US2413439A - Pitch control mechanism - Google Patents
Pitch control mechanism Download PDFInfo
- Publication number
- US2413439A US2413439A US410807A US41080741A US2413439A US 2413439 A US2413439 A US 2413439A US 410807 A US410807 A US 410807A US 41080741 A US41080741 A US 41080741A US 2413439 A US2413439 A US 2413439A
- Authority
- US
- United States
- Prior art keywords
- valve
- pressure
- blades
- conduit
- cylinder
- 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
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
- B64C11/42—Blade pitch-changing mechanisms fluid, e.g. hydraulic non-automatic
-
- Y—GENERAL 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/904—Propeller or air plane system
Definitions
- Another object is to provide such a blade lock in which the pitch adjusting servo is utilized to apply the locking force.
- a further object is to provide an hydraulic blade lock which is not affected by leakage of pressure fluid at the rings through which the uid is transferred from the stationary to the rotating parts.
- Still another object is to adapt the blade locking mechanism for control from a remote point.
- the invention also resides in the novel arrangement of valves by which the locking action is effected.
- the governor includes a rotary head II pivotally supporting yballs I2 having arms bearing upwardly against the head I3 of a valve rod I4 which is urged downwardly by an adjustable Speeder spring I5.
- the ball head II is on the upper end of a sleeve I6 journaled in the governor casing and driven from its lower end through a gear connection I1 with the engine crankshaft 2.
- valve rod has a land I8 which cooperateswith a port I9 in the sleeve I6, the latter in turn communicating with a conduit 20 constituting the outlet of a booster pump 2l.
- Oil is delivered to the pump from a branch 22 leading from the outlet of a gear pump 23 that supplies oil at low pressure to the engine lubricating system.
- the pressures developed by the pumps are determined by the setting of by-pass valves 24 and 25,
- the lower end of the valve sleeve I6 may be opened and closed according to the positionv of a land 26 on the lower end of the stem I4. Intermediate the lands IB and 26, the sleeve is ported and communicates with a conduit 2l which leads through valves 28 and 29 and the usual transfer ring 30 to a valve 3
- the distributor valve comprises a plunger 33 slidable in a cylinder 34 and having spaced lands 35, 3B, 3'I and 38. The cylinder communicates through ports 39, 40 and 4I with a supply conduit 6I leading from the transfer ring 30.
- a conduit 42 extends from a port 43 to the head end of the cylinder 6 while the rod duit 44 with a port 45 between the lands 3'I and peller is driven.
- the blades are mounted on the end of the engine crankshaft 2 which projects forwardly through a hub 3 at the front of the engine frame 4. The blade pitch is changed by an hydraulic actuator or servo rotatable with the 38.
- Another port 46 opening between the lands 36 andv 3'I leads through a conduit 4l to a collector ring 48 which is connected through a conduit 49 and a valve 58 to the supply line of the lubricating pump 23.
- a pressure relief valve 5I is connected to the line 49 and set to pass oil at a pressure somewhat above that delivered by the position shown in which the land 35 abuts against a shoulder 54.
- is slidable in a cylinder 52 through which the supply conduitBI extends.
- a spring 55 strong enough to overcome the normal pressure of the lubricating system urges the plunger to the left as shown, a piston 56 then being disposed in the remote end of the cylinder which communicates through a. port 51 with the conduit 41.
- the valve 29 has a rotary member 58 through which extends a passage 59 which, when turned to the position shown in dotted outline, interrupts the ow of pressure fluid through the conduit 21 to the distributor valve 32.
- An arm 60 fast on the Valve member is connected to a rod 62 which carries the armature of a solenoid 63 energizable by closure of a switch 64 at a remote point of control.
- valve casing 65 communicates with a conduit 66 leading to a, cylinder 61 in which there is the piston 68 of the Valve 28. This is normally urged by a spring 69 to the position shown in which fluid is permitted to flow through the conduit 21.
- the valve casing 65 communicates with a conduit y1IIa leading'to the outlet of a gear pump'1 driven by an electric motor 1I and having its inlet 12 connected to the oil supply line 22.
- This pump is adapted to provide fluid pressure for feathering the propeller.
- is closed under the control of a switch 'I3 in the control cabin.
