Rotary mechanical system with non-contact drive

FIELD: aviation.

SUBSTANCE: mechanical system (10) contains shaft (12), rotatable about its primary axis relative to the structural element (14), movable part (16), mounted on the shaft (12) rotatably with it about the primary axis (A) and moving at random relative to the shaft (12), the driving facility (18) to move the movable part (16) relative to the shaft (12). The driving facility comprises the first fastened section (20), which is mounted on the structural element (14) and the second movable section (22), which is mounted on the shaft (12) and is connected to the movable part (16). The driving facility (18) consists of the electromechanical drive with the air gap between the first section (20) and the second section (22).

EFFECT: reduction of friction between the moving parts.

9 cl, 5 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: system to modify angle of attack of impeller blades mounted on a bushing rotating along the axis of the impeller, comprises a brushless electric motor and mechanical connecting facilities. The electric motor comprises a stator equipped with coils, designed for reliable assembly on a fixed part of the gas turbine engine, and also a rotor equipped with permanent magnets. The rotor and stator are aligned on the axis of impeller rotation and are arranged in such a way that coils are placed opposite to permanent magnets in direction of the rotation axis. Mechanical connecting facilities are located between the rotor and the blade. The rotor is mounted as movable in the axial direction between the blocked position, in which it is fixed to a rotary bushing, and the unblocked position, in which its rotation relative to the specified bushing along the axis of impeller rotation causes through mechanical connecting facilities variation of angle of attack of blades. Other inventions of the group relate to the impeller of the aircraft gas turbine engine, comprising the above system, and also to the gas turbine engine including such impeller. When controlling the angle of attack of impeller blades they unblock the rotor of the brushless electric motor by means of its movement in the axial direction from the blocked into the unblocked position. The rotor is rotated to bring the blades into the requested angle of attack, and the electric motor rotor is blocked by means of its movement in the axial direction from the unblocked into the blocked position.

EFFECT: group of inventions makes it possible to increase reliability and to simplify the system of control of angle of attack of impeller blades.

12 cl, 15 dwg

FIELD: engines and pumps.

SUBSTANCE: turboprop comprises at least of assembly (24a) of controlled-orientation fan blades (26) fixed with rotary ring (28a) articulated with turbine rotor. Every blade of said assembly is coupled with sync ring (30a) for orientation control. Additionally, this device comprises frictionless bearing (54a) with inner cage (56a) to slide on turbine crankcase. Said cage is connected with power cylinder (38) rod (44) and with outer cage (52a) engaged with sync ring with the help of multiple connection levers (40a). Levers are coupled with power cylinder rod and articulated with sync ring so that power cylinder actuation turns said sync ring about lengthwise axis. Turboprop comprises, preferably, turbine (20) with two rotors (22a, 22b) of opposite rotation and two fan (26) blade assemblies (24a, 24b) with controlled orientation.

EFFECT: reliable and accurate control, lower weight.

10 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: turbomachine comprises at least one screw with cowling with variable-pitch blades. These blades are retained by cylindrical plates fitted on spinning pins (B) fitted in radial grooves of circular rotor element and interconnected by their radially inner ends with adjusting ring. Said ring spins about turbomachine shaft (A) and reciprocates there along to drive the plates about their axes. Said adjusting ring is centred and driven about turbomachine axis at means that cannot spin bur are reciprocated along said axis by power cylinder retained by turbomachine stator. Said adjusting ring centring and guiding means comprise circular guide that features U-like cross-section. Aid guide comprises two lateral walls to confine circular flute extending outward. Adjusting ring is fitted in said flute. Bearings are arranged on both sides of adjusting ring between it and lateral walls.

EFFECT: simplified and efficient design.

7 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: turboprop comprises the system (24a) of fan vanes (26) with adjustable orientation rigidly coupled with spinning ring (28a). Said ring is centred relative to lengthwise axis (12) and engaged with turbine rotor. Every vane of said system is connected with timing ring (30a) centred along lengthwise axis for adjustment of vane orientation. Besides, it incorporates power cylinder (38) rigidly engaged at revolution with turbine rotor and mechanically connected with timing ring by several coupling levers (40a). Every lever is coupled with power cylinder con-rod (44) and articulated with timing ring so that power cylinder motion caused rotation of timing ring about lengthwise axis. Turboprop with dual screw comprises turbine (20) with two opposite-rotation rotors and two systems of fan vanes (26) of adjustable orientation.

EFFECT: easy and accurate control, decreased weight.

