurality of blades to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser. A plurality of exhaust pipes is coupled to the housing and extends away from the shaft directing the discharged fluid out of the housing. Each exhaust pipe corresponds to a respective dispenser of the plurality of dispensers. A controller is in communication with the plurality of dispensers and is configured to control the plurality of dispensers.