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AssigneeALSTOM Technology Ltd
InventorHans Ulrich Frutschi
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A gas turbine system comprises a gas turbine (1, 2, 3) having a compressor (1) and a turbine (2), which via a common shaft (3) drive a generator (4), and a combustion chamber (6), the exit of which is connected to the entry to the turbine (2) of the gas turbine (1, 2, 3), has a fuel feed (8) and receives combustion air from the exit of the compressor (1) of the gas turbine (1, 2, 3) via the high-pressure side of a recuperator (5), the exit of the turbine (2) and the entry to the compressor (1) of the gas turbine (1, 2, 3) being connected via the low-pressure side of the recuperator (5), and a first exhaust-gas turbocharger (ATL2) which sucks in air being connected to different locations (9, 10) of the low-pressure side of the recuperator (4) by means of the exit of its compressor (13) and the entry to its turbine (14). A system of this type is suitable for combined heat and power generation installations if the compressor (1) of the gas turbine (1, 2, 3) is designed as a radial compressor.
A method for operating a partially closed, turbocharged gas turbine cycle, in which method fuel is burnt in a combustion chamber (6) when a gaseous, compressed working medium which contains combustion air is supplied, the working medium which contains the hot combustion gases is expanded in a turbine (2) of a gas turbine (1, 2, 3), performing work as it does so, heat is extracted from the expanded working medium in a downstream recuperator (5), the cooled working medium is then compressed in a compressor (1) of the gas turbine (1, 2, 3), and heat is fed to the compressed working medium in the recuperator (4) before it re-enters the combustion chamber (6), and in which method on the low-pressure side of the recuperator (5) some of the expanded working medium is removed at a removal location (9) which is at a suitable first temperature level and is expanded further in the turbine (14) of a first exhaust-gas turbocharger (ATL2), and air is sucked in and compressed by the compressor (13) of the first exhaust-gas turbocharger (ATL2), and the compressed air is fed to the working medium on the low-pressure side of the recuperator (5) at a feed location (10) which is at a suitable second temperature level, characterized in that a gas turbine (1, 2, 3) whose compressor (1) is designed as a radial compressor is used.
The gas turbine system as claimed in one of claims 12 to 15 [sic], characterized in that a precooler (7), which can be used to discharge heating heat, is arranged between the entry to the compressor (1) of the gas turbine (1, 2, 3) and the low-pressure-side exit of the recuperator (5).
The gas turbine system as claimed in one of claims 12 to 16 [sic], characterized in that the first exhaust-gas turbocharger (ATL2) can be driven by an auxiliary machine, in particular in the form of an electrical machine (15) connected to the grid system via converters.
Dependencies are inferred from the claim text.