WO2019098880A1 - Multiple-manifold device for feeding fuel into a combustion chamber of a gas-turbine engine - Google Patents
Multiple-manifold device for feeding fuel into a combustion chamber of a gas-turbine engine Download PDFInfo
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- WO2019098880A1 WO2019098880A1 PCT/RU2018/000641 RU2018000641W WO2019098880A1 WO 2019098880 A1 WO2019098880 A1 WO 2019098880A1 RU 2018000641 W RU2018000641 W RU 2018000641W WO 2019098880 A1 WO2019098880 A1 WO 2019098880A1
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- Prior art keywords
- fuel
- combustion chamber
- gas
- turbine engine
- manifolds
- Prior art date
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- 239000000446 fuel Substances 0.000 title claims abstract description 55
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 abstract description 2
- 238000005086 pumping Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
Definitions
- the invention relates to the field of operation of aircraft gas turbine engines (GTE) and can be used to control the supply of fuel to the manifolds of the main and / or afterburner combustion chambers of the GTE.
- GTE gas turbine engines
- a device for supplying fuel to the combustion chamber of a gas turbine engine which contains fuel lines, output channels to the I and II nozzles of the combustion chamber of the combustion chamber, a shut-off valve connected to a high pressure source and an outlet channel to the I collector, and a control valve that is connected to one side
- a shut-off valve connected to a high pressure source and an outlet channel to the I collector
- a control valve that is connected to one side
- the shut-off element of the shunt valve is installed with the possibility of connecting Nia I channel outputs in the collector output channel II in the collector
- the bypass valve control chamber is connected to the solenoid valve and through a nozzle to a source of constant pressure
- the disadvantage of this device is the lack of the possibility of a smooth increase in the mode of operation of the engine at launch due to the need to fill the second collector with fuel after opening the distribution valve. This leads to a stepwise start-up and, as a result, to an increase in the start-up time, reduces the reliability of the start-up and the service life of the starting devices.
- a device for supplying fuel to the combustion chamber of a gas turbine engine adopted as a prototype, containing a pumping unit, having a connection with a fuel tank with its input, is known.
- output - through the main fuel line through the distributor - with fuel dispensers to the combustion chamber manifolds is that at least one fuel manifold has a second input connected to the first additional fuel line with the output of the pumping unit, and an output connected to the second additional fuel line with the inlet of the pumping unit, with shut-off valves installed in the additional fuel lines, while the first additional fuel line can be equipped with a regulating valve torus of fuel pressure associated with the gas pressure sensor in the combustion chamber (Patent RU JVb 148619, IPC F02C9 / 26, published December 12, 2014)
- the disadvantage of this device is the presence of shut-off valves in additional lines through which the collectors are filled with non-dosed fuel, which complicates the fuel supply system into the combustion chamber, reduces its reliability.
- the fuel pressure upstream of the pump may be higher than the air pressure in the combustion chamber. In this case, the un-dosed fuel can flow into the injectors, which impairs the launch stability and reduces its reliability.
- the technical task of the invention is to simplify the design of the device fuel supply, improving the reliability of its work, improving the reliability of starting the engine on the ground and in flight.
- FIG. 1 shows a diagram of the device, where 1 is the metering unit, 2 is the fuel injectors, 3 is the first collector, 4 is the second collector, 5 is the additional connecting line, 6 is the nozzle, 7 is the third collector, 8 is the additional connecting line, 9 is the nozzle.
- the use of two or more collectors feeding the corresponding groups of fuel injectors makes it possible to more evenly distribute the fuel in the combustion chamber around the circumference during ignition and when the gas turbine engine reaches the low-gas mode. Ignition of the combustion chamber is carried out using the first (starting) collector. As the RPM rotor increases, subsequent collectors are connected. In order to avoid overfilling of the gas temperature before the turbine, a smooth connection of the secondary collectors is necessary. To solve this problem, an additional connecting line with a nozzle is installed between the previous and subsequent collectors. Pre-filling the collector is metered fuel through an additional line.
