Turbofan gas turbine engines and a method of controlling the radial clearance in the turbine bypass ratio gas turbine engine

摘要

1. Turbofan gas turbine engine comprising a compressor, a combustor, a turbine, comprising at least one step with a cooled nozzle apparatus with cavities above and below it, and at least one rotor with a cooled turbine impeller and twist apparatus in front of him and the turbine stator comprising at least one turbine housing with cavities therebetween, and an annular insert of the turbine impeller and the radial clearance control system, characterized in that the stator turbine configured cooled Sports ear of the second circuit, and the system to feed cooling air stator is in the form of the air intake mounted in the second circuit and the flow controller to an actuator, and also contains an onboard computer and sensors for measuring radial clearance, flow regulator drive, and sensors measuring the radial gap are connected in electrical communication with kompyuterom.2 board. Turbofan gas turbine engine according to claim 1, characterized in that the annular insert is pustoteloy.3. Turbofan gas turbine engine according to claim 2, characterized in that the internal cavity is filled with heat accumulating veschestvom.4 insertion. A method for controlling the radial gap in a turbine turbofan engine including a cooling of the rotor of high pressure bleed air from the compressor and stator of the second circuit air, characterized in that for cooling the turbine stator use of the second circuit air flow, which is taken from the air intake and increase the cooling speed cooling air path in the turbine stator, measured for