- the valve 50 has a, member 16 rotatable within the casing 65 and carrying an arm 11 connected to the rod 62 for actuation of the two valves in unison under the control of the solenoid 63.
- the member 16 In the normal position shown, the member 16 is positioned to connect the conduits 22 and 49 and also the conduits 66 and 10e. In the other position of the member shown in dotted outline, the conduits 49 and 1
- the switch 13 is held closed and the pressure cut-out switch above referred to is prevented from operating.
- High pressure oil is again delivered to the rod end of the cylinder.
- the plunger 33 moves against the spring 53 and above the feathering pressure the land 31 covers the port 45 disconnecting the supply line from the rod end of the cylinder 6.
- the land 31 passes the port 45 thereby connecting the head end of the cylinder to the supply line 6
- the piston 5 moves inwardly unfeathering the blades and forcing oil from the rod end of the cylinder into the lubricating system.
- the oil being non-compressible, provides in effect a positive stop preventing movement of the piston 5 toward the rod end of the cylinder thereby locking the propeller blades against movement toward low pitch.
- the combined centrifugal moment and the oil pressure acting on the piston 5 effectively holds the blades in the locked position during rotation of the propeller.
- the servo that normally adjusts the blades to maintain a constant engine speed is utilized to produce ,the force for locking the propeller blades in their limit positions.
- One of the fluid conduits leading to the servo is utilized to produce the hydraulic stop by which the limit position of the blades is determined. This stop is adjustable simply by running the engine at a speed corresponding to the fixed pitch desired preparatory to operating the valves 29 and 50 to disable the governor control and lock the blades at a xed pitch.
- to trap oil in the rod end of the cylinder 6, the centrifugal force component acting on the blades assists in holding the latter in the locked position. This permits a low oil pressure to be employed for locking purposes.
- the combinlahti'en ofan engine having a low pressure lubricating s ⁇ y ⁇ s ⁇ teiillrand.laE propeller driven by said engine and having blades tending to turn toward low pitch when the propeller is rotating, means including a piston movable in opposite directions to increase and decrease the pitch of said blades, a cylinder for said piston rotatable with said propeller, a rst iiuid con-k duit including a transfer ring betweenf the rotating and non-rotating parts and connecting said lubricating system to one end of said cylinder wherebir the low pressure fluid urges said blades toward low pitch, means providing a of fluid from said second source tosaid second conduit, means providing a third source of pressure fluid, higher than said lubricating pressure and said second source of pressure, e normally open valve in said second conduit betweensaid cylinder and said second transfer ring and adapted to close automatically in response to a fluid pressure in said first conduit higher than said lubricating pressure, and valve means in the non
- a servo for adjusting the pitch of power driven propeller blades means responsive to the speed of the propeller to control said servo and adjust said blades for the maintenance of a predetermined propeller speed, a normally inactive stop adapted when active to limit the adjustment of said blades by said servo, manually controllable means selectively operable to render said stop active in any one of a plurality of different positions of said blades, and means operable automatically as an incident to rendering said stop active to energize said servo independently of said speed responsive means and hold the blades against said stop.
- the combination with a hydraulic servo for adjusting the pitch of power driven propeller blades means providing a source of fluid under pressure, means responsive to the rotational 'speed of the propeller blades and controlling the ow of said fluid to and from said source, a normally inactive stop adapted when rendered active to limit the adjustment of said blades by said servo, means providing a source of iiuid under a pressure higher than said rst mentioned pressure, valve means responsive to the pressure of uid from said source to render said stop effective, and manually controllable means selectively operable at any one of a plurality of different positions of said blades to disable said speed responsive means and energize said valve means from said second source.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Description
DCC. 31, 1946. G, F, BRAKE FITCH CONTROL MECHANISM Filed Sept. l5, 1941 N EaNTOg-J l Geo/ye Sgr/@5f ,0f e
Patented Dec. 31, 1946 PITCH CONTROL MECHANISM George Forrest Drake, Rocl'rford, Ill.; assigner to Woodward Governor Company, Rockford, Ill., a corporation of Illinois Application September 15, 1941, Serial N o. 410,807
6 Claims.
This invention relates to mechanisms for controlling the pitch of propcllers for aircraft or the like and has more particular reference to mecham'sms of the hydraulic type.
