Starter/generator module box integration into gear box of gas turbine

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

 

The level of technology

The present invention relates to gas turbines and, in particular, to the mounting of the starter/generator (S/G from the Starter/Generator”) on the gear box or casing of the actuator units. The scope of the invention lies in the field of gas turbines for aircraft engines, i.e. engines of airplanes or helicopters, as well as for auxiliary power units (or APU from “Auxiliary Power Unit”).

In a gas turbine some equipment or units operate using mechanical transmission through the mechanical power extracted by the turbine shaft. This mechanical transmission, which contains a system of gears that are installed in the crankcase, is called a gear box or housing of the actuator units. The units are, in particular, a variety of pumps for the production of hydraulic energy, power, fuel, lubricants, and one or more electric starter/generators.

When the gas turbine is running, the starter/generator or each starter/generator mode of the electric generator and produces electrical voltage, which feeds one or several centers of distribution of electric energy for a plane or helicopter and its engine or engines.

When the gas turbine is not running, the starter/alternator can the t to work as a starter and be powered from an external source of electric voltage to start the gas turbine by bringing the rotation of the turbine shaft, 're connected to the gear box.

The starter/generator S/G known type contains the main synchronous generating unit with the main rotor and the main stator and exciting unit with an anchor on the rotor and the coil on the stator. Anchor driving unit feeds the main rotor of the synchronous generating unit via the rectifier bridge with rotating diodes. In the mode of generation of electric power anchor synchronous generating unit produces an alternating voltage in the cast of the rotation of the induction coil fed by a constant current supplied from the diode bridge excitation block, the frequency of the produced alternating voltage is changed depending on the rotation speed. In run mode the main rotor, driven by a driving unit, and the main stator, variable voltage from an external source, operate as a synchronous motor.

Such known starter/generator is a three-dimensional unit, which is typically installed in a special crankcase on one side of the gear box and mechanically connected to this box. In addition to the electrical equipment starter/generator includes a lubrication system with oil reservoir and the pump driven gear. As a result of significantly increasing the dimensions of the mass, moreover, on one gear box can be installed several starters/generators.

Object and summary of the invention

The present invention provides integrated starter/generator in the gear box of a gas turbine, which allows to significantly reduce the volume and dimensions, while still allowing easy removal.

This task is achieved by using the site, consisting of a gear box of a gas turbine and at least one starter/generator or S/G, mechanically connected to the gear box, in which:

- gear box includes a gear transmission with multiple gears

the starter/generator comprises generating unit with the rotor, forming the inductor, and a stator forming an anchor, and exciting unit with a stator forming the coil inductance, and rotor forming an armature connected to the inductor generating unit, and

the rotor of the generating unit and the rotor driving unit mounted on a common shaft with gear, siteplease gear transmission box, on either side of this gear.

This Assembly provides a significant savings in weight, because without special mechanical connection with gear box, thus providing outa gear included in the gear box after installation of the node.

In addition, compared with the mounting of the starter/generator on one side of the gear box due to the position of the synchronous generating unit and the driving unit on both sides of the gears is achieved a significant reduction in size and a better balancing of the masses.

In addition, gear boxes and starter/generator can be used the same means of lubrication/cooling.

Preferably, the anchor driving unit is connected to the inductor generating unit by means of electrical connections passing through the gear.

Preferably, as the anchor of the driving unit is connected to the inductor of a synchronous generating unit, using a rotating diode bridge, forming the rectifier diodes can be installed on the gear.

In addition, you can provide the generator with permanent magnets containing a rotor mounted on a common shaft.

Preferably, the generator with permanent magnets installed on the same side gear, and an exciting unit that promotes good balancing of the masses.

In an embodiment, the starter/generator S/G together with the gear and the shaft forms a module or module S/G, which can be connected to the gear box or disconnected from it as a result of progressive on what to achieve.

Disconnecting module S/G or its connection with the gear box can be done using a translational motion parallel or perpendicular to the common axis of the shaft.

Module S/G can be installed in the building, which contains at least one opening through which the gear can be connected at least with one other gear gear boxes.

Preferably, the module S/G is installed in the housing which is hermetically connected to the sump gear box.

Module S/G can be powered lubricant/coolant from the loop transmission of the box.

In another embodiment, the gear box and the module S/G set in a common sump.

Preferably, the node formed by the shaft with the said gear and the rotor of the generating unit and the driving unit can be disconnected from the gear box when the translational movement parallel to the axis of the shaft.

