MULTICOMPRESSOR LIQUID-PROPELLANT ROCKET ENGINE

MULTICOMPRESSOR LIQUID-PROPELLANT ROCKET ENGINE

FIELD: mechanical engineering; engines. SUBSTANCE: rocket engine has housing in the form of cylindrical tube divided into steps, detachable units, each accommodating axial flow compressor with separate drive from rotary internal combustion engine. Each step differs in angle of inclination to longitu...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser: POPKOV IVAN IVANOVICH
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung:FIELD: mechanical engineering; engines. SUBSTANCE: rocket engine has housing in the form of cylindrical tube divided into steps, detachable units, each accommodating axial flow compressor with separate drive from rotary internal combustion engine. Each step differs in angle of inclination to longitudinal axis of compressor. Surface of compressor is divided into several similar sectors. Gradual increase in length of directing step of each blade takes place within the limits of each sector. It contributes to forming of air intake space. Rotary internal combustion engine is installed at end of last step of each compressor. Description of separate parts of engine is given in invention. EFFECT: increased economy and flight speed at simplified design and servicing. 6 dwgd