FIELD: physics; measurement.
SUBSTANCE: the said invention may be used to measure nonstationary gas flow velocity. The tube pressure transducer is installed in the receiving tube, which forms a deceleration chamber inside the tube and an annular channel at the chamber outlet. Receiving tube is thin-walled with wall thickness of 0.1-0.2 mm and has a sharp irregular front edge, depth of indentations being 0.1-1.0 of the receiving tube diameter and point angle being 30° to 120°. Invention reduces measurement error of total pressure pulsations in frequency range up to 50 kHz in gradient flows, provides for high local measurement resolution and is almost insensitive to flow angularity within ±15°.
EFFECT: reduced measurement error for total pressure pulsations in frequency range up to 50 kHz in gradient flows, high local measurement resolution.
2 cl, 2 dwg
Title | Year | Author | Number |
---|---|---|---|
FULL PRESSURE RECEIVER | 2005 |
|
RU2282198C1 |
IMPACT PRESSURE PROBE | 0 |
|
SU1049813A1 |
METHOD OF MEASUREMENT OF SUPERSONIC FLOW PULSATIONS AND DEVICE FOR ITS IMPLEMENTATION (OPTIONS) | 2016 |
|
RU2638086C1 |
PROCEDURE MEASURING SPEED AND ANGLE OF RAKE OF FLOW OF LIQUID AND COMBINED RECEIVER OF SPEED AND ANGLE OF RAKE | 1997 |
|
RU2197740C2 |
HIGH-PRESSURE TUBE ( VARIANTS ) | 1998 |
|
RU2152042C1 |
PRESSURE RATIO SENSOR | 0 |
|
SU648863A1 |
METHOD FOR ARRANGEMENT OF WORKING PROCESS IN STRAIGHT-FLOW AIR-JET ENGINE WITH CONTINUOUS-DETONATION COMBUSTION CHAMBER AND DEVICE FOR IMPLEMENTATION THEREOF | 2019 |
|
RU2714582C1 |
DEVICE TO MEASURE FLOW PARAMETERS | 2014 |
|
RU2568962C1 |
MULTI-CHANNEL AEROMETER CONVERTER | 1993 |
|
RU2042137C1 |
METHOD OF AERODYNAMIC TESTING OF AIRCRAFT MODEL (VERSIONS) AND UNIT TO THIS END | 2009 |
|
RU2421702C1 |
Authors
Dates
2009-02-10—Published
2007-09-13—Filed