FIELD: machine building.
SUBSTANCE: exhaust system for gas turbine with separate flows includes flow-directing nozzle and exhaust pipe designed to connect directing nozzle to gas turbine outlet. Directing nozzle contains main nozzle attached to exhaust pipe and secondary nozzle located around the main nozzle. Directing nozzle additionally contains means to attach secondary nozzle directly to exhaust pipe. Note that the said secondary nozzle is supported by exhaust pipe irrespectively of the main nozzle. The other object of this invention is gas turbine with separate flows for aircraft engine including the exhaust system described above. Also the object of invention is method of exhaust system assembly for gas turbine with separate flows described above, in which the secondary nozzle is attached directly to exhaust pipe so that the said secondary nozzle is supported by exhaust pipe irrespectively of the main nozzle.
EFFECT: invention allows reducing mechanical loads affecting the main nozzle.
17 cl, 11 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS TURBINE WITH COMBUSTION CHAMBER MADE OF COMPOSITE MATERIAL | 2005 |
|
RU2310795C2 |
| FLEXIBLE THRUST LINKS FOR FIXATION OF PARTS FROM COMPOSITE MATERIALS WITH CERAMIC MATRIX | 2009 |
|
RU2493395C2 |
| EXHAUST GAS MANIFOLD AND THE GAS TURBINE | 2013 |
|
RU2668302C2 |
| LOW-PRESSURE STEAM TURBINE | 2010 |
|
RU2553582C2 |
| SPACE PROPULSION MODULE WITH ELECTRIC AND SOLID-FUEL CHEMICAL PROPULSION | 2014 |
|
RU2661245C2 |
| MIXER FOR NOZZLE WITH SEPARATED FLOW | 2005 |
|
RU2405958C2 |
| GAS TURBINE WITH COMBUSTION CHAMBER FIXED TO NOZZLE BLOCK | 2005 |
|
RU2368790C2 |
| GAS TURBINE AIR INTAKE PROTECTION SYSTEM AND GAS TURBINE PLANT | 2017 |
|
RU2735460C2 |
| GAS TURBINE EXPANSION COMPENSATOR (VERSIONS) AND METHOD OF PROVIDING FLUID FLOWING FROM EXHAUST CHANNEL | 2007 |
|
RU2445469C2 |
| TURBINE HOUSING ASSEMBLY | 2010 |
|
RU2522264C2 |
