A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

An engine heater system for heating a diesel engine of a vehicle. The engine heater system including a gas turbine. A heat exchanger communicatively coupled to an exhaust of the gas turbine. An electric generator including connection members to couple to a battery of the vehicle, and a shaft rotatably attached between the gas turbine and the electric generator. The heat exchanger utilizes the exhaust of the gas turbine to keep the diesel engine of the vehicle within a desired temperature range, and the electric generator charges the battery when the gas turbine rotates the shaft.

An engine heater system for heating a diesel engine of a vehicle. The engine heater system including a gas turbine. A heat exchanger communicatively coupled to an exhaust of the gas turbine. An electric generator including connection members to couple to a battery of the vehicle, and a shaft rotatably attached between the gas turbine and the electric generator. The heat exchanger utilizes the exhaust of the gas turbine to keep the diesel engine of the vehicle within a desired temperature range, and the electric generator charges the battery when the gas turbine rotates the shaft.

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

The gas turbine engine includes a combustion section including an annular swirl combustor having a combustor inlet, and a compressor section including a centrifugal compressor with an impeller, the impeller compressing and swirling an airflow and discharging the compressed and swirled airflow from the impeller outlet into the combustor inlet. The turbine section includes a radial turbine having a turbine fuel inlet and a turbine fuel outlet, the radial turbine receiving a flow of fuel at the turbine fuel inlet and discharging the flow of fuel from the turbine fuel outlet of the radial turbine into the combustor inlet.

A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

Methods of manufacturing of aerospace structures are disclosed. More specifically, methods of manufacturing relatively lightweight yet strong aerospace structures. In one embodiment, the method includes the addition of a volume of a rigid and flexible polyurethane mixture into a mold to create a composite structure. In one aspect, the method includes the integration of special structures within a larger structure to remove traditionally structurally weak or vulnerable areas.