CN1682023A - jet engine or turbine engine - Google Patents

Abstract

A jet or turbine motor that includes a radial or diagonal compressor containing at least one rotating part pivoted in the fixed part of the jet or turbine motor when a synchronous electromotor containing a mutually cooperating stator and rotor is coupled with at least one rotating part of the compressor where the rotor (200) of the synchronous electromotor (2) is fixed on the rotating part of the jet or turbine motor coupled with the compressor while the stator (201) of the synchronous electromotor (2) is, in alignment with the rotor (200) of the synchronous electromotor (2), placed on a fixed part of the jet or turbine motor and coupled with an electric power supply and/or consumer.

Description

jet engine or turbine engine

technical field

The invention relates to a jet or turbine engine having a radial or diagonal compressor comprising at least one rotating part mounted on a fixed part of the jet or turbine engine so that it can rotate; A synchronous electric machine having a stator and a rotor cooperating with each other connects at least one rotating part of the compressor.

Background technique

For jet or turbine engines with radial or diagonal compressors, after starting the jet or turbine engine, it is necessary to ensure the initial start (rotation) of the rotor to the required speed. A number of solutions are known to bring the initial start-up of a rotor of a jet or turbine engine to the required speed.

There are several known solutions for driving compressor blades with compressed air through nozzles. There are also proposals that utilize the action of pyrope cartridges on the turbine blades, whose rotational motion is transmitted to the compressor wheels via the common shaft of the compressors. It is also known to use a separate commutator motor including an electronic starter, for example, where a jet or turbine engine shaft can be mechanically connected via a gearbox, starter clutch or flywheel clutch. If the electric motor is permanently attached to the jet or turbine engine shaft using the above arrangement, it can also be used to supply electrical power (if the construction allows for this use). There are also structures that contain separate motors or separate generators.

The structure described above has some disadvantages: it is heavy and requires a lot of space. Another disadvantage is that the structure of the known solution is quite complicated, the required relevant manufacturing conditions are high, and the corresponding equipment costs are high.

The object of the invention is to eliminate or minimize the disadvantages of the prior art.

Contents of the invention

The object of the present invention is achieved by means of a jet or turbine engine, the principle of which is as follows: the rotor of the synchronous machine is fixed on the rotating part of the jet or turbine engine connected to the compressor, the stator of the synchronous machine aligned with the rotor of the synchronous machine Placed on a fixed part of a jet or turbine engine and connected to a power source and/or consumer. With this configuration it is possible to reduce the space requirement of the "Synchronous Motor - Jet or Turbine Engine" system, in order to install the rotating part of the synchronous motor, also utilize the current jet or turbine engine rotating part for installation, making the jet or turbine engine simpler and cheaper . It is also convenient to connect the rotor of the synchronous electric machine to the compressor without using other additional equipment such as couplings or gearboxes, since the current connection of the compressor to the associated rotating part of the jet or turbine engine is utilized.

In view of simplifying the structure of jet or turbine engines, it would be convenient if the rotor of the synchronous motor is fixed on the rotating part of the compressor.

According to a convenient design, the rotor of the synchronous motor is fastened on the front of the compressor wheel, and the stator of the synchronous motor is fastened in front of the compressor wheel. This facilitates the manufacture of jet or turbine engines, especially when the rotor of the synchronous electric machine is housed in the hollow in front of the compressor wheel.

At the same time, the stator of the synchronous motor is conveniently installed in the cover body, which is used for aerodynamically covering the middle part of the front end of the compressor wheel, and the cover body is fixed by radial ribs in the middle part of the inlet housing of the jet or turbine engine. This solution is simple, cheap and reliable.

At least one radial rib is hollow and serves as a pipe for holding wires connecting the stator of the synchronous motor with the power supply and/or electrical device.

The stator of the synchronous motor is conveniently accommodated in a housing suspended from the cover, which is simple and inexpensive.

According to a convenient design, the rotor of the synchronous machine comprises hollow permanent magnets with an even number of poles, the stator of the synchronous machine comprises electromagnets with multiphase windings located in the cavity of the rotor of the synchronous machine, the multiphase windings Connect to power and/or consumers. This solution is especially suitable for applying the built-in synchronous motor to the front of the compressor wheel.

