FIELD: motors and pumps.
SUBSTANCE: group of inventions relates to the field of aircraft engine building. Rotor of engine LPT comprises LPA shaft with journal and LPT impeller including disk and blade rim with system of working blades. Impeller disc is equipped with air supply unit for cooling of blades containing pressure ring with air intake impeller. On the rear side, the disc hub is made integral with the cantilever ring element made with a polyfunctional air-transparent flange. Said flange is provided with holes for fasteners for detachable connection with journal arranged one way with channels of LPT rotor air cooling circuit. On the front side, the disc hub is provided with a flange for detachable connection to the annular rotor element enveloping the disc hub and creating a prolonged channel of the LPT rotor cooling path together with the hub. LPT rotor impeller blade includes shank and feather with convex-concave profile. Cavity of the blade is made on the full length of the blade body and is open to the flow of air flow. Cavity of the feather in the middle most heat-stressed part is equipped with a regular set of rods endowed with the function of a high-conductivity web between the walls of the blade body.
EFFECT: technical result consists in improvement of efficiency of cooling of heat-stressed LPT elements, reliability and resource of LPT and engine in general.
8 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| HIGH-PRESSURE TURBINE ROTOR OF A GAS TURBINE ENGINE (VERSIONS) | 2018 |
|
RU2691868C1 |
| METHOD FOR COOLING OF NOZZLE ASSEMBLY OF A LOW-PRESSURE TURBINE (LPT) OF A GAS TURBINE ENGINE AND A LPT NOZZLE ASSEMBLY WHICH IS COOLED BY THIS METHOD, A METHOD FOR COOLING A BLADE OF LPT NOZZLE ASSEMBLY AND A NOZZLE ASSEMBLY BLADE, COOLED BY THIS METHOD | 2018 |
|
RU2691202C1 |
| NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS) | 2018 |
|
RU2691203C1 |
| METHOD FOR COOLING TURBINE BLADE OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE AND ROTOR BLADE OF LPT, COOLED BY THIS METHOD | 2018 |
|
RU2691867C1 |
| METHOD OF COOLING THE ROTOR OF A HIGH PRESSURE TURBINE (HPT) OF GAS TURBINE ENGINE (GTE), HPT ROTOR AND HPT ROTOR BLADE COOLED BY THIS METHOD, KNOT OF THE DEVICE OF TWISTING OF AIR OF HPT ROTOR | 2018 |
|
RU2684298C1 |
| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
|
RU2614708C1 |
| IMPELLER WHEEL OF THIRD STAGE OF HIGH PRESSURE COMPRESSOR (HPC) ROTOR OF TURBOCHARGER ENGINE (VARIANTS), HPC ROTOR IMPELLER WHEEL DISC, HPC ROTOR IMPELLER WHEEL BLADE, HPC ROTOR IMPELLER WHEEL BLADE RING | 2016 |
|
RU2630921C1 |
| ROTOR FORTH 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 |
|
RU2630919C1 |
| 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 |
| 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 |
