Provided is a combustor that has an efficient cooling structure. Also provided is a gas turbine engine that is provided with the combustor. A combustor that is for a gas turbine and that is provided with a combustion liner and with a fuel injection part that is provided to one end of the combustion liner so as to pass through the combustion liner. The combustion liner is provided with an inner liner that forms a combustion chamber inside the combustion liner, with a coolant flow path that is an annular space that is formed outside the inner liner, and with a coolant supply means that supplies hydrogen gas to the coolant flow path. In this combustor, the inner liner that is the combustion chamber is cooled by the hydrogen gas that flows in the coolant flow path.

Provided is a combustor that has an efficient cooling structure. Also provided is a gas turbine engine that is provided with the combustor. A combustor that is for a gas turbine and that is provided with a combustion liner and with a fuel injection part that is provided to one end of the combustion liner so as to pass through the combustion liner. The combustion liner is provided with an inner liner that forms a combustion chamber inside the combustion liner, with a coolant flow path that is an annular space that is formed outside the inner liner, and with a coolant supply means that supplies hydrogen gas to the coolant flow path. In this combustor, the inner liner that is the combustion chamber is cooled by the hydrogen gas that flows in the coolant flow path.

A solar chemically recuperated gas turbine system includes an exhaust-gas reformer, a solar reformer and a gas turbine unit with a combustion chamber. The reaction outlet of the exhaust-gas reformer is connected to the inlet of the solar reformer, the flue gas side inlet of the exhaust-gas reformer is connected to the exhaust-gas outlet of the gas turbine. The solar reformer outlet is connected to the combustion chamber inlet. Combustion gas drives the gas turbine after fuel burns in the combustion chamber, and the exhaust gas enters the exhaust-gas reformer. Fuel and steam are mixed and enter the reaction side of the exhaust-gas reformer through a fuel inlet. A reforming reaction between the fuel and steam under heating of the exhaust gas generates syngas. A further reforming reaction occurs by absorbing concentrated solar energy after the syngas enters the solar reformer, and the reactant is provided to combustion chamber.

A solar chemically recuperated gas turbine system includes an exhaust-gas reformer, a solar reformer and a gas turbine unit with a combustion chamber. The reaction outlet of the exhaust-gas reformer is connected to the inlet of the solar reformer, the flue gas side inlet of the exhaust-gas reformer is connected to the exhaust-gas outlet of the gas turbine. The solar reformer outlet is connected to the combustion chamber inlet. Combustion gas drives the gas turbine after fuel burns in the combustion chamber, and the exhaust gas enters the exhaust-gas reformer. Fuel and steam are mixed and enter the reaction side of the exhaust-gas reformer through a fuel inlet. A reforming reaction between the fuel and steam under heating of the exhaust gas generates syngas. A further reforming reaction occurs by absorbing concentrated solar energy after the syngas enters the solar reformer, and the reactant is provided to combustion chamber.

The present embodiments describe a method to reduce vanadium corrosion in a gas turbine by adding an oleophilic corrosion inhibitor into a combustion fuel, in which the oleophilic corrosion inhibitor comprises carbon black support particles and magnesium bonded to the carbon black support particles. The carbon black support particles comprise a particle size less than 40 nanometer (nm), and oxygen content less than 1 weight percent (wt %), and a surface area of at least 50 square meters per gram (m.sup.2/gram).

An intake-air cooling device is disposed on a rear-stage side of a pre-filter disposed on an intake-air inlet side of an intake-air duct for guiding intake air taken in from an intake-air inlet to a compressor, for cooling the intake air by spraying water to the intake air. The intake-air cooling device includes a plurality of nozzles configured to spray the water to the intake air, a plurality of water conduit pipes including the plurality of nozzles arranged in an axial direction of the plurality of water conduit pipes, and a plurality of supply pumps configured to supply the water to a corresponding one of the plurality of water conduit pipes. Each of the plurality of water conduit pipes is an endless member which has a different perimeter.

An intake-air cooling device is disposed on a rear-stage side of a pre-filter disposed on an intake-air inlet side of an intake-air duct for guiding intake air taken in from an intake-air inlet to a compressor, for cooling the intake air by spraying water to the intake air. The intake-air cooling device includes a plurality of nozzles configured to spray the water to the intake air, a plurality of water conduit pipes including the plurality of nozzles arranged in an axial direction of the plurality of water conduit pipes, and a plurality of supply pumps configured to supply the water to a corresponding one of the plurality of water conduit pipes. Each of the plurality of water conduit pipes is an endless member which has a different perimeter.

A system includes a gas turbine engine that may combust a fuel to generate power and an exhaust gas, an exhaust gas path in fluid communication with the gas turbine engine and that may receive the exhaust gas from the gas turbine engine, and a reductant skid fluidly coupled to the exhaust gas path. The reductant skid includes an injection system that may supply a reductant to the exhaust gas path. The system also includes a flow path separate from the exhaust gas path and fluidly coupling the gas turbine engine and the reductant skid. The first flow path may supply a first heated fluid to the reductant skid to aid in vaporization of the reductant.

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each GT; adjusting at least one of a fuel flow or a water flow for each GT to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio.

A system and method for generating an exhaust syngas are disclosed. The system includes a mixing unit, a heat exchanger, and an engine. The mixing unit is configured to mix a hydrocarbon fuel, an oxidant, and water to generate a fuel mixture. The heat exchanger is coupled to the mixing unit and is configured to receive the fuel mixture from the mixing unit, evaporate the water by heating the fuel mixture using a hot fluid, and generate a heated fuel mixture. The engine is coupled to the heat exchanger and is configured to receive the heated fuel mixture from the heat exchanger and generate an exhaust syngas by partially combusting the heated fuel mixture.