The general object is to equip a propeller adjusting mechanism of the above character with selectively operable means by which the propeller blades may be locked positively at some fixed pitch so as to assist in proper setting of the carburetor mixture of the engine by which the propeller is driven.
Another object is to provide such a blade lock in which the pitch adjusting servo is utilized to apply the locking force.
A further object is to provide an hydraulic blade lock which is not affected by leakage of pressure fluid at the rings through which the uid is transferred from the stationary to the rotating parts.
Still another object is to adapt the blade locking mechanism for control from a remote point.
It is another object to utilize the auxiliary feathering pump as a source of locking pressure.
The invention also resides in the novel arrangement of valves by which the locking action is effected.
Other objects and advantages of the invention Will become apparent from the following detailed description taken in connection with the accompanying drawing which is a schematic view and circuit diagram of an hydraulic pitch control mechanism involving the novel features of the present invention.
.The invention is susceptible of various modiications and alternative constructions and of use with various kinds of blade adjusters, and I have shown in the drawing and will herein describe in detail a preferred embodiment of the invention applied to a common type hydraulic adjusting mechanism. It is to be understood, however, that I do not intend to limit the invention by such'disclosure but aim to cover al1 modifications and alternative constructions and uses falling y the now of oil is metered by a valve 9 actuated l in response to engine speed changes detected by a centrifugal 'governor I0. As shown, the governor includes a rotary head II pivotally supporting yballs I2 having arms bearing upwardly against the head I3 of a valve rod I4 which is urged downwardly by an adjustable Speeder spring I5. The ball head II is on the upper end of a sleeve I6 journaled in the governor casing and driven from its lower end through a gear connection I1 with the engine crankshaft 2. The
valve rod has a land I8 which cooperateswith a port I9 in the sleeve I6, the latter in turn communicating with a conduit 20 constituting the outlet of a booster pump 2l. Oil is delivered to the pump from a branch 22 leading from the outlet of a gear pump 23 that supplies oil at low pressure to the engine lubricating system. The pressures developed by the pumps are determined by the setting of by-pass valves 24 and 25,
The lower end of the valve sleeve I6 may be opened and closed according to the positionv of a land 26 on the lower end of the stem I4. Intermediate the lands IB and 26, the sleeve is ported and communicates with a conduit 2l which leads through valves 28 and 29 and the usual transfer ring 30 to a valve 3| which forms a part of the present blade lock control and the usual distributor valve 32, both valves being disposed within the engine shaft 2. The distributor valve comprises a plunger 33 slidable in a cylinder 34 and having spaced lands 35, 3B, 3'I and 38. The cylinder communicates through ports 39, 40 and 4I with a supply conduit 6I leading from the transfer ring 30. A conduit 42 extends from a port 43 to the head end of the cylinder 6 while the rod duit 44 with a port 45 between the lands 3'I and peller is driven. The blades are mounted on the end of the engine crankshaft 2 which projects forwardly through a hub 3 at the front of the engine frame 4. The blade pitch is changed by an hydraulic actuator or servo rotatable with the 38. Another port 46 opening between the lands 36 andv 3'I leads through a conduit 4l to a collector ring 48 which is connected through a conduit 49 and a valve 58 to the supply line of the lubricating pump 23. A pressure relief valve 5I is connected to the line 49 and set to pass oil at a pressure somewhat above that delivered by the position shown in which the land 35 abuts against a shoulder 54.
'Ihe plunger 3I of the valve 3| is slidable in a cylinder 52 through which the supply conduitBI extends. A spring 55 strong enough to overcome the normal pressure of the lubricating system urges the plunger to the left as shown, a piston 56 then being disposed in the remote end of the cylinder which communicates through a. port 51 with the conduit 41.
The valve 29 has a rotary member 58 through which extends a passage 59 which, when turned to the position shown in dotted outline, interrupts the ow of pressure fluid through the conduit 21 to the distributor valve 32. An arm 60 fast on the Valve member is connected to a rod 62 which carries the armature of a solenoid 63 energizable by closure of a switch 64 at a remote point of control. When the solenoid is deenergized, a
spring 14 holds the Valve 29 in open position as the casing 65 of the valve 56 communicates with a. conduit 66 leading to a, cylinder 61 in which there is the piston 68 of the Valve 28. This is normally urged by a spring 69 to the position shown in which fluid is permitted to flow through the conduit 21. Opposite the conduit 22, the valve casing 65 communicates with a conduit y1IIa leading'to the outlet of a gear pump'1 driven by an electric motor 1I and having its inlet 12 connected to the oil supply line 22. This pump is adapted to provide fluid pressure for feathering the propeller. The circuit for the motor 1| is closed under the control of a switch 'I3 in the control cabin.