- the size of the nozzle is chosen in such a way as to ensure the filling of the manifold fuel to the injectors at a given rotation of the rotor of the ARC. This allows us to simplify the design of the fuel supply device, increase its reliability, and increase the stability of engine start on the ground and in flight.
- the proposed device allows for consistent metered filling of fuel collectors through connecting lines with jets, to increase the reliability of the fuel supply device and the reliability of the engine start process in ground and flight conditions.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to the field of operating aviation gas-turbine engines (GTEs) and can be used for controlling the feeding of fuel into manifolds of a main combustion chamber and/or afterburning combustion chamber of a gas-turbine engine. A multiple-manifold device for feeding fuel into a combustion chamber of a gas-turbine engine comprises two or more fuel manifolds for supplying fuel to fuel nozzles, and a metering device. Between each two consecutively connected fuel manifolds there is additionally a connecting line with a metering orifice mounted therein, suitable for the metered flow of fuel from one manifold to another during starting modes of the gas-turbine engine. The proposed invention makes it possible to provide consecutive metered filling of fuel manifolds via connecting lines containing metering orifices, and to increase the reliability of operating of a fuel feed device and the reliability of the process of starting an engine in on-ground and in-flight conditions.
Description
Многоколлекторное устройство подачи топлива в камеру сгорания газотурбинного двигателя Multi-collector fuel supply to the combustion chamber of a gas turbine engine
Изобретение относится к области эксплуатации авиационных газотурбинных двигателей (ГТД) и может быть использовано для управления подачей топлива в коллекторы основной и/или форсажной камер сгорания ГТД. The invention relates to the field of operation of aircraft gas turbine engines (GTE) and can be used to control the supply of fuel to the manifolds of the main and / or afterburner combustion chambers of the GTE.
Известно устройство подачи топлива в камеру сгорания газотурбинного двигателя, содержащее топливные магистрали, каналы выхода в I и II коллекторы форсунок камеры сгорания, запорный клапан, соединенный с источником высокого давления и с каналом выхода в I коллектор, и распределительный клапан, который соединен с одной стороны с каналом выхода в I коллектор, а с другой - с каналом выхода во II коллектор, дополнительно введены шунтирующий и электромагнитный клапаны, причем запорный элемент шунтирующего клапана установлен с возможностью соединения канала выхода в I коллектор с каналом выхода во II коллектор, а полость управления шунтирующего клапана соединена с электромагнитным клапаном и через жиклер с источником постоянного давления A device for supplying fuel to the combustion chamber of a gas turbine engine is known, which contains fuel lines, output channels to the I and II nozzles of the combustion chamber of the combustion chamber, a shut-off valve connected to a high pressure source and an outlet channel to the I collector, and a control valve that is connected to one side With the output channel into the I collector, and on the other with the output channel into the II collector, shunt and solenoid valves are additionally introduced, and the shut-off element of the shunt valve is installed with the possibility of connecting Nia I channel outputs in the collector output channel II in the collector, and the bypass valve control chamber is connected to the solenoid valve and through a nozzle to a source of constant pressure
(Патент RU N* 2616327, МПК F02C7/22, публ.14.04.2017). (Patent RU N * 2616327, IPC F02C7 / 22, publ.14.04.2017).
Недостатком устройства является отсутствие возможности плавного повышения режима работы двигателя на запуске ввиду необходимости заполнения топливом второго коллектора после открытия распределительного клапана. Это приводит к ступенчатому запуску и, как следствие, к повышению времени запуска, снижает надежность запуска и срок службы пусковых устройств. The disadvantage of this device is the lack of the possibility of a smooth increase in the mode of operation of the engine at launch due to the need to fill the second collector with fuel after opening the distribution valve. This leads to a stepwise start-up and, as a result, to an increase in the start-up time, reduces the reliability of the start-up and the service life of the starting devices.
