Abstract: A method for operating a gas turbine power plant, and a gas turbine power plant in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet.

Abstract: A method is provided for operating a gas turbine plant, in which compressed air is extracted from a compressor and for cooling is directed in an internal cooling passage through thermally loaded components to the combustion chamber and/or to the turbine, then re-cooled, and added to the compressor main flow in the compressor. At least a portion of the recirculated air is supersaturated, or partially saturated, with drops of water during or before recirculation into the compressor and a cooling mist is created. A gas turbine plant is provided with a closed cooling circuit which, for implementing the method, includes an injection arrangement for introducing water into the recirculated cooling air.

Abstract: What is described is a method for operating a gas turbine power plant, in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet.

Abstract: A gas turbine generator set includes a compressor unit including at least one compressor, at least one generator and at least one combustion chamber. Exhaust gases from at least one turbine are recirculated for a further thermal utilization. At least one cooling fluid compressor is configured to compress a cooling fluid including at least one of fresh air and a portion of the recirculated exhaust gases for a cooling of thermally loaded parts.

Abstract: A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.

Abstract: A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.

Abstract: A method is provided for operating a gas turbine plant, in which compressed air is extracted from a compressor and for cooling is directed in an internal cooling passage through thermally loaded components to the combustion chamber and/or to the turbine, then re-cooled, and added to the compressor main flow in the compressor. At least a portion of the recirculated air is supersaturated, or partially saturated, with drops of water during or before recirculation into the compressor and a cooling mist is created. A gas turbine plant is provided with a closed cooling circuit which, for implementing the method, includes an injection arrangement for introducing water into the recirculated cooling air.

Abstract: A gas turbine generator set includes a compressor unit including at least one compressor, at least one generator and at least one combustion chamber. Exhaust gases from at least one turbine are recirculated for a further thermal utilization. At least one cooling fluid compressor is configured to compress a cooling fluid including at least one of fresh air and a portion of the recirculated exhaust gases for a cooling of thermally loaded parts.

Abstract: A gas turbine installation (1), in particular in a power plant for generating electricity, includes a turboset (2) having a turbine (4), a compressor (5) and a combustion chamber (6) arranged in a gas path (9) connecting the compressor (5) to the turbine (4), and a flue gas recirculation device (3), which passes combustion flue gas from the turbine (4) from a flue gas path (14) connected to the turbine (4) via a recirculation path (16) to a fresh gas path (13) connected to the compressor (5). To improve the efficiency of the gas turbine installation (1), a control device (17) controls a volumetric flow and/or a temperature of the recirculated combustion flue gases in such a way that a fresh gas/flue gas mixture which enters the compressor (5) is at a predetermined desired temperature.

Abstract: A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.

Abstract: A turbine blade or vane (1) has a shell (2), including a first side wall (8) and a second side wall (9), which are connected together at a leading edge (10) and at a trailing edge (11), which extend longitudinally from a root (7) to a tip (6) and which are connected together between leading edge (10) and trailing edge (11) by a plurality of inner ribs (13). In the inner region (12) of the turbine blade/vane (1), the ribs (13) form at least one cooling gas path (15), which guides a cooling gas flow from the root (7) to the tip (6) and, in the process, is deflected a plurality of times in serpentine shape from the outside to the inside and from the inside to the outside.

Abstract: A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formation of hot gas, as well as a turbine in which the hot gas is expanded while providing work output. In a method for cooling this gas turbine system, compressed air is removed from the compressor, is fed as cooling air for cooling inside an internal cooling channel through thermally loaded components of the combustor and/or the turbine, is then compressed and added to the compressor end air. An improved cooling without disadvantage for the efficiency of the system is achieved in that, in the manner of a targeted leakage, a small part of the cooling air is fed for film cooling into the turbine stream through drilled film cooling openings provided on the components.

Abstract: A gas turbine installation (1), in particular in a power plant for generating electricity, includes a turboset (2) having a turbine (4), a compressor (5) and a combustion chamber (6) arranged in a gas path (9) connecting the compressor (5) to the turbine (4), and a flue gas recirculation device (3), which passes combustion flue gas from the turbine (4) from a flue gas path (14) connected to the turbine (4) via a recirculation path (16) to a fresh gas path (13) connected to the compressor (5). To improve the efficiency of the gas turbine installation (1), a control device (17) controls a volumetric flow and/or a temperature of the recirculated combustion flue gases in such a way that a fresh gas/flue gas mixture which enters the compressor (5) is at a predetermined desired temperature.

