Engineering, 01.02.2021 20:50 brookedeanovich
A Russian rocket engine (RD-110 with LOX-kerosene) consists of four thrust chambers supplied by a single turbopump. The exhaust from the turbine of the turbopump then is ducted to four vernier nozzles (which can be rotated to provide some control of the flight path). Using the information below, determine the thrust and mass flow rate of the four vernier gas nozzles. For individual thrust chambers (vacuum): F= 73.14 kN, c = 3279 m/sec Overall engine with verniers (vacuum): F= 297.93 kN, c = 3197 m/sec.
Answers: 3
Engineering, 04.07.2019 18:10
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Engineering, 04.07.2019 18:20
Wiy doeres rere okhn a pump whon working betwon the same pressure range?
Answers: 2
A Russian rocket engine (RD-110 with LOX-kerosene) consists of four thrust chambers supplied by a si...
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