10 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: system of propeller screw blade pitch control in a turboshaft engine comprises the first and second circular guides, an activating element, and also the first and second blocking elements. The first circular guide provides for installation of an angle of attack of the specified blade and has the first and second seats that are distant from each other along the circumference. Each seat is formed with the first and second thrust surfaces. The second circular guide is made concentrically with the first guide and is located outside relative to it. The second thrust surface of the first seat and the first thrust surface of the second seat are aligned towards the second guide. The activating element is placed between the first and second guides and has the first and second thrust surfaces. The first blocking element is placed in the first seat opposite to the specified second thrust surface of the activating element. The second blocking element is placed in the second seat opposite to the first thrust surface of the activating element. The first and second blocking elements are made as capable of taking normal centralised position, and also unblocking position in the first and second circular directions. During control of the above system of propeller screw blade pitch control, the activating torque is applied to the activating element. Other inventions of the group relate to a propeller screw of a turboshaft engine comprising the above system of blade pitch control, and also to an aircraft engine comprising such propeller screw.

EFFECT: inventions make it possible to increase reliability of a system of blade pitch control, to reduce its weight.

10 cl, 7 dwg

FIELD: transport.

SUBSTANCE: set of inventions relates to the airscrew blade pitch adjustment system for aircraft gas turbine engine. Proposed system comprises the following components that follow: first race coupled with airscrew blade to allow setting the angle of attack of said blade in rotation and second race, drive element 60 for first race arranged between said and second races and having the section with angular recesses. Besides, it has, at least, one locking element 64 arranged between said first and second races at said section with angular recess of drive element in V-like groove of the first race. Element 64 can seat at normal centered element to drive simultaneously said first and second race and at unlocking position to allow shift in rotation of assembly including first race, element 64 and element 60.

EFFECT: simplified design, no use of separate locking mechanism, decreased weight, higher reliability.

17 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed turboprop comprises propeller with blades secured to annular rotary support adjoining the outer stationary casing enveloping turbine driving said rotary support. Every blade is fitted on pivot to turn relative to rotary support. Gear wheel is fitted on every pivot to engage with driving annular structure making gear wheel fitted to rotate about engine axis about rotary support. Driving annular structure is coupled with outside annular control structure fitted aligned with rotary support via planetary train arranged on rotary support. Planetary train comprises annular spider arranged to rotate on rotary support. Two sets of planetary gears are fitted on said spider. Note here that gears of the first set are located between rim of rotary support and ring gear of stationary casing while gears of the second set are mounted between rim of driven annular support and ring gear of annular control structure.

EFFECT: simplified design.

4 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: position control device of turning guide blades of compressor or turbine of gas turbine engine includes synchronising rings arranged outside the housing of compressor or turbine and connected to guide blades with adjustable rods and drive mechanism containing at least one blade position angle sensor. The latter is connected to one of shafts of blade drive through levers and additional rod, one end of which is hinged to one of levers of blade drive shaft, and the other end of additional rod - to levers of sensor; at that, levers of blade drive shaft, one of which is kinematically connected to sensor and the other one - to drive mechanism, are made separately on drive shaft with possibility of being moved in parallel planes.

EFFECT: ensuring fail-safe operation of device owing to accurate measurement of actual angles ϕHA of blade position of compressor or turbine of gas turbine engine at failure of drive mechanism of the above blades.

3 dwg

Gas turbine // 2351770

FIELD: engines and pumps.

SUBSTANCE: invention relates to turbojet engine gas turbines. Gas turbine blades are mounted on a cylindrical sleeve to rotate and axially move thereon which is provided for by attaching it to structural circular wall tapered ledge. The said wall central part represents a two-wall cylinder incorporating a spring fitted between the cylinder walls and resting upon the circular ledge of cylindrical barrel rigidly fixed on the shaft. The barrel rear part has a circular wall made integral with a part of vortex turbine blades to allow the second part of aforesaid blades made on the structural circular wall inner surface to enter into the said first part to have both parts aligned in axial travel. Circular webs arranged on the turbojet engine intermediate structural casing confine the vortex turbine blade outer parts. Fuel, in compliance with the fuel lines, actuates the cylindrical sleeve axial travel mechanism to vary the circular gap size controlling the passage of gas flow onto the gas turbine blades.

EFFECT: power take-off adjustment.

2 cl, 5 dwg

Screw-turbine // 2330966

FIELD: engines and pumps.

SUBSTANCE: invention relates to power engineering. The screw-turbine consists of the blade supports fitted on an axle parallel to a liquid or gas motion direction. The first support is rigidly fitted on the said axle. Other details are fitted on the axle to allow varying the number of the screw-turbine blades due to aligning the blades details at their within the limits set by limiters. The last detail is coupled with the axle by a spring mechanism. The blades supports are interconnected by springs. Each blade support is connected by the spring to the axle.

EFFECT: higher ratio of utilisation of energy of variable-speed moving gases and liquids and continuous reduction of pressure at the screw turbine blades at increasing loads.

