RU2018147310A - Combustion chamber of a ram engine for an aircraft - Google Patents

Combustion chamber of a ram engine for an aircraft Download PDF

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Publication number
RU2018147310A
RU2018147310A RU2018147310A RU2018147310A RU2018147310A RU 2018147310 A RU2018147310 A RU 2018147310A RU 2018147310 A RU2018147310 A RU 2018147310A RU 2018147310 A RU2018147310 A RU 2018147310A RU 2018147310 A RU2018147310 A RU 2018147310A
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RU
Russia
Prior art keywords
combustion chamber
aircraft
ram engine
channel area
reactor
Prior art date
Application number
RU2018147310A
Other languages
Russian (ru)
Other versions
RU2018147310A3 (en
RU2737463C2 (en
Inventor
Сергей Анатольевич Зосимов
Виктор Владимирович Власенко
Андрей Викторович Сысоев
Геннадий Павлович Носков
Валерий Николаевич Серманов
Алексей Анатольевич Николаев
Original Assignee
Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского"
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.)
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Application filed by Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" filed Critical Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского"
Priority to RU2018147310A priority Critical patent/RU2737463C2/en
Publication of RU2018147310A3 publication Critical patent/RU2018147310A3/ru
Publication of RU2018147310A publication Critical patent/RU2018147310A/en
Application granted granted Critical
Publication of RU2737463C2 publication Critical patent/RU2737463C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Claims (3)

1. Камера сгорания прямоточного воздушно-реактивного двигателя, содержащая проточный термохимический реактор с входным и выходным устройствами, отличающаяся тем, что выходное устройство термохимического реактора выполнено в виде дозвукового щелевого сопла с расположенными на щелях на внешней поверхности стенок сопла полых смесительных лепестков.1. The combustion chamber of a ramjet engine containing a flowing thermochemical reactor with input and output devices, characterized in that the output device of the thermochemical reactor is made in the form of a subsonic slot nozzle with hollow mixing lobes located on slots on the outer surface of the walls of the nozzle. 2. Камера сгорания по п. 1, отличающаяся тем, что вершины лепестков установлены по кругу образующей камеры сгорания.2. The combustion chamber according to claim 1, characterized in that the tops of the petals are installed in a circle around the generatrix of the combustion chamber. 3. Камера сгорания по п. 1, отличающаяся тем, что площадь канала входного устройства реактора составляет 30-40% по отношению к площади канала камеры сгорания в том же сечении.3. The combustion chamber according to claim 1, characterized in that the channel area of the reactor inlet device is 30-40% with respect to the channel area of the combustion chamber in the same section.
RU2018147310A 2018-12-28 2018-12-28 Combustion chamber of straight-flow air-jet engine for aircraft RU2737463C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2018147310A RU2737463C2 (en) 2018-12-28 2018-12-28 Combustion chamber of straight-flow air-jet engine for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2018147310A RU2737463C2 (en) 2018-12-28 2018-12-28 Combustion chamber of straight-flow air-jet engine for aircraft

Publications (3)

Publication Number Publication Date
RU2018147310A3 RU2018147310A3 (en) 2020-06-29
RU2018147310A true RU2018147310A (en) 2020-06-29
RU2737463C2 RU2737463C2 (en) 2020-11-30

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2018147310A RU2737463C2 (en) 2018-12-28 2018-12-28 Combustion chamber of straight-flow air-jet engine for aircraft

Country Status (1)

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RU (1) RU2737463C2 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053340A (en) * 1958-07-21 1962-09-11 Gen Electric Noise suppression nozzle
US4131260A (en) * 1977-05-09 1978-12-26 Center For Design Research And Development N.V. Chair seat mount which permits the seat to tilt forward
RU2034996C1 (en) * 1993-10-11 1995-05-10 Владимир Федорович Антоненко Method and device for obtaining thrust
RU2454607C1 (en) * 2011-02-01 2012-06-27 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Method for stabilisation of fuel combustion process in combustion chamber, and combustion chamber of straight-jet engine of aircraft

Also Published As

Publication number Publication date
RU2018147310A3 (en) 2020-06-29
RU2737463C2 (en) 2020-11-30

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