In each embodiment, the gear box can be integrated, at least two of the starter/generator, with each starter/generator mounted on a common shaft with the gear transmission box.

The object of the present invention is a gas turbine equipped with a node formed by the gear box and at least one is above the starter/generator, as well as aircraft engines or auxiliary power unit equipped with such a gas turbine.

The object of the present invention is also a module starter/generator or module S/G, integrated in the gear box of a gas turbine, this module contains the generating unit with the rotor, forming the inductor, and a stator forming an anchor, exciting unit with a stator forming the coil inductance, and rotor forming an armature electrically connected with the inductor generating unit, gear and shaft, which together with the gear set, the rotor of the generating unit and the rotor of the exciting unit on both sides of the gear.

Module S/G can be installed in the building, which contains at least one opening through which the gear can be connected at least with one other gear gear boxes.

According to distinctive feature of the module S/G anchor driving unit is connected to the inductor generating unit by means of electrical connections passing through the gear.

According to another distinctive feature of the module S/G anchor driving unit is connected to the inductor generating unit using a rotating diode bridge, and the diodes are installed on the pole is not.

The module may further comprise a generator with permanent magnets containing a rotor mounted on a common shaft. Preferably the generator with permanent magnets located on the same side of the gear, and stimulating the block.

Brief description of drawings

The present invention will be more apparent from the following description, presented as a non-restrictive example, with reference to the accompanying drawings, on which:

Figure 1 - simplified diagram of a gas turbine engine.

Figure 2 - General a simplified circuit diagram of the starter/generator.

Figure 3 - schematic view of the integration module S/G in the gear box of a gas turbine according to the first variant implementation of the invention.

4 is a more detailed view in section of the module S/G, shown in figure 3.

5 and 6 is a simplified schematic view of the integration module S/G in the transmission box according to the first variant implementation of the invention.

7 is a more detailed view in section of the module S/G, shown in figure 5 and 6.

Fig - schematic view of the integration module S/G in the transmission box according to another variant implementation of the invention.

Detailed description of embodiments

The scope of the invention lies in the field of aircraft gas turbine engines, such as engine, CX is shown in figure 1 may be put at risk, however, the invention can also be applied to other aircraft engines, as a rule, for helicopter engines, as well as for gas turbine auxiliary power units.

The engine shown in figure 1, includes a combustion chamber 1, while the gaseous products of combustion coming from the camera, cause the rotation of the turbine 2 high pressure turbine 3 low pressure. Turbine 2 connected to the shaft with the compressor 4 high pressure supply chamber 1, the combustion by compressed air, while the turbine 3 is connected to the other shaft with fan 5 mounted on the inlet of the engine.

Gear box 7 or the housing of the actuator units are connected using the device 9 selection of mechanical power from the turbine shaft and contains a system of gears to bring the rotation of the various units, among which at least one (usually two) starter/generator or S/G.

Figure 2 shows a simplified General electric circuit of the starter/generator containing a synchronous generating unit 10, a driving unit 20 and the generator 30 with permanent magnets or PMG (Permanent Magnet Generator), rotating parts or rotors are coaxial and mounted on the same rotating shaft with the axis A.

Synchronous generating unit 10 forming main machine, contains the main rotor, forming a coil the inductance 12, and the main stator, forming the anchor 14. Exciting unit 20 includes a rotor forming an armature 22, which is connected to a rotating diode bridge 24, which forms the rectifier and the stator constituting the inductor 26. The generator 30 PMG permanent magnet includes a rotor 32 that has permanent magnets 34 and the stator forming the anchor 36.

In the mode of generation of electric power inductor 12 synchronous generating unit, connected to the rectifier 24, receives the direct current produced by the agitation unit, and the AC voltage produced by the anchor 14 and is transmitted through the wiring 18 on bus AC 42 circuit distribution of electrical energy, such as on-Board network of 44 aircraft or helicopter. The control scheme 40 or GCU (Generator Control Unit) is powered by PMG 30 through the wiring 38. Through the line 46, the circuit 40 receives information about the value of the output AC voltage produced by the power generation unit 10, and controls the constant current supplied to the coil 26 of the exciting unit through the wiring 28 for regulating the amplitude of the output voltage control value, and this voltage has a frequency varying depending on the speed of rotation of the shaft A.

Mode starter control scheme 40 is powered by a voltage through the line 48 on the bus AC 42 (or other source) to ensure their work and for power to the coil 26 of the exciting unit AC. Simultaneously, the anchor 14 is powered by an alternating current through the wiring 18 bus AC 42 (or other source)in this case corresponds to the synchronous motor.

