RU94037894A - Method of obtaining propulsive mass on three-component propellant and device for realization of this method - Google Patents

Method of obtaining propulsive mass on three-component propellant and device for realization of this method

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Publication number
RU94037894A
RU94037894A RU94037894/06A RU94037894A RU94037894A RU 94037894 A RU94037894 A RU 94037894A RU 94037894/06 A RU94037894/06 A RU 94037894/06A RU 94037894 A RU94037894 A RU 94037894A RU 94037894 A RU94037894 A RU 94037894A
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RU
Russia
Prior art keywords
hydrogen
kerosene
oxygen
gas
burning
Prior art date
Application number
RU94037894/06A
Other languages
Russian (ru)
Other versions
RU2108477C1 (en
Inventor
В.С. Рачук
Н.С. Гончаров
В.А. Орлов
В.А. Туртушов
Ю.А. Ефремов
Н.П. Веремеенко
Б.Г. Макаренко
Original Assignee
КБ химавтоматики
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by КБ химавтоматики filed Critical КБ химавтоматики
Priority to RU94037894A priority Critical patent/RU2108477C1/en
Publication of RU94037894A publication Critical patent/RU94037894A/en
Application granted granted Critical
Publication of RU2108477C1 publication Critical patent/RU2108477C1/en

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Abstract

FIELD: power engineering and rocketry. SUBSTANCE: in burning of three-component propellant "oxygen-kerosene-hydrogen", gas generation products are formed at excess of propellant without solid particles due to burning of field at different temperature zones through successive supply of kerosene and hydrogen. Use is made of bonding of free carbon which is likely to be formed in course of reactions of oxygen and kerosene with hydrogen and forming gaseous methane ((C+2H= CH)) due to addition of 5 to 15 percent of hydrogen to zone of burning of oxygen with kerosene. At second stage of operation of gas generator, kerosene is replaced with warm hydrogen for obtaining products of gas generation. For realization of this method, use is made of various devices for supply of ballasting kerosene and hydrogen to obtain guaranteed high-temperature burning zones and complete combustion. EFFECT: enhanced efficiency. 12 cl, 8 dwg

Claims (1)

Изобретение относится к энергетике и может быть использовано в ракетной технике и в других областях. Цель изобретения - получение продуктов газогенерации с избытком горючего при сгорании трехкомпонентного топлива кислород+керосин+водород без твердых частиц углерода и полноты работоспособности газа за счет организации процесса горения горючего с разными температурными зонами путем последовательной подачи керосина и водорода. Кроме того, используется возможность связывания свободного углерода, который может образоваться в процессе рабочих реакций кислорода и керосина, с водородом и образования газообразного метана (C + 2H2=CH4) путем добавления 5...15% водорода в зону горения кислорода с керосином. Для получения продуктов газогенерации на втором режиме работы газогенератора керосин замещают теплым водородом. Способ реализуется в устройстве, работающем на кислороде+керосине+водороде на первом режиме и кислороде+водороде на втором. Для обеспечения гарантированных высокотемпературных зон горения и полноты работоспособности газа подача балластировочного керосина и водорода осуществляется различными конструктивными устройствами.The invention relates to energy and can be used in rocket technology and in other fields. The purpose of the invention is the production of gas products with excess fuel during the combustion of three-component fuel oxygen + kerosene + hydrogen without solid carbon particles and the completeness of the gas’s working capacity due to the organization of the fuel combustion process with different temperature zones by sequential supply of kerosene and hydrogen. In addition, the possibility of binding free carbon, which can be formed during the working reactions of oxygen and kerosene, with hydrogen and the formation of gaseous methane (C + 2H 2 = CH 4 ) is used by adding 5 ... 15% hydrogen to the combustion zone of oxygen with kerosene . To obtain gas generation products in the second mode of operation of the gas generator, kerosene is replaced with warm hydrogen. The method is implemented in a device operating on oxygen + kerosene + hydrogen in the first mode and oxygen + hydrogen in the second. To ensure guaranteed high-temperature combustion zones and complete gas operability, the supply of ballasting kerosene and hydrogen is carried out by various structural devices.
RU94037894A 1994-09-16 1994-09-16 Method of and device for production of working medium on three-component fuel RU2108477C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94037894A RU2108477C1 (en) 1994-09-16 1994-09-16 Method of and device for production of working medium on three-component fuel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94037894A RU2108477C1 (en) 1994-09-16 1994-09-16 Method of and device for production of working medium on three-component fuel

Publications (2)

Publication Number Publication Date
RU94037894A true RU94037894A (en) 1996-11-20
RU2108477C1 RU2108477C1 (en) 1998-04-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU94037894A RU2108477C1 (en) 1994-09-16 1994-09-16 Method of and device for production of working medium on three-component fuel

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RU (1) RU2108477C1 (en)

