US2316021A - Air log - Google Patents

Air log Download PDF

Info

Publication number
US2316021A
US2316021A US406015A US40601541A US2316021A US 2316021 A US2316021 A US 2316021A US 406015 A US406015 A US 406015A US 40601541 A US40601541 A US 40601541A US 2316021 A US2316021 A US 2316021A
Authority
US
United States
Prior art keywords
impeller blade
shaft
hub
hub portion
impeller
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US406015A
Inventor
Edward V Rippingille
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Motors Liquidation Co
Original Assignee
Motors Liquidation Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Priority to US406015A priority Critical patent/US2316021A/en
Application granted granted Critical
Publication of US2316021A publication Critical patent/US2316021A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
    • G01F1/05—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects
    • G01F1/10—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects using rotating vanes with axial admission
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
    • G01P5/02—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring forces exerted by the fluid on solid bodies, e.g. anemometer
    • G01P5/06—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring forces exerted by the fluid on solid bodies, e.g. anemometer using rotation of vanes
    • G01P5/07—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring forces exerted by the fluid on solid bodies, e.g. anemometer using rotation of vanes with electrical coupling to the indicating device

Definitions

  • This invention relatesto i'devices having an impeller .which is driven by lluid flow.
  • It relates especially to uid flow meters, distance logs or odometers and the like, in lwhich the speed at which the impeller is driven is used as a measure of the rate of fluid flow.
  • Such instruments are desirably small and lightly constructed, -with impeller blades which are conveniently sheet steel stampings.
  • the object of the invention is a means of adjusting the performance of such a device to a given standard.
  • a more specific object of the invention is a means of adjusting the pitch of the impeller so that the instrument will conform to the desired standard of response.
  • screw means are provided for adjusting the pitch of the impeller yblade by bending deflection of its hub portion in a direction longitudinally of its supporting shaft, in a Iplane containing the shaft axis and normal to the center line of the impeller blade.
  • the drawing shows the application of the invention to an air log for measuring the distance traversed by an airplane relatively to the ambient a1r.
  • Figure 1 is a View of the device in part-sectional elevation.
  • Figure 2 is a View on line 2 2 of Figure 1.
  • Figure :3 is a view on line 3-3 of Figure l.
  • Figure 4 is a sectional view on line 4-4 of Figure 1.
  • Figure 5 is an enlarged View of part of Figure 4 showing the manner in which the pitch off the impeller blade is adjusted by bending deflection of its hub portion.
  • the impeller blade I has a hub portion 2, secured to a hub l3, on a shaft 4 which has end pivots supported in adjustable jewel bearings 5 and l6 in a housing 1 and a housing 8 respectively, which are connected together by a U- shaped .portion lo whichwin not interfere with turning of the impeller blade.
  • That portion of the shaft 4 within the housing 1 is provided with a worm I2, engaging a worm Wheel I4, on a cross shaft I5, on which there is a cam I6 which lifts the spring arm Il of a point I8 of a conta-ct breaker away from a stationary point I9 thereof, once for a definite number of revolutions of the shaft 4.
  • the points I8 and I9 of the contact breaker are arranged to make and break an electrical circuit through an electromagnetic counter (not shown), and since the number of revolutions of the shaft 4 is proportionate to the rate of air flow driving the impeller, the distance traversed relatively to the air by an airplane on which the air log may be mounted will be indicated by the counter reading, provided the instrument is properly calibrated. Calibration can be effected by comparison and adjustment of the device to a known standard in a wind tunnel or in any other suitable way.
  • the instrument is provided with only one impeller blade, and its circular hub portion 2 is secured to the hub 3 by two rivets 22 and 23, at spaced points along a line parallel to and removed from the center line of the impeller blade on one side of aplane -b containing the shaft axis and the center line of the impeller blade, as shown most clearly in Figure 2.
  • the hub 3 is chamfered at 25 and scooped away at 26 to remove weight to balance the rotor assembly about the shaft axis in the manner shown best in Figures 1 and 3.
  • a screw 28 is in screw threaded engagement with the hub 3 on that side of the plane a-b of Figure 2 opposite tothe rivets 2 Zand 23, and adjustably extends therethrough, parallel to the shaft 4, to bear against the hub portion 2 of the impeller blade.
  • the screw 28 provides for the required delicate adjustment of the pitch of the impeller blade. As shown in Figure 5, it may be screwed through the hub 3 to bend the hub portion 2 away from the hub 3 and thereby adjust the pitch of the blade.
  • a spring 30 is provided as a backing for the hub portion of the impeller blade. As shown, the spring 30 is secured to the hub 3 by the rivets 22 and 23 with the hub portion 2 of the impeller blade therebetween. It serves to resiliently oppose bending deflection of the hub portion of the impeller blade, to hold it against the screw 28, and to return it to its original ilat position against the face of the hub 3 upon retraction of the screw 28, in the event that the material of the hub portion of the impeller blade is insuiciently springy to assure this.
  • a shaft an impeller blade with a bendable hub portion extending substantially normal to the axis of said shaft on opposite sides of a plane containing the shaft axis and the center line of the impeller blade, said hub portion of the impeller blade being attached to the shaft only on one side of said plane along a line parallel to and removed from the center line of the impeller blade, and screw means on the other side of said plane for adjusting the pitch of the impeller blade by bending deflection of its hub portion about its line of at'- tachment to the shaft.
  • the screw adjusting means including a screw in screw threaded engagement with one of said hubs and adjustably extending therethrough, parallel with said shaft, to exert a thrust on the other of said hubs, whereby the bendable hub portion of the impeller blade is bent to effect the required adjustment of the pitch thereof.

