Gear box for power take-off in gas turbine engine consisting of kinematic circuit with engagement lines arranged in non-parallel planes

FIELD: engines and pumps.

SUBSTANCE: gear box of the gas turbine engine for actuating its additional equipment comprises a housing, a kinematic circuit within the housing, a row of gears, and a power take-off mechanism for engagement with transmission shaft of the gas turbine engine. The housing comprises attachment points to the gas turbine engine and to the equipment, and the kinematic circuit comprises at least two end engagement lines arranged in non-parallel planes and joined to each other by adjacent engagement consisting of a pair of gears with non-parallel axes. At least one end engagement line at the end of the kinematic circuit is placed in the end branch of the housing which has the largest dimension in the axial direction of the gas turbine engine when the gearbox is attached to the gas turbine engine. Another engagement line is placed in the intermediate branch of the housing, in the circular section that partially surrounds a portion of gas turbine engine circumference when the box is attached to the gas turbine engine.

EFFECT: invention makes it possible to reduce the overall dimensions of the gear box of the gas turbine engine.

6 cl, 5 dwg



Same patents:

FIELD: engines and pumps.

SUBSTANCE: mid housing (20) of turbojet blower compartment (Cs) comprises the following components: Shell ring (22), circular web (24), suspension beam (28) and auxiliary gearbox (30). Shell ring (22) is centred in gas turbine engine lengthwise axis (X-X). Circular web (24) is centred in engine lengthwise axis and located opposite shell ring downstream side. Suspension beam (28) is secured to said web to extend in flow direction, parallel with engine lengthwise axis. AGB (30) swivels on said beam and comprises upstream lateral side (30b) axially spaced from the web, downstream lateral side (30a) opposite said upstream lateral side. Besides, it comprises multiple auxiliary hardware (32) arranged opposite downstream lateral side and along engine lengthwise axis.

EFFECT: possibility to fit AGB in aircraft central compartment.

8 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed device comprises first and second gears rigidly fitted in starter-generator shaft, first and second mid gears, clutch and clutch drive. Said first and second mid gears are fitted on turbine shaft to engage with first and second fixed gears, respectively, to allow different gear ratio. Said clutch is fitted in between mid gears and engaged mechanically with turbine shaft. Said clutch can displace on turbine shaft between the position whereat it engages with first mid gear and that whereat it engages with second mid gear. Clutch drive displaces the clutch from one position to another when the sum of torques between turbine shaft and starter-generator shaft changes its sign. Another invention of the set relates to aircraft turbine incorporating aforesaid gear ratio variator.

EFFECT: higher reliability, decreased weight.

9 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: gear box assembly of units and a tank for lubricating oil of a jet-turbine engine includes a box with two compartments and a partition wall separating the compartments from each other. One of the compartments forms a gear box of units, and the other compartment forms a tank for lubricating oil and a support at least of one of the units driven with the gear box of units. The gear box of units includes a gear transmission connected to shafts for mechanical actuation of units, which are parallel to each other. The partition wall is located perpendicular to shafts of the gear box of units and closes interaction between two compartments to avoid oil flow between them. The box has a curved shape adaptable for tracing the shape of the cylindrical casing of the jet-turbine engine, on which it is fixed.

EFFECT: invention allows simplifying production of a gear box assembly of units and a lubricating oil tank.

8 cl, 2 dwg

FIELD: transport.

SUBSTANCE: holding bracket for aircraft equipment includes flange for attachment to carrying structure, equipment mounting crossbar and intermediate reinforcement element all made of one bended plate of sheet metal. The reinforcement element consists of two reinforcement ribs each one of which is located between flange and crossbar and connected with them by means of elbow connection. Most of reinforcement ribs are placed at an angle, not perpendicular to the main plane of flange passage and the main plane of crossbar passage. Crossbar and flange does not contain other connection than reinforcement ribs, where the reinforcement ribs are connected with both sides of crossbar. Flange and crossbar passage planes are mutually perpendicular. The reinforcement ribs are made flat, expanding as they approach the crossbar and pass in convergent directions thus forming an angle differing from 180. The crossbar has projections in direction perpendicular to plane of flange extending portion and to each side of flange and contains several equipment mounting facilities.

EFFECT: higher strength of holding bracket.

3 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: intermediate case of a two-flow jet turbine engine includes at least one annular partition wall for separation of a gas flow into two annular concentric flows, primary and secondary ones respectively. Between inner hub and outer cylindrical shell there located is a variety of radial racks. At least one of the racks is hollow and includes the first part passing through primary flow and the second part passing through secondary flow. In the above radial rack there installed with possibility of being rotated is a transmission shaft of the drive of auxiliary units. The first end of the transmission shaft passes through the inner hub, and the second end passes through outer cylindrical shell. Inner volume of the radial rack consists of one section, in which the transmission shaft is arranged and which forms a channel for lubricating fluid. The other object of the invention is a jet turbine engine containing a chamber with support bearings, a gear box of auxiliary units and the above described intermediate case. Radial rack of the case provides interaction between the chamber and the gear box of auxiliary units.

