Gas turbine engine with generator assembly
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
The technical field to which the invention relates.
The present invention relates to a gas turbine engine, particularly for an aircraft, containing at least one rotor shaft that has at least one compressor and turbine, as well as the body.
The level of technology
Gas turbine engines of the type in question have generators that are installed on at least one of the shafts of the rotor so that by connecting to the shaft to remove the mechanical power that is converted into electrical energy. When this gas turbine engine can be operated on an aircraft, but we can talk about a stationary gas turbine engine. The electrical energy required to operate various electrical devices of the gas turbine engine and aircraft, and recent studies indicate that the demand of the engine and aircraft into electrical energy continues to increase due to the increasing degree of electrification of various units. These various electrical units are devices that previously worked only with a mechanical drive, such as fuel pumps and hydraulic pumps, which are often driven by the so-called box units, AB future could/should get an electric actuator. Energy demand is constantly growing and on Board the aircraft.
Proposed in the invention of the gas turbine engine is, in particular, turbofan engine, made by twin-shaft scheme, and the fan is a machine blade, providing a preliminary compression of the incoming engine air and creates a second circuit flowing path of the air flow surrounding the hot jet stream. Also known single-shaft engines, having located in front of the multistage compressor and located in the rear part of the single or multi - stage turbine.
From the publication US 2002/0122723 A1 known gas turbine engine of this type having a generator that is built into the high pressure compressor of the gas turbine engine. Gas turbine engine has a compressor stage of the compressor, surrounded the building, but outside of the body is a generator. The generator consists of a stator with an electric winding and a rotor connected to the motor shaft so that together with him to make a rotational movement. The rotor rotates inside the stator and induces in the stator winding voltage. Moreover, the elements of the rotor are located at the outside of the blades of the high pressure compressor and are radially outward of stator generator.
Another execution scheme generator, built-in gas turbine engine is known from patent US 6378293 B1. When this gas turbine engine has several shafts connecting the compressor with the relevant turbines gas turbine engine. A generator to generate electricity, the supply of the electromagnetic bearings and partially used to power the electrical equipment of the aircraft, if this is the end of the engine away from the electromagnetic bearings and is made as a separate unit. The drive generator by its connection with the shaft of the low pressure gas turbine engine. The disadvantage of this system is the difficulty of maintenance and installation, causing significant costs. In this connection liquid/gas lines have, as a rule, through a complex set of connecting devices, which are attached to cables and pipelines that when removing the generator disconnected again.
From RU 2168024 C2 known gas turbine engine, particularly for an aircraft, containing at least one rotor shaft that has at least one compressor and turbine and the housing, and at least one shaft of the rotor has at least one node of the power generator, the ate generator includes a mounting plate and a generator and has a removable manner on the mounting plate, located on the side of the engine.
In known prior art solutions for the installation site of the generator shaft gas turbine engine has a problem, namely, that the place of installation of generators inaccessible due to cramped conditions, in particular for installation in a zone of high pressure compressor. Even when installing a generator at the end of the shaft of the low-pressure compressor possibilities of installation, maintenance and execution of the corresponding pneumatic/hydraulic, mechanical and electrical connections of the generator with the gas turbine engine or the aircraft extremely difficult. Due to this significantly increases the amount of maintenance and installation, and very complex, in particular, replacement of the generator. When assembling or disassembling the generator it must first mechanically disconnected from the shaft of the low-pressure compressor, as you have to divide the electrical wires and pipes made, usually through a complex connective devices, such as cables and penstocks. The mechanical connection between the motor shaft and the generator includes in most cases, mechanical coupling, Assembly and disassembly which is also time-consuming.
Disclosure of inventions
The poet is the basis of the present invention was based on the task of creating a gas turbine engine with the node generator, which would be easy to install on a gas turbine engine and deregistration. The aim of the invention is the reduction of maintenance work to a minimum.
This problem is solved proposed in the invention of the gas turbine engine, particularly for an aircraft, containing at least one rotor shaft that has at least one compressor and turbine and the housing, and at least one shaft of the rotor has at least one node of the power generator, the node generator includes a mounting plate and a generator and has a removable manner on a mounting plate located on the side of the engine.
