Turbine wheel flow measuring transducer

• US 4,467,660 A
• Filed: 03/29/1982
• Issued: 08/28/1984
• Est. Priority Date: 03/29/1982
• Status: Expired due to Term

• Current Assignee: Robert D. Mcmillan Jr
• Original Assignee: Robert D. Mcmillan Jr
• Inventors: McMillan, Robert D. Jr.
• Primary Examiner(s): Ruehl, Charles A.
• Application Number:
  US06/362,889
• Time in Patent Office: 883 Days
• Field of Search: 73/861.77, 73/861.87, 73/861.88, 73/861.33, 73/861.79, 128/726
• US Class Current: 73/861.87
• CPC Class Codes: G01F 1/065 with radiation as transfer means to the indicating device, e.g. light transmission

Abstract

A turbine wheel flow measuring transducer having a reaction turbine wheel measures low flow rates of a gas. A disk (D) is rotatably mounted in a chamber (C) formed within a housing (H) through which the gas to be measured passes through a nozzle assembly (N). Plural teeth (T) are formed around the periphery of disk (D) for receiving the impact of the gas from nozzle assembly (N). A photoelectric circuit (P) directs light onto side portions of disk (D) to measure the relative movement of disk (D) in response to the impact of the gas against teeth (T).

Claims

1. An apparatus for measuring low flow rates of gas at pressure drops in the order of twenty inches of water pressure or less, and at flow rates in the order of twenty milliliters per minute to ten thousand milliliters per minute, comprising:

a housing having a chamber through which the gas to be measured passes;

a disk rotatably mounted about a center thereof in said chamber;

said disk having reaction turbine blades formed around the entire periphery thereof, said blades located on a spacing of ten to twenty degree segments about said central axis of said disk, each blade having an impact surface thereon for receiving the impact of said gas entering said chamber;

nozzle means mounted in said housing in a plane substantially parallel to the plane wherein said disk is disposed for directing substantially the entire flow of the gas entering said chamber sequentially against individual ones of said impact surfaces at velocities between five to twenty feet per second, thereby presenting the adjacent impact surface;

photoelectric circuit means for directing light onto side portions of said disk and measuring relative movement thereof in response to impact of the gas against said impact surfaces; and

said disk further having reflecting surfaces formed on side portions thereof for reflecting light directed from said photoelectric circuit means.

2. The apparatus of claim 1 including said reaction turbine blades having a trailing surface formed at an acute angle of about 30 degrees to a tangent of said disk to permit said impact surfaces to continue to receive gas from said nozzle during movement away therefrom.

3. The apparatus of claim 1 wherein:

said nozzle means is mounted at an acute angle with respect to said impact surfaces to direct the gas thereagainst.

4. The apparatus of claim 1, wherein said impact surfaces are formed along a radial line extending from said center of said disk.

5. The apparatus of claim 1, wherein said impact surfaces are formed along a portion of a radial line extending from said center of said disk.

6. The apparatus of claim 1 including said disk having a centrally disposed axle having a pivotal tip for supporting said disk for rotatable movement and further including removable carriage means for mounting said disk in said chamber, said carriage means having bearing surfaces for rotatably mounting said axle.

7. The apparatus of claim 6 including said carriage means having said nozzle means mounted therewith for directing the gas against said impact surface on each of said blades on said disk.

8. The apparatus of claim 1, wherein:

said nozzle means is interchangeable in said housing thereby allowing a variation in the range of flow rates to be measured.

9. The apparatus of claim 1 wherein:

said reflective surfaces extend to an angle substantially ninety degrees on the side of said disk, said reflective surfaces being equally spaced on said disk.

10. A rotatable apparatus for measuring low gas flow rates in the order of twenty milliliters per minute to ten thousand milliliters per minute at pressure drops in the order of twenty inches of water pressure or less in a flow meter of the type which includes a housing having a chamber through which the gas to be measured passes and a photoelectric circuit for measuring relative movement of said apparatus as the gas passes through the housing, said apparatus comprising:

a disk adapted to be rotatably mounted in the chamber;

plural reaction turbine blades formed around the entire periphery of said disk for receiving the impact of substantially the entire flow of gas entering the chamber in a direction parallel to the plane wherein said disk is disposed sequentially against individual ones of said blades thereby presenting the adjacent blade; and

,

reflective surfaces formed on portions of said disk for reflecting light directed from the photoelectric circuit.

11. The apparatus of claim 10 including said turbine blades having a trailing surface formed at an acute angle to a tangent of said disk to permit said turbine blades to continue to receive gas during rotation of said disk.

12. The apparatus of claim 11, wherein said turbine blades are formed along a radial line extending from said center of said disk.

13. The apparatus of claim 11, wherein said impact surfaces are formed along a portion of a radial line extending from said center of said disk.

14. The apparatus of claim 10 wherein:

said reflective surfaces extend to an angle substantially ninety degrees on the side of said disk, said reflective surfaces being equally spaced on said disk.

15. A rotatable disk assembly for measuring low gas flow rates in a flow meter of the type which includes a housing having a chamber through which the gas to be measured passes and a photoelectric circuit for forming an output proportional to the gas flow rate, said assembly comprising:

a disk having a centrally disposed axle having a pivotal tip to support said disk for rotatable movement;

turbine blades formed around the entire periphery of said disk for receiving substantially the entire flow of gas entering the chamber in a direction parallel to the plane wherein said disk is disposed on a spacing of ten to twenty degree segments about said central axis of said disk;

reflective surfaces formed on portions of said disk for reflecting light directed from the photoelectric circuit;

removable carriage means for mounting said disk in the chamber;

said carriage means having bearing surfaces for rotatably mounting said axle; and

said carriage means having a removably mounted nozzle assembly for directing the impact of the gas sequentially against individual ones of said turbine blades at a controlled location, thereby presenting the adjacent turbine blade, and permitting nozzle assemblies of varying sizes to be mounted in said carriage means to effectively vary the sensitivity of the assembly to gas flows.

16. The assembly of claim 15, wherein:

said disk is 0.03 inches thick or less.

17. The assembly of claim 15, wherein:

said blades extend to a height of approximately 10% of the radius of said disk.

18. The assembly of claim 15 wherein:

said reflective surfaces extend to an angle substantially ninety degrees on the side of said disk, said reflective surfaces being equally spaced on said disk.