Abstract: A liquid drain valve assembly for a charge air cooler includes a valve housing configured to couple to the charge air cooler, the valve housing having a condensate inlet configured to receive condensate from the charge air cooler, and a condensate outlet, a valve mechanism slidingly disposed within the valve housing and configured to selectively close the condensate inlet and the condensate outlet to facilitate preventing charge air from leaking during condensate draining, and a diaphragm assembly disposed within the valve housing and configured to selectively engage the valve mechanism to selectively open the condensate inlet and the condensate outlet to drain condensate from the charge air cooler when the charge air cooler is in a boosted condition and isolated from the atmosphere.

Abstract: An internal combustion engine system includes a compressor arranged to compress air, at least one combustor, at least one of the at least one combustor being arranged to receive the compressed air, and an exhaust treatment device arranged to process exhaust gases produced by at least one of the at least one combustor, a heat exchanger arranged to receive the compressed air from the compressor before it reaches the at least one of the at least one combustor, and wherein the heat exchanger is arranged to transfer heat from the compressed air to the exhaust treatment device.

Abstract: An assembly for an aircraft having a propeller, including an engine assembly having an engine shaft configured for driving engagement with the propeller. The engine assembly includes first and second heat exchangers configured for circulation of at least one of a liquid coolant and a lubricant therethrough. A wheel well is configured for receiving a retracted landing gear. A first cooling duct receives the first heat exchanger and has a first outlet downstream of the first heat exchanger, and a second cooling duct receives the second heat exchanger and has a second outlet downstream of the second heat exchanger. The outlets are in direct fluid communication with an environment of the aircraft, and laterally spaced from each other. The wheel well is located between the outlets. A method of cooling an engine assembly is also discussed.

Abstract: A turbomachine may include a turbine arranged in a housing and configured to be acted on with a hot working medium. The turbomachine may include at least one bypass channel for heating the housing through the working medium. The bypass channel may extend completely within the housing and be configured to bypass the turbine.

Abstract: An auxiliary power unit for an aircraft, having an engine core, a compressor having an outlet in fluid communication with the engine core inlet, a turbine section in fluid communication with the engine core outlet, and an excess air duct having a first end in fluid communication with the compressor outlet and a second end in fluid communication with a turbine inlet of the turbine section. The excess air duct defines a flow path between the compressor outlet and the turbine section separate from the engine core. The auxiliary power unit may include a generator in driving engagement with the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: The invention relates to a device for conditioning the atmosphere when testing engines, comprising an inlet duct connected to an engine intake, an outlet duct connected to the exhaust of the engine, a communication duct that connects the inlet duct to the outlet duct, a bypass valve in the inlet duct, a super-charging turbo assembly in the inlet duct, a heat exchanger in the outlet duct, and a turbocharger after the heat exchanger. The device further comprises a first three-way valve that connects the inlet duct to the outlet duct, an on/off valve in the outlet duct, a second three-way valve in the outlet duct, a control valve in a duct that connects the outlet duct to the atmosphere, and a section of the outlet duct that connects the exchanger to the communication duct.

Abstract: A turbine housing includes an accommodation space that accommodates a turbine wheel, a discharge passage connected to the accommodation space, and a bypass passage that extends from the scroll passage bypassing the accommodation space and is connected to the discharge passage. The bypass passage extends so that an end surface on an upstream side of the catalytic device is located on a center axis of the bypass passage. An air-fuel ratio sensor is located closer to a center axis of the accommodation space than the center axis of the bypass passage. A protuberance that protrudes from an inner wall surface of the discharge passage is located between the accommodation space and the air-fuel ratio sensor. The protuberance protrudes toward the center axis of the accommodation space.

Abstract: The exhaust system of a diesel engine includes components such as a turbocharger and an exhaust manifold which can have very high internal temperatures (e.g., any surface having a temperature above 135° C.). In accordance with the invention the components subject to the high temperatures are coated with at least a first layer of thermally insulating material and a second layer overlying the first layer to provide surface protection. So coated, the temperature of the outer coated surfaces of these components is brought below an undesirably high level. Also, selected ones of the components may be water cooled and/or have a fitted jacket and/or be placed within an explosion proof enclosure. The input fuel line may also include a magnetic explosion proof fuel economizer to control the combustion process and reduce the internal temperature.

Abstract: The present disclosure relates to a turbocharged internal combustion engine which will flush dirt periodically from the heat exchange surfaces of the LT-charge air cooler by using water condensed on the heat exchange surfaces for the flushing.

