COOLED TURBINE OF DOUBLE-FLOW GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C7/06 F01D25/12 F02C7/12 

FIELD: mechanics.

SUBSTANCE: invention relates to operation of gas turbine engines, in particular to engines used as drive of gas transfer units and power plants, and can be used in development of power plants with oil cooling in closed circulating system and for modernization of heating systems for maintenance of working temperature of oil in oil tanks of gas turbine engines. Known cooled turbine of double-flow gas turbine engine comprising distributing header with unit for connection with source of high temperature air, header with unit for connection with low-temperature air source, inter-disk cavity interconnected with high-temperature air source, high and low pressure turbines impellers with working blades and disks, high and low pressure turbine disks trunnions, nozzle device blades, rear supports of high and low pressure turbines with bearings, oil cavities of high and low pressure turbines interconnected through system of holes made in low pressure turbine disc trunnion, supercharging cavities and pre-oil cavities of high and low pressure turbine, wherein the low-pressure turbine pre-oil cavity is communicated via air ducts in the low pressure turbine rear support with the atmosphere, and the high pressure turbine pre-oil cavity is communicated with the low-temperature air source, wherein the high and low pressure turbine pre-oil cavities are communicated with each other and via the oil moving seals with the same oil cavities, is provided with additional air ducts and channels made in the high pressure turbine rear support, channels communicate, on one hand, with high- and low-pressure turbine pre-oil cavities, and, on the other side, via additional air ducts at outlet with pressure area lower than in pre-oil cavities. Furthermore, it is possible that pressure area is lower, than in pre-oil cavities, is gas-air pipeline after turbine or atmosphere. Cooled turbine of the double-flow gas turbine engine may contain one or more throttling devices arranged at the outlet of the additional air ducts, and the additional air ducts themselves may be placed in cavities of the vane nozzle blades.

EFFECT: application of the invention provides the oil temperature reduction by 2 times, ensures its properties stability and further multiple use in the oil supply line to the bearings of the support, improved operating conditions of high and low pressure turbine bearings and, as a result, increased service life and durability, as well as exclusion of coke formation on elements of turbine support structure.

5 cl, 2 dwg