RU2014147840A - METHOD FOR REGULATING THE AIRCRAFT TURBOREACTIVE ENGINE - Google Patents
METHOD FOR REGULATING THE AIRCRAFT TURBOREACTIVE ENGINE Download PDFInfo
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- RU2014147840A RU2014147840A RU2014147840A RU2014147840A RU2014147840A RU 2014147840 A RU2014147840 A RU 2014147840A RU 2014147840 A RU2014147840 A RU 2014147840A RU 2014147840 A RU2014147840 A RU 2014147840A RU 2014147840 A RU2014147840 A RU 2014147840A
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- RU
- Russia
- Prior art keywords
- pressure
- engine
- maximum
- value
- combustion chamber
- Prior art date
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- 238000000034 method Methods 0.000 title claims abstract 3
- 230000001105 regulatory effect Effects 0.000 title claims abstract 3
- 238000002485 combustion reaction Methods 0.000 claims abstract 8
- 230000003466 anti-cipated effect Effects 0.000 claims 2
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- Control Of Turbines (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
Способ регулирования авиационного турбореактивного двигателя, включающий эксплуатационные ограничения максимальных значений частот вращения роторов низкого и высокого давления и температуры газов на максимальном режиме работы двигателя, отличающийся тем, что дополнительно ограничивают максимальное значение давления в камере сгорания до P, величину которого определяют для каждого конкретного двигателя по значению полного давления за компрессором, измеренного при стендовых испытаниях двигателя в реальных атмосферных условиях, для чего предварительно устанавливают значение давления Pниже значения полного давления за компрессором на максимальном режиме, выводят двигатель по частоте вращения с режима малого газа до наступления ограничения режима работы двигателя до P, измеряют при этом режиме полное давление за компрессором P*и давление в камере сгорания P, а величину ограничения максимального значения давления в камере сгорания определяют по следующей зависимости:P=P+(P-P*),где P- предельно допустимое значение давления в камере сгорания.A method for regulating an aircraft turbojet engine, including operational restrictions on the maximum rotational speeds of low and high pressure rotors and gas temperatures at maximum engine operation, characterized in that they further limit the maximum pressure in the combustion chamber to P, the value of which is determined for each specific engine by the value of the total pressure behind the compressor, measured during bench tests of the engine in real atmospheric conditions, for whereupon the pressure value P is preliminarily set lower than the total pressure behind the compressor at maximum mode, the engine is driven out from the idle speed until the engine is limited to P, the total pressure behind the compressor P * and the pressure in the combustion chamber P are measured, and the limit value of the maximum pressure in the combustion chamber is determined by the following relationship: P = P + (PP *), where P is the maximum permissible pressure in the combustion chamber.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2014147840/06A RU2592360C2 (en) | 2014-11-27 | 2014-11-27 | Aircraft turbojet engine control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2014147840/06A RU2592360C2 (en) | 2014-11-27 | 2014-11-27 | Aircraft turbojet engine control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2014147840A true RU2014147840A (en) | 2016-06-20 |
| RU2592360C2 RU2592360C2 (en) | 2016-07-20 |
Family
ID=56131816
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2014147840/06A RU2592360C2 (en) | 2014-11-27 | 2014-11-27 | Aircraft turbojet engine control method |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2592360C2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2627628C1 (en) * | 2016-10-10 | 2017-08-09 | Публичное Акционерное Общество "Уфимское Моторостроительное Производственное Объединение" (Пао "Умпо") | Control method of aircraft jet turbine engine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2228977B (en) * | 1985-08-02 | 1990-11-21 | Lucas Ind Plc | Running control for a gas turbine engine |
| US5622042A (en) * | 1995-02-27 | 1997-04-22 | Compressor Controls Corporation | Method for predicting and using the exhaust gas temperatures for control of two and three shaft gas turbines |
| US6568166B2 (en) * | 2000-12-22 | 2003-05-27 | Pratt & Whitney Canada Corp. | Back-up control apparatus for turbo machine |
| RU2221929C1 (en) * | 2002-11-10 | 2004-01-20 | ОАО "КБ Электроприбор" | Gas-turbine engine parameters automatic control system |
| RU27842U1 (en) * | 2002-11-11 | 2003-02-20 | ОАО "КБ Электроприбор" | SYSTEM OF AUTOMATIC REGULATION OF PARAMETERS OF A GAS TURBINE ENGINE (GTE) |
-
2014
- 2014-11-27 RU RU2014147840/06A patent/RU2592360C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2592360C2 (en) | 2016-07-20 |
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