The present disclosure relates to a novel gas turbine system having applications, for example, in thermal power generation in an environmentally friendly manner. The multiloop gas turbine system may have multiple functional units each comprising a compressor, a regenerator, a combustion unit, and a turbine. Typically, exhaust flow of a turbine of a preceding loop may be routed to the combustion unit of the next loop, allowing mixing of exhaust flow with hot compressed air of the next loop, and the expanded exhaust from the turbine of the ultimate loop is fed back into the regenerators of each loop to recover exhaust heat.

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.

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 vehicle provided with a power plant having at least one heat engine, the vehicle having an air-conditioning system comprising a fluid circulating in a fluid circulation system, the fluid circulation system comprising at least one pump configured to cause the fluid to circulate in a fluid circuit. The vehicle comprises one injection member per heat engine configured to inject the fluid into the associated heat engine, the vehicle comprising a back-up circuit fluidly connecting the fluid circulation system to each injection member, the back-up circuit comprising a distribution device controlled by a controller to authorize, on command, circulation of the fluid towards an injection member.

A propulsion system for an aircraft includes a hydrogen fuel system supplying hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from an exhaust gas flow and includes a plurality of spiral passages disposed within a collector. The spiraling passages generate a transverse pressure gradient to direct water out of the exhaust gas flow toward the collector.

A contrail suppression system includes a shell having an exhaust gas inlet, an exhaust gas outlet, a condensate drain and a flow chamber in fluid communication with the exhaust gas inlet, the exhaust gas outlet and the condensate drain. The exhaust gas inlet is in fluid communication with a jet exhaust nozzle of a gas turbine engine. A first tube bundle is disposed within the flow chamber downstream from the exhaust gas inlet. The first tube bundle includes an inlet and an outlet. The inlet of the first tube bundle is fluidly connected to a first cooling medium source. A second tube bundle is disposed within the flow chamber downstream from the first tube bundle and upstream from the exhaust gas outlet. The second tube bundle includes an inlet and an outlet. The inlet of the second tube bundle is fluidly connected to a second cooling medium source.

A method and system for enhancing power generated by a gas turbine system. The system may include a turbine inlet cooling system and a wet compression air fogging system. Air entering the gas turbine system is cooled by the turbine inlet cooling system and the wet compression air fogging system. The wet compression air fogging system may increase the mass flow rate of the air entering the gas turbine system at the compressor.

A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.

A device for temporarily increasing power in order to increase the power from at least one first turbine engine and from at least one second turbine engine, the device including a tank of coolant liquid, a first injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the first turbine engine, a second injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the second turbine engine, each of the first and second injection circuits including at least one first valve and at least one second valve arranged upstream from said at least one first valve, and a bridge pipe connecting together the first injection circuit and the second injection circuit upstream from their respective first valves and downstream from their respective second valves.

An inflatable device equipped with a guiding mechanism and methods of installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, an inflatable device includes a backbone and an inflatable bladder connected thereto. The backbone is formed of a flexible and inextensible material. The inflatable bladder is formed of an expandable material. To install the inflatable device within an annular chamber of a gas turbine engine, the backbone is inserted into a first access port of the engine and is moved circumferentially around the annulus of the chamber. The backbone is retrieved through a second access port. The inflatable bladder is moved into position within the chamber by pushing the backbone into the first access port and/or pulling the backbone out of the second access port. When positioned in place, the inflatable bladder is inflated to form an annular seal.