RU2012132688A - METHOD FOR ENSURING UNLESS-OPERATING TURBO-PUMP UNIT OF MULTI-MODE LIQUID ROCKET ENGINE ON DEEP THROTTLE MODES - Google Patents
METHOD FOR ENSURING UNLESS-OPERATING TURBO-PUMP UNIT OF MULTI-MODE LIQUID ROCKET ENGINE ON DEEP THROTTLE MODES Download PDFInfo
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- RU2012132688A RU2012132688A RU2012132688/06A RU2012132688A RU2012132688A RU 2012132688 A RU2012132688 A RU 2012132688A RU 2012132688/06 A RU2012132688/06 A RU 2012132688/06A RU 2012132688 A RU2012132688 A RU 2012132688A RU 2012132688 A RU2012132688 A RU 2012132688A
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- pumps
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- pressure
- gas
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Abstract
1. Способ обеспечения бессрывной работы насосов турбонасосного агрегата дросселируемого жидкостного ракетного двигателя, основанный на установке перед насосами бустерных насосов, привод каждого из которых осуществляется турбиной газовой или гидравлической, при этом вход в каждую турбину гидравлически соединен с помощью трубопровода либо с выходом одного из насосов в случае гидротурбины, либо с газовым трактом, расположенным за турбиной турбонасосного агрегата, в случае газовой турбины, отличающийся тем, что при снижении давления на входе в насосы ниже уровня, необходимого для бессрывной работы насосов, возможное при глубоком дросселировании двигателя осуществляют повышение напоров бустерных насосов путем подвода рабочего тела к дополнительным сопловым аппаратам со своими входными коллекторами, предварительно установленными в указанных турбинах через трубопроводы с регулирующими устройствами.2. Способ по п.1, отличающийся тем, что в качестве регулирующих устройств может быть применен многопозиционный клапан.3. Способ по п.1, отличающийся тем, что в качестве регулирующих устройств применен регулятор давления.1. A method of ensuring the continuous operation of the pumps of a turbopump unit of a throttle liquid propellant rocket engine, based on the installation of booster pumps in front of the pumps, each of which is driven by a gas or hydraulic turbine, while the entrance to each turbine is hydraulically connected via a pipeline or with the output of one of the pumps in case of a hydraulic turbine, or with a gas path located behind the turbine of the turbopump unit, in the case of a gas turbine, characterized in that when the pressure is reduced in the stroke in the pumps is lower than the level necessary for the continuous operation of the pumps, which is possible with deep throttling of the engine, they increase the pressure of the booster pumps by supplying the working fluid to additional nozzle devices with their inlet manifolds pre-installed in these turbines through pipelines with control devices. 2. The method according to claim 1, characterized in that a multiposition valve can be used as control device. The method according to claim 1, characterized in that a pressure regulator is used as control devices.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012132688/06A RU2513023C2 (en) | 2012-07-31 | 2012-07-31 | Method of flawless operation of liquid-propellant all-mode rocket engine turbo pump at high throttling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2012132688/06A RU2513023C2 (en) | 2012-07-31 | 2012-07-31 | Method of flawless operation of liquid-propellant all-mode rocket engine turbo pump at high throttling |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2012132688A true RU2012132688A (en) | 2014-02-10 |
| RU2513023C2 RU2513023C2 (en) | 2014-04-20 |
Family
ID=50031816
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2012132688/06A RU2513023C2 (en) | 2012-07-31 | 2012-07-31 | Method of flawless operation of liquid-propellant all-mode rocket engine turbo pump at high throttling |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2513023C2 (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2076229C1 (en) * | 1994-09-22 | 1997-03-27 | Игорь Алексеевич Клепиков | Rocket engine feed system |
| RU2158839C2 (en) * | 1999-01-21 | 2000-11-10 | Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" | Liquid-propellant rocket reheat engine |
| RU2190114C2 (en) * | 2000-06-30 | 2002-09-27 | ОАО "НПО Энергомаш им. акад. В.П.Глушко" | Liquid-propellant engine working on cryogenic components of propellant with closed loop of drive of turbine of turbo-pump unit |
| US7389636B2 (en) * | 2005-07-06 | 2008-06-24 | United Technologies Corporation | Booster rocket engine using gaseous hydrocarbon in catalytically enhanced gas generator cycle |
-
2012
- 2012-07-31 RU RU2012132688/06A patent/RU2513023C2/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2513023C2 (en) | 2014-04-20 |
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