RU2006100531A - METHOD FOR PROTECTING A GAS TURBINE ENGINE FROM THE ORIGIN OF UNSTABLE COMPRESSOR OPERATION - Google Patents

METHOD FOR PROTECTING A GAS TURBINE ENGINE FROM THE ORIGIN OF UNSTABLE COMPRESSOR OPERATION Download PDF

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Publication number
RU2006100531A
RU2006100531A RU2006100531/06A RU2006100531A RU2006100531A RU 2006100531 A RU2006100531 A RU 2006100531A RU 2006100531/06 A RU2006100531/06 A RU 2006100531/06A RU 2006100531 A RU2006100531 A RU 2006100531A RU 2006100531 A RU2006100531 A RU 2006100531A
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Russia
Prior art keywords
compressor
protecting
air pressure
turn
origin
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RU2006100531/06A
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Russian (ru)
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RU2310100C2 (en
Inventor
Алексей Николаевич Саженков (RU)
Алексей Николаевич Саженков
Юрий Семенович Савенков (RU)
Юрий Семенович Савенков
Юрий Иванович Тимкин (RU)
Юрий Иванович Тимкин
Юрий Абрамович Трубников (RU)
Юрий Абрамович Трубников
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Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
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Priority to RU2006100531/06A priority Critical patent/RU2310100C2/en
Publication of RU2006100531A publication Critical patent/RU2006100531A/en
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Publication of RU2310100C2 publication Critical patent/RU2310100C2/en

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Claims (1)

Способ защиты двигателя от возникновения неустойчивой работы компрессора, включающий измерение давления воздуха за компрессором, определение скорости изменения этого давления, сравнение с ее пороговым значением, и при его превышении формирование сигнала на выключение подачи топлива в камеру сгорания и включение перепуска воздуха в компрессоре, отличающийся тем, что дополнительно измеряют давление воздуха на входе в двигатель Рвх*, частоту вращения ротора высокого давления n вд, по измеренному значению n вд определяют ее первую производную
Figure 00000001
вд и при последующем снижении скорости изменения давления воздуха за компрессором ниже ее порогового значения формируют сигнал на включение подачи топлива в камеру сгорания, причем дозирование топлива производится по закону управления приемистостью
Figure 00000001
вд/Рвх*=const.A method of protecting the engine from the occurrence of unstable operation of the compressor, including measuring the air pressure behind the compressor, determining the rate of change of this pressure, comparing with its threshold value, and when it is exceeded, generating a signal to turn off the fuel supply to the combustion chamber and turn on the air bypass in the compressor, characterized in further measured air pressure at the engine inlet Pjn *, high pressure rotor speed n tm, the measured value of n tm determine its first mfr dnuyu
Figure 00000001
air pressure and with a subsequent decrease in the rate of change of air pressure behind the compressor below its threshold value, a signal is generated to turn on the fuel supply to the combustion chamber, and the fuel is dosed according to the law of injectivity control
Figure 00000001
vd / Pvh * = const.
RU2006100531/06A 2006-01-10 2006-01-10 Method to protect gas-turbine engine from unstable operation of compressor RU2310100C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2006100531/06A RU2310100C2 (en) 2006-01-10 2006-01-10 Method to protect gas-turbine engine from unstable operation of compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2006100531/06A RU2310100C2 (en) 2006-01-10 2006-01-10 Method to protect gas-turbine engine from unstable operation of compressor

Publications (2)

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RU2006100531A true RU2006100531A (en) 2007-07-20
RU2310100C2 RU2310100C2 (en) 2007-11-10

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RU2006100531/06A RU2310100C2 (en) 2006-01-10 2006-01-10 Method to protect gas-turbine engine from unstable operation of compressor

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Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2972233B1 (en) * 2011-03-04 2017-10-20 Snecma METHOD FOR REMOVING ROTATING DECOLUTION IN TURBOMACHINE
FR3063782B1 (en) * 2017-03-07 2021-06-18 Safran Aircraft Engines METHOD AND DEVICE FOR DETECTION OF CONDITIONS FRIENDLY TO THE APPEARANCE OF PUMPING WITH A VIEW TO PROTECTING A COMPRESSOR OF AN AIRCRAFT TURBOMACHINE

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