Description

April 6, 1943. E. v. RIPPINGILLE 2,316,021
` AIR LoG Filed Aug. 8, 1941 "IIS,
Bu 4 MEV;- Gttornegs Stwentor u Patented Apr. 6, 1943 VfRippingille, DetroitfMich., assignor to A,(reneral- Motors Corporation, Detroit, Mich., a
corporation of Delaware ll'AipliatimiAugust s, 1941, seria1No.4os,o`15
., 4 Claims.
This invention relatesto i'devices having an impeller .which is driven by lluid flow.
It relates especially to uid flow meters, distance logs or odometers and the like, in lwhich the speed at which the impeller is driven is used as a measure of the rate of fluid flow.
More specifically, it relates to impeller blades in air logs for measuring the distance which.
an object traverses relatively to the air.
Such instruments are desirably small and lightly constructed, -with impeller blades which are conveniently sheet steel stampings.
While such instruments can be produced within reasonable tolerance limits, the blades particularly are too fragile to permit manufacture and assembly Within sufliciently close limits to insure duplication of performance characteristics of the assembly, and some means of adjustment for accuracy is necessary.
The object of the invention is a means of adjusting the performance of such a device to a given standard.
A more specific object of the invention is a means of adjusting the pitch of the impeller so that the instrument will conform to the desired standard of response.
The above and other objects of the invention will be apparent as the description proceeds.
According to the invention, screw means are provided for adjusting the pitch of the impeller yblade by bending deflection of its hub portion in a direction longitudinally of its supporting shaft, in a Iplane containing the shaft axis and normal to the center line of the impeller blade.
The drawing shows the application of the invention to an air log for measuring the distance traversed by an airplane relatively to the ambient a1r.
In the drawing:
Figure 1 is a View of the device in part-sectional elevation.
Figure 2 is a View on line 2 2 of Figure 1.
Figure :3 is a view on line 3-3 of Figure l.
Figure 4 is a sectional view on line 4-4 of Figure 1.
Figure 5 is an enlarged View of part of Figure 4 showing the manner in which the pitch off the impeller blade is adjusted by bending deflection of its hub portion.
The impeller blade I has a hub portion 2, secured to a hub l3, on a shaft 4 which has end pivots supported in adjustable jewel bearings 5 and l6 in a housing 1 and a housing 8 respectively, which are connected together by a U- shaped .portion lo whichwin not interfere with turning of the impeller blade.
That portion of the shaft 4 within the housing 1 is provided with a worm I2, engaging a worm Wheel I4, on a cross shaft I5, on which there is a cam I6 which lifts the spring arm Il of a point I8 of a conta-ct breaker away from a stationary point I9 thereof, once for a definite number of revolutions of the shaft 4.
The points I8 and I9 of the contact breaker are arranged to make and break an electrical circuit through an electromagnetic counter (not shown), and since the number of revolutions of the shaft 4 is proportionate to the rate of air flow driving the impeller, the distance traversed relatively to the air by an airplane on which the air log may be mounted will be indicated by the counter reading, provided the instrument is properly calibrated. Calibration can be effected by comparison and adjustment of the device to a known standard in a wind tunnel or in any other suitable way.
As shown, the instrument is provided with only one impeller blade, and its circular hub portion 2 is secured to the hub 3 by two rivets 22 and 23, at spaced points along a line parallel to and removed from the center line of the impeller blade on one side of aplane -b containing the shaft axis and the center line of the impeller blade, as shown most clearly in Figure 2.
The hub 3 is chamfered at 25 and scooped away at 26 to remove weight to balance the rotor assembly about the shaft axis in the manner shown best in Figures 1 and 3.
A screw 28 is in screw threaded engagement with the hub 3 on that side of the plane a-b of Figure 2 opposite tothe rivets 2 Zand 23, and adjustably extends therethrough, parallel to the shaft 4, to bear against the hub portion 2 of the impeller blade.
The screw 28 provides for the required delicate adjustment of the pitch of the impeller blade. As shown in Figure 5, it may be screwed through the hub 3 to bend the hub portion 2 away from the hub 3 and thereby adjust the pitch of the blade.
A spring 30 is provided as a backing for the hub portion of the impeller blade. As shown, the spring 30 is secured to the hub 3 by the rivets 22 and 23 with the hub portion 2 of the impeller blade therebetween. It serves to resiliently oppose bending deflection of the hub portion of the impeller blade, to hold it against the screw 28, and to return it to its original ilat position against the face of the hub 3 upon retraction of the screw 28, in the event that the material of the hub portion of the impeller blade is insuiciently springy to assure this.
I claim:
1. In a device driven by fluid ow, a shaft, an impeller blade with a bendable hub portion extending substantially normal to the axis of said shaft on opposite sides of a plane containing the shaft axis and the center line of the impeller blade, said hub portion of the impeller blade being attached to the shaft only on one side of said plane along a line parallel to and removed from the center line of the impeller blade, and screw means on the other side of said plane for adjusting the pitch of the impeller blade by bending deflection of its hub portion about its line of at'- tachment to the shaft.
2. The combination according to claim 1, in which the hub portion of the impeller blade is secured to a rigid hub on the shaft, the screw adjusting means including a screw in screw threaded engagement with one of said hubs and adjustably extending therethrough, parallel with said shaft, to exert a thrust on the other of said hubs, whereby the bendable hub portion of the impeller blade is bent to effect the required adjustment of the pitch thereof.
3. The combinationV according to claim 1 in which the hub portion of the impeller blade is secured to a rigid hub on the shaft, the screw adjusting means including a screw in screw threaded engagement with said rigid hub and adjustably extending therethrough to exert a thrust on the hub portion of the impeller blade, whereby the latter is bent to eiect the required adjustment of the pitch thereof.
4. The combination according to claim 1 in which bending deflection of the hub portion of the impeller blade by the screw means is opposed by spring means secured to said shaft.
EDWARD V. RIPPINGILLE.
US406015A 1941-08-08 1941-08-08 Air log Expired - Lifetime US2316021A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US406015A US2316021A (en) 1941-08-08 1941-08-08 Air log

