Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

A heat recovery unit for generating a heated fluid by a hot exhaust gas includes a housing having an inlet for introducing hot exhaust gas and an outlet for discharging treated exhaust gas, and arranged in the housing at least one heat exchanger for heat exchange between the hot exhaust gas and a fluid, and an auxiliary combustor for combusting fuel with hot exhaust gas. The auxiliary combustor is provided with a fuel supply, which auxiliary combustor is arranged downstream of the at least one heat exchanger in the housing. An exhaust gas bypass for a part of the hot exhaust gas is provided, having an inlet for exhaust gas, and being positioned upstream of the at least one heat exchanger, and having an outlet in direct fluid communication with the auxiliary combustor.

A method for the short-term adjustment of the output of a steam turbine of a combined-cycle power plant, includes: opening, respectively closing, a backed-up turbine valve of a pressure stage, according to a required change in output; comparing a desired pressure with a pressure measurement upstream of the turbine valve to measure pressure of steam mass flow flowing into the pressure stage; and opening, respectively closing, a feed line for introducing a variable proportion of water into the steam mass flow as soon as the pressure falls below or exceeds the desired pressure; the variable proportion of water is introduced into the steam mass flow until an adjusted desired steam temperature is reached, which is determined from the difference between a basic specified desired steam temperature and the default value of a controller which operates at least proportionally and evaluates the difference between the pressure measurement and the desired pressure.

The invention relates to a method for starting up a gas turbine engine of a combined cycle power plant. The method includes applying load to the gas turbine engine and increasing the load until a predetermined combustor firing temperature is reached, while keeping the adjustable inlet guide vanes in a start position adapted to reduce the mass flow of air into the compressor; further increasing the load of the gas turbine engine while opening the adjustable inlet guide vanes and keeping the predetermined combustor firing temperature constant until the inlet guide vanes reach an end position adapted to increase the mass flow of air into the compressor; further increasing the load of the gas turbine engine while keeping the adjustable inlet guide vanes in the end position until a predetermined load of the gas turbine engine is reached.

A direct carbonaceous material to power generation system integrates one or more solid oxide fuel cells (SOFC) into a fluidized bed gasifier. The fuel cell anode is in direct contact with bed material so that the H.sub.2 and CO generated in the bed are oxidized to H.sub.2O and CO.sub.2 to create a push-pull or source-sink reaction environment. The SOFC is exothermic and supplies heat within a reaction chamber of the gasifier where the fluidized bed conducts an endothermic reaction. The products from the anode are the reactants for the reformer and vice versa. A lower bed in the reaction chamber may comprise engineered multi-function material which may incorporate one or more catalysts and reactant adsorbent sites to facilitate excellent heat and mass transfer and fluidization dynamics in fluidized beds. The catalyst is capable of cracking tars and reforming hydrocarbons.

A heat recovery system for an engine having an exhaust nozzle whereby exhaust gas is expelled, the heat recovery system comprising a steam generator that supplies hot vaporized coolant to a turbine generator which creates electrical energy. The electrical energy is used to power air compressors that supply clean outside air to the passenger compartment of the aircraft.

A gas turbine provided with: an air cooler that subjects compressed air extracted from a compressor to heat exchange and supplies the cooled compressed air to a cooling system of a rotor system in a turbine; an air cooler bypass line that bypasses the compressed air introduced into the air cooler; an electric valve provided in the air cooler bypass line; and a control unit that controls opening and closing of the electric valve such that, during activation of a gas turbine, a degree of opening of the electric valve is set at or below a low-level degree of opening and such that, after the load of the gas turbine has been increased, the degree of opening of the electric valve is set to be larger than the low-level degree of opening.

Solutions for efficiently filtering air for a machine are disclosed. In one embodiment, a filter element for a filter assembly of a rotary machine is provided. The filter element includes: a first set of pleats, each pleat including a first tip radius and a first spacing; and a second set of pleats, each pleat including a second tip radius and a second spacing, wherein the first and second set of pleats are positioned upon a continuous filter media.

A stator vane assembly for a gas turbine engine in which both higher pressure cooling air and lower pressure cooling air are both supplied to the stator vane assembly to cool both an airfoil and inner and outer diameter endwall cavities of the stator vane assembly, in which the spent higher pressure cooling air is then discharged into a combustor of the gas turbine engine. The higher pressure cooling air flows through a closed loop cooling circuit formed within the stator vane assembly while the lower pressure cooling air is discharged through exit holes into the hot gas stream of the turbine.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.