This mounting plate located on the side of the engine, has connecting elements for detachable connection node of the generator, and this mounting plate has at least one mechanical installation element, the transmission device motion generator, and the electrical contacts and/or leads for the connection of pipelines.
The basis of the invention is the idea that the node generator to generate electricity must have a device or a docking device (interface), which, firstly, rigidly connects the node generator with mounting plate, located outside the s engine and forming a second half of a multifunctional coupling devices and, secondly, directly or indirectly (through an intermediate mechanical transmission), connects the generator shaft with the shaft of the rotor. For this mounting plate located on the side of the engine, must be provided with a hole, the diameter of which is larger than the diameter of the shaft of the generator. To simplify the installation site of the generator to the mounting plate and remove the mounting plate is required at least one centering pin, which is included between two connected nodes, before any other elements will come into connection with each other.
The node generator can be located on the compressor side in the front and/or side of the turbine in the rear part of the gas turbine engine and is mounted on the shaft of the compressor/turbine. Both options are feasible within the framework of the present invention, and, of course, in both these places you can also install a generator. In front of the motor on the compressor side site generator can be built into the nose cone and the inlet guide device, and the place of installation in the rear part of the turbine, may be provided in the so-called output cone and the outlet guide device. Crucial to this are the conditions of placement and installation, and installation of the side of the compressor has the advantage that the sides of the engine are dominated by lower temperature.
However, the mechanical connection providing a drive, can also bind other rotor shaft of the motor generator, and this connection may include additional gear stage. When the installation site of the generator once still install the mounting plate, located on the side of the engine, in the input and/or output guide apparatus of the gas turbine engine and multi-function connecting device creates an electric, pneumatic/hydraulic and mechanical connections. Half of the multi-function connecting device located on the generator side, includes mirror image of the same functional parts as the second half of that in the attached state of the built-in generator to ensure unimpeded passage of electric current and fluid flows. Half of the connecting device from the generator may be his lanzoprazol an integral part of or can be installed as a separate component. In this connection elements are available in both halves of the multi-function connecting device electrical contacts and self-closing conclusions for joining pipelines, and sootwetstwujiut and pipelines are derived from the backside of the connecting device.
If the generator is removed from the node generator or replaced by a generator, it is sufficient to disconnect the alternator from the mounting plate, and a connection can be made simply and do not require time-consuming Assembly or disassembly. This greatly simplifies maintenance, since the generator can be performed according to the modular principle and its maintenance can simply be removed from the mounting plate on the side of the generator.
To get electrical wiring and piping between the mounting plate located on the engine side, and the non-rotating parts in the engine, is provided for mounting the plate on the stator of the gas turbine engine, the stator has a hollow rack that can be installed electrical cables and/or pipelines. In particular, heat-sensitive electrical wires conveniently laid in cavities (if necessary with additional insulation) of the poles of the stator, and it is also possible mechanical fastening of the mounting plate in the engine through a mechanical connection provided inside the cavities of the stator.
Preferably, the conclusions for the connection of the pipelines were made self-closing, so that when the disconnection to prevent the release of fluid. In this way ensure the scarfing lossless and careful dismantling, therefore, in particular with regard to cramped conditions, for automatic circuit connections are connection elements to the design. After making connections possible the free movement of the fluid and the separation of compounds from both the mounting plate and the generator valve shut-off device prevents leakage of fluid and contaminants from entering the piping. The fluid medium may be mainly the coolant of the cooling circuit connected to the generator. Electrical connections can be contacts (pins), without requiring a separate disconnection or re-connection.
Another preferred implementation of the present invention provides that the connecting element may have a seal formed by o-rings. This version of the seal, which when using connectors corresponding construction can be used and other types of seals.
Preferably, the connecting elements had razmykaetsya megaampere contacts providing electrical connection of the generator with the engine or aircraft. Load capacity current mnogomernyh contacts the can is up to 500 And, moreover, the electrical connections are particularly high reliability.