Известно устройство подачи топлива в камеру сгорания газотурбинного двигателя, принятое за прототип, содержащее, насосный блок, имеющий возможность своим входом соединение с топливным баком, а
выходом - посредством основной топливной магистрали через распределитель - с дозаторами топлива в коллекторы камеры сгорания, новым является то, что как минимум, один топливный коллектор имеет второй вход, соединенный первой дополнительной топливной магистралью с выходом насосного блока, и выход, соединенный второй дополнительный топливной магистралью с входом насосного блока, причем в дополнительных топливных магистралях установлены отсечные клапаны, при этом в первой дополнительной топливной магистрали может быть установлен регулятор давления топлива, связанный с датчиком давления газов в камере сгорания (Патент RU JVb 148619, МПК F02C9/26, публ.10.12.2014) A device for supplying fuel to the combustion chamber of a gas turbine engine, adopted as a prototype, containing a pumping unit, having a connection with a fuel tank with its input, is known. output - through the main fuel line through the distributor - with fuel dispensers to the combustion chamber manifolds, is that at least one fuel manifold has a second input connected to the first additional fuel line with the output of the pumping unit, and an output connected to the second additional fuel line with the inlet of the pumping unit, with shut-off valves installed in the additional fuel lines, while the first additional fuel line can be equipped with a regulating valve torus of fuel pressure associated with the gas pressure sensor in the combustion chamber (Patent RU JVb 148619, IPC F02C9 / 26, published December 12, 2014)
Недостатком устройства является наличие отсечных клапанов в дополнительных магистралях, через которые осуществляется заполнение коллекторов недозированным топливом, что усложняет систему подачи топлива в камеру сгорания, снижает ее надежность. Кроме этого, на запуске двигателя давление топлива перед насосом может быть выше давления воздуха в камере сгорания. В этом случае недозированное топливо может перетекать в форсунки, что ухудшает стабильность запуска, снижает его надежность. The disadvantage of this device is the presence of shut-off valves in additional lines through which the collectors are filled with non-dosed fuel, which complicates the fuel supply system into the combustion chamber, reduces its reliability. In addition, at the start of the engine, the fuel pressure upstream of the pump may be higher than the air pressure in the combustion chamber. In this case, the un-dosed fuel can flow into the injectors, which impairs the launch stability and reduces its reliability.
Технической задачей предлагаемого изобретения является упрощение конструкции устройства подачи топлива, повышение надежности его работы, повышение надежности запуска двигателя на земле и в полете. The technical task of the invention is to simplify the design of the device fuel supply, improving the reliability of its work, improving the reliability of starting the engine on the ground and in flight.
Техническая задача решается за счет того, что в многоколлекторном устройстве подачи топлива в камеру сгорания газотурбинного двигателя, содержащем два и более топливных коллектора для подвода топлива к топливным форсункам, дозатор, согласно изобретению, между каждыми двумя последовательно подключаемыми топливными коллекторами дополнительно содержится соединительная магистраль с установленным в ней жиклером, с возможностью дозированного перетекания топлива из одного коллектора в другой на режимах запуска газотурбинного двигателя.
На фиг. 1 представлена схема устройства, где 1 - дозатор, 2 - топливные форсунки, 3 - первый коллектор, 4 - второй коллектор, 5 - дополнительная соединительная магистраль, 6 - жиклер, 7 - третий коллектор, 8 - дополнительная соединительная магистраль, 9 - жиклер. The technical problem is solved due to the fact that in the multi-collector fuel supply device to the combustion chamber of a gas turbine engine containing two or more fuel collectors for supplying fuel to the fuel injectors, the dispenser according to the invention, additionally contains a connecting line with each there is a jet in it, with the possibility of metered flow of fuel from one collector to another on the gas-turbine engine start-up modes. FIG. 1 shows a diagram of the device, where 1 is the metering unit, 2 is the fuel injectors, 3 is the first collector, 4 is the second collector, 5 is the additional connecting line, 6 is the nozzle, 7 is the third collector, 8 is the additional connecting line, 9 is the nozzle.
