GAS-TURBINE ENGINE WITH GEAR TRANSMISSION Russian patent published in 2018 - IPC F02K3/06 F02K1/06 F01D17/14 

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine comprises an internal-loop engine, an internal nacelle, a fan nacelle, a fan nozzle with variable cross-section square, a fan and a reduction gearbox. Internal loop engine includes a compressor and a low pressure turbine, as well as a compressor and a high-pressure turbine. Internal nacelle is installed around the internal loop engine, and the fan nacelle is installed around the internal nacelle. Fan nozzle with variable cross-sectional square is installed able to move relative to the fan nacelle in order to change the square of the fan nozzle outlet cross-section and to control the degree of pressure change in the fan with respect to the airflow from the fan in the outer loop during the engine operation. Fan is located prior to the inner loop engine. Reduction gearbox is driven by the inner loop engine in order to drive the fan and has a gear ratio greater than or equal to approximately 2.3. Engine is designed able to provide, at the cruise flight mode with the speed of approximately M 0.8 and at the altitude of approximately 35,000 feet (10,668 m), the degree of pressure change in the fan of less than 1.45 and the reduced peripheral speed of the fan blade of less than 1,150 ft/sec (350 m/sec).

EFFECT: invention makes it possible to optimize the performance of a gas turbine engine fan with a variable square of the fan nozzle.

15 cl, 11 dwg