FIELD: mechanical engineering; gas-turbine engines. SUBSTANCE: proposed combustion chamber of gas-turbine engine contains at least one igniter whose working space communicates through branch pipes with flue tube. At least one pair of additional spaces is made in igniter housing. First space accommodates main explosive charge with free end face surface. Second space accommodates additional explosive charge and electric igniter with switch-on unit connected to engine electric circuit. First space communicates with working space of igniter through channel in which burst diaphragm is installed. Second space communicates with first space through channel whose axis is pointed to center of free end face surface of main charge. EFFECT: provision of reliable starting of combustion chamber of gas- turbine engine after long period of idling, especially under heavy conditions. 2 cl, 2 dwg
Title | Year | Author | Number |
---|---|---|---|
COMBUSTION CHAMBER IGNITER | 2003 |
|
RU2245447C1 |
RING COMBUSTION CHAMBER FOR GAS-TURBINE ENGINE | 2004 |
|
RU2280814C1 |
GAS-TURBINE ENGINE AFTERBURNER | 2002 |
|
RU2218471C1 |
COMBUSTION CHAMBER FOR GAS-TURBINE ENGINE | 2004 |
|
RU2277676C1 |
GAS-TURBINE PLANT | 2001 |
|
RU2181163C1 |
IGNITER | 1994 |
|
RU2103610C1 |
AIRCRAFT GAS-TURBINE ENGINE BEARING SUPPORT COOLING SYSTEM | 2002 |
|
RU2213875C1 |
FLAME TUBE FOR ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 2003 |
|
RU2238477C1 |
METHOD FOR MANUFACTURING FLAME TUBE OF AIRCRAFT GAS-TURBINE ENGINE COMBUSTION CHAMBER | 2004 |
|
RU2258869C1 |
AIRCRAFT GAS-TURBINE ENGINE COMBUSTION CHAMBER BURNER UNIT | 2002 |
|
RU2212588C1 |
Authors
Dates
2003-10-20—Published
2002-08-22—Filed