The invention concerns land-based gas turbine plants with a multi-spool gas turbine arrangement for generating electrical power to supply a load (200). The invention comprises at least three spools (10a-10c). Each of the at least three spools (10a-10c) comprises a shaft (11a-11c), a compressor (C1-C3) and a turbine (T1-T3). Each one of the shafts (11a-11c) of the at least three spools (10a-10c) are independently rotatable with respect to each other. The invention further comprises electrical generators (G1-G3) mounted on each of the shafts (11a-11c) of the at least three spools (10a-10c), the output power of the generators being independently controllable and at least 60 percent of a total output power supplied to said load (200) in a form of electrical and rotational power is generated by the at least three generators (G1-G3) in the form of electrical energy.

Systems and methods of augmenting the thrust of the prime power engine(s) of an aircraft from a tank of compressed gas are described herein.

A burner for a combustion chamber of a gas turbine with a mixing and injection device, which includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies. Each streamlined body extends in a first transverse direction into the gas-flow channel, and has two lateral surfaces that are arranged essentially parallel to the main-flow direction. The lateral surfaces are joined to one another at their upstream and downstream sides to form leading and trailing edges of the body, respectively. At least one of the streamlined bodies includes a mixing structure and at least one fuel nozzle at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel. At least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.

The invention relates to the compression of a pyrolysis product to facilitate light olefin separation. The pyrolysis product is produced in a pyrolysis reaction. A power generator produces a first shaft power and a second shaft power. The pyrolysis product is compressed using at least part of the first shaft power and at least part of the second shaft power.

A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel. Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body. Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile. At least one of the streamlined bodies is provided with a mixing structure and with at least one fuel nozzle located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel, wherein at least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor. The invention also relates to a method of using said burner in a gas turbine.

A system includes a gas turbine having a turbine stage disposed in a combustion gas path, wherein the turbine stage includes turbine vanes disposed upstream from turbine blades. The system includes an isothermal expansion system coupled to the turbine stage. The isothermal expansion system includes multi-fluid injectors configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion, wherein at least one of the multi-fluid injectors is coupled to each of the turbine vanes. Each of the multi-fluid injectors includes a fuel port configured to inject a fuel, an oxidant port configured to inject an oxidant, and a barrier fluid port configured to inject a barrier fluid between the fuel and the oxidant, wherein the barrier fluid is configured to delay mixing between the fuel and the oxidant.

The invention provides a new path of combustion technology for gas turbine operation with multifuel capability, low emissions of NO.sub.x and CO and high thermal efficiency. Further to the present invention providing a method for operating a combustor for a gas turbine and a combustor for a gas turbine are disclosed. The combustor includes a first combustion chamber with a wide operating range, a subsequent deflection unit for deflecting the hot gas flow of the first combustion chamber at least in circumferential direction and components for injecting and mixing additional air and/or fuel, and a sequential combustion chamber with a short residence time, where the temperature of the hot gases reaches its maximum.

A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

A method is provided for operating a gas turbine installation which has at least one compressor for compressing combustion air, at least one combustion chamber for combusting a supplied fuel, using the compressed combustion air, and also at least one turbine which is exposed to throughflow by the hot gases from the at least one combustion chamber. Both a first fuel on a carbon base, especially in the form of natural gas, and also a second fuel, in the form of a hydrogen-rich fuel or pure hydrogen, are used as fuel. A reduction of the CO.sub.2 emission without basic modifications to the installation is achieved by the first and the second fuels being intermixed and combusted together in the at least one combustion chamber.