3 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: system to modify angle of attack of impeller blades mounted on a bushing rotating along the axis of the impeller, comprises a brushless electric motor and mechanical connecting facilities. The electric motor comprises a stator equipped with coils, designed for reliable assembly on a fixed part of the gas turbine engine, and also a rotor equipped with permanent magnets. The rotor and stator are aligned on the axis of impeller rotation and are arranged in such a way that coils are placed opposite to permanent magnets in direction of the rotation axis. Mechanical connecting facilities are located between the rotor and the blade. The rotor is mounted as movable in the axial direction between the blocked position, in which it is fixed to a rotary bushing, and the unblocked position, in which its rotation relative to the specified bushing along the axis of impeller rotation causes through mechanical connecting facilities variation of angle of attack of blades. Other inventions of the group relate to the impeller of the aircraft gas turbine engine, comprising the above system, and also to the gas turbine engine including such impeller. When controlling the angle of attack of impeller blades they unblock the rotor of the brushless electric motor by means of its movement in the axial direction from the blocked into the unblocked position. The rotor is rotated to bring the blades into the requested angle of attack, and the electric motor rotor is blocked by means of its movement in the axial direction from the unblocked into the blocked position.

EFFECT: group of inventions makes it possible to increase reliability and to simplify the system of control of angle of attack of impeller blades.

12 cl, 15 dwg

FIELD: engines and pumps.

SUBSTANCE: system to modify angle of attack of impeller blades mounted on a bushing rotating along the axis of the impeller, comprises a brushless electric motor and mechanical connecting facilities. The electric motor comprises a stator equipped with coils, designed for reliable assembly on a fixed part of the gas turbine engine, and also a rotor equipped with permanent magnets. The rotor and stator are aligned on the axis of impeller rotation and are arranged in such a way that coils are placed opposite to permanent magnets in direction of the rotation axis. Mechanical connecting facilities are located between the rotor and the blade. The rotor is mounted as movable in the axial direction between the blocked position, in which it is fixed to a rotary bushing, and the unblocked position, in which its rotation relative to the specified bushing along the axis of impeller rotation causes through mechanical connecting facilities variation of angle of attack of blades. Other inventions of the group relate to the impeller of the aircraft gas turbine engine, comprising the above system, and also to the gas turbine engine including such impeller. When controlling the angle of attack of impeller blades they unblock the rotor of the brushless electric motor by means of its movement in the axial direction from the blocked into the unblocked position. The rotor is rotated to bring the blades into the requested angle of attack, and the electric motor rotor is blocked by means of its movement in the axial direction from the unblocked into the blocked position.

EFFECT: group of inventions makes it possible to increase reliability and to simplify the system of control of angle of attack of impeller blades.

12 cl, 15 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft applications, in particular to electric systems of aircrafts. The aircraft engine contains the stator, the main shaft, the transmission gear, the first and second electric devices, supported the first and second rotors respectively, the control unit, the first and second armature windings, supported by the first and second rotors respectively. The transmission gear converts the rotation of the main shaft into the rotation of the first and second rotors in different directions. The control unit induces DC current in the first excitation winding. The first and second armature windings are connected to the first and second electric devices. The first excitation winding is located between the first armature winding and the second armature winding in one position of the main shaft.

EFFECT: decrease of mass-dimensional parameters of devices, supported by the aircraft engine rotor is achieved.

7 cl, 7 dwg

FIELD: aviation.

SUBSTANCE: mechanical system (10) contains shaft (12), rotatable about its primary axis relative to the structural element (14), movable part (16), mounted on the shaft (12) rotatably with it about the primary axis (A) and moving at random relative to the shaft (12), the driving facility (18) to move the movable part (16) relative to the shaft (12). The driving facility comprises the first fastened section (20), which is mounted on the structural element (14) and the second movable section (22), which is mounted on the shaft (12) and is connected to the movable part (16). The driving facility (18) consists of the electromechanical drive with the air gap between the first section (20) and the second section (22).

EFFECT: reduction of friction between the moving parts.

9 cl, 5 dwg

Screw-turbine // 2330966

FIELD: engines and pumps.

SUBSTANCE: invention relates to power engineering. The screw-turbine consists of the blade supports fitted on an axle parallel to a liquid or gas motion direction. The first support is rigidly fitted on the said axle. Other details are fitted on the axle to allow varying the number of the screw-turbine blades due to aligning the blades details at their within the limits set by limiters. The last detail is coupled with the axle by a spring mechanism. The blades supports are interconnected by springs. Each blade support is connected by the spring to the axle.

EFFECT: higher ratio of utilisation of energy of variable-speed moving gases and liquids and continuous reduction of pressure at the screw turbine blades at increasing loads.

3 cl, 8 dwg

Gas turbine // 2351770

FIELD: engines and pumps.