The above-described starter/generator, as well as his work and its regulation scheme GCU in themselves known, in the mode of generating electric power generator with PMG excitation unit and a synchronous generating unit to form a series of steps to gain from one step to another. It should be noted that the presence of the PMG is not required if the control scheme 40 can be powered from another source. It should also be noted that the functions of the GCU can be attached to the electronic control scheme of the engine or ECU (Engine Control Unit).

Figure 3 and 4 shows a variant implementation of integration in accordance with the present invention module S/G 50 in the gear box of a gas turbine. Gear box 70 contains a crankcase 72 containing the gear 80, and are mechanically connected by means of power line 90 with the turbine shaft of the gas turbine, such as turbine engine of the aircraft or engine turbine helicopter or APU.

Module S/50 G contains the actual starter/generator, which is installed inside the crankcase or housing 52 with the gear 86, which comes between the two gears 85, 87 gear 80 with which it is carried is is.

The rotating part of the synchronous generating unit 10, a driving unit 20 and PMG 30, forming the starter/generator is mounted on the shaft 54 together with the gear 86. Synchronous generating unit 10 is installed on one side of the gear 86, while stimulating the block 20 and PMG 30 mounted on its other side to limit the imbalance masses between the two sides of the gear 86 and, therefore, to restrict the length of the protruding part of the module S/G 50 on the gear box 70.

The shaft 54 is installed in the housing 52 on the bearings 53A, 53b. The shaft 54 may be made as a single part or may consist of several parts, aligned in line in the axial direction and rigidly connected in rotation. In the present example, the rotor of the generating unit is inserted between the two tubular parts of the shaft 54. Gear 86 can be made as a single part with the shaft 54 or part of it or may be made separately and connected in rotation with the shaft 54, for example, by means of the spline.

The main rotor windings of an induction coil 12 generating unit is installed, thus, on the shaft 54, while the main stator windings of the armature 14 is mounted on the wall inside the housing 52. Wiring 18 connected to the anchor 14, hermetically passes through the housing 52, continuing on or connecting with connecting the beginning to 55.

Similarly, the rotor driving unit 20 with the windings of the armature 22 is mounted on the shaft 54, while the stator excitation unit with the windings of the inductor 26 is fixed inside the housing 52. Rotating diode bridge, forming a rectifier, is connected, on the one hand, with the anchor 22 with the side gear 66, where is this anchor, and, on the other hand, with the inductor 12 of the synchronous generating unit is on the other side of the gear 66. The connection between the armature 22 and the inductor 12 passes through the passage 86a, made in the gear 86. Preferably, the rotating diodes of the bridge 24 is installed on the gear 86 in one or more grooves 86b, which is made on the side of the gear 66, addressed to vozbujdayuschego unit 20 or to the cash generating unit 10. This provides an effective mounting of the diodes to avoid damage to them and damaging their joints during rotation. The supply current to the coil 26 of the exciting unit is supplied through the wiring 28 which is connected to the connector 56 mounted on the outer surface of the housing 52, and hermetically passes through this connector.

In the present example, the PMG 30 is mounted on the end of shaft 54, thus stimulating the block 20 is located between the gear 66 and PMG 30. The magnets 34 of the PMG mounted on the shaft 54, have a look at is how armature winding 36 of the PMG, located opposite the magnets 34, performed on the workpiece 37, is fixed inside the housing 52. The current produced by the PMG, is transmitted through the wiring 38, which, like the wiring 28 is connected to the connector 56, passing through the housing 52. As mentioned above, from PMG can be waived.

The housing 52 has a General cylindrical shape with the same axis as the shaft 54, and contains part 52a, in which, essentially, is installed generating unit 10, part C, within which the exciting unit 20 and PMG 30, and an intermediate portion 52b connecting portion 52a and s, which is located inside the gear 86. At its axial ends of the housing 52 is sealed lids.

The intermediate wall portion 52b includes holes or openings 57a, 57b, which are made in opposite zones of the wall and through which the gear 86 can engage with the gears 85 and 87. When the module 50 is installed in the gear box (figure 4), part 52a and s housing 52 protrude outwards from the outer sides of the opposite side walls 74, 76 Carter 72 gear box 70.