Along with the electrical power contacts of the connecting elements may include control contacts for controlling a generator and/or the contacts of the bus system for controlling a generator/provide feedback on its parameters. Thus, the electrical contacts include a generally signal connections are performed by separate elements of the connection between the mounting plate and the generator.
As a particularly preferred variant, in particular to achieve high flexibility, it is proposed to perform the docking interface mounting plate modular, which allows for the installation of generators of various designs. The generators are also made in the form of generator modules that have the same docking interface to install or mount them on a standard mounting plate. While various designs of generators can be synchronous, asynchronous or reactive, i.e. suitable, in particular, for the considered application.
In another preferred embodiment of the invention, the device for transmission of movement between the drive shaft located on the engine side, and the shaft of the generator includes a gear (splined)connection. When the shaft generator is designed as a hollow shaft and passes through a hole in the mounting plates. It can be connected with the shaft end of the rotor (turbine) engine, and the rotor shaft (turbine) installed in the bearings of the stator of the turbine. In this case, the axial fixation of the mates of both of the shafts is accomplished by attaching the flange of the generator to the mounting plate located on the side of the engine.
A pair of shafts may include, for example, the pinion shaft with curved teeth that provides both axial and radial movement of the rotor shaft (turbine). This allows easy, without additional auxiliary means to install and to remove or to install or remove a node generator with mounting plate, located on the engine side.
To ensure reliable fastening of the Assembly of the generator, it is proposed that the mounting space of the generator consisted of a cylindrical cavity with a diameter only slightly greater than the outer diameter of the mounting plate. So, there is formed a hollow cylinder glass type, containing in itself the mounting plate, so the generator is located inside the hollow cylinder. Thus, there is a kind of housing that protects the generator, in particular from the jet of hot gases at the outlet of the gas turbine engine. For this we can provide you atemperature isolation cylindrical cavity, forming a mounting space, to protect the site of the generator from the high temperatures of hot gases located in the rear of the output device of the engine. Thus, provided high-temperature insulation surrounds the generator, and it is preferable to use non-combustible or difficult flammable materials.
Brief description of drawings
Other embodiments of the invention are described in dependent claims or are explained in the description of the preferred embodiment of the invention with reference to the accompanying drawings on which is shown:
figure 1 is a side view of the node generator with mounting plate and mounted on the generator;
figure 2 is a perspective view of a gas turbine engine with an electric hub generator in accordance with the established state;
figure 3 is a perspective view of a gas turbine engine with an electric node of the generator, and the generator is shown removed from the mounting plate, located on the engine side;
figure 4 - scheme of the node generator mounted on the mounting plate, located on the engine side, and you can see the piping on the transition from multi-function connecting device;
figure 5 - diagram of the multi-function connecting device in a plane transverse széchenyi the V-V according to figure 4.
In the drawings, the technical implementation of the present invention is shown only as an example.
The implementation of the invention
Figure 1 shows a side view of the node 10 of the generator (consisting of a mounting plate 11b and the generator 12). On the left diagram shows the mounting plate 11a multi-function connecting device 17 located on the side of the engine right mounting plate 11b multi-function connecting device 17 from the generator. Both mounting plates are round and they are mounted are not shown here corresponding removable electrical modules and self-closing pipe joints. The right of a multifunctional coupling devices installed generator 12 having a cylindrical shape and on the middle axis 19 concentrically followed by half of the multi-function connecting device 17 from the generator. Between the generator 12 and the mounting plate 11b has a connector 13A, 13b, 13C and 13d, including power wires, signal wires for sensors, tires, and pipelines, which serves, for example, the coolant for cooling the generator 12. These wires and pipes are connected in a multi-function connecting device and are ejected from the rear side of the mounting plate 11a (in the drawing, the output is s not shown) through the hollow rack stator and the motor. Through the hole in the multi-function connecting device 17, concentric middle axis 19, is a shaft 14 of the generator for connection to the turbine shaft.