EFFECT: invention allows laying the auxiliary equipment of the engine in the structural rack of the case.

8 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: auxiliary power is taken off by means of shaft brought into action by means of high pressure turbine, and low pressure turbine efficiency is reduced at idle operation so that possibility of high pressure turbine operation at the speed that is sufficient for supply of the required auxiliary power can be provided.

EFFECT: invention allows optimum redistribution of powers of low and high pressure turbines.

4 cl, 2 dwg

Gas turbine drive // 2457346

FIELD: engines and pumps.

SUBSTANCE: gas turbine drive comprises inlet device, radial-flow compressor, combustion chamber, turbine, outlet device and reduction gear. Intermediate housing accommodating torque transmission is arranged between reduction gear and inlet device to make common oil chamber there between. Intermediate housing incorporates extra flange with through hole to allow connection with mate flange of extra ganging module housing. Extra ganging module comprises drive gear to engage with, at least, two gear wheels, one being engaged with gear connected with starter. Another wheel of said extra module allows transmitting torque to extra driven assemblies. Said extra module is connected with torque transmission via spring and does not depend upon reduction gearbox gear ratio. Said spring passes through opening in intermediate housing wall to be connected with extra module drive gear and torque transmission bevel gear. Said bevel gear is fitted on torque transmission assembly with its central axis aligned with gas turbine drive rotational axis. Intermediate shaft is engaged with drive shaft and reduction gear drive wheel to transmit torque from gas turbine.

EFFECT: higher performances and reliability, longer life.

2 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: aircraft gas turbine engine 1 comprises, at least, one rotor shaft supporting, at least, one compressor, turbine and housing. At least, one generator assembly 10 is fitted on rotor shaft to generate electric power. Generator assembly 10 comprises mounting plate 11b and generator 12. Assembly 10 is fitted on said mounting plate 11a arranged on engine side and may de detached therefrom. Said plate 11a has connection elements to fasten generator assembly 10 thereto. Mounting plate 11a comprises, at least, one mechanical mount, device to transmit motion to generator, electrical contacts and/or pipeline connection ports.

EFFECT: simplified mounting/dismantling and servicing.

11 cl, 5 dwg

FIELD: turbojet engine.

SUBSTANCE: double-flow turbojet engine contains the intermediate jacket, with installed drive shaft of transfer gearbox in its radial arm designed to auxiliary drives. The drive shaft of output transfer gearbox is connected on its first end with the mechanical transfer mechanism placed on the drive shaft of the turbojet engine, and on the second end with the mechanical transmission to the abovementioned gearbox. The drive shaft of output transfer gearbox has a conic gearwheel between two ends of this shaft and allows providing mechanical linkage with additional auxiliary equipment. The drive shaft of output transfer gearbox in combination with the abovementioned gearwheel is encased forming an oil circuit, sealed in relation to the radial arm.

EFFECT: allows limiting a inflammable area at the expense oil leak elimination.

16 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: rotor drive of auxiliary unit, which is installed on support of units of gas-turbine engine, which contains rotor shaft drive means, includes tubular shaft rotated with the above means and supported with the first and the second support bearings rigidly connected to the support of the units. Rotor shaft is installed coaxially with tubular shaft, and engagement device with rotation is provided between rotor shaft and tubular shaft. Rotor shaft is supported with the third support bearing rigidly connected to the support of the units. The first and the second support bearings have the size which is less than size of the third support bearing. The other invention of the group refers to the support of gas-turbine engine units, which contains the gears rotating the above drive. One more invention of the group refers to gas-turbine engine containing the shaft and power take-off devices on the shaft, rotary gears of the above support of the units.

EFFECT: inventions allow improving reliability of rotor drive of auxiliary unit.

12 cl, 6 dwg

Gas-turbine unit // 2245448

FIELD: power engineering.

SUBSTANCE: proposed gas-turbine unit has low-pressure compressor, intermediate air cooler, high-pressure compressor, regenerator, combustion chamber, gas turbine wherefrom spent gas is conveyed to regenerator coupled with exhaust pipe that uses energy of exhaust gases and is provided with nozzle and intake chamber for cooling down atmospheric air arriving from intermediate air cooler. Proportion of exhaust pipe parts is chosen to ensure desired proportion of sizes of gas-turbine components.

EFFECT: enhanced reliability of gas-turbine unit and ability of its off-line operation.

1 cl, 1 dwg

FIELD: aircraft engineering; gas turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device to transmit torque from compressor shaft to box of auxiliaries of gas-turbine engine includes spur gear wheel and bevel gear spaced and connected by seat surfaces and splines. Bevel gear is mounted on separate bearing support. Inductor is fitted in inner space of spur gear.