Abstract: In a method for operating a power plant by means of a CO2 process, isentropic compression first takes place, subsequently an isobaric heat supply, then isentropic expansion, and finally isobaric heat discharge. The CO2 process broken down here takes place with internal combustion, a fuel (21) and the oxygen (18) necessary for oxidization being supplied. After the charging of the CO2 circuit (23) has been carried out, the excess CO2 formed from combustion is discharged continuously, in that this gas is led through a cooler (14), in which said gas is condensed. In order to dispose of this condensed CO2 (15), there are available here, for example, the possibilities of storing this CO2 on the ocean floor or of introducing the condensed CO2 into a worked-out deposit of natural gas.

Abstract: The invention relates to an axial-flow thermal turbomachine having a metallic rotor (1), in which rotor blades (3) made of an intermetallic compound are mounted in a circumferential groove to form a row of blades. The invention is characterized in that at least two rotor blades (3?) which are at a uniform distance from one another and are made of a more ductile material are arranged in the said row of blades between the intermetallic rotor blades (3), the rotor blades (3?) made of the more ductile material either being considerably longer than the intermetallic blades (3) or, if they are of the same length, having a different blade tip shape than the intermetallic blades (3).

Abstract: The invention relates to an axial-flow thermal turbomachine, having a rotor (1) made from a metallic material with a first density (D1), in which rotor blades (3, 3?) and intermediate pieces (4) are mounted alternately in a circumferential groove. It is characterized in that said intermediate pieces (4) consist of a material with a second density (D2), which is lower than the first density (D1). Particularly suitable materials for the intermediate pieces (4) are intermetallic compounds, preferably intermetallic ?-titanium aluminide alloys or intermetallic orthorhombic titanium aluminide alloys, but also titanium alloys.

Abstract: The invention relates to an axial-flow thermal turbomachine having a metallic rotor (1), in which rotor blades (3) made of an intermetallic compound are mounted in a circumferential groove to form a row of blades. The invention is characterized in that at least two rotor blades (3?) which are at a uniform distance from one another and are made of a more ductile material are arranged in the said row of blades between the intermetallic rotor blades (3), the rotor blades (3?) made of the more ductile material either being considerably longer than the intermetallic blades (3) or, if they are of the same length, having a different blade tip shape than the intermetallic blades (3).

Abstract: The invention relates to an axial-flow thermal turbomachine, having a rotor (1) made from a metallic material with a first density (D1), in which rotor blades (3, 3?) and intermediate pieces (4) are mounted alternately in a circumferential groove. It is characterized in that said intermediate pieces (4) consist of a material with a second density (D2), which is lower than the first density (D1). Particularly suitable materials for the intermediate pieces (4) are intermetallic compounds, preferably intermetallic ?-titanium aluminide alloys or intermetallic orthorhombic titanium aluminide alloys, but also titanium alloys.

Abstract: A turbine blade or vane (1) has a shell (2), including a first side wall (8) and a second side wall (9), which are connected together at a leading edge (10) and at a trailing edge (11), which extend longitudinally from a root (7) to a tip (6) and which are connected together between leading edge (10) and trailing edge (11) by a plurality of inner ribs (13). In the inner region (12) of the turbine blade/vane (1), the ribs (13) form at least one cooling gas path (15), which guides a cooling gas flow from the root (7) to the tip (6) and, in the process, is deflected a plurality of times in serpentine shape from the outside to the inside and from the inside to the outside.

Abstract: In a method for the operation of a power plant with a closed or quasi-closed cycle, the power plant substantially comprises at least one compressor unit (1) or a pump, at least one combustion chamber (2), at least one turbine (3) and at least one heat sink (4). In the combustion chamber (2), a fuel mass flow (14) reacts with at least one oxygen flow (12), the excess combustion products which are formed as a result (CO2, H2O) are removed from the cycle at a suitable location (5, 6), and the oxygen stream (12) fed to the combustion chamber is obtained by means of an air fractionation installation (11). Means (9) for coarse fractionation of the supplied air (8) are connected upstream of the air fractionation installation (11) in order to supply oxygen-enriched air (10) to the air fractionation installation (11).