Figure 2 and 3 shows a perspective view proposed in the invention of the gas turbine engine 1. Gas turbine engine 1 includes a front input part 15 and the rear output device 16. The diameter of the gas turbine engine 1 in front of 15 more, as there are built-in fan. In the rear output device 16, the engine has a smaller diameter, and inside the output device 16 provides a mounting space into which the node generator 10 in accordance with this example embodiment of the invention. In figure 2 the node generator presented in the established state, while figure 3 shows in perspective before you place the actual installation inside the rear area 16 of the exhaust gas turbine engine 1. Thus, figure 3 is visible mounting plate 11a located on the engine side, on which the connection 20 and 20A of the pipelines, the plug 21 of the cable connector from the sensor and the contact 22 of the connector of the power cable. In addition, you can see the shaft 14 of the generator, positioned opposite the shaft 18 of the turbine and connected through a clutch or other device for connecting the shafts.
Figure 4 schematically show is about the connection node 10 of the generator (12 and 11b) with mounting plate 11a, installed on the engine side. In the plane of the section between the mounting plate 11a, shown with the release hatching on the drawing, and lanzoprazol connection part 11b of the generator 12 are actually connecting elements, whereby the connected connectors 13A, 13b and 13C. The connecting lines are like electrical wires, in particular the signal wires, tires and power wires and pipelines to supply coolant.
Top view on half of the multi-function connecting device 17 is shown schematically in figure 5. The connecting device 17 includes a connection 20 and 20A piping for supply and drainage of the coolant between the engine and the generator. Further provided by the contacts of the plug connector of the sensor cable and bus 21, which is transmitted signals and connector pins 22 power supply for supplying a current to the engine or aircraft. Details multi-function connecting device 17 in the flange 11b of the generator to match the type of mirror image parts in the mounting plate 11a, therefore, the contacts and the pins 21 and 22 of the connectors and connections 20 and 20A pipelines are fixed in the corresponding adjoint components.
The present invention is not limited to the above preferred Ave is Merom implementation. Also available a wide range of options using the solution described even with fundamentally different types.
1. Gas turbine engine (1), primarily for aircraft, containing at least one rotor shaft that has at least one compressor and turbine and the housing, and at least one shaft of the rotor has at least one node (10) generator to generate electricity, the node (10) of the generator includes a mounting plate (11b) and the generator (12) and a removable manner on a mounting plate (11a)located on the side of the engine, characterized in that the mounting plate (11a)located on the side of the engine, has a connecting element (13) for detachable connection node (10) of the generator, and this mounting plate has at least one mechanical installation element, the transmission device motion generator, and the electrical contacts and/or leads for the connection of pipelines.
2. Gas turbine engine (1) according to claim 1, characterized in that the hub (10) of the generator is located on the compressor side in the front and/or side of the turbine in the rear part of the gas turbine engine (1) and is mounted on the shaft of the compressor/turbine.
3. Gas turbine engine (1) according to claim 2, characterized in that the mounting plate (11)is installed on the stator of the gas turbine engine (1), moreover, the stator has a hollow rack, which house electrical wiring and/or piping.
4. Gas turbine engine (1) according to claim 1, characterized in that at least the conclusions (13 ending in 20 and 20A) for joining pipes made self-closing, so that when the disconnection to prevent the release of fluid or contamination of pipelines.
5. Gas turbine engine (1) according to claim 4, characterized in that the connecting elements (13) are fitted with seals formed by sealing rings of round section.
6. Gas turbine engine (1) according to claim 1, characterized in that the connecting elements (13, ending 22) have razmykaetsya megaampere contacts providing electrical connection of the generator (12) with the engine or aircraft.
7. Gas turbine engine (1) according to claim 1, characterized in that the connecting elements (13, ending in 21) have control contacts for controlling a generator (12) and/or the contacts of the bus system for controlling a generator/provide feedback on its parameters.
8. Gas turbine engine (1) according to claim 1, characterized in that the connecting interface mounting plate (11a) made modular/expandable with optional generator (12) various designs.
9. Gas turbine engine (1) according to claim 1, characterized in that th is device transmit motion between the drive shaft (18), located on the engine side, and the shaft (14) of the generator includes a gear connection with arcuate teeth.
