FIELD: gas-turbine manufacture. SUBSTANCE: boundary layer is sucked out of mixing chamber at flow rate of 8-12% of cooling air flow. EFFECT: improved cooling conditions. 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SECTION OF GAS-TURBINE PLANT COMBUSTION CHAMBER | 1990 |
|
RU2023187C1 |
| FRONTAL ARRANGEMENT OF COMBUSTION CHAMBER | 1990 |
|
RU2013708C1 |
| ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 0 |
|
SU1719801A1 |
| METHOD OF JET-POROUS COOLING OF HEAT-STRESSED ELEMENTS | 2011 |
|
RU2469242C1 |
| ROTARY HIGH-VELOCITY GAS-AND-LIQUID HIGH-TEMPERATURE CONTACT SURFACE HEAT EXCHANGER | 1998 |
|
RU2141087C1 |
| COMBUSTION LINER OF GAS-TURBINE ENGINE | 2006 |
|
RU2343355C2 |
| COMBINED COOLING METHOD OF HEAT-STRESSED COMPONENTS (VERSIONS) | 2011 |
|
RU2483250C2 |
| METHOD FOR MANUFACTURING FLAME TUBE OF AIRCRAFT GAS-TURBINE ENGINE COMBUSTION CHAMBER | 2004 |
|
RU2258869C1 |
| AIRCRAFT GAS-TURBINE ENGINE BEARING SUPPORT COOLING SYSTEM | 2002 |
|
RU2213875C1 |
| RING COMBUSTION CHAMBER FOR GAS-TURBINE ENGINE | 2004 |
|
RU2280814C1 |
