Measuring and testing – Volume or rate of flow – Using turbine
Patent
1990-11-06
1992-05-05
Goldstein, Herbert
Measuring and testing
Volume or rate of flow
Using turbine
7386192, G01F 112
Patent
active
051097052
DESCRIPTION:
BRIEF SUMMARY
FIELD OF THE INVENTION
The present invention relates to mechanical engineering and has specific reference to a turbine rate-of-flow transducer.
DESCRIPTION OF THE PRIOR ART
Widely known is a turbine rate-of-flow transducer (JP; a: 52-25,748) in a cylindrical body whereof there are consecutively located in the cocurrent direction a first flow straightener, a means of balancing an axial force of the flow, a rotor and a second flow straightener. Each of the flow straighteners is a fairing which faces the oncoming flow stream in a coaxial position relative to the body and is fitted with radial fins secured to the body. The means of balancing the axial force is a truncated cone, the small base whereof interacts with an end face of the first fairing. In the side surface of the means of balancing the axial force, there are provided passages which are spaced equidistantly apart all the way along the circumference and extend parallel to the generatices. The rotor is fitted with provision for revolving in the body in a coaxial position therewith. A pickup generating a pulse each time a vane tip passes is fitted to the body in the zone of the motor.
The prior art transducer is adapted to measure the flow rate of fluids with a variable viscosity. However, the rectilinear passages provided in the means of balancing the axial force are a disadvantage, for they fail to form a fully-developed velocity profile and set up an adequate turbulence which would give rise to a transition Reynolds number causing the rotor to operate under the conditions of self-similarity when a linearization of the static characteristic of the transducer takes place and the effect of a changeable viscosity is at a minimum. Poor accuracy and a short range of measurements are therefore unavoidable.
SUMMARY OF THE INVENTION
The principal object of the invention is to provide a turbine rate-of-flow transducer wherein features of the design of the means of balancing the axial force of the flow would ensure a comparatively high accuracy of measurements under conditions of a flow rate and viscosity varying over a wide range.
This object is realized by a turbine rate-of-flow transducer incorporating a cylindrical body consecutively located wherein in the cocurrent direction there are a first flow straightener, which is a fairing facing the oncoming flow stream in a coaxial position relative to the body and having radial fins attached to the body; a means of balancing the axial force of the flow, which is a truncated cone the small base whereof interacts with an end face of the fairing and in the side surface whereof there are made passages spaced equidistantly apart all the way along the circumference; a rotor fitted with provision for revolving in the body in a coaxial position therewith; a second flow straightener, which is located symmetrically relative to an axis extending at right angles to an axis of revolution of the rotor and is identical with the first flow straightener: and, a pickup which is fitted to the body in the zone of the rotor and generates a pulse each time a vane tip passes. According to the invention every passage in the means of balancing the axial force of the flow is directed so that a projection of a longitudinal axis thereof on a plane through the axis of revolution of the rotor makes with this axis an angle between 7.degree. and 20.degree., the vertex whereof being pointed towards the vertex of an angle inclined whereat are the rotor vanes, and the aggregate cross-sectional area of the passages in the zone of the large base of the means of balancing is between 2% and 6% of the area of flow section at the inlet into the rotor.
To minimize the drag of the rotor vanes, ensure an impactless entry of the mainstream into the rotor and reduce the moment of the forces of viscous friction at the inlet into the rotor, it is expedient that the leading edge of each rotor vane is formed by two planes making with each other an angle between 2/3(90.degree.-.gamma.) and (90.degree.-.gamma.), where .gamma. is the angle which the vanes o
REFERENCES:
patent: 3238776 (1966-03-01), Potter
patent: 3248943 (1966-05-01), Francisco, Jr.
patent: 3757578 (1973-09-01), Clinton
patent: 4242916 (1981-01-01), Amemori et al.
patent: 4790195 (1988-12-01), Feller
Aprakin Alexandr S.
Drobakh Viktor T.
Masyagutov Robert G.
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