| 摘要 |
FIELD: power plants for aero-space aeroplanes; winged missiles. SUBSTANCE: engine has straight-flow combustion chamber and liquid propellant supply system. Central body with turbo-pump unit arranged in it is mounted coaxially relative to straight-flow combustion chamber. Turbo-pump unit includes axial-flow gas turbine and group of high-pressure centrifugal pumps with parallel delivery of fuel mounted on common shaft. Located around impellers of pumps are concentric fuel manifolds where bands of jet liquid injectors are provided at shifted pitch. Injectors may be made in form of tangential bores in walls of manifolds. Turbine is located after pumps in way of flow. EFFECT: improved power characteristics of engine. 3 cl, 3 dwgt
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