Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

Abstract: An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.

Abstract: A one-way valve, comprises a valve housing; a valve member provided within the valve housing, the valve member being operative to open and close the valve and comprising a diaphragm with a central orifice to allow fluid to pass from one side of the diaphragm to the other; a valve inlet provided on a first side of the diaphragm; and a valve outlet provided on a second side of the diaphragm; wherein the configuration of the diaphragm and the valve housing biases the diaphragm to seal the inlet at rest.

Abstract: An auxiliary power unit having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft drivingly engaged to the engine shaft, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

Abstract: An insert for a vehicle wheel having a plurality of spokes which define, in part, an outwardly-facing wheel surface, and further define between adjacent ones of the spokes, a cavity for receiving the insert, in use, the insert comprising: an outer profile of complementary shape to the cavity and arranged to fit securely within the cavity, in use; and a flow redirecting surface which is aerodynamically shaped so as to reduce drag on an adjacent spoke of the wheel, in use.

Abstract: A one-way valve, comprises a valve housing; a valve member provided within the valve housing, the valve member being operative to open and close the valve and comprising a diaphragm with a central orifice to allow fluid to pass from one side of the diaphragm to the other; a valve inlet provided on a first side of the diaphragm; and a valve outlet provided on a second side of the diaphragm; wherein the configuration of the diaphragm and the valve housing biases the diaphragm to seal the inlet at rest.

Abstract: An analysis apparatus for performing biochemical analysis of a sample using nanopores comprises: a sensor device that that supports plural nanopores, reservoirs holding material for performing the analysis; a fluidics system; and plural containers for receiving respective samples, all arranged in a cartridge that is removably attachable to an electronics unit arranged to generate drive signals to perform signal processing circuit to generate output data representing the results of the analysis. The fluidics system supplies samples selectively from the containers to the sensor device using a rotary valve. In one valve, a stator defines a plurality of first ports arranged around the rotational axis and a collection chamber extending in around the axis of rotation in communication with a second port. A rotor provides a passage extending between the collection chamber and a position in communication with any one of the plurality of first ports.

Abstract: In at least one illustrative embodiment, a winch may include first and second end frames, a drum coupled between the first and second end frames and configured to rotate to wind or unwind a cable, a brake configured to resist rotation of the drum when engaged, a switch configured to cause the brake to engage the drum when the switch is activated, a slack arm frame having a first end engaged with the cable and a second end pivotally coupled between the first and second end frames, where the slack arm frame is configured to pivot between a first position when the cable is taut and a second position when the cable is slack, and a cam coupled to the slack arm frame and configured to rotate with the slack arm frame to activate the switch when the slack arm frame is in the second position.

Abstract: An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

Abstract: A press roller spring frame is provided. The spring frame includes a frame body having a first section having an arcuate shape, a second section extending from the first section and having a substantially planar shape, a third section extending from the first section and having a substantially planar shape. The second and third sections are configured to oppose one another with the first section therebetween. The spring frame further includes a roller operatively coupled to the third section and configured to rotate about an axis. A compressive force may be applied to the roller to displace the third section closer to the second section, whereby the arcuate shape of the first member is compressed. The compression causes the first member to produce a spring force that resists the compressive force applied against the roller to keep the roller against the object applying the compressive force.

Abstract: In at least one illustrative embodiment, a winch may include first and second end frames, a drum coupled between the first and second end frames and configured to rotate to wind or unwind a cable, a brake configured to resist rotation of the drum when engaged, a switch configured to cause the brake to engage the drum when the switch is activated, a slack arm frame having a first end engaged with the cable and a second end pivotally coupled between the first and second end frames, where the slack arm frame is configured to pivot between a first position when the cable is taut and a second position when the cable is slack, and a cam coupled to the slack arm frame and configured to rotate with the slack arm frame to activate the switch when the slack arm frame is in the second position.

Abstract: A vehicle comprises a driver display on which is displayed an advisory maximum wading speed according to the current wading depth of the vehicle. The advisory speed is in one embodiment displayed on the vehicle speedometer. The display may also include an elevation of a vehicle on which is indicated one or more of maximum wading depth, current wading depth and vehicle inclination.

Abstract: An analysis apparatus for performing biochemical analysis of a sample using nanopores comprises: a sensor device that that supports plural nanopores, reservoirs holding material for performing the analysis; a fluidics system; and plural containers for receiving respective samples, all arranged in a cartridge that is removably attachable to an electronics unit arranged to generate drive signals to perform signal processing circuit to generate output data representing the results of the analysis. The fluidics system supplies samples selectively from the containers to the sensor device using a rotary valve. In one valve, a stator defines a plurality of first ports arranged around the rotational axis and a collection chamber extending in around the axis of rotation in communication with a second port. A rotor provides a passage extending between the collection chamber and a position in communication with any one of the plurality of first ports.

Abstract: A pump for use in low-profile applications comprises a barrel for holding fluid; and a piston that converts a rotational driving force into a longitudinal driving motion within the barrel. The pump provides space saving advantages by reducing the need for external equipment and mechanisms around the pump for providing actuation or moving the actuating mechanism.

Abstract: Speaker bracket comprising an attachment body (2) having a pivot column formed within a recessed channel. An arm assembly is provided comprising a tiltable inner arm portion (4) at least partially housed within an outer arm portion (3). The outer arm portion has a pivot channel into which the pivot column is received for connecting the arm assembly to the attachment body (2) and permitting it to swivel about the pivot column. A rotatable assembly is provided comprising an interface plate (6) connected to the front of the inner arm portion (4) and a speaker fixing plate (8) for attachment to a speaker and being rotatably connected to the interface plate (6) through a shaft (9) and fastener. The shaft (9) and fastener are at least partially received within a cavity in the front of the inner arm portion (4).

Abstract: A compound engine assembly for use as an aircraft auxiliary power unit, having an engine core including internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the engine core inlet, and a turbine section having an inlet in communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in communication with the engine core outlet, and a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

Abstract: An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.