10. Gas turbine engine (1) according to one of the preceding paragraphs, characterized in that the installation space of the generator (12) is a cylindrical cavity with a diameter only slightly greater than the outer diameter of the mounting plate (11a).
11. Gas turbine engine (1) according to claim 10, characterized in that the cylindrical cavity forming the mounting area has a high temperature insulation to protect the site of the generator from the high temperatures of hot gases located in the rear of the output device (16) of the engine.
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
FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises low- and high-pressure rotors, extra gearbox and transfer shaft drive to transfer drive force to extra gearbox. Said drive comprises high-pressure gear wheel on high-pressure rotor shaft, low-pressure gear wheel on low-pressure rotor shaft and p.t.o-unit engaged with drive gear wheels. P.T.O.-unit comprises housing and two p.t.o.-gears. High-pressure p.t.o.-gear engages with high-pressure drive gear, while low-pressure p.t.o.-gear is in mesh with low-press p.t.o.-gear. Another invention of proposed set relates to p.t.o.-unit of proposed gas turbine engine. One more invention relates to method of assembling said gas turbine engine that comprises mounting high-pressure rotor, p.t.o.-unit, transfer shafts in p.t.o.-unit and low-pressure rotor.
EFFECT: simplified design and assembly.
9 cl, 1 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
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: 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.
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: 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
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 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: machine building.
SUBSTANCE: turbo-electro-generator consists of turbo-compressor consisting of rotor and stator, of combustion chamber and of high-speed electro-generator. The rotor consists of shaft whereon there are installed propellers of the compressor and turbine with blade units and bearing disks. The stator consists of a turbine nozzle unit and of a compressor outlet diffuser. Bearing-thrust units of the rotor shaft are arranged in the stator of the turbo-compressor. The high-speed electro-generator comprises a rotor part containing magnetic ceramic elements and a stator part. The rotor part of the electro-generator is mounted on the shaft of the turbo-compressor between propellers of the compressor and turbine and consists of a magnetic ceramic casing consisting of cylinder segments arranged along axis of the shaft of the turbo-compressor and divided with planes passing through axis of the shaft into equal sectors; the ceramic casing is enclosed into a cylinder casing of metal alloy. On bearing disks there are cut grooves wherein there is installed the cylinder casing. The stator part of the electro-generator is installed in the stator of the turbo-generator.
EFFECT: increased reliability of resource of turbo-generator.
FIELD: engines and pumps.
SUBSTANCE: jet turbine engine includes high pressure housing; at least one rear bearing; and electric generator. High pressure housing includes high pressure compressor arranged along X-axis. High pressure compressor includes rotor and carter. The above bearing is arranged between carter and rotor of high pressure compressor. Electric generator is located coaxially with the housing and includes inductance coil rigidly connected to rotor of high pressure compressor during rotation. Armature is rigidly connected to carter. Electric generator is located before the above rear bearing in air flow direction. Electric generator includes at least the first cooling circuit passing around the above armature and downstream lubricating jet nozzle of rear bearing after cooling.
EFFECT: higher efficiency.
11 cl, 2 dwg
SUBSTANCE: electric generator (EG) includes housing with detachable covers, housing of inductor also with detachable covers made as an integral part of hollow shaft. Electromagnets with cores and coils are installed on inductor housing. Inductor assembled with electromagnets and covers is installed on bearings arranged in covers of EG housing. Two armatures are installed in EG, one of which is fixed, and the other one is movable, or one is movable with possibility of its rotation inside inductor. Windings of fixed armature are fixed in slots of detachable EG housing, and windings of movable armature are fixed in slots of armature housing made as an integral part of shaft and installed inside inductor by means of bearings on brackets fixed on EG base. Between inductor and movable armature there installed is reduction gear which provides simultaneous synchronous rotation of inductor and armature in opposite directions or as per simplified scheme, or with possibility of automatic control of rotation frequency of inductor and armature, and the condition at which the ratio of speeds of opposite rotation of inductor and armature Vi/Va=const is met in both cases.
