Abstract: A structural and acoustical vibration dampener for a rotatable blade comprises a layer of structural/acoustic damping material coupled to at least a portion of the blade. A fan blade comprises a structural layer and a layer of damping material coupled to at least a portion of the structural layer. A method of applying a structural and acoustical vibration dampener to a fan blade comprises identifying a region on the fan blade and securing the structural/acoustical vibration dampener to the fan blade over at least a portion of the region.

Abstract: An acoustical vibration dampening system for a rotatable blade comprises at least one section of a rotatable blade and a layer of acoustic damping material coupled to a portion of the at least one section of a rotatable blade. A fan blade comprises a first structural section of a fan blade, a second structural section of the fan blade, and a layer of acoustic damping material provided between the first structural section and the second structural section of the fan blade. A method of making a fan blade with acoustic damping comprises forming at least two sections of a fan blade, and disposing an acoustical vibration dampener between the at least two sections of the fan blade.

Abstract: An acoustical vibration dampening system for a rotatable blade comprises at least one section of a rotatable blade and a layer of acoustic damping material coupled to a portion of the at least one section of a rotatable blade. A fan blade comprises a first structural section of a fan blade, a second structural section of the fan blade, and a layer of acoustic damping material provided between the first structural section and the second structural section of the fan blade. A method of making a fan blade with acoustic damping comprises forming at least two sections of a fan blade, and disposing an acoustical vibration dampener between the at least two sections of the fan blade.

Abstract: A structural and acoustical vibration dampener for a rotatable blade comprises a layer of structural/acoustic damping material coupled to at least a portion of the blade. A fan blade comprises a structural layer and a layer of damping material coupled to at least a portion of the structural layer. A method of applying a structural and acoustical vibration dampener to a fan blade comprises identifying a region on the fan blade and securing the structural/acoustical vibration dampener to the fan blade over at least a portion of the region.

Abstract: An exhaust gas recirculation cooler, typically of the drawn cup design, with a bypass and control valve is disclosed. The control valve can direct a proportion of the exhaust gas to the cooler and a proportion to bypass the cooler depending on the input temperature of the exhaust gas and the required temperature of the exhaust gas. The proportion of the exhaust gas directed to the cooler/bypassing the cooler can be varied as required and so the temperature of the exhaust gas can be controlled. One benefit of certain embodiments of the invention is that engine damaging chemicals, such as sulphuric acid, which result from over-cooling the exhaust gas are reduced.

Abstract: An exhaust gas recirculation cooler, typically of the drawn cup design, with a bypass and control valve is disclosed. The control valve can direct a proportion of the exhaust gas to the cooler and a proportion to bypass the cooler depending on the input temperature of the exhaust gas and the required temperature of the exhaust gas. The proportion of the exhaust gas directed to the cooler/bypassing the cooler can be varied as required and so the temperature of the exhaust gas can be controlled. One benefit of certain embodiments of the invention is that engine damaging chemicals, such as sulphuric acid, which result from over-cooling the exhaust gas are reduced.

Abstract: A compressor impeller for use with a boreless turbocharger is provided in accordance with this invention. The compressor impeller comprises an integral hub projecting axially therefrom that includes a partial bore therein that extends from an open to a close bore end. The bore includes a threaded portion that is configured to accommodate threaded engagement with an end of a common shaft disposed through a turbocharger housing and attached at an opposite end to a turbine wheel. The hub is specially configured so that the threaded portion has a relatively increased wall thickness when compared to a remaining portion of the bore disposed between the threaded portion and the end of the bore. The bore is configured providing a section having a reduced wall thickness, between the threaded portion and the bore closed end, for purposes of providing a preferential stress relief mechanism.

Abstract: A buffer chamber and outlet guide provide an air path from an intake passage in a compressor housing to an upstream position relative to an intake port of the compressor. Surging is minimized during low airflow conditions while cyclic forces on the blades of the impeller are minimized during high airflow conditions. By providing an air path through the buffer chamber and outlet guide, ribs or other supporting structures are eliminated within the air pathway through the intake port and intake passage within the compressor housing.

Abstract: A buffer chamber and outlet guide provide an air path from an intake passage in a compressor housing to an upstream position relative to an intake port of the compressor. Surging is minimized during low airflow conditions while cyclic forces on the blades of the impeller are minimized during high airflow conditions. By providing an air path through the buffer chamber and outlet guide, ribs or other supporting structures are eliminated within the air pathway through the intake port and intake passage within the compressor housing.

Abstract: A compressor impeller for use with a boreless turbocharger is provided in accordance with this invention. The compressor impeller comprises an integral hub projecting axially therefrom that includes a partial bore therein that extends from an open to a close bore end. The bore includes a threaded portion that is configured to accommodate threaded engagement with an end of a common shaft disposed through a turbocharger housing and attached at an opposite end to a turbine wheel. The hub is specially configured so that the threaded portion has a relatively increased wall thickness when compared to a remaining portion of the bore disposed between the threaded portion and the end of the bore. The bore is configured providing a section having a reduced wall thickness, between the threaded portion and the bore closed end, for purposes of providing a preferential stress relief mechanism.