In the example shown in figure 3 and 4, the module 50 can be removed from the gear box 70 simultaneously disconnecting the gear 86 from gears 85 and 87, or may be installed in the gear box 70 with the simultaneous connection of the gear 86 with gears 85 and 87 by postupatel the nogo movement, parallel to the axis A. In figure 3, the module 50 is shown partially removed from the gear box 70.

Removing (disconnecting) module 50 or integration (connection) in this example, the carry out from the side wall 74, which is part 52a of the housing 52. During the movement of the disconnection or connection part 52 from the housing 52 passes through a circular coaxial holes a, 76A, made in the walls 74 and 76, and between the gears 85 and 87, while the intermediate portion 52b of the housing 52 passes through a hole a. Accordingly choose the dimensions of the parts 52b, C, holes a, 76A and the distance between the gears 85, 86. Part 52a includes an outer flange 58 near its connection with the intermediate part 52b, which limits the movement of the joints of the body due to the emphasis in the wall 74 of the crankcase 72, and this thrust position coincides with the connection gear 86 with gears 85 and 87.

The housing 52 is fixed to the crankcase 72, for example, by bolting the flange 58 on the wall 74. Of course, it is possible to envisage other ways of fastening, such as options for quick mounting of a known type using providermetadata bodies locked.

Essentially, at the level of connections between parts 52a and 52b and between parts 52b and C the outer wall of the housing comes into the holes a and 76A with appropriate gaskets 74b, 76b. So the m way implement a watertight installation of the module S/G 50 on the gear box 70, the openings 57a, 57b is opened only inside the crankcase 72, when the module 50 is inserted into the gear box.

The tide 52d housing 52 made channel 59 power module S/50 G of a cooling and lubricating fluid, which opens on the surface of the flange 58, facing the wall 74, connecting with the pipe 78 connected to the cooling circuit and the lubrication of the gear box 70. Tight connection between the channel 59 and the pipe 78 is provided by a fitting 79 passing through the wall 74. The channel 59 is connected to the circuit 14a cooling of the armature 14 generating unit 10 and, in addition, connected to the nozzles (not shown), providing, in particular, the lubrication of the bearings 53A, 53b and creating an oil mist inside the housing 52. The cooling and lubricating liquid is collected in a sump 72 through the hole 57a (arrow f) and then resumes the circulation through the cooling circuit and the lubrication of gear boxes. The internal volume of the part s housing 52 is isolated from the rest of the body due to the installation of the bearing 53b, essentially at the level of connections between parts 52b and s, with the support bearing 53b provided with channels for circulation of fluid in the part s corps and beyond.

Although the above has been described the case 52 in a generally cylindrical shape with a round hole the parties a, 76A, it is possible to provide for other forms of housing, and consequently choose the form of holes.

In addition, despite the fact that was presented to the integration of only a single module S/50 G, gear box 70, you can integrate several of these modules, as a rule, two modules at different levels of gear.

Figure 5-7 shows a variant implementation of integration in accordance with the present invention, a module in the gear box of a gas turbine.

This implementation differs from the variant shown in figure 3 and 4, mainly the fact that the module S/G 150 is inserted into the gear box 70 with one end and can be connected to the box or disconnect from it by a translational movement perpendicular to the axis a of the module S/G.

Elements in common with Fig 3 and 4, on the one hand, and with 5-7, on the other hand, is marked the same positions.

Module S/G 150 differs from module S/G 50 executing the body 152 of the module, while the other part of the module 150, mostly generating unit 10, a driving unit 20, PMG 30 and the gear 86 mounted on a common shaft 54, such an integral part of the module 50.

The housing 152 has a General cylindrical shape and in its Central part comprises a tubular connecting portion 152d, which is made in one with the body 152 and limits otverstie. The hole 153 is located in the plane and covered by the outer flange 158.

The housing 152 is connected with the sump 72 is a gear box on the end of the crankcase, where it made a hole 73 having a shape corresponding to the hole 153. The connection between the housing 152 and the sump 72 is carried out, for example, by bolting flange 158 on similar flange 73a of the crankcase 72 covering the hole 73. Gasket 73b between the flanges 173 and 73 provides a watertight installation of the module S/G 150 on the gear box 70. You can use other means of connection, such as a known drug fast connection with the locking of using providermetadata elements. Although shown holes 153 and 73 are rectangular in shape, it is possible to envisage other forms. In addition, the surface of the joint between the housing 152 and the housing 72 can be both flat and not flat.

The integration or connection module S/G 150 with gear box 70 and removed or disconnected from the gear box carried by the translational motion perpendicular to the axis A. the Gear 86 engages with the gear 87 gear gear box through the holes 73 and 153.

