Gas turbine with bilateral drive

FIELD: power industry.

SUBSTANCE: gas turbine system comprising a gas turbine (23), a first load (71) and a second load (72) driven by a gas turbine. The gas turbine (23) comprises a gas generator (27), a low pressure turbine (50) and a drive shaft (65) driven by a low pressure turbine (50). The drive shaft has the first end (65H) connected with ability to transmit the driving force to the first load, and the second end (65C) connected with ability to transmit the driving force to the second load. The first load and the second load are located on opposite sides of the gas turbine, wherein the drive shaft (65) extends axially through the gas turbine from the first end to the second end. Wherein, the first load and the second load contain a compressor with a vertical housing connector. Method for operating gas turbine system is also provided.

EFFECT: invention allows to increase the efficiency of system.

14 cl, 5 dwg

 



 

Same patents:

FIELD: transport.

SUBSTANCE: system counter-rotating propellers for aircraft turbine machine. Power turbine contains the first and the second counter-rotating rotors. Mechanical transmission device is located between the first and the second propellers and contains epicycloidal transfer mechanism including planetary gear, pinion gears, pinion cage and crown gear. The planetary gear is actuated by the first rotor of free power turbine, the pinion gears are geared with the mentioned planetary gear, and pinion cage actuates the first propeller. Actuated by the second rotor crown gear is geared with each pinion gear and imparts rotary motion to the second propeller. Another invention from the set relates to aircraft turbine machine containing above mentioned system of counter-rotating propellers.

EFFECT: simplified design and smaller dimensions of turbine machine.

10 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: connection assembly of rotors of the compressor and turbine of the gas turbine engine contains compressor clutch installed on the intermediate shaft, turbine shaft, tension puller, lock pipe, and regulating bushing and stop nut. The turbine shaft is installed on the intermediate shaft and is connected with it in circle direction by means of the spline joint, and tension puller is connected in circle direction with the lock pipe by means of the spline joint. The compressor clutch is installed on the turbine shaft and is connected with it in axial direction by means of the mentioned tension puller, and in circle direction byy means of the spline joint. The regulating bushing is installed on the turbine shaft by means of the thread connection and is in contact with the intermediate shaft over the end faces, and in circle direction the regulating bushing is connected with the compressor clutch by means of the spline joint. The stop nut is installed on the intermediate shaft by means of the tread connection and is connected in circle direction with the compressor clutch by means of the spline joint. The end faces of the stop nut and the compressor clutch are in contact with the end face of the regulating bushing.

EFFECT: invention ensures increased service life of the connecting assembly of the rotors of the compressor and turbine, reduces its weight and size, simplifies assemblage.

2 cl, 1 dwg

Turbomachine rotor // 2534680

FIELD: machine building.

SUBSTANCE: turbomachine rotor comprises a turbine disk connected to the compressor shaft by bolt connection, and a bush set on the inner side of the disk hub. The bush consists of movable and fixed parts. The tail of the fixed part is provided with a circumferential rib and an annular groove. The movable part is placed on the side of the bolt connection and is able of axial displacement. The front tail of the movable bush part is provided with sealing rings and is fixed in the radial direction by a compressor bush. The rear tail of the movable bush part is provided with axial grooves and radial protrusions. The rear tail of the movable bush part is fixed in the radial direction by the circumferential rib of the fixed bush part. In the circumferential direction the rear tail of the movable bush part is fixed by the radial ribs of the fixed bush part tail which are inserted in the axial grooves of the movable bush part tail. In the axial direction the rear tail of the movable bush part is fixed by radial protrusions which are inserted in the inner annular groove of the fixed bush part tail.

EFFECT: improved reliability and manufacturability of a turbomachine rotor.

5 dwg

FIELD: engines and pumps.

SUBSTANCE: differential speed reduction gear of a turbo-propeller engine includes an inlet gear shaft, internal and external outlet gear shafts, four gears with a big gear rim, as well as two gears with a small gear rim for external and internal outlet gear shafts respectively. The inlet gear shaft is adjacent through external gear engagement to gears with the large gear rim. The internal outlet gear shaft is adjacent through external gear engagement to gears with the large gear rim. The external outlet gear shaft is installed concentrically relative to the internal outlet gear shaft. Gears with the large gear rim are located symmetrically around the inlet gear shaft and adjacent to the inlet gear shaft through helical-gear train. Gears with the low gear rim for the external outlet gear shaft are located symmetrically relative to each other; besides, each of them is installed concentrically by means of a spline connection onto the corresponding gear with the large gear rim and adjacent through external helical-gear train engagement to the external outlet gear shaft. Gears with the low gear rim for the internal outlet gear shaft are located symmetrically relative to each other; besides, each of them is installed concentrically by means of a spline connection onto the corresponding gear with the large gear rim and adjacent through external helical-gear train engagement through an intermediate gear to the internal outlet gear shaft.