EFFECT: higher quality of voltage supplied to electric mains, higher EG capacity, operating reliability, reducing material consumption, reducing manufacturing cost of EG, and enlarging application field.
8 cl, 5 dwg
FIELD: power industry.
SUBSTANCE: at least one water-moderated nuclear reactor connected via pipeline to turbine and gas injectors with drives is installed in one of compartments. Each turbine is connected by means of shaft to electric generator which is electrically connected through commutator to drives of gas injectors and to storage batteries. Supply and discharge gas lines are introduced tightly and upward vertically inside rugged housing. Detachable connections having the possibility of being connected to supply and discharge branch pipes of gas line and made perpendicular to it are arranged on ends of gas pipelines Branch pipes are installed on both sides of bypass pipeline having two shutoff valves on its ends
EFFECT: higher reliability and safety of operation.
8 cl, 4 dwg
FIELD: machine building.
SUBSTANCE: rotor consists of metal shaft. Propellers of the compressor and gas turbine with blade units and bearing disks are arranged on this shaft. The stator consists of a stator case, of a turbine nozzle unit and of a compressor outlet diffuser. Bearing-thrust units of the rotor shaft are arranged in the stator of the turbo-compressor. The electro-generator consists of a rotor part with magnet ceramic elements and of a stator part in form of a metallic torus containing current conducting winding. The turbo-compressor also includes a heat regenerator of gases exhausting the turbine. An outlet of the regenerator has an air connection with the inlet of the combustion chamber. The rotor part of the electro-generator is mounted on the shaft of the turbo-compressor between the propellers of the compressor and turbine and consists of segments of a magnetic ceramic casing placed into an internal cavity of at least one toroid casing out of metal alloy. The stator part of the electro-generator with through axial channels is installed in the stator of the turbo-generator. An axial symmetrical distributing cavity is made behind the outlet diffuser of the compressor. The cavity is restricted with the stator case, bearing disk of the compressor propeller and an end of the torus of the stator part of the electro-generator facing the compressor. The outlet from the compressor diffuser and inlet sections of the through axial channels are communicated with this distributing cavity. The outlet sections of through axial channels are communicated with an axial symmetrical collecting cavity restricted with the stator case, bearing disk of the turbine propeller and end of torus of the stator part of the electro-generator facing the turbine. The combustion chamber and the regenerator are encased into a single cavity with inlet and outlet routes. The inlet route is located on the side of the combustion chamber and is communicated with the axial symmetrical distributing cavity, while the outlet route is located in the side of the regenerator and is communicated with the air inlet into the regenerator.
EFFECT: increased reliability and efficiency of turbo-generator.
5 cl, 1 dwg
FIELD: machine building.
SUBSTANCE: gas-turbine engine consists of electric starter-generator, rotor of which is driven to rotation by shaft of compressor of high pressure, stator of which is mounted on intermediate carter of gas-turbine engine. The starter-generator is enclosed into a pressure tight case installed in a front compartment of the gas-turbine engine inside the intermediate carter containing oil. Compressed air is supplied into the pressure tight case of the starter-generator. The pressure tight case consists of the first elements of connection with electric cables running in structure poles of the intermediate carter. Also the first elements of connection are pressure tight and are arranged inside a chamber restricted with the case and the intermediate carter; the chamber is fed with compressed air. The starter-generator consists of an external cylinder element forming a support for the stator, of an internal cylinder element coaxial to the external cylinder element and forming the support of the rotor, and of circular covers secured on axial ends of the external cylinder element and interacting with the internal cylinder element. Bent devices for connection of stator coils with electric cables projecting outside the case in axial direction are arranged on the external cylinder element of the case.
EFFECT: facilitation of assembly and disassembly of built-in starter-generator and simplification of its connection with feeding electric cables or cables of current distribution.
15 cl, 5 dwg
FIELD: machine building.
SUBSTANCE: turbine expander plant in gas-distributing station system includes turbine expander, electric generator, high pressure natural gas line, gas-steam heat exchanger and electric steam generator connected to counter-pressure turbine. Gas steam heat exchanger is connected to high pressure line and turbine expander. Electric steam generator is supplied with power from electric generators of turbine expander and counter-pressure turbine.
