Abstract: A gas turbine unit having a compressor section, a combustion chamber section containing at least one combustion chamber, and a turbine section, wherein, starting from a compressor inlet, a flow path extends. The gas turbine unit is equipped with at least one first and one second cooling air path. The first cooling air path draws off compressed air from the flow path upstream of the at least one combustion chamber. The first cooling air path has a higher pressure level than the second cooling air path and feeds the cooling air. The second cooling air path has a draw-off point in the compressor section, and extends from the compressor section to the turbine section, bypassing the at least one combustion chamber. After components have been cooled, the first cooling air path feeds the cooling air into the second cooling air path at an infeed point as additional cooling air.

Abstract: A gas turbine unit having a compressor section, a combustion chamber section containing at least one combustion chamber, and a turbine section, wherein, starting from a compressor inlet, a flow path extends. The gas turbine unit is equipped with at least one first and one second cooling air path. The first cooling air path draws off compressed air from the flow path upstream of the at least one combustion chamber. The first cooling air path has a higher pressure level than the second cooling air path and feeds the cooling air. The second cooling air path has a draw-off point in the compressor section, and extends from the compressor section to the turbine section, bypassing the at least one combustion chamber. After components have been cooled, the first cooling air path feeds the cooling air into the second cooling air path at an infeed point as additional cooling air.

Abstract: A combined cycle power plant including a gas turbine engine having a first compressor providing compressed air for combustion to form a hot working gas, and a turbine section for expanding the hot working gas. A first heat recovery steam generator (HRSG) is provided for receiving an exhaust gas flow from the turbine section to form a reduced temperature exhaust gas and to produce a high pressure steam flow which is provided to a high pressure steam turbine. A second compressor is provided for receiving and compressing the reduced temperature exhaust gas to add energy and form a reheated exhaust gas. A second heat recovery steam generator (HRSG) is provided for receiving and removing heat from the reheated exhaust gas to produce a low pressure steam flow, and a low pressure steam turbine is provided for receiving and expanding the low pressure steam flow.

Abstract: A gas turbo set including a first turbine, a second turbine, and a combustion chamber connected between the first and second turbines and operated by auto-ignition is provided. The turbines and the combustion chamber are located on a common shaft that may be rotated about an axis. To increase the efficiency of the gas turbo set, the outer periphery of the second turbine is at a greater distance from the axis than that of the first turbine, leading to a reduction in the size and/or the number of turbine blades.

Abstract: A combined cycle power plant including a gas turbine engine having a first compressor providing compressed air for combustion to form a hot working gas, and a turbine section for expanding the hot working gas. A first heat recovery steam generator (HRSG) is provided for receiving an exhaust gas flow from the turbine section to form a reduced temperature exhaust gas and to produce a high pressure steam flow which is provided to a high pressure steam turbine. A second compressor is provided for receiving and compressing the reduced temperature exhaust gas to add energy and form a reheated exhaust gas. A second heat recovery steam generator (HRSG) is provided for receiving and removing heat from the reheated exhaust gas to produce a low pressure steam flow, and a low pressure steam turbine is provided for receiving and expanding the low pressure steam flow.

Abstract: A gas turbo set including a first turbine, a second turbine, and a combustion chamber connected between the first and second turbines and operated by auto-ignition is provided. The turbines and the combustion chamber are located on a common shaft that may be rotated about an axis. To increase the efficiency of the gas turbo set, the outer periphery of the second turbine is at a greater distance from the axis than that of the first turbine, leading to a reduction in the size and/or the number of turbine blades.