EFFECT: invention allows reducing mass-and-dimensional characteristics of a speed reduction gear, as well as increasing its production accuracy.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: reduction gearbox comprises input pinion shaft with external gearing with the set of planetary pinions, inner output shaft and outer output shaft with solid of revolution including the inner gearing rim. Inner output shaft is fitted concentrically in outer output shaft. Input pinion shaft is equipped with bearings. Note here that al least one bearing of input pinion shaft is concentrically is fitted in inner output shaft. Input pinion shaft is engaged via outer helical gearing with small rim of the set of planetary pinions engaged with inner output shaft provided with bearing arranged aligned with outer output shaft bearing. Large rim of the set of planetary pinions is engaged via inner spur gearing with the rim of solid of revolution. Outer output shaft inner gearing rim pitch circle diameter relates to input pinion shaft pitch circle as 1.5-2.

EFFECT: decreased overall dimensions, decreased losses in gearing.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises central assembly support, gearing assembly and flexible support. Central assembly support makes an inner circular wall for axial stage and comprises first spline joint elements. Gearing assembly engages shaft and fan running about axis. Flexible support coupled said gearing assembly with central assembly support and comprises second spline joint elements to be engaged with aforesaid first spline joint elements to transmit torque there between. In disassembly of engine front section, access is allowed to forward-facing fasteners that secure central assembly support to flexible support, gearing housing to remove said fasteners. Then, first and second spline joint elements made at central assembly support and flexible support are disengaged.

EFFECT: simplified disassembly.

20 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: countershaft is arranged between low-pressure compressor rotor shaft and low-pressure turbine shaft and splined therewith tangentially while axially it is coupled by coupling bolt and pipe, respectively. Note here that coupling pipe is locked tangentially by coupling pipe splines. Said pipe locks tangentially said coupling bolt by splines and is splined with low-pressure compressor rotor. Note here that spring is arranged between coupling bolt and lock pipe and aligned with the latter. Besides, cavity is made at stator section confined by sleeve and axially displacing piston. Said cavity communicated with hydraulic system delivery side via channel with bypass line. Note also that said piston is locked tangentially relative to sleeves by splines. Note that spring is arranged between said sleeve and piston and aligned with the latter. Besides, near tend surface of lock pipe and piston are tapered to make the gap there between. Bypass valve is connected with digital control system computer.

EFFECT: preservation is shafts alignment at worst-case situation.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed mechanism comprise two opposite rotation propellers, drive turbine, shaft engaged therewith, fixed casing supporting the turbine by shaft and two bearings, transmission and hub. Transmission comprises planetary gearing with central planetary gear drive by turbine, pinion carrier equipped with plane pinions engaged with planetary gears and outer rim to be engaged with plane pinions. Pinion carrier drives of the propellers while outer rim drives the second propellers. The bush is engaged with turbine and planetary gear and is surrounded by said shaft. Note here that clearance is maintained between said bush and shaft. Bush features larger elasticity than the shaft so that it bends when unbalances forces are applied to planetary gear in radial direction. Spacing between one of the bearings and planetary gear is the spacing between two bearings.

EFFECT: lower mechanical strain in gearing, higher reliability.

6 cl, 4 dwg

Turbo unit // 2518919

FIELD: energy industry.

SUBSTANCE: turbo unit of gas-compressor unit (GCU) or gas turbine power plant (GTPP) comprises a gas turbine engine (GTE), a casing of the gas turbine engine, a compressor (blower) with labyrinth shaft seals, a transmission, a transmission casing with flanges, located between the casing of the gas turbine engine and the compressor. The transmission casing is provided with the inner wall forming the air duct together with its outer wall, which connects the casing cavity of the gas turbine engine with the area in front of the labyrinth compressor seals through the openings formed in the flange of the transmission casing, and the openings formed in the inner wall of the transmission casing, connected to it through the radial channel formed by the partitions fastened to the inner wall of the casing.

EFFECT: use of the proposed invention enables to increase pressure in the exhaustion area in front of the compressor seals that will prevent the penetration of oil and its vapour from the compressor into the cavity of the casing of GTE and will prevent occurrence of emergencies.