На запуске двигателя во время раскрутки ротора компрессора высокого давления (КВД) пусковым устройством или при его авторотации в условиях полета топливо от дозатора 1 подается в первый коллектор 3 и группу топливных форсунок 2, запитываемую этим коллектором. Одновременно, под действием перепада давления между давлением топлива в коллекторе 3 и давлением в камере сгорания, топливо поступает во второй коллектор 4 через дополнительную соединительную магистраль 5 с жиклером 6. Величина расхода топлива через дополнительную соединительную магистраль 5 определяется размером жиклера 6 и подбирается исходя из условия полного заполнения топливом коллектора 4 к моменту начала подачи топлива в коллектор 4 от дозатора 1 при раскрутке ротора КВД. Аналогичным образом осуществляется предварительное заполнение третьего коллектора 7 через дополнительную соединительную магистраль 8 с жиклером 9. At the start of the engine during the spin-up of the high-pressure compressor (HPC) rotor by the starting device or during autorotation under flight conditions, fuel from the dispenser 1 is fed to the first collector 3 and a group of fuel injectors 2 powered by this collector. At the same time, under the action of a pressure differential between the pressure of the fuel in the manifold 3 and the pressure in the combustion chamber, the fuel enters the second manifold 4 through the additional connecting line 5 with the nozzle 6. The fuel consumption through the additional connecting line 5 is determined by the size of the nozzle 6 and is selected on the basis of complete filling of the collector 4 with fuel by the moment of the beginning of the supply of fuel to the collector 4 from the dispenser 1 during the spin-off of the high-pressure boiler rotor. Similarly, the pre-filling of the third collector 7 through an additional connecting line 8 with a nozzle 9.
Применение двух и более коллекторов, запитывающих соответствующие группы топливных форсунок, позволяет более равномерно распределить топливо в камере сгорания по окружности на розжиге и при выходе газотурбинного двигателя на режим малого газа. Розжиг камеры сгорания осуществляется с помощью первого (пускового) коллектора. По мере увеличения оборотов ротора КВД происходит подключение последующих коллекторов. Для того, чтобы исключить заброс температуры газа перед турбиной необходимо плавное подключение вторичных коллекторов. Для решения этой задачи между предыдущим и последующим коллекторами устанавливается дополнительная соединительная магистраль с жиклером. Предварительное заполнение коллектора осуществляется дозированным топливом через дополнительную магистраль. Размер жиклера подбирается таким образом, чтобы обеспечить заполнение коллектора
топливом до форсунок на заданных оборотах ротора КВД. Это позволяет упростить конструкцию устройства подачи топлива, повысить его надежность, повысить стабильность запуска двигателя на земле и в полете. The use of two or more collectors feeding the corresponding groups of fuel injectors makes it possible to more evenly distribute the fuel in the combustion chamber around the circumference during ignition and when the gas turbine engine reaches the low-gas mode. Ignition of the combustion chamber is carried out using the first (starting) collector. As the RPM rotor increases, subsequent collectors are connected. In order to avoid overfilling of the gas temperature before the turbine, a smooth connection of the secondary collectors is necessary. To solve this problem, an additional connecting line with a nozzle is installed between the previous and subsequent collectors. Pre-filling the collector is metered fuel through an additional line. The size of the nozzle is chosen in such a way as to ensure the filling of the manifold fuel to the injectors at a given rotation of the rotor of the ARC. This allows us to simplify the design of the fuel supply device, increase its reliability, and increase the stability of engine start on the ground and in flight.
Таким образом, предлагаемое устройство позволяет обеспечить последовательное дозированное заполнение топливных коллекторов через соединительные магистрали с жиклерами, повысить надежность работы устройства подачи топлива и надежность процесса запуска двигателя в наземных и полетных условиях.
Thus, the proposed device allows for consistent metered filling of fuel collectors through connecting lines with jets, to increase the reliability of the fuel supply device and the reliability of the engine start process in ground and flight conditions.
