RU2015137946A - The method of operation of a gas turbine engine - Google Patents

The method of operation of a gas turbine engine Download PDF

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Publication number
RU2015137946A
RU2015137946A RU2015137946A RU2015137946A RU2015137946A RU 2015137946 A RU2015137946 A RU 2015137946A RU 2015137946 A RU2015137946 A RU 2015137946A RU 2015137946 A RU2015137946 A RU 2015137946A RU 2015137946 A RU2015137946 A RU 2015137946A
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RU
Russia
Prior art keywords
pressure
rotor speed
gas
measurements
engine
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RU2015137946A
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Russian (ru)
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RU2612663C9 (en
RU2612663C1 (en
Inventor
Юрий Николаевич Балабан
Виктор Викторович Куприн
Иван Александрович Хотеенков
Original Assignee
Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО"
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Priority to RU2015137946A priority Critical patent/RU2612663C9/en
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Publication of RU2612663C1 publication Critical patent/RU2612663C1/en
Publication of RU2015137946A publication Critical patent/RU2015137946A/en
Publication of RU2612663C9 publication Critical patent/RU2612663C9/en

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Claims (1)

Способ эксплуатации газотурбинного двигателя, включающий определение в начале эксплуатации при проведении приемо-сдаточных испытаний исходных значений температуры газа за турбиной, давления газа и частоты вращения ротора и определение допустимых пороговых отклонений от исходных значений, а при эксплуатации периодическое измерение параметров температуры, давления и частоты вращения ротора двигателя, сравнивание измеряемых и исходных значений и регулирование частоты вращения ротора или его остановку в зависимости от результатов сравнивания измерений и пороговых отклонений, отличающийся тем, что давление газа измеряют за компрессором, в качестве параметра сравнения используют давление и частоту вращения ротора, измерения производят при постоянной температуре газа за турбиной через промежутки времени 0,2…0,5 с, а сравнивание измерений и определение пороговых отклонений производят, по крайней мере, по двум предшествующим и двум последующим текущим значениям параметров, а остановку двигателя производят при снижении частоты вращения ротора на 0,2…0,5% и давления за компрессором на 1,0…1,5%. A method of operating a gas turbine engine, including determining at the beginning of operation during acceptance tests the initial values of the gas temperature behind the turbine, gas pressure and rotor speed and determining acceptable threshold deviations from the initial values, and during operation, periodically measuring temperature, pressure and speed rotor of the engine, comparing the measured and initial values and regulating the rotor speed or stopping it depending on the results of measurement measurements and threshold deviations, characterized in that the gas pressure is measured behind the compressor, the pressure and rotor speed are used as a comparison parameter, measurements are made at a constant gas temperature behind the turbine at time intervals of 0.2 ... 0.5 s, and measurements are compared and determination of threshold deviations is carried out according to at least two previous and two subsequent current parameter values, and the engine is stopped when the rotor speed is reduced by 0.2 ... 0.5% and the pressure per computer spring by 1.0 ... 1.5%.
RU2015137946A 2015-09-07 2015-09-07 Gas turbine engine operation RU2612663C9 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2015137946A RU2612663C9 (en) 2015-09-07 2015-09-07 Gas turbine engine operation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2015137946A RU2612663C9 (en) 2015-09-07 2015-09-07 Gas turbine engine operation

Publications (3)

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RU2612663C1 RU2612663C1 (en) 2017-03-13
RU2015137946A true RU2015137946A (en) 2017-03-13
RU2612663C9 RU2612663C9 (en) 2017-06-09

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Application Number Title Priority Date Filing Date
RU2015137946A RU2612663C9 (en) 2015-09-07 2015-09-07 Gas turbine engine operation

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Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2118810C1 (en) * 1996-05-07 1998-09-10 Казанский государственный технический университет им.А.Н.Туполева Method of diagnostics of technical state of aircraft gas turbine jet engines
RU2168163C1 (en) * 1999-12-16 2001-05-27 Открытое акционерное общество "А.Люлька-Сатурн" Method of operation of turbofan engine by its technical condition
RU2308014C2 (en) * 2005-08-16 2007-10-10 Открытое акционерное общество Конструкторское-производственное предприятие "Авиамотор" Method of operating the engine
US7966804B2 (en) * 2006-07-12 2011-06-28 General Electric Company Method and apparatus for testing gas turbine engines
US8510060B2 (en) * 2010-06-07 2013-08-13 General Electric Company Life management system and method for gas turbine thermal barrier coatings
RU2484441C1 (en) * 2012-04-12 2013-06-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Gas-turbine engine, test method of gas-turbine engine, production method of batch of gas-turbine engines (versions), and operating method of gas-turbine engine

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Publication number Publication date
RU2612663C9 (en) 2017-06-09
RU2612663C1 (en) 2017-03-13

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