EFFECT: reaching ecological cleanness owing to absence of fuel burning process, increasing economic effectiveness and eliminating frost and ice formation on working surfaces of turbine expander owing to gas heated with waste turbine steam.
FIELD: machine building.
SUBSTANCE: turbo-generator consists of case with cover, of rotor and of stator of electro-generator. The case with cover are tightened with fasteners and have a common internal cavity wherein there is installed a turbine wheel mounted of a shaft. The case is equipped with an inlet branch for supply of working medium into the turbine wheel. An output cavity communicated with the output branch for withdrawal of working medium is made on the side of withdrawal of working medium from the turbine wheel. The shaft is installed on two ball bearings located on opposite sides of the turbine wheel. One of the ball bearings is installed in the case, while another - in its cover. From the end facing the input branch the shaft has a blind port connected with a working channel of the turbine wheel on the side of the bottom of the blind port. The inlet branch of the case has a cylinder head introduced into the blind port of the shaft; the latter has a labyrinth packing enveloping fitting of the case. The rotor of electro-generator is made as a cartridge with an orifice in the bottom. The turbine wheel is equipped with a hub where the rotor is put on through an orifice in the cartridge bottom; the rotor is fixed relative to the turbine wheel and concentrically envelopes the stator of the electro-generator stationary fixed in the cavity of the case on its cover.
EFFECT: increased reliability of turbo-generator operation and improved weight and dimension characteristics.
FIELD: power industry.
SUBSTANCE: electro-generating installation with carbon-hydrogen fuel consists of steam boiler with carbon-hydrogen fuel, high temperature steam turbine of average pressure, condensation steam turbine, electro-generators, high temperature hydrogen super-heaters, water steam condenser, steam generator, working agent consumption regulators, regenerating heater of feed water, condensate pumps, and feeding pumps. Notably, by means of a pipeline a heating steam output of the installation is connected with an intermediary input of the condensate steam turbine, the input of which is connected to outputs of the steam generator for secondary steam and steam from the steam boiler. Also high temperature steam turbines have their own feeding pump, while the condensate steam turbine has its own feed pump; to outputs of both there comes condensate from the condenser of water steam and from the regenerating heater of feed water; the latter is installed at the input to the steam boiler. Steam for feed water heating comes through the steam pipe from the output of the condensate steam turbine.
EFFECT: increased energy and economic efficiency.
FIELD: power engineering.
SUBSTANCE: gas-pumping station on offshore platform comprises container separated by partition into two tight compartments. In one compartment there is at least one gas-turbine drive comprising inlet device, compressor, combustion chamber, turbine, free turbine and exhaust device. Free turbine by load shaft is connected to electric generator. In the other compartment there are gas injectors installed with drives. Electric generator is connected to free turbine via magnetic coupling and is connected by electric links via switchboard to drives of gas injectors and to accumulator batteries. Inside container there are supplying and exhausting gas lines introduced as vertical upward, in which detachable joints are arranged at the ends. Compounds may be connected to supplying and exhausting nozzles of gas manifold, are arranged perpendicular to it and are installed at both sides of bypass pipeline having two stop valves at its ends. Stop valves are arranged with remote drives, and between the injectors and their drives there are magnetic couplings installed.
EFFECT: improving station operation reliability.
4 cl, 5 dwg
FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: invention relates to self-contained power supply and starting system of gas-turbine engines. Proposed gas-turbine engine contains at least one rotor of turbocompressor installed in bearing supports and at least one electrical machine built into turbocompressor and containing system of permanent magnets secured on rotor of turbocompressor, and stator of electrical machine with winding installed on bearing support housing. Stator of electrical machine is secured on outer surface of bearing support housing of turbocompressor rotor. Permanent magnet system of electrical machine is installed on inner surface of turbocompressor rotor to enclose outer surface of stator of electrical machine.
EFFECT: increased power of built in electrical machine in initial dimensions of gas-turbine engine.