RU2011106384A - METHOD FOR CONTROL TURBOREACTIVE DOUBLE-CIRCUIT ENGINE WITH FORCING CHAMBER - Google Patents
METHOD FOR CONTROL TURBOREACTIVE DOUBLE-CIRCUIT ENGINE WITH FORCING CHAMBER Download PDFInfo
- Publication number
- RU2011106384A RU2011106384A RU2011106384/06A RU2011106384A RU2011106384A RU 2011106384 A RU2011106384 A RU 2011106384A RU 2011106384/06 A RU2011106384/06 A RU 2011106384/06A RU 2011106384 A RU2011106384 A RU 2011106384A RU 2011106384 A RU2011106384 A RU 2011106384A
- Authority
- RU
- Russia
- Prior art keywords
- characterizing
- control
- engine
- afterburner
- fuel consumption
- Prior art date
Links
Landscapes
- Control Of Turbines (AREA)
Abstract
Способ управления турбореактивным двухконтурным двигателем с форсажной камерой (ТРДДФ), при котором на основании, по меньшей мере, одной управляющей величины и, по меньшей мере, одной измеряемой величины, характеризующей режим работы турбокомпрессорной части двигателя, с помощью математической модели определяют величину, характеризующую, по меньшей мере, управляющий сигнал, подаваемый на исполнительный орган, отличающийся тем, что на форсированных режимах в качестве измеряемых величин используют расход топлива (Gтокс), характеризующий расход топлива в основную камеру сгорания (ОКС), частоту вращения (nв), характеризующую частоту вращения вала низкого давления, давление , характеризующее текущее полное давление воздуха за компрессором, в качестве управляющей величины используют температуру , характеризующую полную температуру воздуха на входе в двигатель, и угол (αруд), характеризующий положение рычага управления двигателем (РУД); в качестве величины, характеризующей управляющий сигнал, используют расход топлива Gтф, подаваемый в форсажную камеру сгорания на форсированных режимах, который определяют в соответствии программой по закону , и подают для воздействия на исполнительный орган, определяющий топливоподачу в форсажную камеру сгорания. A control method for a turbojet dual-circuit engine with an afterburner (TRDDF), in which, based on at least one control quantity and at least one measured quantity characterizing the operation mode of the turbocompressor part of the engine, a quantity characterizing at least a control signal supplied to the actuator, characterized in that in forced modes, fuel consumption (Gtox), which characterizes fuel consumption in the main combustion chamber (ACS), rotational speed (nv) characterizing the rotational speed of the low-pressure shaft, pressure characterizing the current total air pressure behind the compressor, the temperature characterizing the total air temperature at the engine inlet is used as a control quantity, and angle (αrud), characterizing the position of the engine control lever (ORE); as a quantity characterizing the control signal, the fuel consumption Gtf supplied to the afterburner in forced mode, which is determined in accordance with the program according to the law, is used and applied to the actuator that determines the fuel supply to the afterburner.
Claims (1)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011106384/06A RU2464437C1 (en) | 2011-02-22 | 2011-02-22 | Control method of jet turbine double-flow engine with afterburner |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011106384/06A RU2464437C1 (en) | 2011-02-22 | 2011-02-22 | Control method of jet turbine double-flow engine with afterburner |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2011106384A true RU2011106384A (en) | 2012-08-27 |
RU2464437C1 RU2464437C1 (en) | 2012-10-20 |
Family
ID=46937335
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2011106384/06A RU2464437C1 (en) | 2011-02-22 | 2011-02-22 | Control method of jet turbine double-flow engine with afterburner |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU2464437C1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2540204C2 (en) * | 2013-05-23 | 2015-02-10 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Electrically driven pump |
RU2578780C1 (en) * | 2015-01-20 | 2016-03-27 | Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО УМПО | Aircraft turbojet engine control method |
RU2726966C1 (en) * | 2019-07-30 | 2020-07-20 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" | Method for controlling fuel flow into afterburner combustion chamber of by-pass engine |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2063532C1 (en) * | 1988-03-01 | 1996-07-10 | Харьковский авиационный институт им.Н.Е.Жуковского | Method of supply of fuel to afterburning gas-turbine engines and device for its realization |
US7475545B2 (en) * | 2005-04-29 | 2009-01-13 | General Electric Company | Fladed supersonic missile turbojet |
RU2387857C2 (en) * | 2008-06-30 | 2010-04-27 | Открытое акционерное общество "СТАР" | Method control operation of aircraft gas turbine engine with afterburner |
RU2435969C2 (en) * | 2009-01-29 | 2011-12-10 | Открытое акционерное общество "СТАР" | Control method of gas turbine engine with afterburner |
RU2442001C2 (en) * | 2009-03-05 | 2012-02-10 | Открытое акционерное общество "СТАР" | Control method gas-turbine engine with afterburner |
-
2011
- 2011-02-22 RU RU2011106384/06A patent/RU2464437C1/en active
Also Published As
Publication number | Publication date |
---|---|
RU2464437C1 (en) | 2012-10-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP6248993B2 (en) | Control device for internal combustion engine | |
JP5389238B1 (en) | Waste gate valve control device for internal combustion engine | |
US9869239B2 (en) | Wastegate valve control device | |
BRPI0602953A (en) | method and device for controlling the turbo supercharger rotation speed in an internal combustion engine | |
EP2600063A3 (en) | Method of operating a gas turbine with staged and/or sequential combustion | |
RU2011106384A (en) | METHOD FOR CONTROL TURBOREACTIVE DOUBLE-CIRCUIT ENGINE WITH FORCING CHAMBER | |
US20150354443A1 (en) | Engine control system with variable turbocharger and method thereof | |
US10227938B2 (en) | Method and system for controlling supercharger of vehicle | |
CN105240109A (en) | Condensation control system for engine | |
RU2009107249A (en) | METHOD FOR FUEL CONSUMPTION CONTROL TO FORCING COMBUSTION CHAMBER OF A GAS TURBINE ENGINE | |
RU2008103208A (en) | METHOD FOR GAS-TURBINE ENGINE CONTROL | |
CN110446837A (en) | System and its application method including electric auxiliary turbine pressurizer | |
BRPI0900249A2 (en) | internal combustion engine controller | |
CN110318864B (en) | Altitude-based two-stage supercharging system opening correction method and two-stage supercharging system | |
RU2008126612A (en) | METHOD FOR GAS-TURBINE ENGINE CONTROL WITH FORCING COMBUSTION CHAMBER | |
US10260405B2 (en) | Fuel injection control of a turbocharged internal combustion engine | |
CN106032774B (en) | The control method and device of engine management system | |
RU2009102885A (en) | METHOD FOR GAS-TURBINE ENGINE CONTROL WITH FORCING COMBUSTION CHAMBER | |
KR101382767B1 (en) | Device and method for adjusting air supply amount of engine having supercharger | |
JP6724510B2 (en) | Learning device | |
JP2013072300A (en) | Atmospheric pressure estimation control device and atmospheric pressure estimation method for internal combustion engine | |
CN204126718U (en) | Explosive motor | |
JP2010185302A (en) | Control device for internal combustion engine | |
CN108291492A (en) | Method for running internal combustion engine | |
RU2006100531A (en) | METHOD FOR PROTECTING A GAS TURBINE ENGINE FROM THE ORIGIN OF UNSTABLE COMPRESSOR OPERATION |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PC43 | Official registration of the transfer of the exclusive right without contract for inventions |
Effective date: 20210804 |