The valve 50 has a, member 16 rotatable within the casing 65 and carrying an arm 11 connected to the rod 62 for actuation of the two valves in unison under the control of the solenoid 63. In the normal position shown, the member 16 is positioned to connect the conduits 22 and 49 and also the conduits 66 and 10e. In the other position of the member shown in dotted outline, the conduits 49 and 1|]a are connected and 66 is connected to the conduit 22.
The circuit arrangement thus far described is that of the so-called hydromatic control with the addition of the valves 29, 3| and 50. parts will be positioned as 'shown when the engine is operating at the speed corresponding to the setting of governor speeder spring I5. An increase in engine speed raises the pilot valve member I4 admitting oil from the governor pump into the sleeve I6. The oil ows through the cut-off valve 28, the transfer ring 30, valve 3l, passage 6I, ports 39 and 45 of the distributor valve into the rod end of the cylinder 6. When the pressure thus applied to piston 5 exceeds the com- -bined forces urging the blades toward low pitch, the piston moves outwardly, and oil in the head end of the cylinder is displaced into the engine lubricating system. Its path is through tube 42 distributor valve ports 43 and 46, conduit 41, transfer ring 48, Valve 56, and pump relief valve 25. The outward motion of the piston 5 is translated into rotary motion of the cam 1 which, through bevel gears increases the blade angle. This increase is accompanied by a decrease in engine speed and, because of decreasedrcentrifugal force, the governor yweights move inwardly The governor pump is discharged through the relief valve 24.
When the engine speed drops below the Set Value, the flyweights move inwardly, lowering the pilot valve and allowing oil from the rod end of the cylinder to flow back through the distributor valve into the governor, where it is discharged through a governor drain port which is then opened by the land 26. Under the action of centrifugal twisting movement and engine oil pressure, the blades now assume a lower angle, the engine speed increases, and the pilot valve rises due to the outward motion of the ilyweights. When the engine has reached the speed for which the governor is set, the pilot valve again assumes a neutral position, neither admitting oil`to nor draining it from the propeller cylinder. The forces are then in equilibrium and again the propeller runs at the selected speed.
To feather the propeller, it is only necessary to start the motor 1I by closing its control switch 13. The pump 10 supplies oil at a pressure substantially higher than the governor pump causing the piston 68 to move and close the valve 28 thereby disconnecting the governor. taneously, the valve connects the high pressure oil conduit 66 to the conduit 21, permitting oil to flow to the rod end of the cylinder 6 as described above, causing the piston 5 and the cam rollers 1a to move under the increased pressure to the feathering or low mechanical'advantage portion of the cam 1. Then the pressure builds up rapidly and this increase may be utilized to actuate means (not shown) for deenergizing the motor 1I, :the blades remaining feathered. During feathering, the position of the distributor valve is not changed, the pressure being insufficient to overcome the spring 53 which acts on the plunger 33.
To unfeather, the switch 13 is held closed and the pressure cut-out switch above referred to is prevented from operating. High pressure oil is again delivered to the rod end of the cylinder. As the pressure in the distributor valve increases, the plunger 33 moves against the spring 53 and above the feathering pressure the land 31 covers the port 45 disconnecting the supply line from the rod end of the cylinder 6. 4- As the pressure rises to a predetermined higher value, the land 31 passes the port 45 thereby connecting the head end of the cylinder to the supply line 6| through ports 4I and 43, the rod end being connected to the low pressure line 41 through ports 45 and 46. Under this increased pressure, the piston 5 moves inwardly unfeathering the blades and forcing oil from the rod end of the cylinder into the lubricating system. Then, the blades begin to windmill. When a predetermined speed is attained, the control switch 13 is released, stopping the motor 1I and allowing the distributor and cut-off valves to return to their normal positions so as to transfer the control of the pitch actuator back to the governor.
