The present disclosure relates to a gas engine heat pump including: an engine which burns a mixed air of air and fuel; a first charger which compresses the mixed air and supplies to the engine; a first exhaust flow path which is connected to the engine, and through which exhaust gas discharged from the engine flows; and a second charger which is driven by the exhaust gas branched from the first exhaust flow path to a second exhaust flow path, and compresses the exhaust gas discharged from the engine and supplies the compressed exhaust gas to the engine, thereby reducing the emission of nitrogen oxide by recirculating the exhaust gas without additional power consumption.

A method of operating a forced induction gaseous-fueled engine includes mixing gaseous-fuel and engine intake air to form a mixture at a fuel mixer. The method includes delivering the mixture to an intake manifold by at least partially bypassing a charge air cooler.

Various methods and systems are provided for a detecting surge of a turbocharger in an engine system. In one example, system includes a turbocharger including a compressor coupled to a turbine and a controller and sensor system configured to detect a surge event of the turbocharger based on at least one of a rate of change of a pressure measured by sensors downstream of the compressor and a measured rate of change of turbine speed, store operational data associated with the surge event in memory of the controller, and determine a performance of the turbocharger based at least in part on one or more of a cumulative number of detected surge events, a magnitude of detected surge events, or associated operational data.

Various methods and systems are provided for a detecting surge of a turbocharger in an engine system. In one example, system includes a turbocharger including a compressor coupled to a turbine and a controller and sensor system configured to detect a surge event of the turbocharger based on at least one of a rate of change of a pressure measured by sensors downstream of the compressor and a measured rate of change of turbine speed, store operational data associated with the surge event in memory of the controller, and determine a performance of the turbocharger based at least in part on one or more of a cumulative number of detected surge events, a magnitude of detected surge events, or associated operational data.

A method of operating a gasoline engine having a first subset of cylinders and a second subset of cylinders includes providing a flow of compressed air from a single-sequential compressor to the engine, selectively deactivating the first subset of cylinders, and igniting gasoline mixed with the compressed air in the second subset of cylinders. The single-sequential compressor includes a dual sided impeller having a first blade arrangement in fluid communication with a first air inlet, and an opposing second blade arrangement in fluid communication with a second air inlet. Additionally, deactivating the first subset of cylinders includes sealing the first subset of cylinders such that the flow of compressed air is provided only to the second subset of cylinders.

A method of operating a gasoline engine having a first subset of cylinders and a second subset of cylinders includes providing a flow of compressed air from a single-sequential compressor to the engine, selectively deactivating the first subset of cylinders, and igniting gasoline mixed with the compressed air in the second subset of cylinders. The single-sequential compressor includes a dual sided impeller having a first blade arrangement in fluid communication with a first air inlet, and an opposing second blade arrangement in fluid communication with a second air inlet. Additionally, deactivating the first subset of cylinders includes sealing the first subset of cylinders such that the flow of compressed air is provided only to the second subset of cylinders.

An asymmetric double-entry turbine is provided with a turbine housing that includes a first volute, a second volute and a turbine receiving bore. The first volute has a first exhaust gas inlet and a first exhaust gas outlet. The second volute has a second exhaust gas inlet and a second exhaust gas outlet. The turbine receiving bore is in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction. The first exhaust gas outlet has an angular opening amount of more than 180 degrees around the turbine receiving bore. The second exhaust gas outlet has an angular opening amount of less than 180 degrees around the turbine receiving bore.

An asymmetric double-entry turbine is provided with a turbine housing that includes a first volute, a second volute and a turbine receiving bore. The first volute has a first exhaust gas inlet and a first exhaust gas outlet. The second volute has a second exhaust gas inlet and a second exhaust gas outlet. The turbine receiving bore is in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction. The first exhaust gas outlet has an angular opening amount of more than 180 degrees around the turbine receiving bore. The second exhaust gas outlet has an angular opening amount of less than 180 degrees around the turbine receiving bore.

An engine system is disclosed. The engine system may have an engine having an accessory end and a drive end opposite the accessory end. The engine system may also have a turbocharger arrangement located adjacent the accessory end. The turbocharger arrangement may be configured to receive exhaust from the engine and to deliver compressed air to the air cooling arrangement. Further, the engine system may have an air cooling arrangement located adjacent the accessory end and configured to deliver fresh air to the engine. In addition, the engine system may have a mixing duct extending from the accessory end to the drive end and configured to receive the exhaust from the turbocharger arrangement. The engine system may also have an after-treatment system located adjacent the drive end. The after-treatment system may be configured to receive the exhaust from the mixing duct and to discharge the exhaust to an ambient.

An engine system is disclosed. The engine system may have an engine having an accessory end and a drive end opposite the accessory end. The engine system may also have a turbocharger arrangement located adjacent the accessory end. The turbocharger arrangement may be configured to receive exhaust from the engine and to deliver compressed air to the air cooling arrangement. Further, the engine system may have an air cooling arrangement located adjacent the accessory end and configured to deliver fresh air to the engine. In addition, the engine system may have a mixing duct extending from the accessory end to the drive end and configured to receive the exhaust from the turbocharger arrangement. The engine system may also have an after-treatment system located adjacent the drive end. The after-treatment system may be configured to receive the exhaust from the mixing duct and to discharge the exhaust to an ambient.