SUBSTANCE: invention relates to turbojet engine gas turbines. Gas turbine blades are mounted on a cylindrical sleeve to rotate and axially move thereon which is provided for by attaching it to structural circular wall tapered ledge. The said wall central part represents a two-wall cylinder incorporating a spring fitted between the cylinder walls and resting upon the circular ledge of cylindrical barrel rigidly fixed on the shaft. The barrel rear part has a circular wall made integral with a part of vortex turbine blades to allow the second part of aforesaid blades made on the structural circular wall inner surface to enter into the said first part to have both parts aligned in axial travel. Circular webs arranged on the turbojet engine intermediate structural casing confine the vortex turbine blade outer parts. Fuel, in compliance with the fuel lines, actuates the cylindrical sleeve axial travel mechanism to vary the circular gap size controlling the passage of gas flow onto the gas turbine blades.

EFFECT: power take-off adjustment.

2 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: position control device of turning guide blades of compressor or turbine of gas turbine engine includes synchronising rings arranged outside the housing of compressor or turbine and connected to guide blades with adjustable rods and drive mechanism containing at least one blade position angle sensor. The latter is connected to one of shafts of blade drive through levers and additional rod, one end of which is hinged to one of levers of blade drive shaft, and the other end of additional rod - to levers of sensor; at that, levers of blade drive shaft, one of which is kinematically connected to sensor and the other one - to drive mechanism, are made separately on drive shaft with possibility of being moved in parallel planes.

EFFECT: ensuring fail-safe operation of device owing to accurate measurement of actual angles ϕHA of blade position of compressor or turbine of gas turbine engine at failure of drive mechanism of the above blades.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed turboprop comprises propeller with blades secured to annular rotary support adjoining the outer stationary casing enveloping turbine driving said rotary support. Every blade is fitted on pivot to turn relative to rotary support. Gear wheel is fitted on every pivot to engage with driving annular structure making gear wheel fitted to rotate about engine axis about rotary support. Driving annular structure is coupled with outside annular control structure fitted aligned with rotary support via planetary train arranged on rotary support. Planetary train comprises annular spider arranged to rotate on rotary support. Two sets of planetary gears are fitted on said spider. Note here that gears of the first set are located between rim of rotary support and ring gear of stationary casing while gears of the second set are mounted between rim of driven annular support and ring gear of annular control structure.

EFFECT: simplified design.

4 cl, 2 dwg

FIELD: transport.

SUBSTANCE: set of inventions relates to the airscrew blade pitch adjustment system for aircraft gas turbine engine. Proposed system comprises the following components that follow: first race coupled with airscrew blade to allow setting the angle of attack of said blade in rotation and second race, drive element 60 for first race arranged between said and second races and having the section with angular recesses. Besides, it has, at least, one locking element 64 arranged between said first and second races at said section with angular recess of drive element in V-like groove of the first race. Element 64 can seat at normal centered element to drive simultaneously said first and second race and at unlocking position to allow shift in rotation of assembly including first race, element 64 and element 60.

EFFECT: simplified design, no use of separate locking mechanism, decreased weight, higher reliability.

17 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: system of propeller screw blade pitch control in a turboshaft engine comprises the first and second circular guides, an activating element, and also the first and second blocking elements. The first circular guide provides for installation of an angle of attack of the specified blade and has the first and second seats that are distant from each other along the circumference. Each seat is formed with the first and second thrust surfaces. The second circular guide is made concentrically with the first guide and is located outside relative to it. The second thrust surface of the first seat and the first thrust surface of the second seat are aligned towards the second guide. The activating element is placed between the first and second guides and has the first and second thrust surfaces. The first blocking element is placed in the first seat opposite to the specified second thrust surface of the activating element. The second blocking element is placed in the second seat opposite to the first thrust surface of the activating element. The first and second blocking elements are made as capable of taking normal centralised position, and also unblocking position in the first and second circular directions. During control of the above system of propeller screw blade pitch control, the activating torque is applied to the activating element. Other inventions of the group relate to a propeller screw of a turboshaft engine comprising the above system of blade pitch control, and also to an aircraft engine comprising such propeller screw.

EFFECT: inventions make it possible to increase reliability of a system of blade pitch control, to reduce its weight.

10 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: turboprop comprises the system (24a) of fan vanes (26) with adjustable orientation rigidly coupled with spinning ring (28a). Said ring is centred relative to lengthwise axis (12) and engaged with turbine rotor. Every vane of said system is connected with timing ring (30a) centred along lengthwise axis for adjustment of vane orientation. Besides, it incorporates power cylinder (38) rigidly engaged at revolution with turbine rotor and mechanically connected with timing ring by several coupling levers (40a). Every lever is coupled with power cylinder con-rod (44) and articulated with timing ring so that power cylinder motion caused rotation of timing ring about lengthwise axis. Turboprop with dual screw comprises turbine (20) with two opposite-rotation rotors and two systems of fan vanes (26) of adjustable orientation.

EFFECT: easy and accurate control, decreased weight.

10 cl, 5 dwg

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