5 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine gas generator comprises two-stage rotary compressor, combustion chamber and, at least, one turbine axial stage coupled with compressor along the axis to make single-piece rotor running stator bearings. Compressor and turbine impellers are composed of solid discs with front and rear tubular journals at every disc. Impeller of compressor first stage has its journals running in stator bearings. Note here that splines are made inside rear journal. Compressor second stage impeller front journal runs in stator roller bearings while journal splines are engaged with compressor first stage rear journal splines. Turbine impeller front journal outer surface has cylindrical thrust collar and splines and second cylindrical thrust collar on its inner surface, both being engaged with cylindrical thrust collar on compressor second stage cylindrical thrust collar outside compressor second stage impeller rear journal. Rear journals of compressor first and second stages are splined by disengage couplings with compressor second stage front journal and turbine impeller front journal.

EFFECT: higher reliability, decreased weight and costs.

15 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: rotor system of magnetoelectric machine contains a casing of the turbine block, shaft installed turbine, the shaft installed in bearings, a generator casing, a rotor. The rotor contains uniformly installed permanent magnets, magnetised in radial direction with alternating polarity. Turbine and rotor are installed on same hollow shaft, with possibility of coolant pumping through its cavity by the pump installed at the turbine side. At end of the hollow shaft a spiral channels are made. The hollow shaft with rotor creates a cylinder with permanent cross-section, on its external surface a bandage shell is installed out of high strength non-magnetic material. The bearings can be made in form of the contact-free gas supports, electromagnetic bearings or hybrid magnetic bearings.

EFFECT: minimised heating of the permanent magnets, and heat transfer between the turbine shaft and generator shaft, increased rigidity and mechanical strength of the system due to the generator shaft and turbine shaft making as single hollow shaft with possibility of the coolant pumping through its cavity, and spiral grooves making at the rotor end.

4 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed turbo generator comprises the turbine fitted on generator shaft integrated with said turbine in tight housing with inlet and outlet flanges for connection to gas-distributing station. Said turbine represents a vortex turbine. Generator shaft can rotate and displace axially relative to said housing. Said housing accommodates hydraulic resistance adjusting assembly secured at housing cover inner part to allow axial displacement of generator shaft. Said hydraulic resistance adjusting assembly is connected via branch pipe with the housing inlet chamber.

EFFECT: higher reliability, controlled power output.

4 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine, in particular for helicopter, comprises gas generator and free turbine driven by gas flow generated by the latter and reversible electrical machine to be connected with said gas generator. Reversible electrical machine drives aforesaid gas generator in starting of gas turbine engine and can be coupled with free turbine after gas turbine starting for electric power generation.

EFFECT: optimised load at engine, decreased fuel consumption.

12 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: jet-turbine engine includes a high-pressure housing, a low-pressure housing, a nacelle and an electric generator. The low-pressure housing brings into rotation the fan located in a fixed casing being a part of the nacelle. Electric generator is located in the fan and takes power from it. Electric generator includes a rotor built into a fan and includes constant magnets fixed on the fan blades. Besides, the electric generator includes a stator built into the fan casing and a deflector installed in the fan casing for cooling of the above stator.

EFFECT: possibility of avoiding problems with operation of an engine in an idle mode and conversion of mechanical power to electric power with increased efficiency; simpler plant and maintenance of an electric generator.

FIELD: machine building.

SUBSTANCE: proposed assembly comprises rotor, stator, electric generator, support assemblies, working body inlet, groove seal and turbine exhaust. Impeller and compressor wheel ate fitted on assembly rotor shaft while electric generator rotor section is fitted there between. Turbo electric generator assembly stator consists of turbine and compressor cases and includes electric generator stator arranged between turbine and compressor cases. Working body feed channel extending from inlet to compressor is made in rotor hollow shaft. Groove seal area between turbine exhaust and working body inlet accommodates extra axial compressor stage. Rotor shaft has openings to communicate working body feed channel with assembly stator cavity. Assembly stator has channel for cooling electric generator stator, supports and turbine hub.

EFFECT: higher efficiency of cooling.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: two-shaft gas turbine jet engine comprises high-pressure and low-pressure rotors. High-pressure rotor shaft is coupled by its front end with encased fan. Fixed cowl element aligned with engine axis is arranged ahead of fan to support current generator mounted to take off low-pressure rotor shaft power to be converted into electric power. Current generator comprises stator element jointed with fixed cowl element and rotor elements driven by low-pressure shaft front end. Turbojet includes also power transfer gears fitted on generator rotor element and low-pressure rotor shaft front end. Said gears engage to transmit rotation of low-pressure rotor shaft to current generator rotor.

