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An apparatus for controlling a cooling air flow, in particular a gas turbine cooling air flow, is for the control, specific to requirement, of a cooling air flow using low-maintenance. A control fluid flow is introduced into the cooling air flow in the region of the flow duct with a flow component t

An apparatus for controlling a cooling air flow, in particular a gas turbine cooling air flow, is for the control, specific to requirement, of a cooling air flow using low-maintenance. A control fluid flow is introduced into the cooling air flow in the region of the flow duct with a flow component transverse to the flow direction of the cooling air flow through the flow duct. As such, the flow rate of the cooling air flow is adjustable as a function of control parameters of the control fluid flow and/or other parameters.

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1. An apparatus for controlling a cooling air flow which flows through a flow duct of a gas turbine, comprising: a control fluid flow channel, including a control fluid flow introduced into the flow duct, with a flow component transverse to the flow direction of the cooling air flow through the fl

1. An apparatus for controlling a cooling air flow which flows through a flow duct of a gas turbine, comprising: a control fluid flow channel, including a control fluid flow introduced into the flow duct, with a flow component transverse to the flow direction of the cooling air flow through the flow duct, wherein a flow rate of the cooling air flow is influenced as a function of the control fluid flow, said control fluid flow being dynamically variable. 2. The apparatus as claimed in claim 1, wherein the flow rate of the cooling air flow is adjustable as a function of control parameters of the control fluid flow.3. The apparatus as claimed in claim 2, wherein the flow rate of the cooling air flow is adjustable by adjusting the pressure of the control fluid flow.4. The apparatus as claimed in claim 1, wherein the flow rate of the cooling air flow is adjustable by adjusting the pressure of the control fluid flow.5. The apparatus as claimed in claim 1, wherein the flow rate of the control fluid flow is small relative to the flow rate of the cooling air flow.6. The a apparatus as claimed in claim 1, wherein the control fluid flow is radially introducable into the cooling air flow flowing through the flow duct.7. The apparatus as claimed in claim 1, wherein the control fluid flow is tangentially introducable into the cooling air flow flowing through the flow duct.8. The apparatus as claimed in claim 1, wherein the control fluid flow is introducable in the manner of a secant into the cooling air flow flowing through the flow duct.9. The apparatus as claimed in claim 1, wherein the flow duct includes a nozzle and a downstream diffuser with a specified opening angle, and wherein the control fluid flow is introducable in a transitional peripheral region between the nozzle and the diffuser.10. The apparatus as claimed in claim 9, wherein the diffuser, through which flow occurs, includes an opening angle of approximately 30° and wherein there is a ratio of approximately 1:3 between an inlet area of the nozzle and an outlet area of the diffuser.11. The apparatus as claimed in claim 9, wherein the diffuser, through which flow occurs, includes an opening angle of approximately 10° and wherein there is a ratio of approximately 1:3 between an inlet area of the nozzle and an outlet area of the diffuser.12. The apparatus as claimed in claim 1, comprising: a plurality of apparatuses connected in series or parallel, with the cooling air flow flowing through the apparatuses. 13. The apparatus as claimed in claim 1, wherein the cooling air flow is an effective gas flow and the control fluid flow is a control gas flow.14. The apparatus as claimed in claim 1, wherein the flow of the cooling air is further influenced by an angle of the control fluid flow channel with respect to the flow duct.15. The apparatus as claimed in claim 1, wherein the flow of the cooling air is further influenced by the shape of the flow duct.16. The apparatus as claimed in claim 1, wherein the flow of the cooling air is further influenced by an angle of the control fluid flow channel with respect to the flow duct and the shape of the flow duct.17. A gas turbine comprising: rotor blades inserted in carrier disks; stationary guide blades arranged between the carrier disks, wherein cooling air flows through the guide blades from a radially outer region to a radially inner region; and between the rotor blades and the guide blades, a respective carrier disk lateral space to which at least part of the cooling air flowing through the guide blades is supplied, wherein at least one guide blade includes, on a radially inner end region, an apparatus which influences cooling air supply, said apparatus including a control fluid flow channel permitting control fluid to influence the cooling air flow, said control fluid flow being dynamically variable. 