US2407115A - Governor - Google Patents

Governor Download PDF

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Publication number
US2407115A
US2407115A US561777A US56177744A US2407115A US 2407115 A US2407115 A US 2407115A US 561777 A US561777 A US 561777A US 56177744 A US56177744 A US 56177744A US 2407115 A US2407115 A US 2407115A
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Prior art keywords
speed
chamber
valve
pressure
passage
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Expired - Lifetime
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US561777A
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Stanley M Udale
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16Control of working fluid flow
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00Fluid handling
    • Y10T137/7722Line condition change responsive valves
    • Y10T137/7781With separate connected fluid reactor surface
    • Y10T137/7784Responsive to change in rate of fluid flow
    • Y10T137/7787Expansible chamber subject to differential pressures
    • Y10T137/7789With Venturi tube having a connection to throat

Definitions

  • the object er this invention is te govern the u flow of liquid fuel to a burner in a gas turbine.
  • the figure shows diagrammatically the elements of my invention.
  • Pump A of positive displacement circulates a liquid through a venturi B.
  • the pressure onA the upstream side of the venturi B acts on the chamber V ⁇ below diaphragm Cthrough passage X.
  • the relative suction in the venturi B actson the chamber U on the upper side of diaphragm D through the passage Y.
  • the chambers E and F are normally at the same pressure -dueto the leakage between the two through the opening Z.
  • a valve G is drawn by the suction transmitted through pipe S to the right against a spring R to the position shown in the drawing. This allows the pressure from the pump A to enter the chamber E below the diaphragm D so that the diaphragms C and D are both Operated by the full pressure diierence.
  • a bypass H-K downstream of the venturi B is controlled by a spring-loaded valve J and thus cooperates with a throttle valve O controlled by a lever N.
  • a balanced valve L controlled by a lever M is operated by a link P connected to the two diaphragms C and D.
  • the outlet from the venturi B is in free communication with the passage A1.
  • the outlet chamber Az on the downstream side of the valve L is in free communi cation with the passage A3, which is in communication with the outlet lpassage A4, through the valve O.
  • the fuel regulated by the balanced valve L ilows Vinto a chamber A5 where it is consumed.
  • the pump A which is driven by the turbine combination, rotates at some speed proportionate to the speed of the gas turbine.
  • the throttle lever N is moved so that valve O is opened suddenly, and the pump A accelerates ,as the engine picks up speed; the flow through the venturi B therefore also accelerates.
  • the suction acting on the right of valve G causes valve G to assume the position Ishown in the drawing.
  • the pressure in V below the diaphragm C (which equals pressure upstream of the venturi B) is thus applied to the bottoms of both the diaphragms C and D.
  • the suction (relative) in the throat of the venturi B is applied to chambers U and F-that is to the upper surfaces of both diaphragms C and D.
  • the link P rotates the lever M and thus closes the balanced valve L and temporarily checks the rate of increase in iiow and thus in speed.
  • the valve G is pushed by its spring to the left.
  • the pressure in the two chambers E and F is equalized by the leakage past the annular opening Z.
  • the loW pressure in the chamber above the diaphragm D then is the only force governing the speed.
  • the spring Q thus governs the normal speed of rotation oi the pump A, but the governor acts faster when accelerated.
  • chambers E and F also are subjected to the suction in the venturi B but in the interim the suction in the chambers E and F is less than the low suction instantly applied to the chamber U because of the fact that the c-ommunication between the chamber F and the passage Y is past the adjustable needle valve W, that is it is restricted and the communication between the chamber F and the chamber E is through the very restricted annular passage Z.
  • the valve G is moved away from the stop T against which it is normally pressed by the spring R and the valve G is thus moved into the position in which it is shown in the drawing. In this position the pressure in the chamber V is transmitted directly to the chamber E past the valve G and to the chamber F through the very restricted passage Z.
  • the volume decrease of the chamber U has no in iuence on the pressure in the chamber U.
  • the governor anticipates the ultimate increase in speed so that before the increased governor speed has been reached the governor valve L has already started to move so that it can be moved into its ultimate position before the power plant has exceeded the desired speed.
  • the adjustment W when closed prevents the governor anticipating the change in speed.
  • the degree of anticipation can be regulated.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of The Air-Fuel Ratio Of Carburetors (AREA)