According to another convenient design, the rotor of the synchronous machine includes permanent magnets with an even number of poles and is located in the cavity of the stator of the synchronous machine, the stator of the synchronous machine includes hollow electromagnets with polyphase windings connected to the power supply and/or electrical appliances. This design is suitable for: a built-in synchronous motor in the front of the compressor wheel mentioned above, and the rotor of the synchronous motor is mounted on the compressor shaft behind the compressor wheel for example, or becomes another rotation of the jet or turbine engine connected to the compressor Parts, for example, become turbines on a common shaft with compressors, etc.

In order to cool part of the synchronous machine it is expedient if a cooling duct system is provided for the stator and/or the rotor of the synchronous machine.

The combined advantages of the jet or turbine engine of the present invention are high electrical efficiency and maintenance-free operation. Another advantage of the jet or turbine engine of the invention is that the torque of the synchronous machine is high, and a synchronous machine with permanent magnets can be operated as a generator at high speed without the additional need for an increase in the magnetic gap between the stator and rotor of the synchronous machine Bands. Smaller magnetic gaps allow the use of smaller thickness magnets to achieve the same output.

Description of drawings

A diagrammatic representation of the technical solution of the present invention is shown in the accompanying drawings. Figure 1 shows a longitudinal section of an embodiment of a single-shaft jet engine with a synchronous electric machine constituting an electric starter integrated in the compressor inlet section of the jet engine. Figure 1 shows a cross-sectional view along a hollow radial rib.

Detailed ways

A design embodiment of a jet engine will be described below, which has a compressor section 10 and a turbine section 11, between which there is a combustion chamber 13 on the air path compressed by the compressor, and a fuel nozzle 14 in this combustion chamber exit. The combustion chamber 13 also has a suitable ignition system, not shown in the figures, for initially igniting the mixture of compressed air and fuel.

The compressor section 10 comprises a radial compressor rotor wheel 15 and the turbine section 11 comprises a turbine rotor wheel 16 . In the illustrated embodiment, the wheels 15 of the radial compressor and 16 of the turbine pivot about a common shaft 17 which is pivoted by bearings 19, 19'

The jet engine is provided with the rotor 200 of the synchronous electric machine 2 in alignment with the axis of rotation of the rotary part of the radial compressor. The rotor 200 of the synchronous motor 2 is fixed on a suitable rotating part of the jet engine connected to the compressor, for example, it is mounted on the compressor wheel, or it is mounted on the common shaft 17 of the compressor or turbine or connected to the compressor on the jet engine. on another rotating part of the machine. The rotor 200 of the synchronous motor 2 rotates together with the rotating part of the compressor, for the pivoting required for the operation of the synchronous motor 2, the pivoting of the corresponding part of the jet engine is used, for example, the rotation of the compressor or the pivoting of the common shaft 17, etc. wait.

In the illustrated embodiment, the rotor 200 of the synchronous motor 2 is fixed at the front of the wheel 15 of the radial compressor, or in the hollow at the front of the wheel 15 of the radial compressor. In the illustrated embodiment, the rotor 200 of the synchronous motor 2 fixed in the front hollow of the wheel 15 of the radial compressor comprises a magnetic Ring 20. Two permanent magnets 21 are mounted on the magnetic ring 20 along the direction toward the free space of the hollow part. In a design embodiment not shown, the rotor 200 of the synchronous motor 2 is fixed on the common shaft 17 together with the turbine, or mounted on the turbine, and so on.

In the corresponding part of the jet engine, the stator 201 of the synchronous motor 2 is fixed in the stator part of the jet engine. The shafts of a pair of stator 201 and rotor 200 of the synchronous motor are aligned and interlocked in a known manner to be used as a synchronous motor 2 .

In the illustrated design embodiment, the stator 201 of the synchronous machine 2 is fixed in front of the front of the wheel 15 of the radial compressor, for example in a cover 240 . The cover body 240 is used to aerodynamically cover the middle part of the front end of the wheel 15 of the radial compressor, and is installed in the middle part of the inlet casing 24 in front of the radial compressor of the jet engine through radial ribs 27 . The stator has polyphase windings 23 whereby the stator 201 is located in the cavity between the permanent magnets 21 of the rotor 200 of the synchronous machine 2 mounted in the front hollow of the wheel 15 of the radial compressor. For example, by using wires 25 passing through a hollow radial rib 27, the polyphase winding 23 is connected to a power unit external to the actual body of the jet engine. In the illustrated embodiment, the multi-phase winding 23 is mounted by means of bolts 30 on a housing 29 suspended in a cover 240 .

