US3112913A - Turbine speed sensing device - Google Patents

Turbine speed sensing device Download PDF

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Publication number
US3112913A
US3112913A US803922A US80392259A US3112913A US 3112913 A US3112913 A US 3112913A US 803922 A US803922 A US 803922A US 80392259 A US80392259 A US 80392259A US 3112913 A US3112913 A US 3112913A
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United States
Prior art keywords
turbine
vane
speed
sensing device
sensing
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US803922A
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Raymond W Irwin
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Raytheon Technologies Corp
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United Aircraft Corp
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P1/00—Details of instruments
    • G01P1/07—Indicating devices, e.g. for remote indication
    • G01P1/08—Arrangements of scales, pointers, lamps or acoustic indicators, e.g. in automobile speedometers
    • G01P1/10—Arrangements of scales, pointers, lamps or acoustic indicators, e.g. in automobile speedometers for indicating predetermined speeds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/06—Arrangement of sensing elements responsive to speed
    • 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
    • G01P5/04—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 deflection of baffle-plates

Definitions

  • Turbomachinery of the type used in power conversion devices must be regulated to either provide a desirable speed range for the turbine or to prevent excessive speed thereof to prevent disintegration. Therefore, sensing the speed of rotation of the turbine is an important factor in such devices. Ordinary centrifugal speed sensing devices or electrical or electronic devices are often inadequate in that they lag in their signaling or are entirely too complex for a particular installation. '1.
  • FIG. 1 is a partial schematic and cross section of a turbine including the elements of this invention.
  • FIG. 2 is a side elevation of FIG. l illustrating schematically a motor for driving the valve controlling the iluids flowing to the turbine.
  • FIG. 1 a partial top view of an impulse turbine Wheel is illustrated.
  • the turbine wheel 10 is adapted to rotate about some predetermined axis.
  • the gases llowing through the duct 12 impinge on the bucket surfaces 14.
  • the duct 12 may include a butterfly-type valve 16 which can regulate the ilow of fluid passing through the turbine nozzles 1S.
  • the turbine nozzles 18 are formed in any desirable manner, but as shown herein, are formed by a plurality of airfoil shaped members 2o spaced -transversely on the duct 12.
  • Vane 30 is provided and is pivotally mounted at 32.
  • vane 30 is made symmetrical about its chordwise axis but need not be limited thereto.A
  • the prime importance is making the body aerodynamically shaped to afford the minimal resistance to the gaseous stream.
  • Vane 30 comprises a body portion having a convex top surface 41 and a convex bottom surface 42 each terminating to form trailing edge 44 and leading edge 46.
  • the vane is placed in a position with respect lto the turbine such that the gas discharging therefrom rst contacts the leading edge of vane 30.
  • the vane 30l may carry an upstanding arm 34 which when moved to the dotted line position illustrated can trip a switch 36.
  • the switch 36 may be utilized to energize a light ⁇ or any other suitable device In order to sense the angle 4which will indicate that a predetermined maximum speed of the turbine has been reached.
  • the turbine 10 may have the flow controlled thereto by the butterlly valve 16 and the vane 30 may have its arm 34 trip a suitable switch or other suitable electrical positioning device such that a signal is directed to a motor schematically illustrated at 40.
  • the motor 40 then may be utilized to completely shut olf the duct 12 by moving the butterfly valve 16 to its closed position.
  • the butterly valve 16 may be controlled to any desirable position such that the turbine 10 could be held at some predetermined constant speed.
  • a suitable stop 35 may be provided to prevent over travel of the vane 30.
  • a turbine means for sensing the speed of said turbine, the direction of discharge of the exhaust stream from said turbine varying with the speed thereof, a vane located in the exhaust ilow from the turbine, and means for substantially freely pivotally mounting said vane downstream of said turbine whereby the vane assumes a position parallel to the direction of exhaust ilow from the turbine, said means for mounting including a pivotal axis extending transversely of the axis of rotation of the turbine, switch means responsive to a predetermined position iof said vane providing a signal commensurate with a predetermined speed of the turbine, and means responsive to said signal for controlling an operating variable of said turbine.
  • a turbine a housing rotatably supporting said turbine having an inlet for receiving the ilow of iluid and an outlet for discharging said fluid, the angle of efllux of the discharging lluid varying with the speedrof the turbine, in combination with means for sensing the speed of said turbine, said means including a vane in the outlet having generally convexed shaped top and bottom faces dening an aerodynamically shaped body with leading and trailing edges, means for freely pivotally mounting said vane so that the leading edge faces said turbine and receives the discharging iluid, whereby the vane assumes a position in coincidence with said angle of eillux, and signal means responsive to the position of said vane for regulating theI speed of said turbine.
  • a turbine in combination, a housing rotatably supporting said turbine having an inlet for receiving ilow of fluid to rotate said turbine and an outlet discharging the lluid from thereof, the exhaust stream of said turbine varying with the speed of the turbine, a substantially symmetrical airfoil shaped body having leading and trailing edges disposed in said outlet ⁇ adjacent the turbine with the leading edge facing the direction of the discharged iluid, means for substantially freely pivotally mounting said symmetrical airfoil shaped body whereby said body assumes a posi-tion parallel to the exhaust tlow of the turbine, means for controlling the ilow of fluid to the turbine including valve means in said inlet upstream of the turbine, and means responsive to the position of said symmetrical iairfoil shaped body for regulating said controlling means.
  • a turbine a housing rotatably supporting said turbine and having lan inlet receiving llow of lluid and an outlet discharging said uid, the direction of discharge of the exhaust stream of said turbine varying with the speed thereof, in combination with means for sensing the speed of said turbine, said means including a vane in .the outlet having convexed top yand bottom surfaces defining an aerodynamic shaped body with a leading and trailing edge, means in the outlet for substantially freely pivotally mounting said vane so that the leading edge is adjacent said turbine and being disposed so that the vane assumes a position parallel to -the direction of the discharge stream from the turbine, and means connected to said vane responsive to the position thereof.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Turbines (AREA)