Description

Patented Sept. 3, 1946 `2,407,115 GOVERNOR Stanley M. Udale, Detroit, Mich., assigner to George M. Holley and Earl Holley Application November a, 1944, serial No. 561,777
' l1 claim. (c1. 15s-36.4)
The object er this invention is te govern the u flow of liquid fuel to a burner in a gas turbine.
It is desirable that the speed shall not "exceed the governed speed. If the turbine is acceleratn ed, the speed will naturally exceed the governed speed unless the governor can be madeto anticipate the Ispeed increase. T
To arrive at an increase in speed, it is necessary to have a period when speed is increasing. During this period, it is desirable to utilize the rate of increase in speed to check the speed. Il' the speed is increased gradually, no problem exists. I-f the speed is increased rapidly, a serious problem is presented due tothe fact that the means to check the speed will only comeinto ac` tion when the desired speed has been reached. During the interval of time which the governor takes to become active, the speed will rise above the desired maximum speed.
The figure shows diagrammatically the elements of my invention.
Pump A of positive displacement circulates a liquid through a venturi B. The pressure onA the upstream side of the venturi B acts on the chamber V `below diaphragm Cthrough passage X.
The relative suction in the venturi B actson the chamber U on the upper side of diaphragm D through the passage Y. The chambers E and F are normally at the same pressure -dueto the leakage between the two through the opening Z. However, when the speed changes, there is a sudden increase in suction inthe chamber U above diaphragm D, and a valve G is drawn by the suction transmitted through pipe S to the right against a spring R to the position shown in the drawing. This allows the pressure from the pump A to enter the chamber E below the diaphragm D so that the diaphragms C and D are both Operated by the full pressure diierence.
When the speed becomes stable, however, the valve G i-s pushed to the left against the stop T by the spring R, and the pressure in the cham-- bers E and F equalizes through the leakage path Z provided.
A bypass H-K downstream of the venturi B is controlled by a spring-loaded valve J and thus cooperates with a throttle valve O controlled by a lever N. A balanced valve L controlled by a lever M is operated by a link P connected to the two diaphragms C and D. The outlet from the venturi B is in free communication with the passage A1. The outlet chamber Az on the downstream side of the valve L is in free communi cation with the passage A3, which is in communication with the outlet lpassage A4, through the valve O. The fuel regulated by the balanced valve L ilows Vinto a chamber A5 where it is consumed. rlhe products of combustion flow to a chamber Ae, which contains a gas turbine which drives a belt Av, which drives the pump A at a speed proportional to engine speed. A spring Q is provided to balance the effect of the flow through the venturi B. An adjustment W is provided. The restriction formed around the end of the needle W delays the pressure drop in the throat `of the venturi B, being transmitted to the chamber F quite as quickly as this drop in pressure is transmitted through the pipe Y to the chamber U.
Operation The pump A, which is driven by the turbine combination, rotates at some speed proportionate to the speed of the gas turbine. Let us assume that the throttle lever N is moved so that valve O is opened suddenly, and the pump A accelerates ,as the engine picks up speed; the flow through the venturi B therefore also accelerates. The suction acting on the right of valve G causes valve G to assume the position Ishown in the drawing. The pressure in V below the diaphragm C (which equals pressure upstream of the venturi B) is thus applied to the bottoms of both the diaphragms C and D. The suction (relative) in the throat of the venturi B is applied to chambers U and F-that is to the upper surfaces of both diaphragms C and D.
Hence, the link P rotates the lever M and thus closes the balanced valve L and temporarily checks the rate of increase in iiow and thus in speed. When the acceleration period is over, the valve G is pushed by its spring to the left. The pressure in the two chambers E and F is equalized by the leakage past the annular opening Z. The loW pressure in the chamber above the diaphragm D then is the only force governing the speed. The spring Q thus governs the normal speed of rotation oi the pump A, but the governor acts faster when accelerated. When the flow of fuel is accelerated by the sudden opening of valve O, the suction due to the increased flow of fuel through the venturiV B is transmitted instantly through the unobstructed passage Y to the chamber U. Subsequently, chambers E and F also are subjected to the suction in the venturi B but in the interim the suction in the chambers E and F is less than the low suction instantly applied to the chamber U because of the fact that the c-ommunication between the chamber F and the passage Y is past the adjustable needle valve W, that is it is restricted and the communication between the chamber F and the chamber E is through the very restricted annular passage Z. During this interim the valve G is moved away from the stop T against which it is normally pressed by the spring R and the valve G is thus moved into the position in which it is shown in the drawing. In this position the pressure in the chamber V is transmitted directly to the chamber E past the valve G and to the chamber F through the very restricted passage Z.
Obviously the pressure in the cham-ber E becomes instantly equal to the pressure in chamber V and the pressure in the chamber F rises slightly due to the small flow through the leakage passage Z and out to the passage Y past the needle valve W.
Hence the force acting in an upward direction on the rod P is considerably greater than it was when valve G was pushed over to the left against its stop T by the spring R. As the suction in the venturi B continues to slowly increase in spite of the gradual closure of the control v alve L, the suction in the chamber U also increases.
As the diaphragms D and C rise the volume of the chambers U and F are decreased. The volume decrease of the chamber U has no in iuence on the pressure in the chamber U.
The volume decrease of the chamber F-due to the restricted passage past the needle valve W-causes a temporary increase in pressure in the chamber F. After a short period of time the suction in the chamber F also increases and eventually-depending on the adjustment of the valve W, the valve G return-s to its original position in which position the passage connecting chamber V directly with chamber E is obstructed.
When the valve G obstructs this passage then the pressure in the two chambers E and F quickly equalizes through the leakage passage Z. In effeet normally only one diaphragm is acting. In effect when in its open position, that is the position in which it is shown, then the chamber F is at some suction less than the suction in the chamber V because of the leakage past the leak* age passage Z but substantially equal to more than one-half the suction in the chamber U. By this means the pull upwardly on the rod P is at least fifty percent greater than that due to the suction or pressure difference acting on the single diaphragm U. Thus the tendency to start the valve L to close occurs before the critical speed has been reached which would be too late to prevent over-speeding. After the critical speed has been reached the difference in suction between the chamber U and chamber F is not sufficient to keep the valve G in the position in which it is shown, and valve G is pushed `back into place by spring R.
Hence there is normally only one diaphragm in operation to regulate the speed of the power plant except during acceleration when the equivalent of 11/2 or of 1% diaphragms are in operation to prevent over-speeding.
Hence during acceleration the governor anticipates the ultimate increase in speed so that before the increased governor speed has been reached the governor valve L has already started to move so that it can be moved into its ultimate position before the power plant has exceeded the desired speed.
The adjustment W, when closed prevents the governor anticipating the change in speed. When adjusted, the degree of anticipation can be regulated.
VWhat I claim is:
An anticipatory hydraulic governor of the type which regulates the speed, when the speed is increasing, before the speed reaches the desired speed, adapted for use with a liquid fuel pump connected to a prime mover which is adapted to -be driven by the fuel supplied by said pump and to drive said pump at a speed proportional to the speed of the prime mover, said liquid fuel pump being of the type that has a constant displacement per revolution, an outlet from said pump, a fuel venturi therein, a balanced throttle valve in said outlet, a diaphragm responsive to the pressure difference created by the flow through said venturi connected to said valve, a second diaphragm also responsive to the pressure diierence created by said flow and also connected to said throttle valve, a passage connecting the pressure side of said venturi to the pressure side of one of said diaphragms, a passage connecting the pressure side of said diaphragms together, an automatic valve therein, yielding means opera*- ing to move said automatic valve into the position in which said passage is obstructed Iso that only one of said diaphragms is operative, means responsive to a sudden increase in speed of flow to move said automatic valve against said yielding means so a-s to open said connecting passage to render both of said diaphragms operative, so as to close said throttle valve rapidly when the speed of the prime mover is increasing rapidly.
STANLEY M. UDALE.
US561777A 1944-11-03 1944-11-03 Governor Expired - Lifetime US2407115A (en)

