LIQUID-FUEL ROCKET ENGINES (CHAPTER XIX),

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Abstract:

Basic structural elements of liquid-fuel rocket engines are 1 combustion chamber, consisting of head, combustion chamber itself, and nozzle. In combustion chamber occurs burning of fuel and conversion of heat to kinetic energy of stream of gases, as a result of which jet thrust is created. In chamber complicated thermodynamic processes take place, and there are colossal heat flows 2 fuelfeed system, consisting of fuel tanks, device for forced supply of components of fuel to chamber, lines, and fittings 3 ignition system, intended to ignite fuel for starting. Engines using spontaneously inflammable fuel have no ignition system.

Author(s):
Tyutyunov, V. A. ; Lovinskii, S. I.
Author Organization(s):
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
Supplementary Note:
Edited machine trans. of mono. Aviatsionnye Dvigateli, Moscow, 1964 p310-327.
Pagination:
0021

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
FTD-MT-66-41
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means
Communities of Interest:
Weapons Technologies
Descriptor(s):
*LIQUID PROPELLANT ROCKET ENGINES, *LIQUID ROCKET FUELS, ROCKET WARHEADS, ENGINES, COMBUSTION CHAMBERS, COMBUSTION CHAMBER GASES, KINETIC ENERGY, ROCKET NOZZLES, ROCKET IGNITERS, FUEL TANKS, FUEL TANKS
Field(s)/Group(s):
Rocket Engines, Rocket Propellants
Report Date:
1966 Sep 13