RU2008128585A - METHOD FOR DEBUGGING A GAS TURBINE ENGINE WITH AN AFTER CHAMBER - Google Patents
METHOD FOR DEBUGGING A GAS TURBINE ENGINE WITH AN AFTER CHAMBER Download PDFInfo
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- RU2008128585A RU2008128585A RU2008128585/06A RU2008128585A RU2008128585A RU 2008128585 A RU2008128585 A RU 2008128585A RU 2008128585/06 A RU2008128585/06 A RU 2008128585/06A RU 2008128585 A RU2008128585 A RU 2008128585A RU 2008128585 A RU2008128585 A RU 2008128585A
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- RU
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- afterburner
- jet nozzle
- area
- debugging
- temperature
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- Control Of Turbines (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
1. Способ отладки газотурбинного двигателя с форсажной камерой путем отладки расхода топлива в форсажную камеру, включающий измерение температуры газов, размеров проходного сечения реактивного сопла, отличающийся тем, что измеряют температуру газа за турбиной и размер проходного сечения реактивного сопла на бесфорсажном режиме работы двигателя, определяют по ним потребное значение площади реактивного сопла на форсажном режиме, и отлаживают расход топлива в форсажную камеру воздействием на расход топлива в форсажную камеру до тех пор, пока проходная площадь сопла не сравняется с потребной, при этом потребное значение площади реактивного сопла определяют по формуле , где Fгф и Fгм - площади реактивного сопла на форсажном и бесфорсажном режимах соответственно, Тт и Тфзад - замеренное и заданное значение температуры газа за турбиной, а форсажный и бесфорсажный режимы осуществляют при одинаковом режиме работы турбокомпрессора газотурбинного двигателя. ! 2. Способ по п.1, отличающийся тем, что при отладке двухконтурных газотурбинных двигателей потребное значение площади реактивного сопла определяют по формуле , где Tсм - температура газов за турбиной после смешения обоих потоков.1. The method of debugging a gas turbine engine with an afterburner by debugging fuel consumption in the afterburner, including measuring the temperature of the gases, the size of the orifice of the jet nozzle, characterized in that they measure the temperature of the gas behind the turbine and the size of the orifice of the jet nozzle at the afterburner engine operation mode, determine on them the required value of the area of the jet nozzle in the afterburner mode, and debug the fuel consumption in the afterburner by affecting the fuel consumption in the afterburner until until the nozzle passage area is equal to the required one, while the required value of the jet nozzle area is determined by the formula, where Fgf and Fgm are the area of the jet nozzle in the afterburner and afterburner modes, respectively, Tm and Tfzad are the measured and set gas temperature behind the turbine, and the afterburner and afterburner modes are carried out with the same mode of operation of a turbocharger of a gas turbine engine. ! 2. The method according to claim 1, characterized in that when debugging dual-circuit gas turbine engines, the required value of the area of the jet nozzle is determined by the formula, where Tcm is the temperature of the gases behind the turbine after mixing both flows.
Claims (2)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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RU2008128585/06A RU2383001C1 (en) | 2008-07-15 | 2008-07-15 | Method of debugging of gas turbine engine with afterburner |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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RU2008128585/06A RU2383001C1 (en) | 2008-07-15 | 2008-07-15 | Method of debugging of gas turbine engine with afterburner |
Publications (2)
Publication Number | Publication Date |
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RU2008128585A true RU2008128585A (en) | 2010-01-20 |
RU2383001C1 RU2383001C1 (en) | 2010-02-27 |
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RU2008128585/06A RU2383001C1 (en) | 2008-07-15 | 2008-07-15 | Method of debugging of gas turbine engine with afterburner |
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RU (1) | RU2383001C1 (en) |
Cited By (2)
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CN110728048A (en) * | 2019-10-08 | 2020-01-24 | 中国航发沈阳发动机研究所 | Method and device for judging success of boosting ignition |
CN111751100A (en) * | 2020-06-30 | 2020-10-09 | 中国航发动力股份有限公司 | Engine nozzle machining, installing and debugging method |
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RU2443890C1 (en) * | 2010-09-30 | 2012-02-27 | Федеральное государственное унитарное предприятие "Научно-производственный центр газотурбостроения "Салют" (ФГУП "НПЦ газотурбостроения "Салют") | Method of controlling critical section area of two-stage gas turbine engine jet nozzle |
RU2466287C1 (en) * | 2011-05-19 | 2012-11-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Control method of gas-turbine engine with afterburner, and system used for its implementation |
RU2493391C1 (en) * | 2012-04-04 | 2013-09-20 | Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" | Method of gas turbine engine adjustment after renewal at test bench |
CN105486511B (en) * | 2015-12-30 | 2018-01-16 | 北京航天三发高科技有限公司 | A kind of adjustment method of test bay state parameter |
RU2755450C1 (en) * | 2020-08-10 | 2021-09-16 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Method for providing strength of turbine of gas turbine engine |
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2008
- 2008-07-15 RU RU2008128585/06A patent/RU2383001C1/en not_active IP Right Cessation
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110728048A (en) * | 2019-10-08 | 2020-01-24 | 中国航发沈阳发动机研究所 | Method and device for judging success of boosting ignition |
CN110728048B (en) * | 2019-10-08 | 2023-10-20 | 中国航发沈阳发动机研究所 | Method and device for judging success of boosting ignition |
CN111751100A (en) * | 2020-06-30 | 2020-10-09 | 中国航发动力股份有限公司 | Engine nozzle machining, installing and debugging method |
Also Published As
Publication number | Publication date |
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RU2383001C1 (en) | 2010-02-27 |
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MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20140716 |