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RU2463469C2 (en) * 2009-10-14 2012-10-10 Федеральное государственное унитарное предприятие "Научно-исследовательский институт машиностроения" (ФГУП "НИИМаш") Mixing head
RU2481494C1 (en) * 2012-03-15 2013-05-10 Владимир Викторович Черниченко Method for supplying fuel components to liquid-propellant engine chamber
RU2483223C1 (en) * 2012-03-15 2013-05-27 Черниченко Владимир Викторович Method of feeding fuel components into liquid-propellant rocket engine chamber
RU2482320C1 (en) * 2012-03-15 2013-05-20 Владимир Викторович Черниченко Method for supplying fuel components to liquid-propellant engine chamber
RU2482317C1 (en) * 2012-03-15 2013-05-20 Владимир Викторович Черниченко Method for supplying fuel components to liquid-propellant engine chamber
RU2479740C1 (en) * 2012-03-15 2013-04-20 Владимир Викторович Черниченко Liquid-propellant rocket engine combustion chamber
RU2481492C1 (en) * 2012-03-15 2013-05-10 Владимир Викторович Черниченко Method for supplying fuel components to liquid-propellant engine chamber
RU2482319C1 (en) * 2012-03-15 2013-05-20 Владимир Викторович Черниченко Method for supplying fuel components to liquid-propellant engine chamber
RU2481487C1 (en) * 2012-03-15 2013-05-10 Владимир Викторович Черниченко Liquid-propellant engine chamber
RU2481493C1 (en) * 2012-03-15 2013-05-10 Владимир Викторович Черниченко Method for supplying fuel components to liquid-propellant engine chamber
RU2481485C1 (en) * 2012-03-15 2013-05-10 Владимир Викторович Черниченко Liquid-propellant engine chamber
RU2482314C1 (en) * 2012-03-15 2013-05-20 Владимир Викторович Черниченко Liquid-propellant engine chamber
RU2497009C1 (en) * 2012-06-27 2013-10-27 Черниченко Владимир Викторович Coaxial spray atomiser
RU2488012C1 (en) * 2012-06-27 2013-07-20 Владимир Викторович Черниченко Method of feeding three-component propellant into combustion chamber of liquid-propellant rocket engine and coaxial-jet atomiser to this end
RU2495271C1 (en) * 2012-06-27 2013-10-10 Черниченко Владимир Викторович Method of feeding three-component fuel into liquid-propellant rocket engine chamber
RU2502887C1 (en) * 2012-06-27 2013-12-27 Черниченко Владимир Викторович Method of fuel components feed in three-component liquid propellant rocket engine combustion chamber and aligned-jet nozzle to this end
RU2493405C1 (en) * 2012-06-27 2013-09-20 Владимир Викторович Черниченко Chamber of liquid-propellant rocket engine
RU2497008C1 (en) * 2012-06-27 2013-10-27 Владимир Викторович Черниченко Method of fuel components feed in three-component liquid propellant rocket engine
RU2497013C1 (en) * 2012-06-27 2013-10-27 Владимир Викторович Черниченко Liquid propellant rocket engine chamber
RU2493404C1 (en) * 2012-06-27 2013-09-20 Владимир Викторович Черниченко Method to supply fuel components in chamber of three-component liquid propellant rocket engine
RU2502886C1 (en) * 2012-06-27 2013-12-27 Владимир Викторович Черниченко Method of fuel components feed in three-component liquid propellant rocket engine combustion chamber
RU2501967C1 (en) * 2012-06-27 2013-12-20 Владимир Викторович Черниченко Method to supply fuel components in chamber of three-component liquid propellant rocket engine and coaxial jet nozzle for implementation of specified method
RU2497011C1 (en) * 2012-06-27 2013-10-27 Владимир Викторович Черниченко Coaxial spray atomiser
RU2490500C1 (en) * 2012-06-27 2013-08-20 Черниченко Владимир Викторович Method for supplying fuel components to chamber ot three-component liquid-propellant engine
RU2495272C1 (en) * 2012-06-27 2013-10-10 Владимир Викторович Черниченко Method of feeding three-component fuel into liquid-propellant rocket engine chamber
RU2497010C1 (en) * 2012-06-27 2013-10-27 Владимир Викторович Черниченко Liquid propellant rocket
CN103644044B (en) * 2013-11-26 2015-10-28 北京航空航天大学 Be applied to polychormism simulated engine and the ignition schemes thereof of the research of Vacuum Plume effect experiment
RU2613011C1 (en) * 2016-02-02 2017-03-14 Владислав Юрьевич Климов Steam-gas generator
RU2630625C1 (en) * 2016-06-03 2017-09-11 Общество с ограниченной ответственностью научно-производственное предприятие "ИнтерПолярис" Method of gas production in a gas generator and gas generator (versions)
RU2635012C1 (en) * 2016-12-09 2017-11-08 Владислав Юрьевич Климов Steam-gas generator

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107939551A (en) * 2017-11-29 2018-04-20 北京航天动力研究所 A kind of precombustion chamber ejector filler structure
CN107939551B (en) * 2017-11-29 2024-02-09 北京航天动力研究所 Pre-combustion chamber injector structure

Also Published As

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