FIELD: engines and pumps.
SUBSTANCE: invention is related to turbines of gas turbine engines of aviation and ground application. Turbine of gas turbine engine includes nozzle vanes installed in external ring arranged on the side of inlet and outlet edges by means of "thorn-slot" joint. Connection from the side of outlet edge is arranged with contact conic surface, external relative to turbine flow path. Thorn of blade with conic surface is aimed to the side of inlet edge, and angle of cone generatrix makes 40…80° to turbine axis.
EFFECT: increased reliability and efficiency factor of turbine by elimination of parasite leaks of cooling air in zone of nozzle vane outlet edge.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| HIGH-TEMPERATURE TURBINE OF GAS TURBINE ENGINE | 2011 |
|
RU2465466C1 |
| GAS TURBINE ENGINE MULTISTAGE TURBINE | 2008 |
|
RU2347914C1 |
| NOZZLE ASSEMBLY OF LOW-PRESSURE TURBINE (LPT) OF GAS TURBINE ENGINE (GTE) (VERSIONS) AND BLADE OF LPT NOZZLE ASSEMBLY (VERSIONS) | 2018 |
|
RU2691203C1 |
| NOZZLE BLOCK OF TURBOMACHINE | 1999 |
|
RU2171381C2 |
| 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 |
| HIGH-PRESSURE TURBINE (HPT) NOZZLE APPARATUS OF GAS TURBINE ENGINE (OPTIONS), NOZZLE CROWN OF HPT AND HPT NOZZLE APPARATUS BLADE | 2018 |
|
RU2683053C1 |
| GAS TURBINE ENGINE HIGH-TEMPERATURE TURBINE | 2013 |
|
RU2518766C1 |
| NOZZLE APPARATUS OF A HIGH-PRESSURE TURBINE OF A GAS TURBINE ENGINE | 2020 |
|
RU2757245C1 |
| HIGH-TEMPERATURE TURBINE STATOR | 2013 |
|
RU2538985C1 |
| NOZZLE SET FOR TURBINE OF GAS-TURBINE ENGINE | 1992 |
|
RU2035594C1 |
