FIELD: machine engineering.
SUBSTANCE: three-tier working blade of the turbo-fan comprises a fan blade and a turbine blade which are arranged in series from a turbo fan casing to a rotor disc, and a turbine blade connected to each other by means of an intermediate element with formation of three flow-through gas channels. The intermediate element is made in form of working blade of a turbo-expander with formation of smooth transition from a profile to the profile of all three working blades. The flow part of the working blade gas channel of the turbo expander is limited by shelves. The fan working blade is connected to the turbo expander working blade by means of a detachable hinged joint.
EFFECT: intensive engine cooling, increased engine thrust, reduced weight and increased strength properties of the three-tier working blade of the turbo-fan, as well as its reliability as a whole.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COOLING SYSTEM FOR TURBINE ELEMENTS OF TURBOJET | 2018 |
|
RU2706524C1 |
| GAS TURBINE ENGINE LOW-PRESSURE TURBINE (LPT) (VERSIONS), ROTOR SHAFT CONNECTION UNIT WITH LPT DISC, LPT ROTOR AIR COOLING PATH AND AIR FEEDING APPARATUS FOR COOLING LPT ROTOR BLADES | 2018 |
|
RU2684355C1 |
| NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS) | 2018 |
|
RU2691203C1 |
| HIGH-PRESSURE TURBINE (HPT) NOZZLE APPARATUS OF GAS TURBINE ENGINE (OPTIONS), NOZZLE CROWN OF HPT AND HPT NOZZLE APPARATUS BLADE | 2018 |
|
RU2683053C1 |
| HIGH-PRESSURE TURBINE ROTOR OF A GAS TURBINE ENGINE (VERSIONS) | 2018 |
|
RU2691868C1 |
| ROTOR EIGHTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630924C1 |
| IMPELLER WHEEL OF SEVENTH STAGE OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VERSIONS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630923C1 |
| BLADE FOR RUNNING MACHINE | 2004 |
|
RU2362885C2 |
| NINTH STAGE IMPELLER WHEEL OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE, HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630925C1 |
| ROTOR SIXTH STAGE IMPELLER OF HIGH-PRESSURE COMPRESSOR (HPC) OF TURBOJET ENGINE (VERSIONS), HPC ROTOR IMPELLER DISC, HPC ROTOR IMPELLER BLADE, HPC ROTOR IMPELLER BLADE RING | 2016 |
|
RU2630922C1 |
