FIELD: mechanical engineering; engines. SUBSTANCE: combustion chamber of gas-turbine engine 28 has primary, secondary and tertiary combustion zones 36, 40, 46, respectively, located in direction of flow one after the other. Chamber has fuel and air secondary mixing tube 64 and fuel and air tertiary mixing tube 76. Secondary mixing tube 64 has secondary air intake device 72 at end located higher in direction of air flow. Tertiary mixing tube 78 has tertiary air intake device 84 at its end located higher in direction of flow. Fuel system 88 has manifold 90 located near secondary mixing tube 64 but separated from tertiary mixing tube 76 by secondary mixing tube 64. Manifold 90 has holes 98 to direct fuel to tertiary air intake device 84 through secondary air intake device 72. Changes in fuel pressure make fuel flow into secondary air intake device 72 or into tertiary air intake device 84. EFFECT: reduced toxicity of exhaust gases. 17 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS-TURBINE COMBUSTION CHAMBER AND GAS-TURBINE ENGINE FUEL INJECTOR | 1995 |
|
RU2135898C1 |
| AIR ENGINE DESIGN | 2004 |
|
RU2355902C2 |
| SOLID-STATE OXIDE FUEL CELL SYSTEM | 2003 |
|
RU2316083C2 |
| FUEL ELEMENT OF GAS TURBINE ENGINE COMBUSTION CHAMBER (VERSIONS), GAS TURBINE ENGINE AND METHOD OF ITS FUNCTIONING | 2007 |
|
RU2433348C2 |
| DUCT BURNING BYPASS ENGINE WITH PROTECTIVE SCREEN FOR NOZZLE RING FUEL MANIFOLD, NOZZLE RING AND PROTECTIVE SCREEN | 2005 |
|
RU2382895C2 |
| INJECTION SYSTEM OF AIR MIXED WITH FUEL TO COMBUSTION CHAMBER OF GAS TURBINE ENGINE | 2008 |
|
RU2478878C2 |
| POWER-GENERATING SYSTEM WITH RING COMBUSTION CHAMBER | 1997 |
|
RU2243383C2 |
| FUEL INJECTOR FOR TURBOMACHINE | 2013 |
|
RU2616141C2 |
| METHOD OF MELTING OF THE GLASS-FORMING MATERIAL IN THE GLASS MELTING FURNACE AND THE OXYFUEL BURNER | 2002 |
|
RU2288193C2 |
| GAS TURBINE ENGINE COMBUSTION CHAMBER AND GAS TURBINE ENGINE | 2007 |
|
RU2444680C2 |
