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WO2001012971A1 - Moteur-fusee a ergol liquide (mfel) a propergol cryogenique avec entrainement de turbine de l'appareil a turbo-pompe en circuit ferme - Google Patents

Moteur-fusee a ergol liquide (mfel) a propergol cryogenique avec entrainement de turbine de l'appareil a turbo-pompe en circuit ferme Download PDF

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Publication number
WO2001012971A1
WO2001012971A1 PCT/RU2000/000219 RU0000219W WO0112971A1 WO 2001012971 A1 WO2001012971 A1 WO 2001012971A1 RU 0000219 W RU0000219 W RU 0000219W WO 0112971 A1 WO0112971 A1 WO 0112971A1
Authority
WO
WIPO (PCT)
Prior art keywords
pump
engine
magisτρali
κameρy
nasοsa
Prior art date
Application number
PCT/RU2000/000219
Other languages
English (en)
Russian (ru)
Inventor
Boris Ivanovich Katorgin
Vladimir Konstantinovich Chvanov
Valery Ivanovich Arkhangelsky
Sergei Georgevich Konovalov
Igor Konstantinovich Levitsky
Viktor Alexeevich Prokhorov
Vladimir Jurevich Bogushev
Alexandr Mikhailovich Kashkarov
Boris Mikhailovich Gromyko
Evgeny Alexeevich Belov
Jury Ivanovich Kanalin
Vadim Grigorievich Dozhdev
Antonina Vasilievna Tzvetova
Boris Petrovich Volostnykh
Evgeny Nikolaevich Belyaev
Vladimir Nikolaevich Khazov
Original Assignee
Otkrytoe Aktsionernoe Obschestvo 'npo Energomash Imeni Akademika V.P.Glushko'
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 Otkrytoe Aktsionernoe Obschestvo 'npo Energomash Imeni Akademika V.P.Glushko' filed Critical Otkrytoe Aktsionernoe Obschestvo 'npo Energomash Imeni Akademika V.P.Glushko'
Publication of WO2001012971A1 publication Critical patent/WO2001012971A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps

Definitions

  • the invention is available in the field of missile technology, more narrowly designed liquid propellant engines (RA).
  • the average level of pressure in the combustion chamber is high - up to 250 kgf / cm, which ensures a higher degree of gas expansion in combination with the camera and a high specific impulse.
  • thermo-dynamic closure of the working cycle is provided, in essence it is a variant of the generally known vapor-liquid cycle of the Genkine.
  • ne ⁇ s ⁇ eds ⁇ venn ⁇ g ⁇ is ⁇ lz ⁇ vaniya ⁇ ame ⁇ n ⁇ g ⁇ ⁇ e ⁇ la for ⁇ lucheniya ⁇ u ⁇ b ⁇ gaza ⁇ a ⁇ iches ⁇ i ⁇ ealiz ⁇ vana in ⁇ isl ⁇ dn ⁇ -v ⁇ d ⁇ dn ⁇ m "bezgaz ⁇ gene ⁇ a ⁇ n ⁇ m” dviga ⁇ ele ⁇ -10 ⁇ az ⁇ ab ⁇ ann ⁇ m in 60 g ⁇ da ⁇ in SSH ⁇ (eg ⁇ ⁇ isanie dan ⁇ , na ⁇ ime ⁇ in ⁇ nige: Ga ⁇ un GG ( ⁇ ed).
  • the problem solved by the invention is the expansion of the functional capabilities of a gas-free rail circuit with a closed or disconnected railroad trap.
  • magis ⁇ ali s ⁇ edinyayuschey vy ⁇ d ⁇ a ⁇ a ⁇ egene ⁇ a ⁇ ivn ⁇ g ⁇ ⁇ lazhdeniya ⁇ ame ⁇ y and v ⁇ d ⁇ u ⁇ biny, us ⁇ an ⁇ vlen ⁇ e ⁇ l ⁇ bmenni ⁇ -nag ⁇ eva ⁇ el, ⁇ e ⁇ l ⁇ n ⁇ si ⁇ elem ⁇ g ⁇ yavlyae ⁇ sya gas ⁇ luchaemy in gaz ⁇ gene ⁇ a ⁇ e, za ⁇ i ⁇ ann ⁇ m of vy ⁇ dny ⁇ magis ⁇ aley nas ⁇ s ⁇ v g ⁇ yucheg ⁇ and ⁇ isli ⁇ elya, ⁇ i e ⁇ m vy ⁇ d ⁇ e ⁇ l ⁇ n ⁇ si ⁇ elya of ⁇ e ⁇ l ⁇ bmenni ⁇ a- nag ⁇ eva ⁇ elya ⁇ d ⁇ lyuchen ⁇ vy ⁇ dn ⁇
  • the heater is mounted on the exhaust pipe of the oxidizer after the outlet of the fuse-heater;
  • a pump is located in the vicinity of the connection to the safe mains, and a check valve is also installed.
  • the entrance to the pump is autonomous. It is connected to the unit via a plug-in connector and is located on the ground launcher.
  • SUMMARY OF THE INVENTION is also included, including in the RAIN, including a chamber with a mixed head and a regenerative cooling system.
  • the main body is between the exit from the exchange and the consumer is in good condition.
  • the main body of the tank is a mobile unit, which is heated and is supplied with a hot pump.
  • the quick-start pump is an independent appliance that is connected to the indicated pump through a plug-in coupling.
  • ⁇ a ⁇ ig. 1 The basic scheme of the railway with a closed circuit of the path of the turbine of the transport unit is presented.
  • ⁇ a ⁇ ig. 2 The basic scheme of the railway with a closed circuit of the tank of the transport unit is presented.
  • ZH ⁇ D ( ⁇ ig. 1) s ⁇ de ⁇ zhi ⁇ ⁇ ame ⁇ u 1 s ⁇ smesi ⁇ eln ⁇ y g ⁇ l ⁇ v ⁇ y 2 and ⁇ a ⁇ m ⁇ egene ⁇ a ⁇ ivn ⁇ g ⁇ ⁇ lazhdeniya 3 ⁇ u ⁇ b ⁇ nas ⁇ sny ag ⁇ ega ⁇ 4 nas ⁇ sami ⁇ isli ⁇ elya 5 and 6.
  • the return valve is installed 22.
  • the actuator 20 is an independent pump and is connected to it through plug-in connector (not indicated). operating after reaching a separate operating mode. In the case of an empty pump, it may be used, for example, a pipe with air or gas.
  • the engine diagram described above with an independent closed circuit in the tank is preferable for vapor liquid acid.
  • ⁇ e ⁇ m case za ⁇ lneniya ⁇ ab ⁇ cheg ⁇ ⁇ n ⁇ u ⁇ a m ⁇ gu ⁇ by ⁇ is ⁇ lz ⁇ vany ⁇ a ⁇ ie ⁇ ab ⁇ chie ⁇ ela, na ⁇ ime ⁇ , ⁇ a ⁇ v ⁇ da, me ⁇ an, ammia ⁇ , ⁇ ya ned ⁇ s ⁇ a ⁇ m v ⁇ dy yavlyae ⁇ sya ⁇ asn ⁇ s ⁇ its zame ⁇ zaniya in ⁇ e ⁇ l ⁇ bmenni ⁇ e- ⁇ ndensa ⁇ e and m ⁇ schn ⁇ s ⁇ nagne ⁇ aniya me ⁇ ana due eg ⁇ mal ⁇ y ⁇ l ⁇ n ⁇ s ⁇ i ⁇ n ⁇ si ⁇ eln ⁇ veli ⁇ a. How to do it. Ammonia is found to be the most practical one.
  • ZH ⁇ D ( ⁇ ig. 2) s ⁇ de ⁇ zhi ⁇ ⁇ ame ⁇ u 24 s ⁇ smesi ⁇ eln ⁇ y g ⁇ l ⁇ v ⁇ y 25 and ⁇ a ⁇ ⁇ egene ⁇ a ⁇ ivn ⁇ g ⁇ ⁇ lazhdeniya 26 ⁇ u ⁇ b ⁇ nas ⁇ sny ag ⁇ ega ⁇ 27 nas ⁇ s ⁇ m ⁇ isli ⁇ elya 28 and 29.
