FIELD: aviation.
SUBSTANCE: invention relates to testing of aircraft and rocket equipment. Installation for gas-dynamic tests contains test chamber (1) and a gas flow generator (7). Gas flow generator (7) accommodates ejector (25) with first-stage active medium channel (26) with supersonic nozzle (27) and first-stage mixing chamber (28) connected by inlet (8) to high-pressure line (4). Concentric to channel (26) there is annular collector (29) of passive medium connected by its inlet to oxygen supply system (14), and by annular channel (30) of passive medium to mixing chamber (28) of the first stage. Annular collector (31) and annular channel (32) of the active medium of the second stage are located concentrically to annular channel (30) of the passive medium. Annular channel (32) is interconnected with the second stage mixing chamber (33), annular collector (31) of the second stage is connected to the fuel supply system (16). Supersonic nozzle (34) is installed in annular channel (32) of the active medium of the second stage, mixing chamber (33) of the second stage is interconnected with combustion chamber (11).
EFFECT: uniform distribution of oxygen and fuel particles in the compressed air flow fed into the combustion chamber.
1 cl, 1 dwg
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Authors
Dates
2022-03-17—Published
2020-08-25—Filed