Description

Dec. 3, 1963 R. w. lRwlN TURBINE SPEED SENSING DEVICE Filed April 3, 1959 INVENTOR RAYMOND W- IRWIN ATTOR-NEY M7 man SWW a mw mv w 7 d/0 y? m m w l 2 millm 0 M ab. M m f m F F United States Patent Otiice l 3,112,913 Patented Dec. 3, 1963 3,112,913 TURBINE SPEED SENSING DEVICE Raymond W. Irwin, Granville, Mass., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware Filed Apr. 3, 1959, Ser. No. 803,922 4 Claims. (Cl. 253-59) This invention relates to turbines and particularly to means for sensing the speed of rotation of the turbines.
Turbomachinery of the type used in power conversion devices must be regulated to either provide a desirable speed range for the turbine or to prevent excessive speed thereof to prevent disintegration. Therefore, sensing the speed of rotation of the turbine is an important factor in such devices. Ordinary centrifugal speed sensing devices or electrical or electronic devices are often inadequate in that they lag in their signaling or are entirely too complex for a particular installation. '1.
It is therefore an object of this invention to provide a speed sensing device for -turbomachinery which is very simple, lightweight, and inexpensive.
It is a further primary object of this invention to provide a #streamlined vane pivotally mounted at the exhaust end of the turbine such that the posi-tion of the vane is an indication of the direction of flow of the lluid being emitted from the turbine.
It is 'known that the angle of elliux of the fluids being exhausted from a rotating turbine varies with the speed of the turbine. In other words, for a given velocity of iluids flowing into the inlet, there will be a particular angle of efllux of the exhaust fluid for every rotational speed of the turbine Wheel.
The above objects and advantages of this invention will become readily apparent from the following detailed description of the drawing in which:
FIG. 1 is a partial schematic and cross section of a turbine including the elements of this invention, and
FIG. 2 is a side elevation of FIG. l illustrating schematically a motor for driving the valve controlling the iluids flowing to the turbine.
Referring to FIG. 1 a partial top view of an impulse turbine Wheel is illustrated. The turbine wheel 10 is adapted to rotate about some predetermined axis. The gases llowing through the duct 12 impinge on the bucket surfaces 14. The duct 12 may include a butterfly-type valve 16 which can regulate the ilow of fluid passing through the turbine nozzles 1S. The turbine nozzles 18 are formed in any desirable manner, but as shown herein, are formed by a plurality of airfoil shaped members 2o spaced -transversely on the duct 12.
Over a range of rotational speeds of the turbine the angle of eillux of fluid from the turbine may vary between the reference line 22 at low speeds of the turbine to an angle indicated by the 4reference line 24 at extremely high speeds of the turbine. of ellux of the fluids from the turbine, a vane 30 is provided and is pivotally mounted at 32. Preferably vane 30 is made symmetrical about its chordwise axis but need not be limited thereto.A However, the prime importance is making the body aerodynamically shaped to afford the minimal resistance to the gaseous stream. Vane 30 comprises a body portion having a convex top surface 41 and a convex bottom surface 42 each terminating to form trailing edge 44 and leading edge 46. The vane is placed in a position with respect lto the turbine such that the gas discharging therefrom rst contacts the leading edge of vane 30. The vane 30l may carry an upstanding arm 34 which when moved to the dotted line position illustrated can trip a switch 36. The switch 36 may be utilized to energize a light `or any other suitable device In order to sense the angle 4which will indicate that a predetermined maximum speed of the turbine has been reached.
As shown in FIG. 2 lthe turbine 10 may have the flow controlled thereto by the butterlly valve 16 and the vane 30 may have its arm 34 trip a suitable switch or other suitable electrical positioning device such that a signal is directed to a motor schematically illustrated at 40. The motor 40 then may be utilized to completely shut olf the duct 12 by moving the butterfly valve 16 to its closed position. On the Iother hand, the butterly valve 16 may be controlled to any desirable position such that the turbine 10 could be held at some predetermined constant speed.