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US406015A US2316021A (en) 1941-08-08 1941-08-08 Air log

Publications (1)

Publication Number Publication Date
US2316021A true US2316021A (en) 1943-04-06

Family

ID=23606181

Family Applications (1)

Application Number Title Priority Date Filing Date
US406015A Expired - Lifetime US2316021A (en) 1941-08-08 1941-08-08 Air log

Country Status (1)

Country Link
US (1) US2316021A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060120859A1 (en) * 2002-07-23 2006-06-08 Fabien Cens Impeller device for data acquisition in a flow

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060120859A1 (en) * 2002-07-23 2006-06-08 Fabien Cens Impeller device for data acquisition in a flow
US7351034B2 (en) * 2002-07-23 2008-04-01 Schlumberger Technology Corporation Impeller device for data acquisition in a flow

Similar Documents

Publication Publication Date Title
US3514997A (en) Airstream direction detector
US2198055A (en) Float-operated liquid level gauge
US2316021A (en) Air log
US3368283A (en) Indicator feeler biasing and reversible means
US2465775A (en) Altimeter
US2619933A (en) Adjustable torque and deflection control mechanism for indicating instruments
US1891134A (en) Indicating apparatus
US2287299A (en) Dynamometer
US2638680A (en) Averaging protractor for matching aircraft propeller blades
US2627401A (en) Speed cup bias spring
US3011351A (en) Speedometer
US2979948A (en) Fluid flow meter
US2032306A (en) Pointer mounting arrangement for
US3224269A (en) Device for indicating wind direction and measuring wind speed
US2677589A (en) Eccentric index arm for measuring instruments
US2922632A (en) Accelerometer
US2227514A (en) Gauge
US2196932A (en) Pressure responsive indicating instrument
US2792802A (en) Indicating means useable per se and as part of length-measuring instruments and gages
US2691305A (en) Barometric altimeter
US3205698A (en) Torque measuring means
US2272988A (en) measuring instrument
US2749623A (en) La barre
US2924883A (en) Deflection measuring device
US2887084A (en) Speedometer