A gas turbine engine (10) comprises a main fluid flow exhaust nozzle (30) bounding a main fluid flow path, and a cooling nozzle (38) provided upstream of the main fluid flow exhaust nozzle (30) in the main fluid flow path. The cooling nozzle (38) is arranged to provide cooling air to a surface (36) of the main fluid flow exhaust nozzle (30), the cooling nozzle (38) comprises first and second outlets (44, 46). The first outlet (44) is located adjacent the main fluid flow exhaust nozzle surface (36) and is spaced from the main fluid flow path by the second outlet (46). The second outlet (46) comprises a convergent divergent nozzle configured to accelerate cooling air exhausted from the second outlet (46) to a velocity greater than air exhausted from the first outlet (44).

A turbocharged compressor system using an Organic Rankine Cycle system to recover waste heat from a compression process. The Organic Rankine Cycle system circulates an organic fluid through an evaporator, where the organic fluid vaporizes and is expanded in a turbine section of a turbocharger to drive a compressor section of the turbocharger. The organic fluid vapor is condensed in a condenser and is pumped to the evaporator once again for recirculation. The compressor section of the turbocharger pre-compresses a working fluid before entering an airend in a compression system. As the working fluid exits the airend, it may be delivered to the evaporator, where the waste heat from the working fluid evaporates the organic fluid flowing in the Organic Rankine Cycle system. The working fluid may also be circulated between intercoolers in multi-stage compressor systems.

A turbocharged compressor system using an Organic Rankine Cycle system to recover waste heat from a compression process. The Organic Rankine Cycle system circulates an organic fluid through an evaporator, where the organic fluid vaporizes and is expanded in a turbine section of a turbocharger to drive a compressor section of the turbocharger. The organic fluid vapor is condensed in a condenser and is pumped to the evaporator once again for recirculation. The compressor section of the turbocharger pre-compresses a working fluid before entering an airend in a compression system. As the working fluid exits the airend, it may be delivered to the evaporator, where the waste heat from the working fluid evaporates the organic fluid flowing in the Organic Rankine Cycle system. The working fluid may also be circulated between intercoolers in multi-stage compressor systems.

A system of an air-augmented gas turbine engine is provided comprising a gas turbine engine drawing air into an increasingly narrow and elongated compression chamber, the action compressing drawn-in air. The system also forces the compressed air into and through a narrowed section of the compression chamber before the air reaching a combustion chamber, the section running alongside a lengthwise exterior surface of the combustion chamber, positioning of the section causing the compressed air to receive increased heating based on proximity of the section to the combustion chamber. The system ignites in the compression chamber a mixture of the heated compressed air and injected fuel, causing increase in temperature and velocity of the mixture. The system also directs the superheated mixture from the combustion chamber through a combustion nozzle and into an entrained state with a larger volume of cooler air, resulting in increased power and efficiency of the engine.

A system of an air-augmented gas turbine engine is provided comprising a gas turbine engine drawing air into an increasingly narrow and elongated compression chamber, the action compressing drawn-in air. The system also forces the compressed air into and through a narrowed section of the compression chamber before the air reaching a combustion chamber, the section running alongside a lengthwise exterior surface of the combustion chamber, positioning of the section causing the compressed air to receive increased heating based on proximity of the section to the combustion chamber. The system ignites in the compression chamber a mixture of the heated compressed air and injected fuel, causing increase in temperature and velocity of the mixture. The system also directs the superheated mixture from the combustion chamber through a combustion nozzle and into an entrained state with a larger volume of cooler air, resulting in increased power and efficiency of the engine.

A system includes at least one component of a turbine section. The at least one component includes an inert gas port formed into a wall of the at least one component. The inert gas port is configured to inject an inert gas into a chamber of the turbine section in a downstream direction. The at least one component also includes a fuel port formed into the wall upstream of the inert gas part. The fuel port is configured to inject a fuel in the downstream direction toward the injected inert gas. The inert gas causes the injected fuel to be lifted away from the surface of the wall and propelled into the hot gas flow path, where the fuel can be ignited by the combustion gases to increase gas turbine engine efficiency and performance.

A system includes at least one component of a turbine section. The at least one component includes an inert gas port formed into a wall of the at least one component. The inert gas port is configured to inject an inert gas into a chamber of the turbine section in a downstream direction. The at least one component also includes a fuel port formed into the wall upstream of the inert gas part. The fuel port is configured to inject a fuel in the downstream direction toward the injected inert gas. The inert gas causes the injected fuel to be lifted away from the surface of the wall and propelled into the hot gas flow path, where the fuel can be ignited by the combustion gases to increase gas turbine engine efficiency and performance.

A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.

A propulsion system for an aircraft having a two stage contra-rotating fan system to generate thrust. The contra-rotating fan system is surrounded by an aerodynamic duct, having the power train within the duct.