Methods and apparatus for de-gasification of vehicle cooling system using a coolant bottle are disclosed. The coolant bottle may include a coolant entrance port configured to be in fluid communication with the vehicle cooling system, and a coolant egress port configured to be in fluid communication with the vehicle cooling system. The coolant egress port is directly connected to the vehicle cooling system. The coolant bottle may further include a plurality of baffle plates placed to divide an interior of the coolant bottle into a plurality of coolant channels. Each baffle plate may include a plurality of apertures configured to provide fluid communication between the plurality of coolant channels.

Methods and apparatus for de-gasification of vehicle cooling system using a coolant bottle are disclosed. The coolant bottle may include a coolant entrance port configured to be in fluid communication with the vehicle cooling system, and a coolant egress port configured to be in fluid communication with the vehicle cooling system. The coolant egress port is directly connected to the vehicle cooling system. The coolant bottle may further include a plurality of baffle plates placed to divide an interior of the coolant bottle into a plurality of coolant channels. Each baffle plate may include a plurality of apertures configured to provide fluid communication between the plurality of coolant channels.

The supercharging system and the internal combustion engine according to the present invention are provided with: a first supercharger (20); a second supercharger (30); an electric motor (23) connected to a shaft end of a first compressor (21); a generator (24) connected to a shaft end of a first turbine (22); a bypass exhaust pipe (L6) that allows exhaust air to bypass the first turbine (22); a cooler (51) that cools the generator (24); and a control device (50) that activates the cooler (51) when the generator (24) is driven by exhaust air that has driven the first turbine (22).

The supercharging system and the internal combustion engine according to the present invention are provided with: a first supercharger (20); a second supercharger (30); an electric motor (23) connected to a shaft end of a first compressor (21); a generator (24) connected to a shaft end of a first turbine (22); a bypass exhaust pipe (L6) that allows exhaust air to bypass the first turbine (22); a cooler (51) that cools the generator (24); and a control device (50) that activates the cooler (51) when the generator (24) is driven by exhaust air that has driven the first turbine (22).

There is provided a vertical multicylinder straight engine in which the temperature distribution of a plurality of cylinder barrels is made close to an even state. A cylinder jacket includes: a jacket inlet; a separated channel; a plurality of separated outlets; and heat dissipater channels for dissipating heat of the respective cylinder barrels to engine cooling water introduced through the separated outlets. The plurality of separated outlets include: a front-side separated outlet to a front-end barrel; a rear-side separated outlet to a rear-end barrel; and middle separated outlets to middle barrels between the front-end barrel and the rear-end barrel, and the jacket inlet is disposed so as to be contained within an entire middle barrel side area that is lateral to the middle barrels and has a front-rear length as long as a length from a front-most end to a rear-most end of the middle barrels.

A marine engine comprises a powerhead having an engine block, a cylinder head and a crankcase containing a crankshaft. Operation of the marine engine causes rotation of the crankshaft. A crankcase cover encloses the crankshaft in the crankcase. A supercharger is on the crankcase cover, the supercharger being configured to provide charge air for combustion in the powerhead. A cooling passage conveys cooling fluid between the crankcase cover and the supercharger so that the cooling fluid cools both in the crankcase and in the supercharger.

An engine-and-electric-machine assembly is provided that includes an engine and an electric machine, a crankshaft being provided in the engine, the crankshaft including a main body and an extension section that extends out to the exterior of the engine, the extension section forming a rotation shaft of the electric machine, and a rotor of the electric machine being mounted on the extension section, wherein a terminal of the rotation shaft is connected to a coolant pump, a rotor of the coolant pump is mounted to the rotation shaft, and while the rotation shaft is rotating the rotation shaft drives the coolant pump to provide coolant to the electric machine. By connecting the rotation shaft of the electric machine to the coolant pump, the pump can be highly integrated into the system and reduce manufacturing cost.

An engine-and-electric-machine assembly is provided that includes an engine and an electric machine, a crankshaft being provided in the engine, the crankshaft including a main body and an extension section that extends out to the exterior of the engine, the extension section forming a rotation shaft of the electric machine, and a rotor of the electric machine being mounted on the extension section, wherein a terminal of the rotation shaft is connected to a coolant pump, a rotor of the coolant pump is mounted to the rotation shaft, and while the rotation shaft is rotating the rotation shaft drives the coolant pump to provide coolant to the electric machine. By connecting the rotation shaft of the electric machine to the coolant pump, the pump can be highly integrated into the system and reduce manufacturing cost.

Passive reduction of internal jet engine component temperature in supersonic and hypersonic vehicles results from use of nanocomposite optical ceramic materials between the heat-generating portions of each jet engine and the ambient environment, allowing heat dissipation from the jet engine components directly to the ambient environment. A propulsion-airframe integrated scramjet aircraft includes a jet engine and an airframe supporting the jet engine, with at least a portion of the airframe between a heat-generating portion of the jet engine and an ambient environment comprising a nanocomposite optical ceramic material in the form of a panel or a grid of windows each supported within a frame. The nanocomposite optical ceramic material portion of the airframe disposed between the heat-generating portion of the jet engine and the ambient environment is infrared-transparent, and may transmit at least 75% of heat energy from the heat-generating portion of the jet engine to the ambient environment.

An aircraft propulsion system comprising a reciprocating liquid cooled engine housed within the fuselage driving twin fuselage mounted ducted-fans is disclosed. The propulsion system may be liquid cooled with a liquid cooled exhaust and at least one turbocharger. The ducted-fans may run fan blade tip speeds of up to 97% Mach driven by a near constant RPM engine through a continuously variable transmission. The propulsion system may be low noise and may meet environmental standards typical in the automotive industry.