Claims
Формула изобретения Claim
Многоколлекторное устройство подачи топлива в камеру сгорания газотурбинного двигателя, содержащее два и более топливных коллектора для подвода топлива к топливным форсункам, дозатор, отличающееся тем, что между каждыми двумя последовательно подключаемыми топливными коллекторами дополнительно содержится соединительная магистраль с установленным в ней жиклером, с возможностью дозированного перетекания топлива из одного коллектора в другой на режимах запуска газотурбинного двигателя.
Multi-collector fuel supply device to the combustion chamber of a gas turbine engine, containing two or more fuel collectors for supplying fuel to fuel injectors, dispenser, characterized in that between each two series-connected fuel collectors there is additionally contained a connecting line with a jet installed in it, with the possibility of metered flow fuel from one collector to another on the start-up modes of a gas turbine engine.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2017139377 | 2017-11-14 | ||
| RU2017139377A RU2664900C1 (en) | 2017-11-14 | 2017-11-14 | Multi-collector device for fuel supply to the camera of combustion of a gas turbine engine |
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| Publication Number | Publication Date |
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| WO2019098880A1 true WO2019098880A1 (en) | 2019-05-23 |
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| PCT/RU2018/000641 WO2019098880A1 (en) | 2017-11-14 | 2018-10-03 | Multiple-manifold device for feeding fuel into a combustion chamber of a gas-turbine engine |
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| Country | Link |
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| RU (1) | RU2664900C1 (en) |
| WO (1) | WO2019098880A1 (en) |
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| RU2704055C1 (en) * | 2019-06-04 | 2019-10-23 | Акционерное общество "ОДК-Климов" | Fuel system of main combustion chamber of gas turbine engine |
| CN111794865B (en) * | 2020-05-29 | 2021-12-10 | 中国人民解放军空军工程大学 | Linear plasma igniter and ignition method for flow direction of scramjet combustion chamber |
| RU2753207C1 (en) * | 2020-10-14 | 2021-08-12 | Федеральное Автономное Учреждение "Центральный институт авиационного моторостроения имени П.И. Баранова" | Fuel supply system to multi-collector combustion chamber |
| RU2752332C1 (en) * | 2020-11-18 | 2021-07-26 | Акционерное общество "ОДК-Климов" | System for regulating fuel supply to afterburner of turbojet engine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2199675C1 (en) * | 2001-09-25 | 2003-02-27 | Федеральное государственное унитарное предприятие Конструкторское бюро химавтоматики | Gas turbine plant and method of its starting |
| RU148619U1 (en) * | 2014-07-31 | 2014-12-10 | Федеральное государственное унитарное предприятие "Научно-производственный центр газотурбостроения "Салют" (ФГУП "НПЦ газотурбостроения "Салют") | FILLING SYSTEM FOR FUEL COLLECTORS OF COMBUSTION CHAMBERS OF A GAS TURBINE ENGINE |
| RU2616327C1 (en) * | 2016-06-14 | 2017-04-14 | Открытое акционерное общество "Омское машиностроительное конструкторское бюро" | Fuel feed system of combustion chamber of gas-turbine engine |
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2017
- 2017-11-14 RU RU2017139377A patent/RU2664900C1/en active
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- 2018-10-03 WO PCT/RU2018/000641 patent/WO2019098880A1/en active Application Filing
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2199675C1 (en) * | 2001-09-25 | 2003-02-27 | Федеральное государственное унитарное предприятие Конструкторское бюро химавтоматики | Gas turbine plant and method of its starting |
| RU148619U1 (en) * | 2014-07-31 | 2014-12-10 | Федеральное государственное унитарное предприятие "Научно-производственный центр газотурбостроения "Салют" (ФГУП "НПЦ газотурбостроения "Салют") | FILLING SYSTEM FOR FUEL COLLECTORS OF COMBUSTION CHAMBERS OF A GAS TURBINE ENGINE |
| RU2616327C1 (en) * | 2016-06-14 | 2017-04-14 | Открытое акционерное общество "Омское машиностроительное конструкторское бюро" | Fuel feed system of combustion chamber of gas-turbine engine |
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| RU2664900C1 (en) | 2018-08-23 |
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