Abstract: An ignition system for an internal combustion engine includes an ignition coil forming a part of a primary circuit and a secondary circuit, a power source to supply power to the ignition coil, and a controller to determine whether the ignition coil is a recognized ignition coil based on a measured risetime and a measured current level in the primary circuit, the measured current level being lower than that required to create a breakdown voltage of the ignition coil.

Abstract: An ignition system for an internal combustion engine includes an ignition coil forming a part of a primary circuit and a secondary circuit, a power source to supply power to the ignition coil, and a controller to determine whether the ignition coil is a recognized ignition coil based on a measured risetime and a measured current level in the primary circuit, the measured current level being lower than that required to create a breakdown voltage of the ignition coil.

Abstract: A priming system for an engine system having a throttle valve configured to regulate a flow of air and fuel into an intake manifold of an engine is disclosed. The priming system may include a first sensor configured to generate a first sensor signal indicative of a value of an engine parameter, an auxiliary fuel line configured to direct fuel from a fuel source to a primed cylinder subset of the plurality of cylinders, an auxiliary fuel valve disposed in the auxiliary fuel line, and a controller in communication with the first sensor and the auxiliary fuel valve. The controller may be configured determine the value of the engine parameter from the first sensor signal and cease directing fuel from the auxiliary fuel line to the primed cylinder subset when the engine parameter value is greater than or equal to a threshold engine parameter value.

Abstract: A control system and method to control cold transient response of an engine. The control system can provide compressed air from a compressed air source to a turbocharger to boost speed of a turbine of the turbocharger, based on determined desired operating characteristics associated with upstream or downstream operation of the engine relative to the turbocharger. The control system can receive data corresponding to actual operating characteristics associated with the upstream or downstream operation of the engine relative to the turbocharger, compare the desired operating characteristics with the data corresponding to actual operating characteristics, and control the air assist from the compressed air source based on the comparison.

Abstract: A spark plug including a pre-chamber for an engine is provided. The spark plug extends along a spark plug longitudinal axis. The spark plug includes a first cylindrical structure having a wall defining a bore. An electrode is positioned inside the bore such that the electrode is spaced apart from the wall to define at least one electrode spark gap. The spark plug further includes a second cylindrical structure configured to receive the first cylindrical structure. The second cylindrical structure has one or more access apertures configured to facilitate access to the wall of the first cylindrical structure, wherein a plane perpendicular to the spark plug longitudinal axis passes through the electrode spark gap and intersects the one or more access apertures.

Abstract: A control system and method to control cold transient response of an engine. The control system can provide compressed air from a compressed air source to a turbocharger to boost speed of a turbine of the turbocharger, based on determined desired operating characteristics associated with upstream or downstream operation of the engine relative to the turbocharger. The control system can receive data corresponding to actual operating characteristics associated with the upstream or downstream operation of the engine relative to the turbocharger, compare the desired operating characteristics with the data corresponding to actual operating characteristics, and control the air assist from the compressed air source based on the comparison.

Abstract: A priming system for an engine system having a throttle valve configured to regulate a flow of air and fuel into an intake manifold of an engine is disclosed. The priming system may include a first sensor configured to generate a first sensor signal indicative of a value of an engine parameter, an auxiliary fuel line configured to direct fuel from a fuel source to a primed cylinder subset of the plurality of cylinders, an auxiliary fuel valve disposed in the auxiliary fuel line, and a controller in communication with the first sensor and the auxiliary fuel valve. The controller may be configured determine the value of the engine parameter from the first sensor signal and cease directing fuel from the auxiliary fuel line to the primed cylinder subset when the engine parameter value is greater than or equal to a threshold engine parameter value.

Abstract: A rocker arm assembly for a valve actuation system of an engine is disclosed. The engine has at least one valve. The rocker assembly includes a rocker arm with a valve retention end, a valve bridge with a rocker engagement portion. The rocker engagement portion sustains an engaged position and a released position relative to the valve retention end. Further, a spring unit is disposed between the valve retention end and the rocker engagement portion. In the engaged position, the valve retention end is in operable abutment with the rocker engagement portion. In the released position, the spring unit is configured to provide a reaction force between the valve retention end and the rocker engagement portion to disconnect the valve bridge from the rocker arm.

Abstract: An aircraft brake system (42) includes a torque tube (44), a plurality of spaced stators (48) mounted on the torque tube (44), a wheel (40) surrounding the torque tube (44) and a plurality of rotors (50) connected to the wheel (40) and projecting into the spaces between adjacent ones of the stators (48). A backing plate (52) mounted on the torque tube (44) has a first side (54) facing the rotors (50) and a second side (56) facing away from the rotors (50), and the second side (56) includes a plurality of keyways (58). A plurality of torque pads (10, 70, 100, 120) are connected to the torque tube (44), each having a body (12, 72, 102, 122) with a first surface (14, 74, 104, 124) contacting the second side (56) of the backing plate (52) and at least one key (22, 82, 112, 114, 130, 132) projecting from the first surface (14, 74, 104, 124) into one of the plurality of keyways (58). Also a torque pad (10, 70, 100, 120) and a method of connecting a backing plate to a torque tube.

Abstract: An aircraft brake system (42) includes a torque tube (44), a plurality of spaced stators (48) mounted on the torque tube (44), a wheel (40) surrounding the torque tube (44) and a plurality of rotors (50) connected to the wheel (40) and projecting into the spaces between adjacent ones of the stators (48). A backing plate (52) mounted on the torque tube (44) has a first side (54) facing the rotors (50) and a second side (56) facing away from the rotors (50), and the second side (56) includes a plurality of keyways (58). A plurality of torque pads (10, 70, 100, 120) are connected to the torque tube (44), each having a body (12, 72, 102, 122) with a first surface (14, 74, 104, 124) contacting the second side (56) of the backing plate (52) and at least one key (22, 82, 112, 114, 130, 132) projecting from the first surface (14, 74, 104, 124) into one of the plurality of keyways (58). Also a torque pad (10, 70, 100, 120) and a method of connecting a backing plate to a torque tube.