RU2011112840A - METHOD FOR STARTING AN AIRCRAFT GAS TURBINE ENGINE - Google Patents
METHOD FOR STARTING AN AIRCRAFT GAS TURBINE ENGINE Download PDFInfo
- Publication number
- RU2011112840A RU2011112840A RU2011112840/06A RU2011112840A RU2011112840A RU 2011112840 A RU2011112840 A RU 2011112840A RU 2011112840/06 A RU2011112840/06 A RU 2011112840/06A RU 2011112840 A RU2011112840 A RU 2011112840A RU 2011112840 A RU2011112840 A RU 2011112840A
- Authority
- RU
- Russia
- Prior art keywords
- engine
- combustion chamber
- starting
- gas turbine
- limit value
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract 3
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 1
- 238000002485 combustion reaction Methods 0.000 claims abstract 6
- 239000000446 fuel Substances 0.000 claims abstract 2
- 238000009987 spinning Methods 0.000 claims abstract 2
Landscapes
- Control Of Turbines (AREA)
- Supercharger (AREA)
Abstract
Способ запуска авиационного газотурбинного двигателя, включающий раскрутку ротора двигателя до частоты вращения ротора необходимой для розжига камеры сгорания, розжиг камеры сгорания и выход на режим малого газа с поддержанием при этом предельного значения параметра работы двигателя, который выбирают заранее, отличающийся тем, что в качестве поддерживаемого параметра работы двигателя выбирают Т4mах, а для поддержания предельного значения Т4mах изменяют расход воздуха через двигатель или (и) расход топлива в камеру сгорания, где Т4mах - максимально допустимая температура газа за турбиной. A method of starting an aircraft gas turbine engine, including spinning up the engine rotor to the rotor speed necessary to ignite the combustion chamber, igniting the combustion chamber and entering the idle mode while maintaining the limit value of the engine operation parameter, which is selected in advance, characterized in that it is the engine operation parameter is selected T4max, and to maintain the limit value T4max, the air flow through the engine or (and) the fuel flow to the combustion chamber is changed, where T4max is m ksimalno permissible gas temperature of the turbine.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2011112840/06A RU2472958C2 (en) | 2011-04-05 | 2011-04-05 | Method of starting aircraft gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2011112840/06A RU2472958C2 (en) | 2011-04-05 | 2011-04-05 | Method of starting aircraft gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2011112840A true RU2011112840A (en) | 2012-10-10 |
| RU2472958C2 RU2472958C2 (en) | 2013-01-20 |
Family
ID=47079198
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2011112840/06A RU2472958C2 (en) | 2011-04-05 | 2011-04-05 | Method of starting aircraft gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2472958C2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2607113C2 (en) * | 2014-11-25 | 2017-01-10 | Общество с ограниченной ответственностью "Газпром трансгаз Казань" | Gas pumping unit and method of its start-up |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3520133A (en) * | 1968-03-14 | 1970-07-14 | Gen Electric | Gas turbine control system |
| JPS5069415A (en) * | 1973-10-23 | 1975-06-10 | ||
| SU585303A1 (en) * | 1976-08-02 | 1977-12-25 | Всесоюзный Дважды Ордена Трудового Красного Знамени Научно-Исследовательский Теплотехнический Институт Имени Ф.Э.Дзержинского | Method of feeding coolant to gas turbine plant blading |
| RU2209990C1 (en) * | 2002-06-10 | 2003-08-10 | ОАО "Омское машиностроительное конструкторское бюро" | Jet engine automatic control system |
| RU2260134C1 (en) * | 2003-11-28 | 2005-09-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Gas-turbine engine starting method |
-
2011
- 2011-04-05 RU RU2011112840/06A patent/RU2472958C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2472958C2 (en) | 2013-01-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PC41 | Official registration of the transfer of exclusive right |
Effective date: 20130926 |
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| PD4A | Correction of name of patent owner |