A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine.

A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine.

An outboard motor includes an exhaust passage that discharges exhaust gases generated in a V-type engine into water from an exhaust opening. The exhaust passage includes first and second branch passages connected to cylinders and disposed inside a V-shaped line, a first upstream collecting passage connected to each of the first branch passages, a second upstream collecting passage connected to each of the second branch passages, and a downstream collecting passage connected to the first and second upstream collecting passages. A portion from an upstream end of the downstream collecting passage to a downstream end of the downstream collecting passage is disposed outside cylinder heads of the V-type engine.

A propulsion system is provided, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

A propulsion system is provided, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

Provided is an engine generator with improved accessibility to an operation panel. An engine generator includes: a casing; a generator; and an engine that drives the generator, the generator and the engine being housed in the casing, wherein a plurality of panels each having a predetermined dimension are respectively removably provided at side surfaces of the casing, and any selected one of the plurality of panels can be exchanged for a console for the engine generator.

A ferritic aero diesel engine. The ferritic aero diesel engine includes an iron crankcase, a steel crankshaft and eight steel piston assemblies. The iron crankcase has a flat, horizontally opposed eight cylinder arrangement with a first set of cylinder walls defining a first set of cylinders in a first bank and a second set of cylinder walls defining a second set of cylinders in an opposed second bank. The steel crankshaft is rotatably mounted at least partially within the iron crankcase. Each of the steel piston assemblies of the plurality of steel piston assemblies is received within a respective cylinder of the iron crankcase and is coupled to the steel crankshaft. The first and second sets of cylinder walls have a minimum wall thickness of between approximately 4.8 and 5.2 mm.

A ferritic aero diesel engine. The ferritic aero diesel engine includes an iron crankcase, a steel crankshaft and eight steel piston assemblies. The iron crankcase has a flat, horizontally opposed eight cylinder arrangement with a first set of cylinder walls defining a first set of cylinders in a first bank and a second set of cylinder walls defining a second set of cylinders in an opposed second bank. The steel crankshaft is rotatably mounted at least partially within the iron crankcase. Each of the steel piston assemblies of the plurality of steel piston assemblies is received within a respective cylinder of the iron crankcase and is coupled to the steel crankshaft. The first and second sets of cylinder walls have a minimum wall thickness of between approximately 4.8 and 5.2 mm.

A waste heat recovery system includes: a heater which evaporates a working medium by exchanging heat between supercharged air supplied to an engine and the working medium; an expander which expands the working medium which has flowed out from the heater; a power recovery device connected to the expander; a condenser which condenses the working medium which has flowed out from the expander; a cooling medium supply pipe for supplying a cooling medium to an air cooler which cools the supercharged air which has flowed out from the heater; a cooling medium pump which is provided in the cooling medium supply pipe and which sends the cooling medium to the air cooler; and a branch pipe which bifurcates a part of the cooling medium flowing in the cooling medium supply pipe, to the condenser, in such a manner that the working medium is cooled by the cooling medium.

A marine propulsion device has an internal combustion engine; an intake manifold that delivers intake air from an upstream inlet to a downstream outlet for combustion in a plurality of piston-cylinders in the internal combustion engine; and a flame arrestor located in the intake manifold at the upstream inlet.