EFFECT: easier access to current generator.

8 cl, 4 dwg

FIELD: power engineering.

SUBSTANCE: line of generator - steam turbine - turbocompressor comprises a frequency-variable generator, a steam turbine and a turbocompressor, driven by the generator and/or the steam turbine, which are interconnected with a shafting, besides, the generator is electrically connected with an electric network for grid supply, and the steam turbine has the possibility for connection to a device of live steam supply for supply of live steam to the steam turbine, so that the line of generator - steam turbine - turbocompressor by means of changing grid supply and/or by means of supply of live steam may be controlled according to the number of rotations.

EFFECT: invention makes it possible to increase efficiency and to provide proper controllability with insignificant investment costs.

7 cl, 3 dwg

FIELD: power engineering.

SUBSTANCE: device for extraction of energy from a compressed gas flow comprises an expansion turbine, having an expansion turbine impeller, and a generator comprising a rotor and a stator. A radial inlet flow arrives into an expansion turbine impeller. The generator comprises a rotor and a stator. The rotor is rotated by the expansion turbine impeller. The external surface of the stator comprises cooling ribs. The expansion turbine and the rotor are installed in the pipe section. The face side of the expansion turbine impeller faces the generator. In the device there is an unlimited passage for an expanded gas flow providing for communication by means of a gas flow between a face side of the expansion turbine impeller and the external surface of the stator. Such multiple devices may be arranged in series. The distribution pipeline of natural gas comprises the specified device.

EFFECT: improved heat removal from a generator without necessity in external cooling.

15 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: device for electric energy generation in multishaft gas turbine engine and for rotation of auxiliary electric machine includes at least one first low pressure rotary shaft containing compressor and turbine, and the second high pressure rotary shaft containing compressor and turbine. Auxiliary electric machine is double-rotor and includes the first and the second rotors. The first rotor is mechanically connected to the first rotary shaft, and the second rotor is mechanically connected to the second rotary shaft. Auxiliary electric machine is reverse-type and made so that it can operate in the electric generator mode when at least one of its two rotors is brought into rotation with one or the other rotary shaft of gas turbine engine, with which it is connected, or it can operate in the actuator mode to bring at least one of the rotary shafts into rotation.

EFFECT: providing the takeoff of power that can be distributed depending on needs between different rotary shafts of gas turbine engine; bringing into rotation at least of one of rotary shafts by means of the same devices during start of gas turbine engine.

10 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine (10) of airborne vehicle, namely helicopter, includes gas generator (12) and free turbine (14) rotated with gas flow (F) generated with gas generator. Gas turbine engine includes motor generator (30) electrically connected to accumulator (32) and mechanically connected to shaft (18) of gas generator (12). Accumulator has the possibility, on one hand, of feeding motor generator (30) during acceleration phase of gas turbine engine in order to supply to shaft (18) additional amount of kinetic rotation energy, and on the other hand, for storage in the form of electric energy the amount of kinetic energy taken with motor generator (30) from shaft of gas generator during braking phase of gas turbine engine. Accumulator (32) is made so that it can be recharged with the first electric generator (34) connected to shaft (16) of free turbine (14).

EFFECT: achieving the acceleration degree exceeding the acceleration of gas turbine engine from known level of equipment at the same stall margin, or providing the possibility of development of gas turbine engines with decreased stall margins, which is expressed in preferable reduction of overall dimension of gas turbine engine.

4 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engines. A turbine pump, in which a pump impeller is connected to one end of a rotary shaft, and a turbine is connected to the other end of the rotary shaft. The turbine pump is made so that the equivalent area between the efficiency curve of the turbine produced on the basis of a conditional expression, in which the number of rotations of the rotary shaft is maintained as permanent regardless of the pump flow speed and efficiency curve of the actual machine turbine, becomes the working area. A rocket engine is considered, using a turbine pump, which is made so that the equivalent area between the efficiency curve of the turbine produced on the basis of a conditional expression, in which the number of rotations of the rotary shaft is maintained as permanent regardless of the pump flow speed and efficiency curve of the actual machine turbine, becomes the working area.

EFFECT: invention provides for reduced moment of inertia of a turbine pump and improves speed of response of a rocket engine of a turbine pump type.

5 cl, 10 dwg

Up!