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2488829A (en) * 1943-07-28 1949-11-22 Hobson Ltd H M Speed governor
US2508260A (en) * 1946-12-31 1950-05-16 George M Holley Fuel feed control for gas turbines
US2564107A (en) * 1946-09-26 1951-08-14 George M Holley Fuel feeding control for gas turbines responsive to fuel flow, temperature, and acceleration
US2581276A (en) * 1945-05-30 1952-01-01 Bendix Aviat Corp Fuel feed and power control system for gas turbines, jet propulsion, and the like
US2586224A (en) * 1948-05-17 1952-02-19 Yuba Mfg Company Fuel burner system
US2604756A (en) * 1945-05-03 1952-07-29 Hobson Ltd H M Fuel supply system for internalcombustion engines
US2613501A (en) * 1945-06-02 1952-10-14 Lockheed Aircraft Corp Internal-combustion turbine power plant
US2616254A (en) * 1945-01-04 1952-11-04 Bendix Aviat Corp Jet engine fuel control for modifying fuel pressure drop across throttle in accordance with altitude
US2618324A (en) * 1947-07-19 1952-11-18 United Aircraft Corp Power plant governor
US2627305A (en) * 1945-01-11 1953-02-03 Bendix Aviat Corp Air density compensating fuel feeding system for gas turbines
US2631658A (en) * 1948-06-21 1953-03-17 Boeing Co Engine speed regulating fuel supply control
US2633704A (en) * 1947-08-14 1953-04-07 Chrysler Corp Fuel-air ratio regulator for gas turbine power plants
US2633830A (en) * 1949-06-27 1953-04-07 Hobson Ltd H M Speed, acceleration, and pressure controls for servomotor systems
US2636553A (en) * 1949-11-08 1953-04-28 Rolls Royce Fuel system for gas turbine engines and the like with main and pilot fuel injectors
US2637374A (en) * 1946-07-17 1953-05-05 Weatherhead Co Automatic fuel control for gas turbine engines
US2644513A (en) * 1945-10-06 1953-07-07 Bendix Aviat Corp Gas turbine fuel feed and power control device responsive to speed and air density
US2658566A (en) * 1945-08-20 1953-11-10 Bendix Aviat Corp Fuel feed and power control device for gas turbines
US2659425A (en) * 1949-08-22 1953-11-17 Lucas Ltd Joseph Liquid fuel regulating means for use with prime movers
US2674847A (en) * 1948-04-22 1954-04-13 Rolls Royce Control means in fuel system of gas-turbine engines
US2688229A (en) * 1948-07-30 1954-09-07 Niles Bement Pond Co Fuel and speed control for internalcombustion engines
US2689606A (en) * 1946-12-13 1954-09-21 Bendix Aviat Corp Fuel feeding system for gas turbine engines
US2708826A (en) * 1949-03-30 1955-05-24 United Aircraft Corp Fuel control for gas turbine
US2761280A (en) * 1950-08-31 1956-09-04 Daniel G Russ Fuel-air control mechanism for metering flow of fuel to afterburners in jet or turbine engines
US3032056A (en) * 1957-04-01 1962-05-01 Garrett Corp Regulating valve