To lock the blades in xed position as during adjustment of the engine carburetor, it is only necessary to close the switches 64 and 13 with Simula the rod 62 and changes the positions of the valves 29 and 50, the former disconnecting the governor from the `regular supply line 21. The valve 50 not only disconnects the pumps 23 and 10 from the propeller servo through the normal supply lines, but also connects the outlet 1lia of the feathering pump 10 to the conduit 49. With the parts thus positioned, oil from the pump 10 is delivered at a pressure determined by the setting of the relief valve 5I and somewhat higher than the lubricating oil pressure. The oil flows through the conduit 49I and the transfer ring- 48 into the passage 41 and, since `the line 6I is then closed by the valve 29, the pressure in the passage 41 rises sufficiently to move the piston 56, the valve plunger 3|a thus being shifted against the action of the spring 55 to close the conduit 6| against the escape of oil from the distributor valve 32.
The oil pressure thus created by the pump 10 is applied to the head end of" the servo piston through the conduit 41, ports 46, 43 of the distributor valve, and the conduit 42, this pressure supplementing the centrifugal moment tending to turn the blades toward low pitch. Such movement of the piston is prevented, however, because the passage leading to the rod end of the cylinder 6 through the distributor valve ports 45, 39 is blocked off or closed by the valve 3l. It will be observed that the point of closure is in the rotating parts and between the distributor valve 432 and the transfer ring 30 so that there is no leakage from the cylinder 6. That is, oil is trapped effectively in the rod end of the cylinder and that portion of the conduits and dis'- tributor valve between the valve 3| and the cylinder. The oil, being non-compressible, provides in effect a positive stop preventing movement of the piston 5 toward the rod end of the cylinder thereby locking the propeller blades against movement toward low pitch. The combined centrifugal moment and the oil pressure acting on the piston 5 effectively holds the blades in the locked position during rotation of the propeller.
After the engine adjustments have been made, the switches 64 and 13 are opened. This stops the pump 10 and allows the valves 29 and 50 to be returned by the spring 14 to their normal po-v sitions restoring the regular governor control.
From the foregoing, it will be seen that the servo that normally adjusts the blades to maintain a constant engine speed is utilized to produce ,the force for locking the propeller blades in their limit positions. One of the fluid conduits leading to the servo is utilized to produce the hydraulic stop by which the limit position of the blades is determined. This stop is adjustable simply by running the engine at a speed corresponding to the fixed pitch desired preparatory to operating the valves 29 and 50 to disable the governor control and lock the blades at a xed pitch. By using the valve 3| to trap oil in the rod end of the cylinder 6, the centrifugal force component acting on the blades assists in holding the latter in the locked position. This permits a low oil pressure to be employed for locking purposes.
I claim as my invention:
1. The combinlahti'en ofan engine having a low pressure lubricating s`y`s`teiillrand.laE propeller driven by said engine and having blades tending to turn toward low pitch when the propeller is rotating, means including a piston movable in opposite directions to increase and decrease the pitch of said blades, a cylinder for said piston rotatable with said propeller, a rst iiuid con-k duit including a transfer ring betweenf the rotating and non-rotating parts and connecting said lubricating system to one end of said cylinder wherebir the low pressure fluid urges said blades toward low pitch, means providing a of fluid from said second source tosaid second conduit, means providing a third source of pressure fluid, higher than said lubricating pressure and said second source of pressure, e normally open valve in said second conduit betweensaid cylinder and said second transfer ring and adapted to close automatically in response to a fluid pressure in said first conduit higher than said lubricating pressure, and valve means in the non-rotatable portions of saidV conduits selectively operable to connect said lubricating and second pressure sources to said rst and second conduits respectively in one position of the valve means to close said second conduit and connect said third pressure source to said rst conduit inthe other position of the valve means.
"2. The combination of an hydraulic servo for adjusting the pitch of propeller blades including a double acting piston and cylinder, means for supplying fluid under pressure to one end of said cylinder, valve means operable in a plurality of different positions of said blades, and means dependently of the blade positions to trap fluid in the other cylinder end and thereby lock the propeller blades at a fixed pitch.
3. The combination of a servo for adjusting the pitch of power driven propeller blades, means responsive to the speed of the propeller to control said servo and adjust said blades for the maintenance of a predetermined propeller speed, a normally inactive stop adapted when active to limit the adjustment of said blades by said servo, manually controllable means selectively operable to render said stop active in any one of a plurality of different positions of said blades, and means operable automatically as an incident to rendering said stop active to energize said servo independently of said speed responsive means and hold the blades against said stop.
