FIELD: gas-turbine engine combustion chambers.
SUBSTANCE: proposed combustion chamber includes flame tubes located in air cavity between outer and inner casings; cooling cavities of flame tubes are diverging from inlet to outlet at ratio of cavity height at inlet H to cavity height at outlet h H/h=1.4-2.0. Radial fin on side of inlet to cooling cavity has thickened portion T relative to thickness t of flame tube wall between cooling cavities T/t=1.3-2.1. Angle between peripheral surface of cooling cavity and inner surface of flame tube wall between cooling cavities is α=8-12°. Ratio of diameter d of holes supplying air to cooling cavity to thickness t of flame tube wall is equal to d/t=0.7-1.4.
EFFECT: enhanced reliability; improved construction of combustion chamber.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ANNULAR COMBUSTION CHAMBER OF GAS TURBINE ENGINE | 2023 |
|
RU2817578C1 |
| COMBUSTION LINER OF GAS-TURBINE ENGINE | 2006 |
|
RU2343355C2 |
| GAS-TURBINE ENGINE COMBUSTION CHAMBER | 1999 |
|
RU2173818C2 |
| FLAME TUBE OF COMBUSTION CHAMBER OF GAS TURBINE ENGINES DN80 AND DU80 | 2023 |
|
RU2805719C1 |
| TUBULAR-ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 2001 |
|
RU2211409C2 |
| GAS TURBINE ENGINE | 2013 |
|
RU2525385C1 |
| TUBULAR ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 2005 |
|
RU2300706C2 |
| POWER PLANT GAS TURBINE COMBUSTION CHAMBER | 1995 |
|
RU2098719C1 |
| GAS-TURBINE ENGINE SPARK PLUG | 1996 |
|
RU2130222C1 |
| FLAME TUBE FOR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 1987 |
|
SU1454021A1 |
