RU96114573A - DEVICE FOR STABILIZING COMBUSTION IN A SUPERSONIC FLOW - Google Patents

DEVICE FOR STABILIZING COMBUSTION IN A SUPERSONIC FLOW

Info

Publication number
RU96114573A
RU96114573A RU96114573/06A RU96114573A RU96114573A RU 96114573 A RU96114573 A RU 96114573A RU 96114573/06 A RU96114573/06 A RU 96114573/06A RU 96114573 A RU96114573 A RU 96114573A RU 96114573 A RU96114573 A RU 96114573A
Authority
RU
Russia
Prior art keywords
nozzle
supersonic flow
stabilizing combustion
additional
main
Prior art date
Application number
RU96114573/06A
Other languages
Russian (ru)
Other versions
RU2119118C1 (en
Inventor
Г.Ф. Глотов
Original Assignee
Центральный аэрогидродинамический институт им.профессора Н.Е.Жуковского
Filing date
Publication date
Application filed by Центральный аэрогидродинамический институт им.профессора Н.Е.Жуковского filed Critical Центральный аэрогидродинамический институт им.профессора Н.Е.Жуковского
Priority to RU96114573A priority Critical patent/RU2119118C1/en
Priority claimed from RU96114573A external-priority patent/RU2119118C1/en
Application granted granted Critical
Publication of RU2119118C1 publication Critical patent/RU2119118C1/en
Publication of RU96114573A publication Critical patent/RU96114573A/en

Links

Claims (1)

Устройство для стабилизации горения в сверхзвуковом потоке, содержащее основное сопло, отличающееся тем, что оно снабжено обечайкой и трубопроводом с дополнительным соплом для подачи жидкого или газообразного горючего, расположенным соосно основному соплу, причем диаметр критического сечения дополнительного сопла составляет от 0,1 до 0,2 диаметра критического сечения основного сопла, а расстояние между критическими сечениями основного и дополнительного сопел равно от 5 до 50 диаметров критического сечения дополнительного сопла.A device for stabilizing combustion in a supersonic flow, comprising a main nozzle, characterized in that it is provided with a shell and a pipe with an additional nozzle for supplying liquid or gaseous fuel, located coaxially with the main nozzle, and the diameter of the critical section of the additional nozzle is from 0.1 to 0, 2 diameters of the critical section of the main nozzle, and the distance between the critical sections of the main and additional nozzles is from 5 to 50 diameters of the critical section of the additional nozzle.
RU96114573A 1996-07-18 1996-07-18 Device for stabilization of supersonic combustion RU2119118C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU96114573A RU2119118C1 (en) 1996-07-18 1996-07-18 Device for stabilization of supersonic combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU96114573A RU2119118C1 (en) 1996-07-18 1996-07-18 Device for stabilization of supersonic combustion

Publications (2)

Publication Number Publication Date
RU2119118C1 RU2119118C1 (en) 1998-09-20
RU96114573A true RU96114573A (en) 1998-10-20

Family

ID=20183485

Family Applications (1)

Application Number Title Priority Date Filing Date
RU96114573A RU2119118C1 (en) 1996-07-18 1996-07-18 Device for stabilization of supersonic combustion

Country Status (1)

Country Link
RU (1) RU2119118C1 (en)

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