Channel 159 power module S/G 150 cooling and lubricating fluid made in the tide connecting h the STI 152d and opens on the surface of the flange 158, facing the flange 73a. Channel 159 is connected to the pipeline 178, connected to the cooling circuit and the lubrication of the gear box 70. The connection between the channel 159 and pipeline 178 implement using fitting 179 passing through the flanges 158 and 73a.

Circulation of cooling and lubricating fluid to provide, as described above in connection with module S/50 G, with the return to the sump 72 is a gear box through holes 173 and 73.

Although the described housing 152 has an overall cylindrical shape, other shapes, the more that there is voltage at the introduction of the housing through the hole in the housing 72 and between the two gears in the gear transmission box.

In addition, in the gear box with its other end, you can insert the second module of the S/G 150. In the same gear box can also be integrated case S/50 G and case S/G 150.

On Fig shows another variant implementation of integration in accordance with the present invention, the starter/generator in the gear box of a gas turbine. For common elements are the same as those of the digital item, and that for the scenarios shown in figure 4. Gear box 70 contains a crankcase 72 containing the gear 80, and are mechanically connected to the turbine shaft of the gas turbine, such as turbine engine of the aircraft or is Recoleta or turbine auxiliary power unit (ARI).

The starter/generator mounted on the gear 86 gear gear box, the gear 86 comes between the gears 85 and 87. Similarly to the other gear can accommodate an extra starter/generator. The rotating part of the power generating unit 10, a driving unit 20 and PMG 30 mounted on a common shaft 54 with the gear 86, which forms, for example, a single item with this shaft. The shaft 54 is installed in the crankcase 72 on the bearings 53A, 53b.

Synchronous generating unit 10 is installed on one side of the gear 86, while stimulating the block 20 and PMG 30 is installed on the other side.

The main rotor windings of an induction coil 12 generating unit is mounted on the shaft 54, while the main stator windings of the armature 14 is fixed on the casing 72. Wiring 18 connected to the anchor 14, hermetically passes through the sump 72 and continued out of or connected with the connecting unit 55.

Similarly, the rotor driving unit 20 with the windings of the armature 22 is mounted on the shaft 54, while the stator excitation unit with the windings of the inductor 26 is fixed on the casing 72. Rotating diode bridge 24, which forms a rectifier, is connected, on the one hand, with the anchor 22 with the side gear 54, where is this anchor, and, on the other hand, is connected to the inductor 12 of the synchronous generating unit and the another side of the gear 86, passing through the passage 86a performed in gear. Preferably, the rotating diodes of the bridge 24 is installed in slots 86b, which is made on the side of the gear 86, converted to the cash generating unit 20, and provides a solid mount diodes to avoid injury and damage to their joints during rotation. The supply current to the coil 26 of the exciting unit is supplied through the wiring 28 which is connected to the connector 56 mounted on the outer surface of the crankcase 72, hermetically passing through the sump.

In the present example, the PMG is installed in the axial recess 60, made at the end of the shaft 54. The magnets 34 of the PMG mounted on the cylindrical inner surface of the recess 60, while the armature winding 36 of the PMG opposite magnets made on the axial rod 68 attached to the sump 72. Such mounting PMG allows you to reduce the axial size of the starter/generator and contributes, therefore, to ensure the compactness of the Assembly, the rotor and the stator excitation unit covers the PMG. In option, you can install PMG offset in the axial direction with respect to the cash generating unit and to mount the magnets on the periphery of the shaft 54, which are covered by the anchor of the PMG attached to the sump 72. The current produced by the second anchor 36, is transmitted through the wiring 38, which, like the wiring 28 is connected to the connector 56, hermetically passing through the sump 72.

The node formed by the shaft 54 with the gear 86, the rotor driving unit 20, the PMG rotor 30 and the main rotor of the synchronous generating unit 10 can be removed by extracting from the gear box when the translational movement parallel to the axis of the shaft 54. In the present example, retrieval can be performed by a synchronous generating unit 10. In this case, to facilitate its extraction, it is desirable that the outer diameter of the rotor driving unit 20 was less than the minimum distance between the gear teeth, which engage with the gear 86 (or, essentially equivalently, smaller diameter gear 86 on the level gaps between the teeth). Similarly, it is desirable that the diameter gear 86 at the level of the tops of the teeth was less than the internal diameter of the stator of the synchronous generating unit 10.

