A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.

A multistage centrifugal compressor includes a casing, a rotor including a plurality of impellers, a diaphragm defining a gas flow path that includes a return flow path, and at least one liquid injection device configured to inject liquid into the gas flow path. The liquid injection device includes a liquid injection path, an internal path, a chamber, and a plurality of nozzles. The liquid injection path penetrates through the casing at a position corresponding to a return bend. The internal path receives a liquid supply pipe inserted from the liquid injection path through the return bend. The chamber is provided in the diaphragm along a circumferential direction and the liquid is introduced into the chamber through the internal path. The plurality of nozzles inject the liquid introduced into the chamber, to the gas flow path from different positions of the chamber in the circumferential direction.

In one embodiment, a plant control apparatus controls a power plant that includes a combustor to burn fuel with oxygen introduced from an inlet guide vane to generate gas, a gas turbine driven by the gas from the combustor, a heat recovery steam generator to generate steam using heat of an exhaust gas from the gas turbine, and a steam turbine driven by the steam from the heat recovery steam generator. The apparatus controls an angle of the inlet guide vane before a start of the steam turbine to a first angle, controls the angle of the inlet guide vane after the start of the steam turbine to a second angle larger than the first angle, and reduce the angle of the inlet guide vane from the second angle to the first angle or more during the predetermined period.

Systems and methods for augmenting power output when operating a load having relatively brief periods of high energy demand and high heat generation. A system comprises a gas turbine engine including a coolant injection assembly, an electrical generator coupled to the gas turbine engine, a high-energy operating load coupled to the electrical generator, and a cooling system adapted to provide cooling to the high-energy operating load. The cooling system is coupled and adapted to provide coolant to the coolant injection assembly of the gas turbine engine. A method comprises coupling the cooling system to the coolant injection assembly at the inlet of the gas turbine engine, selectively diverting at least a portion of the coolant of the cooling system to the coolant injection assembly, and spraying the diverted coolant into air entering the gas turbine engine.

A hydrogen hybrid cycle system configured to convert heat into mechanical work by burning a H2 and an O2. The hydrogen hybrid cycle system comprises a H2 source, an O2 source, a combustion chamber, a first steam injected gas turbine, a load, a heat recovery steam generator and a water pump. The H2 source provides the H2 to the combustion chamber. The O2 source provides the O2 to the combustion chamber. The combustion chamber burns portions of the H2 and the O2. The hydrogen hybrid cycle system burns the H2 and the O2 at or near stoichiometry in the combustion chamber. The hydrogen hybrid cycle system cools the combustion chamber with at least one of a cooling steam and a water.

Various systems and methods are provided for a turbocharger system. In one example, a system for use with a power generator having a rotary machine including a combustor comprises: a heat exchanger positioned to receive exhaust gases from the combustor; and a turbocharger system, comprising: a low pressure compressor fluidly coupled to the heat exchanger and adapted to supply gases to the heat exchanger; a low pressure turbine and a high pressure turbine each fluidly coupled to the heat exchanger and adapted to receive gases from the heat exchanger; a high pressure compressor fluidly coupled to the rotary machine and the low pressure compressor, adapted to receive gases from the low pressure compressor and supply compressed air to the rotary machine; and a water injector adapted to inject water into a flow path between the low pressure compressor and the heat exchanger.

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.

A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.

A gas turbine engine that includes an inlet volume flow control appliance and methods of operating the same are provided. The method includes operating the gas turbine engine with the inlet volume flow control appliance supplying a compressor inlet volume flow that is below a maximum compressor inlet volume flow. A mass flow of a liquid agent is added to a compressor gas mass flow while the gas turbine engine is operated with a compressor inlet volume flow below a maximum compressor inlet volume flow. The mass flow of a liquid agent may be controlled as a function of the pitch of variable inlet guide vanes. The method further comprises adjusting the volume flow control appliance to increase the compressor inlet volume flow and increasing the mass flow of liquid agent added to the compressor gas mass flow while the inlet volume flow control appliance increases the compressor inlet volume.

Methods and apparatus for controlling liquid flow to a turbine fogging array. Some implementations are generally directed toward adjusting the output of a variable output pump that supplies water to the turbine fogging array. In some of those implementations, the output is adjusted based on a determined target pump output value that is indicative of a pump output required to change the moisture content of intake air of a combustion turbine to meet a target humidity value. Some implementations are generally directed toward actuating at least one control valve of a plurality of control valves that control liquid throughput to one or more fogging nozzles of a fogging array.