18. The gas turbine as claimed in claim 17, wherein an apparatus influencing cooling air supply is provided at the radially inner end region of said at least one guide blade, by which the cooling air supply to the carrier disk lateral space is controllable by a control air flow.19. The gas turbine as claimed in claim 18, wherein the control air flow is supplyable through a feed duct to the transition peripheral region between the nozzle and the diffuser, the feed duct being provided within the guide blade and including a control apparatus in its outer region for adjusting the control air pressure.20. The gas turbine as claimed in claim 17, wherein the control air flow is suppliable through a feed duct to the transition peripheral region between the nozzle and the diffuser, the feed duct being provided within the said at least one guide blade and including a control apparatus in its outer region for adjusting the control air pressure.21. The gas turbine as claimed in claim 17, wherein the feed duct includes an intermediate region between the control apparatus, provided in its outer region, and its entry into the transitional peripheral region between the nozzle and the diffuser, the intermediate regions being connected by more than one apparatuses, which influence the cooling air supply, of the guide blades of the carrier disks.22. The gas turbine as claimed in claim 17,wherein the flow of the cooling air is further influenced by an angle of the control fluid flow channel with respect to the flow duct.23. The gas turbine as claimed in claim 17, wherein the flow of the cooling air is further influenced by the shape of the flow duct.24. The gas turbine as claimed in claim 17, wherein the flow of the cooling air is further influenced by an angle of the control fluid flow channel with respect to the flow duct and the shape of the flow duct.25. A method of controlling a cooling air flow which flows through a flow duct comprising: introducing a control fluid flow into the cooling air flow, in the region of the flow duct, with a flow component transverse to the flow direction of the cooling air flow through the flow duct; and adjusting the flow rate of the cooling air flow as a function of the control fluid flow, said control fluid flow being dynamically adjustable. 26. The method as claimed in claim 25, wherein the flow rate of the cooling air flow is adjusted as a function of control parameters of the control fluid flow.27. The method as claimed in claim 26, wherein the flow rate of the cooling air flow is adjusted by adjusting the pressure of the control fluid flow.28. The method as claimed in claim 25, wherein the flow rate of the cooling air flow is adjusted by adjusting the pressure of the control fluid flow.29. The method as claimed in claim 25, wherein the flow rate of the control fluid flow is small relative to the flow rate of the cooling air flow.30. The method as claimed in claim 25, wherein the control fluid flow is introduced radially into the cooling air flow flowing through the flow duct.31. The method as claimed in claim 25, wherein the control fluid flow is introduced tangentially into the cooling air flow flowing through the flow duct.32. The method as claimed in claim 25, wherein the control fluid flow is introduced in the manner of a secant into the cooling air flow flowing through the flow duct.33. The method as claimed in claim 25, wherein the cooling air flow flows through a nozzle and a downstream diffuser with a specified opening angle, and the control fluid flow is introduced in a transitional peripheral region between the nozzle and the diffuser.34. The method as claimed in claim 33, wherein the diffuser, through which flow occurs, includes an opening angle of approximately 30°, and wherein there is a ratio of approximately 1:3 between an inlet area of the nozzle and an outlet area of the diffuser.35. The method as claimed in claim 33, wherein the diffuser, through which flow occurs, includes an opening angle of approximately 10°, and wherein there is a ratio of approximately 1:3 between an inlet area of the nozzle and an outlet area of the diffuser.36. The method as claimed in claim 25, wherein the cooling air flow is controlled by a plurality of apparatuses connected in series or parallel.37. The method as claimed in claim 25, wherein the cooling air flow is an effective gas flow and the control fluid flow is a control gas flow.38. The method as claimed in claim 25, wherein the flow of the cooling air is further influenced by an angle of the control fluid flow channel with respect to the flow duct.39. The method as claimed in claim 25, wherein the flow of the cooling air is further influenced by the shape of the flow duct.40. The method as claimed in claim 25, wherein the flow of the cooling air is further influenced by an angle of the control fluid flow channel with respect to the flow duct and the shape of the flow duct.