A suitable stop 35 may be provided to prevent over travel of the vane 30.
As a result of this invention it is readily apparent that Ian extremely simple mechanism has been provided for sensing and/or controlling the rotational speed of the turbine.
Although only one embodiment of this envention has been illustrated land described herein, it Will be apparent that various changes may be made in the construction and -arrangement of the various parts without departing from the scope of the novel concept.
What it is desired to obtain by Letters Patent is:
1. A turbine, means for sensing the speed of said turbine, the direction of discharge of the exhaust stream from said turbine varying with the speed thereof, a vane located in the exhaust ilow from the turbine, and means for substantially freely pivotally mounting said vane downstream of said turbine whereby the vane assumes a position parallel to the direction of exhaust ilow from the turbine, said means for mounting including a pivotal axis extending transversely of the axis of rotation of the turbine, switch means responsive to a predetermined position iof said vane providing a signal commensurate with a predetermined speed of the turbine, and means responsive to said signal for controlling an operating variable of said turbine.
2. A turbine, a housing rotatably supporting said turbine having an inlet for receiving the ilow of iluid and an outlet for discharging said fluid, the angle of efllux of the discharging lluid varying with the speedrof the turbine, in combination with means for sensing the speed of said turbine, said means including a vane in the outlet having generally convexed shaped top and bottom faces dening an aerodynamically shaped body with leading and trailing edges, means for freely pivotally mounting said vane so that the leading edge faces said turbine and receives the discharging iluid, whereby the vane assumes a position in coincidence with said angle of eillux, and signal means responsive to the position of said vane for regulating theI speed of said turbine.
3. A turbine, in combination, a housing rotatably supporting said turbine having an inlet for receiving ilow of fluid to rotate said turbine and an outlet discharging the lluid from thereof, the exhaust stream of said turbine varying with the speed of the turbine, a substantially symmetrical airfoil shaped body having leading and trailing edges disposed in said outlet `adjacent the turbine with the leading edge facing the direction of the discharged iluid, means for substantially freely pivotally mounting said symmetrical airfoil shaped body whereby said body assumes a posi-tion parallel to the exhaust tlow of the turbine, means for controlling the ilow of fluid to the turbine including valve means in said inlet upstream of the turbine, and means responsive to the position of said symmetrical iairfoil shaped body for regulating said controlling means.
4. A turbine, a housing rotatably supporting said turbine and having lan inlet receiving llow of lluid and an outlet discharging said uid, the direction of discharge of the exhaust stream of said turbine varying with the speed thereof, in combination with means for sensing the speed of said turbine, said means including a vane in .the outlet having convexed top yand bottom surfaces defining an aerodynamic shaped body with a leading and trailing edge, means in the outlet for substantially freely pivotally mounting said vane so that the leading edge is adjacent said turbine and being disposed so that the vane assumes a position parallel to -the direction of the discharge stream from the turbine, and means connected to said vane responsive to the position thereof.
References Cited in the file of this patent UNITED STATES PATENTS 1,655,125 Baule Jan. 3, 1928 4 Anderson June 3, MacDonald et a1. June 10, Andresen Sept. 9, Johnson May 4, Nelson Dec. 3, Dantowitz Dec. 17, York May 27, Manildi June 24, Nardone Apr. 7, Snoy Feb. 16, Pedersen Aug. 13,
FOREIGN PATENTS Great Britain Dec. 21, Germany June 30, Canada Oct. 7,

Claims (1)