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2488829A (en) * 1943-07-28 1949-11-22 Hobson Ltd H M Speed governor
US2616254A (en) * 1945-01-04 1952-11-04 Bendix Aviat Corp Jet engine fuel control for modifying fuel pressure drop across throttle in accordance with altitude
US2627305A (en) * 1945-01-11 1953-02-03 Bendix Aviat Corp Air density compensating fuel feeding system for gas turbines
US2604756A (en) * 1945-05-03 1952-07-29 Hobson Ltd H M Fuel supply system for internalcombustion engines
US2581276A (en) * 1945-05-30 1952-01-01 Bendix Aviat Corp Fuel feed and power control system for gas turbines, jet propulsion, and the like
US2613501A (en) * 1945-06-02 1952-10-14 Lockheed Aircraft Corp Internal-combustion turbine power plant
US2658566A (en) * 1945-08-20 1953-11-10 Bendix Aviat Corp Fuel feed and power control device for gas turbines
US2644513A (en) * 1945-10-06 1953-07-07 Bendix Aviat Corp Gas turbine fuel feed and power control device responsive to speed and air density
US2637374A (en) * 1946-07-17 1953-05-05 Weatherhead Co Automatic fuel control for gas turbine engines
US2564107A (en) * 1946-09-26 1951-08-14 George M Holley Fuel feeding control for gas turbines responsive to fuel flow, temperature, and acceleration
US2689606A (en) * 1946-12-13 1954-09-21 Bendix Aviat Corp Fuel feeding system for gas turbine engines
US2508260A (en) * 1946-12-31 1950-05-16 George M Holley Fuel feed control for gas turbines
US2618324A (en) * 1947-07-19 1952-11-18 United Aircraft Corp Power plant governor
US2633704A (en) * 1947-08-14 1953-04-07 Chrysler Corp Fuel-air ratio regulator for gas turbine power plants
US2674847A (en) * 1948-04-22 1954-04-13 Rolls Royce Control means in fuel system of gas-turbine engines
US2586224A (en) * 1948-05-17 1952-02-19 Yuba Mfg Company Fuel burner system
US2631658A (en) * 1948-06-21 1953-03-17 Boeing Co Engine speed regulating fuel supply control
US2688229A (en) * 1948-07-30 1954-09-07 Niles Bement Pond Co Fuel and speed control for internalcombustion engines
US2708826A (en) * 1949-03-30 1955-05-24 United Aircraft Corp Fuel control for gas turbine
US2633830A (en) * 1949-06-27 1953-04-07 Hobson Ltd H M Speed, acceleration, and pressure controls for servomotor systems
US2659425A (en) * 1949-08-22 1953-11-17 Lucas Ltd Joseph Liquid fuel regulating means for use with prime movers
US2636553A (en) * 1949-11-08 1953-04-28 Rolls Royce Fuel system for gas turbine engines and the like with main and pilot fuel injectors
US2761280A (en) * 1950-08-31 1956-09-04 Daniel G Russ Fuel-air control mechanism for metering flow of fuel to afterburners in jet or turbine engines
US3032056A (en) * 1957-04-01 1962-05-01 Garrett Corp Regulating valve

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