  • the railway comes with a closed circuit 33 of the rudder 34 of the civilian unit 27.
  • the aforementioned civilian is incurred by a death 29
  • the end pipe 31 of this pump is connected through an adjustable divider through 32 with a mixing head 25 and through a bypass valve 35 - with a pipe ⁇ m ⁇ egene ⁇ a ⁇ ivn ⁇ g ⁇ ⁇ lazhdeniya 26 ⁇ ame ⁇ y 24.
  • Za ⁇ us ⁇ dviga ⁇ elya Za ⁇ us ⁇ dviga ⁇ elya, za ⁇ lnenn ⁇ g ⁇ ⁇ s ⁇ emam ( ⁇ ig. 1 and ⁇ ig. 2) nachinae ⁇ sya with ⁇ y ⁇ iya ⁇ us ⁇ sechny ⁇ ⁇ la ⁇ an ⁇ v, us ⁇ an ⁇ vlenny ⁇ v ⁇ v ⁇ dny ⁇ magis ⁇ alya ⁇ nas ⁇ s ⁇ v ⁇ isli ⁇ elya 5 (28) and g ⁇ yucheg ⁇ 6 (29) (not ⁇ azany) and ⁇ s ⁇ u ⁇ leniya ⁇ m ⁇ nen ⁇ v in ⁇ ame ⁇ u 1 (24 ) by itself (due to the pressure of the boost of the tanks) with their subsequent ignition (not indicated).
  • a pipe is used with either a pneumatic or pneumatic drive (not indicated).
  • the return valve 21 is turned off, and the return valve 22 is closed (Fig. 1), the return valve 35 is closed, and the return valve 39 is turned off (2).
  • the single fuel components from pumps 5 and 6 (28 and 29) are emitted in gas generator 16 (40), where they are ignited. Gas from the gas generator 16 (40) is released in the heat exchanger-heater 12 (36).
  • Adjusting the thrust of the engine to the nominal mode is ensured by the operation of the heater with the aid of the regulating system of the drive 17 (42) - by changing the load.
  • the invention is intended for use in a rocket engine for liquid fuel and having a fuel converter ⁇ .
  • processes are underway for the construction of RAWs, which use such components of fuel as liquid and liquid acid.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Le MFEL de l'invention comprend une chambre avec une tête de mélange et une boucle de refroidissement régénératif, un appareil à turbopompe (ATP) avec des pompes de comburant (oxygène liquide) et de propergol, les conduits de sortie desdites pompes étant reliés à la tête de mélange de la chambre. Il comprend également un circuit fermé de turbine de l'ATP qui comporte, reliés en série: une pompe de circulation, une boucle de refroidissement régénératif et un échangeur de chaleur / réchauffeur utilisant en tant que fluide caloporteur le gaz produit par le générateur de gaz et alimenté par les conduits de sortie des pompes de comburant et de propergol. Depuis la sortie de l'échangeur de chaleur / réchauffeur, le fluide caloporteur est introduit dans le conduit de sortie de la pompe de comburant. Le MFEL comprend aussi une turbine et un échangeur de chaleur / condensateur installé à la sortie du conduit de la pompe de comburant, la sortie de l'échangeur de chaleur-condensateur étant reliée à travers un régulateur de débit à l'entrée de la pompe de circulation. Une variante du MFEL se distingue en ce que le circuit d'entraînement de la turbine de l'ATP comprend une pompe de propergol qui remplit également les fonctions de la pompe de circulation. De plus, la sortie de la pompe de propergol est reliée, à travers un régulateur de débit commandé, à la tête de mélange de la chambre et à la boucle de refroidissement régénératif de la chambre.
PCT/RU2000/000219 1999-08-18 2000-06-06 Moteur-fusee a ergol liquide (mfel) a propergol cryogenique avec entrainement de turbine de l'appareil a turbo-pompe en circuit ferme WO2001012971A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU99118107A RU2155273C1 (ru) 1999-08-18 1999-08-18 Жидкостный ракетный двигатель (жрд) на криогенном топливе с замкнутым контуром привода турбины турбонасосного агрегата (варианты)
RU99118107 1999-08-18