Abstract: An exhaust passage 53 includes: a first passage (high-speed passages 24b, 25b, and 26b); and a second passage (low-speed passages 24c, 25c, and 26c). A turbine housing 560 is connected to the exhaust passage 53 downstream from the collector 54. An exhaust device 100 of an engine 1 includes a valve (an exhaust variable valve 3) to open and close the first passage. A controller (an engine controller 7) closes the valve if an engine speed of the engine 1 is lower than a predetermined engine speed and opens the valve if the engine speed of the engine 1 is higher than or equal to the predetermined engine speed. The controller opens the valve even though the engine speed of the engine 1 is lower than the predetermined engine speed if performing the fuel cut control.

Abstract: A variable geometry turbine having a turbine wheel, an inlet passageway, a movable wall member being moveable axially to vary the width of the inlet passageway, an annular seal being mounted to the movable wall member or an adjacent housing member to provide a seal between adjacent surfaces of the movable wall member and housing member respectively, wherein a bypass passage is provided in the other of said movable wall member or housing member, extending from an inlet bypass port to an outlet bypass port, said ports being spaced from each other and provided in said adjacent surface of said other of the movable wall member or housing member, arranged such that as the movable wall member moves axially, the annular seal moves axially relative to the ports to vary the flow that may pass from a region of the cavity inboard of the seal, through the bypass passage.

Abstract: Methods and systems are provided for de-icing a charge-air cooler of a boosted engine system when the engine is turned off. In one example, a method may include recirculating air through a bypass passage including an activated electric supercharger and the CAC. The air is warmed by compression and thaws ice accumulated in the CAC.

Abstract: It is intended to reduce generation of water mist in cooling of compressed air. A multi-stage supercharging system (1) includes a first supercharger (2) of a low-pressure side, an intercooler (3) that cools air discharged from the first supercharger (2), a second supercharger (4) of a high-pressure side that compresses the discharged air after cooling, and a control device (5).

Abstract: Methods and systems are provided for adjusting intake airflow through two parallel induction passages. In response to increased torque demand, intake airflow may be directed through a first induction passage including an exhaust-driven turbocharger compressor and through a second induction passage including an electric compressor. Further, after the turbocharger compressor increases speed, intake airflow may be directed again through the first induction passage to further increase boost.

Abstract: An assembly can include a turbine housing that includes a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat; a bushing disposed at least in part in the bore; a rotatable wastegate shaft received at least in part by the bushing; a wastegate plug that extends from the wastegate shaft; a control arm operatively coupled to the wastegate shaft; a control link operatively coupled to the control arm; a pin that forms a joint between the control arm and the control link; and a biasing element coupled to the pin and to the control link.

Abstract: Disclosed is a two-piece shaft assembly for a driven turbocharger with a traction drive. The turbo shaft is attached to a turbine and compressor, and is inserted into a traction barrel that has traction surfaces to mate to the traction drive. In this way, the traction drive can be assembled with only the traction barrel, and the turbo shaft can be inserted through the barrel at the end to simplify assembly.

Abstract: The invention relates to an exhaust gas conducting system for a gasoline engine, comprising an exhaust gas line which can be connected to an exhaust manifold of the gasoline engine, an inlet line which can be connected to an intake manifold of the gasoline engine, and a turbine which is arranged in the exhaust gas line.

Abstract: A liquid drain valve assembly for a charge air cooler includes a valve housing configured to couple to the charge air cooler, the valve housing having a condensate inlet configured to receive condensate from the charge air cooler, and a condensate outlet. A valve is disposed within the valve housing. The valve includes a diaphragm seated against an inner wall of the valve housing and movable between a first position enabling condensate to flow past the diaphragm and out the condensate outlet to selectively drain condensate from the charge air cooler when the charge air cooler is not in a boosted condition, and a second position preventing condensate flow out the condensate outlet when the charge air cooler is in a boosted condition to thereby isolate the charge air cooler from the atmosphere.

Abstract: The present disclosure relates to internal combustion engines. The teachings thereof may be embodied in methods and devices for actuating an exhaust gas recirculation valve of a forced-induction internal combustion engine with exhaust gas recirculation. A method for building up the charge pressure required to avoid a drop in torque may include: detecting an acceleration indicator; in response, providing an increased target value for an exhaust gas recirculation rate; measuring an instantaneous actual charge pressure; determining a setpoint exhaust gas recirculation rate based on the increased target value, the instantaneous setpoint charge pressure, and the instantaneous actual charge pressure; calculating a control signal using the determined setpoint exhaust gas recirculation rate; and delivering the control signal to the exhaust gas recirculation valve to change its opening state.

Abstract: A turbocharger includes a turbine comprising a scroll passage including at least first and second portions, a gas outlet extending axially from the scroll passage, a turbine wheel including one or more blades disposed in the gas outlet, and structure for establishing a bypass flow between the first and second portions of the scroll passage or for altering gas flow through the turbine. A method for adjusting exhaust gas temperature is also provided.