GAS TURBINE ENGINE Russian patent published in 2014 - IPC F02C3/14 F23R3/04 

FIELD: machine building.

SUBSTANCE: turbine is fitted by a cooled nozzle diaphragm with its blades along the airfoil from the leading edge having the first, second, third and fourth inner cavities connected to a flow passage through the holes in the blade airfoil, and a bypass device. The combustion chamber is fitted by annular space between the inner, outer case and the annular flame tube with heads. The input of the annular flame tube head is connected to the flow passage of the compressor sequentially from the compressor via a circular segment of the vaned diffuser with the output of the latter being connected to the input of the air line - channel pipe branch with its output being connected to the input of the third inner cavity of the cooled nozzle diaphragm's blade with one of its outputs being connected to the input of the flame tube head. The third inner cavity is fitted by two more outputs. One of the outputs is connected to the input of the first inner cavity of the blade via the annular space of the combustion chamber and the annular cavity-receiver. The second input is connected to the fourth inner cavity of the nozzle diaphragm blade via the hole in a partition wall. The nozzle diaphragm has at least one or more blades whose third inner cavity is fitted by the fourth output which connects it to the second inner cavity via the hole in the partition wall. The bypass device is installed in the said blades and is kinematically coupled with a valve set at the input of the fuel nozzle of the head connected to the said blade. The second cavity of the said blades is connected to the second cavity of the blade which is not equipped with the bypass device.

EFFECT: invention provides for efficient operation of the combustion chamber of a gas turbine engine and cooling system of a high temperature gas turbine in different operation modes.

6 cl, 11 dwg