Publications (1)

Publication Number Publication Date
WO2001012971A1 true WO2001012971A1 (fr) 2001-02-22

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2000/000219 WO2001012971A1 (fr) 1999-08-18 2000-06-06 Moteur-fusee a ergol liquide (mfel) a propergol cryogenique avec entrainement de turbine de l'appareil a turbo-pompe en circuit ferme

Country Status (2)

Country Link
RU (1) RU2155273C1 (fr)
WO (1) WO2001012971A1 (fr)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921980B1 (fr) * 2007-10-08 2014-05-09 Astrium Sas Dispositif et procede de motorisation de pompe pour moteur fusee par roue d'inertie
FR2981127B1 (fr) * 2011-10-11 2013-11-29 Snecma Dispositif de propulsion a reaction et procede d'alimentation
RU2484286C1 (ru) * 2011-12-07 2013-06-10 Николай Борисович Болотин Кислородно-водородный жидкостный ракетный двигатель
FR2984452B1 (fr) * 2011-12-14 2014-06-13 Snecma Dispositif et procede de pressurisation
RU2484285C1 (ru) * 2011-12-29 2013-06-10 Николай Борисович Болотин Кислородно-водородный жидкостный ракетный двигатель
RU2477446C1 (ru) * 2012-02-06 2013-03-10 Марина Леонардовна Нефедова Зенитная ракета
RU2477445C1 (ru) * 2012-02-09 2013-03-10 Николай Борисович Болотин Зенитная ракета
RU2488710C1 (ru) * 2012-04-18 2013-07-27 Открытое акционерное общество "Авиадвигатель" Двухконтурный турбореактивный двигатель
FR2998926B1 (fr) * 2012-11-30 2014-12-26 Snecma Ensemble propulsif pour fusee
RU2531833C1 (ru) * 2013-07-17 2014-10-27 Николай Борисович Болотин Жидкостный ракетный двигатель
RU2555422C1 (ru) * 2014-01-09 2015-07-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" Жидкостный ракетный двигатель
RU2551712C1 (ru) * 2014-03-25 2015-05-27 Открытое акционерное общество "Конструкторское бюро химавтоматики" Жидкостный ракетный двигатель
RU2643282C2 (ru) * 2015-03-17 2018-01-31 Николай Михайлович Пикулев Ракетный двигатель
CN111535939B (zh) * 2019-12-12 2022-05-27 西北工业大学 一种适用于再生冷却爆震燃烧室的燃油喷射系统
CN113958425B (zh) * 2021-12-20 2022-05-10 西安航天动力研究所 一种开式循环液氧煤油发动机系统及其使用方法
CN115325732B (zh) * 2022-06-23 2023-05-26 北京航天试验技术研究所 一种用于液氧和甲烷同步过冷的撬装式装置及方法

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US3516254A (en) * 1967-09-11 1970-06-23 United Aircraft Corp Closed-loop rocket propellant cycle
DE1626082B1 (de) * 1967-07-26 1970-06-25 Erno Raumfahrttechnik Gmbh Raketentriebwerk fuer fluessige treibstoffe
DE3506826A1 (de) * 1985-02-27 1986-08-28 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren zum betreiben eines fluessigkeitsraketentriebwerks und raketentriebwerk zur durchfuehrung des verfahrens
US4771600A (en) * 1986-10-20 1988-09-20 United Technologies Corporation Tripropellant rocket engine
RU2065985C1 (ru) * 1994-08-03 1996-08-27 КБ химавтоматики г.Воронеж Трехкомпонентный жидкостный ракетный двигатель
RU2095607C1 (ru) * 1995-07-19 1997-11-10 Ракетно-космическая корпорация "Энергия" им.С.П.Королева Жидкостный ракетный двигатель на криогенном топливе

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1626082B1 (de) * 1967-07-26 1970-06-25 Erno Raumfahrttechnik Gmbh Raketentriebwerk fuer fluessige treibstoffe
US3516254A (en) * 1967-09-11 1970-06-23 United Aircraft Corp Closed-loop rocket propellant cycle
DE3506826A1 (de) * 1985-02-27 1986-08-28 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren zum betreiben eines fluessigkeitsraketentriebwerks und raketentriebwerk zur durchfuehrung des verfahrens
US4771600A (en) * 1986-10-20 1988-09-20 United Technologies Corporation Tripropellant rocket engine
RU2065985C1 (ru) * 1994-08-03 1996-08-27 КБ химавтоматики г.Воронеж Трехкомпонентный жидкостный ракетный двигатель
RU2095607C1 (ru) * 1995-07-19 1997-11-10 Ракетно-космическая корпорация "Энергия" им.С.П.Королева Жидкостный ракетный двигатель на криогенном топливе

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RU2155273C1 (ru) 2000-08-27

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