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 dwg
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|---|---|---|---|
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|
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| FUEL SYSTEM OF FOUR-STROKE INTERNAL COMBUSTION ENGINE | 1995 |
|
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| THREE-STAGE MULTIPLE-CIRCUIT COMPRESSOR | 1995 |
|
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|
RU2136974C1 |