4. The combination of an adjustable pitch propeller, an hydraulic servo rotatable with said propeller for actuating the same, means for supplying pressure fluid to said servo including fluid conduits leading through transfer rings to and from opposite ends of Ithe servo, a pressure actuated valve disposed in one of said conduits between the transfer ring thereof and said servo and selectively operable in a plurality of different pitch settings of said propeller to open and close the conduit whereby to trap iiuid in one end of said servo when the valve is closed and thereby the propeller against the stop formed by said trapped fluid.
5. AThe combination with a hydraulic servo for adjusting the pitch of powei` driven propeller blades, means providing a source of uid under pressure, means responsive to the rotational speed of the propeller blades and controlling the ow of said fluid to and from said source, a normally inactive stop adapted when rendered active to limit the adjustment of said blades by said servo, means providing a source of fluid under a pressure higher than said first mentioned pressure, and manually controllable means selectively operable to render said stop active at any selected one of a plurality of different positions of said blades to render said stop active and admit uid from said second source to said servo to energize the latter and hold the blades against said stop.
6. The combination with a hydraulic servo for adjusting the pitch of power driven propeller blades, means providing a source of fluid under pressure, means responsive to the rotational 'speed of the propeller blades and controlling the ow of said fluid to and from said source, a normally inactive stop adapted when rendered active to limit the adjustment of said blades by said servo, means providing a source of iiuid under a pressure higher than said rst mentioned pressure, valve means responsive to the pressure of uid from said source to render said stop effective, and manually controllable means selectively operable at any one of a plurality of different positions of said blades to disable said speed responsive means and energize said valve means from said second source.
GEORGE FORREST DRAKE.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US410807A US2413439A (en) | 1941-09-15 | 1941-09-15 | Pitch control mechanism |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US410807A US2413439A (en) | 1941-09-15 | 1941-09-15 | Pitch control mechanism |
Publications (1)
Publication Number | Publication Date |
---|---|
US2413439A true US2413439A (en) | 1946-12-31 |
Family
ID=23626309
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US410807A Expired - Lifetime US2413439A (en) | 1941-09-15 | 1941-09-15 | Pitch control mechanism |
Country Status (1)
Country | Link |
---|---|
US (1) | US2413439A (en) |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2472836A (en) * | 1946-07-31 | 1949-06-14 | Earnest R Kennedy | Reversible propeller |
US2513660A (en) * | 1946-10-22 | 1950-07-04 | United Aircraft Corp | Propeller pitch control means |
US2557333A (en) * | 1946-07-18 | 1951-06-19 | Bendix Aviat Corp | Fluid control means |
US2592124A (en) * | 1950-05-25 | 1952-04-08 | United Aircraft Corp | Pitch lock and actuating valve therefor |
US2626668A (en) * | 1948-04-08 | 1953-01-27 | Gen Motors Corp | Propeller feathering |
US2635701A (en) * | 1950-03-13 | 1953-04-21 | Hansford D Hurt | Fluid controlled feathering means for propellers for aircraft |
US2648389A (en) * | 1947-06-14 | 1953-08-11 | Gen Motors Corp | Variable pressure system |
US2737253A (en) * | 1952-03-13 | 1956-03-06 | Gen Motors Corp | Propeller pitch control |
US2748877A (en) * | 1952-03-15 | 1956-06-05 | Gen Motors Corp | Propeller control with pitch lock |
US2754922A (en) * | 1952-04-24 | 1956-07-17 | Gen Motors Corp | Variable pitch propeller control |
US2868303A (en) * | 1953-09-02 | 1959-01-13 | United Aircraft Corp | Propeller auxiliary power control |
US2940426A (en) * | 1953-06-03 | 1960-06-14 | Gen Motors Corp | Volume compensating means for a servo system |
