RU2011104120A - METHOD FOR FIRING A COMBUSTION CHAMBER OF AIRCRAFT GAS TURBINE ENGINES - Google Patents
METHOD FOR FIRING A COMBUSTION CHAMBER OF AIRCRAFT GAS TURBINE ENGINES Download PDFInfo
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- RU2011104120A RU2011104120A RU2011104120/06A RU2011104120A RU2011104120A RU 2011104120 A RU2011104120 A RU 2011104120A RU 2011104120/06 A RU2011104120/06 A RU 2011104120/06A RU 2011104120 A RU2011104120 A RU 2011104120A RU 2011104120 A RU2011104120 A RU 2011104120A
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- air
- spark plug
- combustion chamber
- special sleeve
- working end
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Abstract
Способ розжига камер сгорания авиационных двигателей, заключающийся в том, что воздух от компрессора подают в камеру сгорания, из вторичного контура камеры сгорания воздух подают в зазор, образованный между свечой зажигания и специальной втулкой, установленной между наружным корпусом камеры сгорания и корпусом жаровой трубы, воздух из зазора между специальной втулкой и свечой зажигания подают во внутренний объем жаровой трубы параллельно оси свечи через рабочий торец специальной втулки, создают электрический разряд на рабочем торце свечи зажигания, подают на рабочий торец свечи топливо, распыляемое форсункой, отличающийся тем, что воздух из зазора между специальной втулкой и свечой зажигания подают во внутренний объем жаровой трубы только с одной стороны рабочего торца специальной втулки, обращенной к турбине двигателя, перпендикулярно движению топливовоздушной смеси в зоне расположения свечи зажигания. The method of ignition of the combustion chambers of aircraft engines, namely, that the air from the compressor is supplied to the combustion chamber, from the secondary circuit of the combustion chamber, air is fed into the gap formed between the spark plug and a special sleeve installed between the outer casing of the combustion chamber and the flame tube casing, air from the gap between the special sleeve and the spark plug is fed into the inner volume of the flame tube parallel to the axis of the candle through the working end of the special sleeve, create an electrical discharge at the working end with ignition channels, fuel sprayed by the nozzle is supplied to the working end of the spark plug, characterized in that the air from the gap between the special sleeve and the spark plug is fed into the internal volume of the flame tube from only one side of the working end of the special sleeve facing the engine turbine, perpendicular to the movement of the air-fuel mixture in the area of the spark plug.
Claims (1)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011104120/06A RU2460895C1 (en) | 2011-02-04 | 2011-02-04 | Method of igniting aircraft gas turbine combustion chamber |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011104120/06A RU2460895C1 (en) | 2011-02-04 | 2011-02-04 | Method of igniting aircraft gas turbine combustion chamber |
Publications (2)
Publication Number | Publication Date |
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RU2011104120A true RU2011104120A (en) | 2012-08-10 |
RU2460895C1 RU2460895C1 (en) | 2012-09-10 |
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Family Applications (1)
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RU2011104120/06A RU2460895C1 (en) | 2011-02-04 | 2011-02-04 | Method of igniting aircraft gas turbine combustion chamber |
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RU (1) | RU2460895C1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104028525A (en) * | 2014-05-27 | 2014-09-10 | 楚天科技股份有限公司 | Feeding system of rubber plug cleaning machine |
CN113669161A (en) * | 2021-08-24 | 2021-11-19 | 中国航发贵阳发动机设计研究所 | Igniter with oxygen supplementing structure |
CN113669162A (en) * | 2021-08-31 | 2021-11-19 | 中国航发贵阳发动机设计研究所 | Electric nozzle bush with cooling structure |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3011037B1 (en) * | 2013-09-26 | 2015-10-02 | Turbomeca | HIGH ENERGY GENERATOR WITH DOUBLE CHANNEL |
RU2738223C1 (en) * | 2020-03-12 | 2020-12-09 | Акционерное общество "Уфимское научно-производственное предприятие "Молния" | Ignition method of combustion chamber of aircraft gas turbine engines |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE464278A (en) * | 1942-03-11 | |||
DE2831442A1 (en) * | 1978-07-18 | 1980-01-31 | Bosch Gmbh Robert | INTERNAL COMBUSTION ENGINE WITH A MAIN COMBUSTION CHAMBER AND ITS COMPLETED IGNITION CHAMBER WITH IGNITION DEVICE |
RU2136094C1 (en) * | 1996-06-04 | 1999-08-27 | Акционерное общество "Авиадвигатель" | Spark plug |
RU2130222C1 (en) * | 1996-07-29 | 1999-05-10 | Акционерное общество "Авиадвигатель" | Gas-turbine engine spark plug |
RU2215348C2 (en) * | 2001-12-06 | 2003-10-27 | Открытое акционерное общество "Авиадвигатель" | Gas-turbine engine spark plug |
-
2011
- 2011-02-04 RU RU2011104120/06A patent/RU2460895C1/en active
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104028525A (en) * | 2014-05-27 | 2014-09-10 | 楚天科技股份有限公司 | Feeding system of rubber plug cleaning machine |
CN113669161A (en) * | 2021-08-24 | 2021-11-19 | 中国航发贵阳发动机设计研究所 | Igniter with oxygen supplementing structure |
CN113669162A (en) * | 2021-08-31 | 2021-11-19 | 中国航发贵阳发动机设计研究所 | Electric nozzle bush with cooling structure |
Also Published As
Publication number | Publication date |
---|---|
RU2460895C1 (en) | 2012-09-10 |
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