In order to provide a vapor plant which is operable in an energy-efficient manner, has as high a degree of efficiency as possible and/or enables nitrogen oxide to be reduced without additives, the vapor plant includes the following: a gas turbine device which comprises a compressor, a combustion chamber and a turbine; a vapor device for the production of vapor and for the supply of vapor to the combustion chamber; an exhaust gas system for the removal of the exhaust gas produced in the combustion chamber; a heat exchanger by means of which the exhaust gas system on the one hand and the vapor device on the other are thermally coupled or couplable to one another; a condensing device by means of which the exhaust gas system on the one hand and the vapor device on the other are thermally coupled or couplable to one another.

The present application provides a selective catalyst reduction system for use with a combustion gas stream of a gas turbine. The selective catalyst reduction system may include an inlet positioned about the gas turbine, a combined ammonia-tempering air injection grid positioned about the inlet, and a catalyst positioned downstream of the combined ammonia-tempering air injection grid. The combined ammonia-tempering air injection grid injects air and ammonia into the combustion gas stream upstream of the catalyst.

An aircraft propulsion system a cryogenic fuel system, a superconducting electrical device that is operable at a cryogenic temperature, a cooling system where a cooling fuel flow is utilized for maintaining the superconducting electrical device at the cryogenic temperature, an ejector where the primary fuel flow from the fuel system drives the cooling fuel flow through the cooling system to form a combined fuel flow, and a separator where a first portion of the combined fuel flow from the ejector is routed to the core engine and a second portion of the combined fuel flow is routed back to the cooling system.

The engine described herein utilizes an internal low pressure near the nozzle to draw fluid through a center section/duct of the engine and therefore through an upstream, cold, turbine. The fluid moving through this center duct-section experiences a pressure differential between the zone of the incoming fluid (which raises pressure upstream) and the low pressure zone generated near the nozzle. With fast-moving fluid around each side of this cold turbine duct, inducing a Venturi effect on the fluid passing through the duct, a low pressure is generated and therefore enacts work on the turbine. Using this method, turbine blades are not down stream of the hot combustion section and therefore can be made with light weight and low melting temperature material. With a cold section turbine, the engine can therefore be considerably lighter and cheaper to manufacture and maintain.

The engine described herein utilizes an internal low pressure near the nozzle to draw fluid through a center section/duct of the engine and therefore through an upstream, cold, turbine. The fluid moving through this center duct-section experiences a pressure differential between the zone of the incoming fluid (which raises pressure upstream) and the low pressure zone generated near the nozzle. With fast-moving fluid around each side of this cold turbine duct, inducing a Venturi effect on the fluid passing through the duct, a low pressure is generated and therefore enacts work on the turbine. Using this method, turbine blades are not down stream of the hot combustion section and therefore can be made with light weight and low melting temperature material. With a cold section turbine, the engine can therefore be considerably lighter and cheaper to manufacture and maintain.

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.

Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation.

Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation.

Exhaust systems for gas turbine engines, gas turbine engines with the same, and methods of manufacturing, configuring, and operating a gas turbine engine with an exhaust system. The exhaust system can include an inlet, an outlet, a tubular section extending between the inlet and the outlet, and a nozzle that is positioned in the tubular section. The nozzle can discharge into the flow path to produce a pressure drop. The nozzle can be a Venturi-effect nozzle. The discharge from the nozzle can reduce a pressure generated by the turbine exhaust, and by association, increase the turbine's pressure ratio and power, which can be beneficial for different operational scenarios. The exhaust system may also include a tubular section with a linear design or a non-linear design. The tubular section of the exhaust system may include at least one section with a reduced diameter, e.g., downstream of the nozzle.