Cooling of the stator 201 and the rotor 200 of the synchronous machine 2 is ensured in a suitable manner. For example, in the illustrated embodiment, the cooling of the stator 201 is ensured by conducting the heat of the multiphase winding 23 via the housing 29 to the radial ribs 27 and further to the jet engine inlet casing 24, as well as the compressor suction and Artificial ventilation of flowing air flowing around the cover 240 may also pass through holes and gaps in the cover 240 , and the like. Cooling of the entire synchronous machine 2 is also supported by radial ducts 31 in the front hollow of the wheel 15 of the radial compressor, in the direction from the stator 201 of the synchronous machine 2 to behind the rotor 200 of the synchronous machine 2 .

In an unillustrated design embodiment, the stator 201 and the rotor 200 of the synchronous motor 2 can be manufactured in different suitable ways, and they can also be integrated in the structure of the rotating part and the fixed part of the jet engine in different suitable ways.

To start the jet engine, the synchronous motor 2 acts as a drive. After the jet engine is started, when the fuel and air combust and expand and blow onto the turbine blades, and the compressor keeps rotating, the synchronous motor 2 can operate as a current generator and be used directly inside the jet engine, or it can also be used externally for the jet engine equipment usage, etc.

The present invention is not limited to the design of the jet engine illustrated and described above, and different modifications of the technical solution of the present invention can also be obtained according to the structural settings of various types of jet or turbine engines. A person skilled in the art can apply the technical solution of the present invention to a suitable special structure according to the technical solution of the present invention and utilize his/her normal professional ability.

industrial application

The technical scheme of the present invention is applied to jet engines, turbine engines, and the like.

Claims (10)

1. A jet or turbine engine comprising a radial or diagonal compressor having at least one rotating part rotating in a fixed part of the jet or turbine engine, a synchronous electric machine having a stator and a rotor cooperating with each other to connect compression At least one rotating part of the machine, characterized in that the rotor (200) of the synchronous electric machine (2) is fixed on the rotating part of the jet or turbine engine connected to the compressor, so as to be aligned with the rotor (200) of the synchronous electric machine (2) The stator (201) of the synchronous motor (2) is installed on the fixed part of jet or turbine engine, and is connected with power supply and/or electrical device. 2. Jet or turbine engine according to claim 1, characterized in that the rotor (200) of the synchronous electric machine (2) is fixed on the rotating part of the compressor. 3. Jet or turbine engine as claimed in claim 2, characterized in that the rotor (200) of the synchronous motor (2) is fixed at the front of the compressor wheel, and the stator (201) of the synchronous motor (2) is fixed at In front of the compressor wheel. 4. Jet or turbine engine according to claim 3, characterized in that the rotor (200) of the synchronous electric machine (2) is housed in the front hollow of the compressor wheel. 5. Jet or turbine engine as claimed in claim 3 or 4, characterized in that the stator (201) of the synchronous motor (2) is mounted on a cover (240) for aerodynamically covering the compressor wheel The middle part of the front end, and the covering body (240) is fixed on the middle part of the jet or turbine engine inlet housing (24) by radial ribs (27). 6. Jet or turbine engine as claimed in claim 5, characterized in that at least one radial rib (27) is hollow and acts as a conduit for a wire (25) for connecting a synchronous motor (2 ) of the stator (201) and the power supply and/or electrical device. 7. Jet or turbine engine as claimed in claim 5 or 6, the stator (201) of the synchronous motor (2) is mounted on the housing (29) suspended from the cover (240). 8. Jet or turbine engine according to any one of claims 1 to 7, characterized in that the rotor (200) of the synchronous machine (2) comprises a hollow permanent magnet with an even number of poles, and the synchronous machine (2 The stator (201) of ) includes electromagnets located in the cavity of the rotor (200) of the synchronous motor (2) and having multi-phase windings (23), which are connected to power sources and/or consumers. 9. The jet or turbine engine according to any one of claims 1 to 7, characterized in that the rotor (200) of the synchronous machine (2) comprises a cavity located in the stator (201) of the synchronous machine (2). and permanent magnets with an even number of magnetic poles, while the stator (201) of the synchronous motor (2) includes hollow electromagnets with multiphase windings (23), which are connected to power sources and/or electrical devices. 10. Jet or turbine engine according to any one of claims 1 to 9, characterized in that the stator (201) and/or rotor (200) of the synchronous machine (2) are provided with cooling ductwork.

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