1. A TURBINE, MEANS FOR SENSING THE SPEED OF SAID TURBINE, THE DIRECTION OF DISCHARGE OF THE EXHAUST STREAM FROM SAID TURBINE VARYING WITH THE SPEED THEREOF, A VANE LOCATED IN THE EXHAUST FLOW FROM THE TURBINE, AND MEANS FOR SUBSTANTIALLY FREELY PIVOTALLY MOUNTING SAID VANE DOWNSTREAM OF SAID TURBINE WHEREBY THE VANE ASSUMES A POSITION PARALLEL TO THE DIRECTION OF EXHAUST FLOW FROM THE TURBINE, SAID MEANS FOR MOUNTING INCLUDING A PIVOTAL AXIS EXTENDING TRANSVERSELY OF THE AXIS OF ROTATION OF THE TURBINE, SWITCH MEANS RESPONSIVE TO A PREDETERMINED POSITION OF SAID VANE PROVIDING A SIGNAL COMMENSURATE WITH A PREDETERMINED SPEED OF THE TURBINE, AND MEANS RESPONSIVE TO SAID SIGNAL FOR CONTROLLING AN OPERATING VARIABLE OF SAID TURBINE.
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3285567A (en) * 1963-11-29 1966-11-15 Bristol Siddeley Engines Ltd Axial flow turbines and compressors
US3318574A (en) * 1964-11-30 1967-05-09 Canadian Patents Dev Gas turbine

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1655125A (en) * 1923-12-19 1928-01-03 Baule Marie Emile Alfred Ship's log
GB302953A (en) * 1927-09-21 1928-12-21 Neil Shaw Muir Improvements in or relating to centrifugal blowers, compressors and the like
US2244479A (en) * 1940-11-18 1941-06-03 Albert F Anderson Antiswirl device
US2600309A (en) * 1950-02-14 1952-06-10 Revere Corp America Flow-responsive electrical switch means
US2609685A (en) * 1944-09-22 1952-09-09 Kollsman Instr Corp Aircraft instrument
US2677273A (en) * 1948-01-07 1954-05-04 Power Jets Res & Dev Ltd Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions
DE929668C (en) * 1940-11-17 1955-06-30 Boehler & Co Ag Geb Device for limiting the maximum speed in turbines, especially for grinding devices
US2815188A (en) * 1954-01-11 1957-12-03 Marquardt Aircraft Co Auxiliary power unit
US2816731A (en) * 1955-10-07 1957-12-17 Gen Electric Turbine speed control
US2836064A (en) * 1957-04-24 1958-05-27 Edward P York Remote rotational displacement indicators
US2839922A (en) * 1955-08-10 1958-06-24 G M Giannini & Co Inc Airstream direction indicator
CA564433A (en) * 1958-10-07 U. Weber Paul Overspeed control for full admission impulse turbines
US2880578A (en) * 1956-04-27 1959-04-07 Romeo M Nardone Starting system for engines for jet aeroplanes
US2924941A (en) * 1956-04-13 1960-02-16 Gen Motors Corp Hydrokinetic torque converter having reactor blade pitch regulator
US3100622A (en) * 1959-04-07 1963-08-13 Onsrud Machine Works Inc Turbine governor

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA564433A (en) * 1958-10-07 U. Weber Paul Overspeed control for full admission impulse turbines
US1655125A (en) * 1923-12-19 1928-01-03 Baule Marie Emile Alfred Ship's log
GB302953A (en) * 1927-09-21 1928-12-21 Neil Shaw Muir Improvements in or relating to centrifugal blowers, compressors and the like
DE929668C (en) * 1940-11-17 1955-06-30 Boehler & Co Ag Geb Device for limiting the maximum speed in turbines, especially for grinding devices
US2244479A (en) * 1940-11-18 1941-06-03 Albert F Anderson Antiswirl device
US2609685A (en) * 1944-09-22 1952-09-09 Kollsman Instr Corp Aircraft instrument
US2677273A (en) * 1948-01-07 1954-05-04 Power Jets Res & Dev Ltd Turbine, compressor, or like rotary machine having a pivoted indicator blade responsive to operating conditions
US2600309A (en) * 1950-02-14 1952-06-10 Revere Corp America Flow-responsive electrical switch means
US2815188A (en) * 1954-01-11 1957-12-03 Marquardt Aircraft Co Auxiliary power unit
US2839922A (en) * 1955-08-10 1958-06-24 G M Giannini & Co Inc Airstream direction indicator
US2816731A (en) * 1955-10-07 1957-12-17 Gen Electric Turbine speed control
US2924941A (en) * 1956-04-13 1960-02-16 Gen Motors Corp Hydrokinetic torque converter having reactor blade pitch regulator
US2880578A (en) * 1956-04-27 1959-04-07 Romeo M Nardone Starting system for engines for jet aeroplanes
US2836064A (en) * 1957-04-24 1958-05-27 Edward P York Remote rotational displacement indicators
US3100622A (en) * 1959-04-07 1963-08-13 Onsrud Machine Works Inc Turbine governor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3285567A (en) * 1963-11-29 1966-11-15 Bristol Siddeley Engines Ltd Axial flow turbines and compressors
US3318574A (en) * 1964-11-30 1967-05-09 Canadian Patents Dev Gas turbine

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