EFFECT: improved reliability of engine by provision of accurate signal from device checking frequency of rotation of compressor rotor.

1 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device contains fastening members and movable member telescopically connected with casing. Movable member is on accessory gear box and secured by pressure flange for displacement along end face of box. Clearance is formed between mating surfaces of flange and movable member.

EFFECT: improved reliability of connection of casing and accessory gear box by providing their rigid connection and sealing of inner spaces.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to aviation and particularly to devices for restraint and arrangement of auxiliary equipment in turbojet engines. The device consists of two coaxial rings (12, 14) assembled one into another and connected to each other with hollow radial poles (16, 18, 20 and 22). The pipelines and electrical wires run inside poles. At least one of the side poles (16, 18) bears a removable panel (24, 26) on its side, which after dismounting facilitates an access to the equipment of the turbojet engine arranged radially inside the interior ring (12) in one line with the radial pole (16, 18). Such design of the device provides an access to the equipment, installed in a turbojet engine.

EFFECT: facilitating access to equipment, assembled in a turbojet engine due to arrangement of a restraining device and of auxiliary equipment.

10 cl, 5 dwg

FIELD: electricity.

SUBSTANCE: cable bundle (3) positioning and retaining station on the turbojet engine (1) housing (2) includes bundle supports (3) standardized for directions perpendicular to the turbojet engine (1) axis (4) and bundle supports standardised for directions parallel to the turbojet engine (1) axis (4).

EFFECT: reduction of manufacturing cycle cost and time.

14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: invention is intended for feeding electric power to equipment from gas turbine engine. The proposed system comprises an electronic control device to control, at least, one parameter containing the data on originating variation in consumed power, a control valve controlled by aforesaid system and feeding air take off the engine operated in transient conditions and a pneumatic device receiving aforesaid taken-off air to actuate the aircraft onboard equipment. The latter can represent an air turbine or generator with built-in pneumatic circuitry.

EFFECT: use of engine pneumatic power to drive aircraft onboard equipment.

33 cl, 10 dwg

Air engine design // 2355902

FIELD: engine engineering, aviation.

SUBSTANCE: in accordance with the present invention fillet fairing is installed inside bypass channel of the external engine circuit in order to avoid outer thickness of auxiliary mechanisms and gear boxes and to actuate them. The external circuit channel is between engine housing and inner circuit of compressor/engine turbine. The fillet fairing dimensions are enough to accommodate auxiliary mechanisms. At the same time the external circuit channel is correspondingly made axisymmentrical to avoid or compensate any blocking effect from fillet fairing within the channel limits when air flows. In addition the fillet fairing may be provided for placing engine oil tank as well as filter/heat exchanger mechanisms foreseen for engine. Under the above circumstances it is essential that elongated cylindrical engine profile is maintained so that reduced cross section is required allowing for the engine to keep a reduced glider of air craft. As a result acoustic shock waves profile is improved.

EFFECT: elimination of outer thickness when auxiliary mechanisms are placed.

FIELD: engines and pumps.

SUBSTANCE: proposed unit consists of gas turbine and reduction gear accommodated inside container and coupled via transfer shaft, reduction gear output shaft carrying the pump. Input device is arranged between said reduction gear and engine so that device front face wall part seats on reduction gear, while device read face wall part is located on gas turbine engine. Note here that both aforesaid parts are linked up axially and radially by sealed telescopic couplings with the remaining part of input device fixed container. Inlet inspection window is made in input device front face wall. Input device lower wall is made flat and horizontal. In operation, sealed telescopic couplings allow the engine and reduction gear to move relative to input device with no loss in tightness on the latter.

EFFECT: higher reliability, reduced weight and overall dimensions, easier mounting and control.

3 dwg

FIELD: machine building.

SUBSTANCE: unit consists of gear box of gas turbine and of at least one starter/generator mechanically coupled with gear box. The gear box consists of gears with several pinions. The starter/generator contains a generating block with a rotor, forming an inductance coil and stator forming an anchor; further, the stator/generator contains an actuating block with the stator forming the inductance coil and rotor forming an anchor connected to the inductance coil of the generating block. The rotor of the generating block and the rotor of the actuating block are arranged on a common shaft with a pinion engaging the gear of the gear box on both sides of this pinion. The invention facilitates integration of the starter/generator into the gear box of the gas turbine.

EFFECT: reduced volume and dimensions, ensuring easy disassembly.

23 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: auxiliary mechanism drive of two-shaft gas turbine engine comprising high- and low-pressure shafts incorporates first mechanical transmission between high-pressure shaft and drive box, and hydraulic transmission between low-pressure shaft and drive box. Auxiliary mechanisms are arranged in drive box, while hydraulic transmission is mounted to allow auxiliary mechanism drive rpm being equal to high-pressure shaft rpm.

EFFECT: possibility to take off power from high- and low-pressure shafts without varying auxiliary mechanism rpm.

14 cl, 3 dwg