US2955663A (en) * | 1956-12-11 | 1960-10-11 | Gen Motors Corp | Propeller control system |
US2990888A (en) * | 1957-12-27 | 1961-07-04 | United Aircraft Corp | Propeller control apparatus |
WO2012117095A1 (en) * | 2011-03-03 | 2012-09-07 | Rolls-Royce Deutschland Ltd & Co Kg | Oil supply system and method for supplying oil for a turboprop engine |
US8726787B2 (en) | 2011-03-18 | 2014-05-20 | General Electric Company | Rotary hydraulic actuator with hydraulically controlled position limits |
-
1941
- 1941-09-15 US US410807A patent/US2413439A/en not_active Expired - Lifetime
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2557333A (en) * | 1946-07-18 | 1951-06-19 | Bendix Aviat Corp | Fluid control means |
US2472836A (en) * | 1946-07-31 | 1949-06-14 | Earnest R Kennedy | Reversible propeller |
US2513660A (en) * | 1946-10-22 | 1950-07-04 | United Aircraft Corp | Propeller pitch control means |
US2648389A (en) * | 1947-06-14 | 1953-08-11 | Gen Motors Corp | Variable pressure system |
US2626668A (en) * | 1948-04-08 | 1953-01-27 | Gen Motors Corp | Propeller feathering |
US2635701A (en) * | 1950-03-13 | 1953-04-21 | Hansford D Hurt | Fluid controlled feathering means for propellers for aircraft |
US2592124A (en) * | 1950-05-25 | 1952-04-08 | United Aircraft Corp | Pitch lock and actuating valve therefor |
US2737253A (en) * | 1952-03-13 | 1956-03-06 | Gen Motors Corp | Propeller pitch control |
US2748877A (en) * | 1952-03-15 | 1956-06-05 | Gen Motors Corp | Propeller control with pitch lock |
US2754922A (en) * | 1952-04-24 | 1956-07-17 | Gen Motors Corp | Variable pitch propeller control |
US2940426A (en) * | 1953-06-03 | 1960-06-14 | Gen Motors Corp | Volume compensating means for a servo system |
US2868303A (en) * | 1953-09-02 | 1959-01-13 | United Aircraft Corp | Propeller auxiliary power control |
US2955663A (en) * | 1956-12-11 | 1960-10-11 | Gen Motors Corp | Propeller control system |
US2990888A (en) * | 1957-12-27 | 1961-07-04 | United Aircraft Corp | Propeller control apparatus |
WO2012117095A1 (en) * | 2011-03-03 | 2012-09-07 | Rolls-Royce Deutschland Ltd & Co Kg | Oil supply system and method for supplying oil for a turboprop engine |
US9506476B2 (en) | 2011-03-03 | 2016-11-29 | Rolls-Royce Deutschland Ltd. & Co Kg | Oil supply system and method for supplying oil for a turboprop engine |
US8726787B2 (en) | 2011-03-18 | 2014-05-20 | General Electric Company | Rotary hydraulic actuator with hydraulically controlled position limits |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2413439A (en) | Pitch control mechanism | |
US2402065A (en) | Propeller control | |
US2423191A (en) | Control apparatus for variable pitch propeller adjusting devices | |
US4037986A (en) | Bladed rotors having control means for effecting blade pitch adjustment | |
US5037271A (en) | Pitch control system | |
US2391699A (en) | Propeller control mechanism | |
US3575529A (en) | Method and apparatus for operating a propeller and driving engine fuel valve | |
US2781856A (en) | Control system for variable pitch screw propellers | |
US2722985A (en) | Full feathering propeller | |
US3603697A (en) | Engine, propeller and rotor installations | |
US2507671A (en) | Propeller control | |
US2748877A (en) | Propeller control with pitch lock | |
US2600017A (en) | Variable pitch reversible propeller | |
US3459267A (en) | Bladed rotors | |
US2204639A (en) | Governor mechanism | |
US2205625A (en) | Aircraft propulsion | |
US2352736A (en) | Automatic resetting device for governors | |
US2626669A (en) | Propeller control | |
US2363670A (en) | Variable pitch constant speed propeller assembly | |
US2632516A (en) | Automatic control for reversing propellers | |
US2525694A (en) | Control means for turbo-prop units | |
US2943686A (en) | Hydraulic control system for an aeronautical propeller | |
GB670412A (en) | Improvements in or relating to propeller systems particularly for aircraft comprising two coaxially mounted, adjustable pitch propellers | |
US3163233A (en) | Aeronautical propeller having safety means for propeller feathering | |
US2857007A (en) | Fluid pressure control system for variable pitch propellers |