FIELD: machine building.
SUBSTANCE: invention relates to engineering and can be used in testing cavities of aircraft and rocket equipment, as well as in other technology fields. Essence: the device comprises body (1) with internal cavity (2) and bore (3). Cover (4) is provided in bore (3) provided with fluid connection (5) with radial outlet (6) extending to cylindrical surface (7) of cover (4). First (8) and second (9) radial sealing rings are installed in the grooves of cover (4), sealing the radial clearances between bore (3) and cover (4). Cover (4) is axially movable relative to body (1) and fixed in two positions. In one position of cover (4), radial outlet (6) of the channel of nozzle (5) communicates with inner cavity (2) of body (1), and in another position – isolated from inner cavity (2). Bore (3) is made out of body (1) leaving inner cavity (2) and stepped. One of steps (10) of bore (3) is made with a diameter D, and other (11) – with a diameter d. Outer surface of cover (4) is also made stepped. One of steps (12) of the outer surface of cover (4) is made by the diameter D, and other (13) by the diameter d. First (8) and second (9) radial sealing rings are respectively located in first (14) and second (15) grooves made on steps (12) and (13) of cover (4). Radial outlet orifice (6) of nozzle (5) is formed in a limited diameter d of cover (4) between first (14) and second (15) grooves.
EFFECT: technical result: improving the processability of the device.
1 cl, 2 dwg
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Authors
Dates
2018-05-29—Published
2016-12-29—Filed