A gas turbine engine includes a first combustor having a first fuel nozzle, wherein the first fuel nozzle is configured to supply a water fuel emulsion into the first combustor. The water fuel emulsion includes a water-in-fuel (WIF) emulsion having a plurality of water droplets dispersed in a fuel, wherein the plurality of water droplets is configured to vaporize within the fuel to cause micro-explosions to atomize the fuel, and the atomized fuel is configured to combust to generate a combustion gas. The gas turbine engine further includes a turbine driven by the combustion gas from the first combustor.

The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid supply channel (74) configured to direct a second working fluid to impart torque on the turbine rotor (60) in the same direction as the direction in which torque is imparted on the turbine rotor (60) by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.

A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.

The inventions applicable to industrial gas turbines at power plant to minimize nitrogen oxides from gas turbine exhaust and maximizing gas turbine efficiency done by replacing the standard air filter system by oxygen filtration system (O) to allow oxygen only and substituting the nitrogen by high-pressure water HPW injected in compressor (C) last stages only. The one unit of oxygen to be injected by 4 units of HPW, since air contains 5 units 4 units of nitrogen and 1 unit of oxygen, the 5 units of oxygen are to be injected by 20 units of HPW required for the process. A heat exchanger to be installed at gas turbine exhaust duct to heat the HPW injected into compressor (C) last stages, which is to be mixed with HPW at ambient/atmospheric temperature to cool compressor air outlet temperature to targeted temperature as shown in FIG. 1. A control system is essential to control the process.

A power plant including a compressor, a combustion chamber and a turbine, and a compressor air line, which connects the compressor to the combustion chamber, a first heat exchanger connected into the compressor air line and into an exhaust line branching off the turbine. A first expander is arranged between the first heat exchanger and the combustion chamber in the compressor air line, and the first expander and the compressor are arranged on a common shaft.

The invention concerns an air inlet duct (10) for a compressor (12) of a gas or fuel oil turbine, including: two transition sections (S3, S4) in fluid communication with one another for the circulation of a flow of air through said sections (S3, S4), each of said sections (S3, S4) being self-supporting, a structure (20) for injecting a mist of liquid particles, configured to be disposed between said sections (S3, S4) and in contact with said sections (S3, S4), the structure (20) being removable independently of demounting said sections (S3, S4). The invention also concerns a gas or fuel oil turbine assembly comprising an inlet duct (10) of this type and a method of maintaining an inlet duct (10) of this type.

An improved steam engine is provided for operating on a recirculation of superheated air and steam. A gas turbine is including having a first intake, a first discharge and a power output shaft, said power output shaft providing rotation power output generated from a change in entropy of the gas through the turbine. A power turbine superheats the gas discharge and includes a turbocharger in operational communication with an electric DC motor, and a compressor mechanically driven by the turbocharger. The discharge from the compressor forms the turbine steam intake. A water injection system may be further provided for adding steam to the air recirculating circuit. A drive motor operatively coupled to the turbine may be used for startup to bring the turbine up to operational rotation speeds. A DC generator operatively coupled to recharge a battery driving the drive motor or for providing electrical power output.

An aircraft propulsion system comprises a gas turbine engine arranged to provide propulsive thrust and a fuel cell system having an air input port, the aircraft propulsion system being configured such that air from a compressor of the gas turbine engine is provided to the air input port during operation of the aircraft propulsion system. The fuel cell system is able to provide appreciable electrical power at altitude without the need for a dedicated compressor.

A gas turbine engine comprising a housing coupled to an upstream source of hot gas and superheated water droplets, the housing having a centerline, an annular bay section positioned radially away from the centerline and protruding in an upstream direction, a rotatable shaft positioned along the centerline, a fluid mover coupled to the rotating shaft and positioned to receive the hot gas and superheated water droplets from the upstream source and to move the hot gas and superheated water droplets radially toward the annular bay section of the housing, a separator plate that is fixedly coupled to the housing; and an extractive turbine assembly positioned downstream from the separator plate and the annular bay section. The superheated water droplets mix thoroughly with the hot gas inside the annular bay section causing the water droplets to covert to steam, and the steam flows to the extractive turbine, increasing an efficiency of turbine rotation.

Method and apparatus for improving the energy efficiency of existing gas turbine combined cycle plants in which a compressor pressurises air which is combusted with fuel in a combustion chamber, followed by a turbine and a high temperature heat exchanger and a low temperature heat exchanger. In the secondary circulation after the steam turbine II, steam is condensed in the condenser into water, which is pressurised to the maximum pressure by means of a pump and preheated in low temperature heat exchanger and vaporised in a high temperature heat exchanger. After the high temperature heat exchanger, steam enters the steam turbine wherefrom a tap is taken, if necessary, which is injected after preheating into the combustion chamber of the gas turbine process or at the latest the beginning of the vanes of the turbine. Before steam turbine II, the enthalpy of steam (and additional water) at below 1 atm is increased by means of the condensation heat of the water contained in the combustion gases, after which intermediate superheating is applied to the saturated Rankine circulation steam using the excess heat of the low temperature heat exchanger.