Integrated starter/generator in a transmission box with General Carter 72 according to a variant of execution, shown in Fig, allows not only to reduce the dimensions and weight, but also allows for a starter/generator apparatus for cooling and lubrication of gear boxes, while cooling and lubrication is usually carried out by creating the Oia multiple nozzles oil mist within the crankcase.

The integration according to the invention one or more starters/generators in the gear box of a gas turbine provides a reduction in size and weight that allows you to share resources for cooling and lubrication between the starter/generator and gear box, while providing easy removal. In the embodiment shown in figure 3-7, dismantling and installation of the module S/G can be produced very quickly and easily, so in the event of an aircraft engine can extract module S/G and its replacement with fast transactions under the wing of the plane.

1. The node that contains the gear box of a gas turbine and at least one starter/generator mechanically coupled with a gear box in which the transmission comprises a gear box transmission with multiple gears, starter/generator comprises generating unit with the rotor, forming the inductor, and a stator forming an anchor, and exciting unit with a stator forming the coil inductance, and rotor forming an armature connected to the inductor generating unit, and the rotor of the generating unit and the rotor driving unit mounted on a common shaft with gear, siteplease gear gear box, both sides of this gear.

2. Site at p., in which the anchor driving unit is connected to the inductor generating unit by means of electrical connections passing through said gear.

3. The node of claim 1, wherein the anchor driving unit is connected to the inductor generating unit using a rotating diode bridge, and the diodes mounted on said gear.

4. The node according to claim 1, further comprising a generator with permanent magnets containing a rotor that has permanent magnets, and a stator forming an anchor, and the generator rotor with permanent magnets mounted on said common shaft.

5. The node according to claim 4, in which the generator with permanent magnets mounted on the same side of the said gear, and stimulating the block.

6. The node of claim 1, wherein the starter/generator together with the said gear and the shaft forms a module that can be connected to the gear box or disconnected from it in motion.

7. The node according to claim 6, in which the connection or disconnection of the module from the gear box carried out parallel to the axis of the common shaft.

8. The node according to claim 6, in which the connection or disconnection of the module from the gear box exercise perpendicular to the axis of the common shaft.

9. The node according to claim 6, in which the module is installed in the housing, which sod is RIT, at least one opening through which the gear can be connected, at least one pinion gear boxes.

10. The node according to claim 6, in which the module is installed in the housing which is hermetically connected to the sump gear box.

11. The node according to claim 6, in which the module is supplied with lubricating/cooling fluid from the transmission path box.

12. The node according to claim 1, in which the gear box and the starter/generator is installed in a common sump.

13. The node indicated in paragraph 12, in which the node formed by the shaft with the said gear and the rotor of the generating unit and the driving unit can be disconnected from the gear box when the translational movement parallel to the axis of the shaft.

14. The node according to claim 1, containing at least two starter/generator, each of them mounted on a common shaft with the gear transmission box.

15. Gas turbine containing a gear box mechanically connected to a turbine shaft, and at least one starter/generator, in which the gear box and the starter/generator form a node according to any one of claims 1 to 14.

16. Gas turbine aircraft engine, containing a turbine according to clause 15.

17. Gas turbine auxiliary power unit containing a turbine according to clause 15.

18. Module starter/generator, integrate the th in the gear box of a gas turbine, containing a generating unit with a rotor forming the inductor, and a stator forming an anchor, exciting unit with a stator forming the coil inductance, and rotor forming an armature connected to the inductor generating unit, gear and shaft, which together with the gear set, the rotor of the generating unit and the rotor of the exciting unit on both sides of the gear.

19. Module p, when this module is installed in the housing, which contains at least one opening through which the gear can be connected, at least one pinion gear boxes.

20. Module p, in which the anchor driving unit is connected to the inductor generating unit by means of electrical connections passing through said gear.

21. Module p, in which the anchor driving unit is connected to the inductor generating unit using a rotating diode bridge, and the diodes mounted on said gear.

22. Module according to any one of p-21, additionally comprising a generator with permanent magnets containing a rotor mounted on a common shaft.

23. The module according to item 22, wherein the generator with permanent magnets located on the same side gear, and a stimulating unit.



 

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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

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

The invention relates to the field of aircraft propulsion, specifically to aircraft engines with built-in generators, resulting in rotation without an intermediate gearbox

The invention relates to the field of energy and can be used in heat exchange systems for gas turbine units (GTU) with a liquid or gaseous coolant

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 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

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

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