FIELD: gas-turbine engineering. SUBSTANCE: engine has gas generator and low-pressure fan positioned at the back. The fan is provided with blade stages arranged in the zone of the first stages of the power turbine. The inner surface of the blade is at the distance from the outlet edge of the blade of the last stage of the fan which is equal to 0.25,0.5, 0.75, and 0.9 of the length of the nozzle, and relative increments of radii are equal to 0.1-0.2, 0.35- 0.55,0.75-0.9, 0.93-0.99. EFFECT: enhanced efficiency. 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF OPERATING TURBOFAN AIRCRAFT ENGINES WITH EXTERNAL FAN MODULE | 2014 |
|
RU2580608C2 |
| AXIAL-FLOW FAN OR COMPRESSOR IMPELLER AND FAN OF BYPASS FANJET INCORPORATING SAID IMPELLER | 2010 |
|
RU2460905C2 |
| COOLING SYSTEM OF GAS TURBINE OF DOUBLE-FLOW TURBOJET ENGINE WITH ADDITIONAL COMPRESSION OF AIR ION SMALL-SIZE FAN | 2006 |
|
RU2323359C1 |
| TURBO-JET ENGINE | 1991 |
|
RU2027054C1 |
| AIRCRAFT POWER PLANT | 2019 |
|
RU2716643C1 |
| HIGH BY-PASS RATIO TURBOJET ENGINE | 2006 |
|
RU2315879C2 |
| FLYING VEHICLE POWER PLANT | 2001 |
|
RU2205972C2 |
| "MAXINIO" STANDARD TECHNOLOGY OF VEHICLE MANUFACTURING AND OPERATION, NO-RUN TAKE-OFF AND LANDING ELECTRIC AIRCRAFT (VERSIONS), LIFTING DEVICE, TURBO-ROTARY ENGINE (VERSIONS), MULTISTEP COMPRESSOR, FAN COWLING, TURBO-ROTARY ENGINE OPERATION METHOD AND METHOD OF ELECTRIC AIRCRAFT LIFTING FORCE CREATION METHOD | 2010 |
|
RU2457153C2 |
| METHOD FOR PROTECTING GAS GENERATOR OF TURBOJET BY-PASS ENGINE FROM DUST PARTICLES | 2020 |
|
RU2752681C1 |
| TWO-LOOP TURBOJET ENGINE | 1992 |
|
RU2029881C1 |
