A unique seal for a wave rotor disk engine is disclosed herein. The seal is operable for sealing a region between a rotor and a rotor casing. The seal is spring loaded and will engage with the tip of the rotor to reduce pressure loss within the wave rotor disk engine.

Various systems and methods are provided for a turbocharger system. In one example, a system for use with a power generator having a rotary machine including a combustor comprises: a heat exchanger positioned to receive exhaust gases from the combustor; and a turbocharger system, comprising: a low pressure compressor fluidly coupled to the heat exchanger and adapted to supply gases to the heat exchanger; a low pressure turbine and a high pressure turbine each fluidly coupled to the heat exchanger and adapted to receive gases from the heat exchanger; a high pressure compressor fluidly coupled to the rotary machine and the low pressure compressor, adapted to receive gases from the low pressure compressor and supply compressed air to the rotary machine; and a water injector adapted to inject water into a flow path between the low pressure compressor and the heat exchanger.

Various systems and methods are provided for a turbocharger system. In one example, a system for use with a power generator having a rotary machine including a combustor comprises: a heat exchanger positioned to receive exhaust gases from the combustor; and a turbocharger system, comprising: a low pressure compressor fluidly coupled to the heat exchanger and adapted to supply gases to the heat exchanger; a low pressure turbine and a high pressure turbine each fluidly coupled to the heat exchanger and adapted to receive gases from the heat exchanger; a high pressure compressor fluidly coupled to the rotary machine and the low pressure compressor, adapted to receive gases from the low pressure compressor and supply compressed air to the rotary machine; and a water injector adapted to inject water into a flow path between the low pressure compressor and the heat exchanger.

The present disclosure discloses an intake oxygen concentration control system suitable for an engine with lean NO.sub.x trapping technology. The system adopts an exhaust turbocharging device to provide a pressure difference for an oxygen-enriched membrane to generate oxygen-rich and oxygen-deficient gases, and controls the intake oxygen concentration of different cylinders by adjusting the opening of flow control valves to match lean and rich combustion cycles of a lean NO.sub.x trapping system. In a lean combustion cycle, all four cylinders are filled with an oxygen-rich gas, which can make the combustion more complete and improve the thermal efficiency and fuel economy. In a rich combustion cycle, one of the four cylinders is filled with an oxygen-deficient gas, and the other three cylinders are filled with air or an oxygen-rich gas with a low concentration, so that less fuel is required to create a reducing atmosphere to realize the release and reduction of NO.sub.x in a lean NO.sub.x trapping device, thereby reducing the fuel consumption and ensuring the output power of the other three cylinders.

The present disclosure discloses an intake oxygen concentration control system suitable for an engine with lean NO.sub.x trapping technology. The system adopts an exhaust turbocharging device to provide a pressure difference for an oxygen-enriched membrane to generate oxygen-rich and oxygen-deficient gases, and controls the intake oxygen concentration of different cylinders by adjusting the opening of flow control valves to match lean and rich combustion cycles of a lean NO.sub.x trapping system. In a lean combustion cycle, all four cylinders are filled with an oxygen-rich gas, which can make the combustion more complete and improve the thermal efficiency and fuel economy. In a rich combustion cycle, one of the four cylinders is filled with an oxygen-deficient gas, and the other three cylinders are filled with air or an oxygen-rich gas with a low concentration, so that less fuel is required to create a reducing atmosphere to realize the release and reduction of NO.sub.x in a lean NO.sub.x trapping device, thereby reducing the fuel consumption and ensuring the output power of the other three cylinders.

The present disclosure discloses an intake oxygen concentration control system suitable for an engine with lean NO.sub.x trapping technology. The system adopts an exhaust turbocharging device to provide a pressure difference for an oxygen-enriched membrane to generate oxygen-rich and oxygen-deficient gases, and controls the intake oxygen concentration of different cylinders by adjusting the opening of flow control valves to match lean and rich combustion cycles of a lean NO.sub.x trapping system. In a lean combustion cycle, all four cylinders are filled with an oxygen-rich gas, which can make the combustion more complete and improve the thermal efficiency and fuel economy. In a rich combustion cycle, one of the four cylinders is filled with an oxygen-deficient gas, and the other three cylinders are filled with air or an oxygen-rich gas with a low concentration, so that less fuel is required to create a reducing atmosphere to realize the release and reduction of NO.sub.x in a lean NO.sub.x trapping device, thereby reducing the fuel consumption and ensuring the output power of the other three cylinders.

The present disclosure discloses an intake oxygen concentration control system suitable for an engine with lean NO.sub.x trapping technology. The system adopts an exhaust turbocharging device to provide a pressure difference for an oxygen-enriched membrane to generate oxygen-rich and oxygen-deficient gases, and controls the intake oxygen concentration of different cylinders by adjusting the opening of flow control valves to match lean and rich combustion cycles of a lean NO.sub.x trapping system. In a lean combustion cycle, all four cylinders are filled with an oxygen-rich gas, which can make the combustion more complete and improve the thermal efficiency and fuel economy. In a rich combustion cycle, one of the four cylinders is filled with an oxygen-deficient gas, and the other three cylinders are filled with air or an oxygen-rich gas with a low concentration, so that less fuel is required to create a reducing atmosphere to realize the release and reduction of NO.sub.x in a lean NO.sub.x trapping device, thereby reducing the fuel consumption and ensuring the output power of the other three cylinders.

A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.