A turbine engine rotor assembly and a turbine engine

Abstract

The present invention discloses a turbine engine rotor assembly and a turbine engine. The turbine engine includes: an engine main shaft, a permanent magnet motor, a turbine bearing, a gas turbine group, and a compressor turbine. Among them: The gas turbine group includes at least one gas turbine, and the gas turbine group is installed at one end of the engine main shaft; the turbine bearing is installed at the other end of the engine main shaft; the compressor turbine is sleeved on the turbine bearing and is floatingly installed on the engine main shaft through the turbine bearing; the permanent magnet motor is arranged between the engine main shaft and the compressor turbine and is used to transmit the torque of the engine main shaft to the compressor turbine to drive the compressor turbine to rotate. Through the embodiments of the present invention, the working state of the compressor turbine can be controlled, the occurrence of surging can be prevented, the entire turbine engine can operate with a wider surging margin, and the turbine engine can have a faster power response speed.

Description

Technical Field

[0001] The present invention relates to the field of engines, and particularly to a turbine engine rotor assembly and a turbine engine. Background Art

[0002] Surge is an abnormal operating state of various turbine engines. When surge occurs, it will cause severe vibration of the engine and a rapid increase in the hot end temperature. If not effectively controlled, it will cause serious damage to the engine components. Therefore, the engine compressor must never operate in the surge state for a long time.

[0003] As Figure 1 shown, the rotor of the existing turbine engine mainly consists of an engine main shaft 1, a gas turbine group 4 and a compressor turbine 5 installed on the engine main shaft 1.

[0004] The fundamental reason for the surge of the engine compressor turbine is that the angle of attack is too large, causing the air flow to separate on the back of the compressor turbine blade.

[0005] Currently, the main methods for controlling surge in aeroengines are as follows: bleeding air from the intermediate stage of the compressor; adjustable guide vanes and stator vanes; dual-rotor or triple-rotor.

[0006] The first method: Using bleeding air from the intermediate stage of the compressor to prevent surge. Preventing surge by bleeding air from the intermediate stage of the compressor is to change the magnitude of the absolute velocity at the inlet of the working impeller by changing the flow rate, thereby changing the magnitude and direction of its relative velocity, changing the angle of attack, and achieving the purpose of preventing surge. In this way, the structure of bleeding air from the intermediate stage of the compressor is simple and is beneficial to the stability of the compressor at low speeds. However, bleeding air from the intermediate stage of the compressor will cause its pressure ratio to decrease, resulting in a reduction in power output.

[0007] The second method: Preventing surge with adjustable angle stator vane cascades. If the installation angle of the inlet guide vane changes accordingly with the change in the air flow rate through the compressor, so as to keep the angle of attack unchanged to achieve the purpose of preventing surge, that is, by changing the installation angle of the inlet guide vane or the stator vane, changing the angle of the air flow entering the compressor, and keeping the direction of the resultant velocity unchanged. The advantages of using adjustable guide vanes and stator vanes in this way are high efficiency at off-design points, improving the acceleration performance of the engine, and being applicable to engines with high pressure ratios. However, its control actuator is complex, and the manufacturing difficulty and cost are also very high.

[0008] The third method: anti-surge with a dual-rotor or triple-rotor. Anti-surge with a dual-rotor or triple-rotor is achieved by changing the rotational speed, that is, by changing the tangential velocity of the compressor moving blade cascade to change the relative velocity and direction at the inlet of the working impeller, so as to adjust the angle of attack to operate near the design value and achieve the purpose of anti-surge. In this method, due to the structure, the compressor is divided into two sections, which are driven by a high-pressure turbine and a low-pressure turbine respectively. There is no direct mechanical transmission connection between the high-pressure and low-pressure compressors. As for the whole system, partial decoupling is achieved, separating the mechanical coupling that is unfavorable for engine operation, and realizing self-adjusting rotational speed anti-surge through hydrodynamic action. The engine adopting this structure has large thrust, high efficiency and is easy to start. However, this method has a more complex internal and external support system, lubrication and cooling system, and also has a large weight, and the maintenance is complex. Summary of the Invention

[0009] In view of this, a turbine engine rotor assembly and a turbine engine provided by an embodiment of the present invention can control the working state of the compressor turbine, prevent the occurrence of surge phenomenon, enable the whole turbine engine to have a wider surge margin during operation, enable the turbine engine to have a faster power response speed, and adopt a single-rotor structure to simplify the structure of the compressor turbine so as to simplify the structure of the turbine engine, greatly reduce the structural weight of the turbine engine, reduce the manufacturing difficulty of the turbine engine and reduce the overall cost of the turbine engine.

[0010] The technical solutions adopted by the present invention to solve the above technical problems are as follows:

[0011] According to one aspect of an embodiment of the present invention, a turbine engine rotor assembly is provided. The turbine engine includes: an engine main shaft, a permanent magnet motor, a turbine bearing, a gas turbine group and a compressor turbine; wherein:

[0012] The gas turbine group includes at least one gas turbine, and the gas turbine group is installed at one end of the engine main shaft;

[0013] The turbine bearing is installed at the other end of the engine main shaft;

[0014] The compressor turbine is sleeved on the turbine bearing and is floatingly installed on the engine main shaft through the turbine bearing;

[0015] The permanent magnet motor is arranged between the engine main shaft and the compressor turbine and is used to transmit the torque of the engine main shaft to the compressor turbine to drive the compressor turbine to rotate.

[0016] In a possible design, the compressor turbine includes a turbine disk and a plurality of turbine blades, and the plurality of turbine blades are installed on the outside of the turbine disk along the circumferential direction.

[0017] In a possible design, the permanent magnet motor includes an active winding rotor and a driven permanent magnet rotor. The active winding rotor is installed on the engine main shaft, and the driven permanent magnet rotor is installed in the circumferential direction inside the turbine disk of the compressor turbine.

[0018] In a possible design, the turbine engine further includes: a control signal sending module, configured to receive a control signal transmitted externally and send the control signal outward in a preset control manner, where the control signal is a signal for controlling power transmission between the engine main shaft and the compressor turbine.

[0019] In a possible design, the control signal sending module includes a control signal sending circuit, and the control signal sending circuit includes a control signal input terminal and a sending circuit; wherein:

[0020] The control signal input terminal is used to be connected to an external control signal output terminal to receive the control signal transmitted externally;

[0021] The sending circuit is connected to the control signal input terminal and is used to send the control signal outward.

[0022] In a possible design, the sending circuit includes a light-emitting diode and a third resistor. The positive electrode of the light-emitting diode is connected to the control signal input terminal, and the negative electrode is connected to the third resistor.

[0023] In a possible design, the turbine engine further includes: a control signal receiving and driving module, configured to receive the control signal and control the on / off of the current loop of the active winding rotor.

[0024] In a possible design, the control signal receiving and driving module includes a control signal receiving and driving circuit, and the control signal receiving and driving circuit includes: a receiving circuit, a bridge rectifier circuit, and a driving circuit, wherein:

[0025] The bridge rectifier circuit is configured to rectify the induced electromotive force generated on the active winding rotor into a DC voltage and load the DC voltage onto the driving circuit;

[0026] The receiving circuit is configured to receive the control signal sent by the control signal sending module;

[0027] The driving circuit is configured to control the on / off of the current loop of the active winding rotor according to the control signal and the DC voltage.

[0028] In a possible design, the drive circuit includes an NMOS transistor; the bridge rectifier circuit includes a plurality of diodes, and every two diodes are connected in series to form a rectification component. The negative electrode of one diode in the rectification component is directly connected or connected to the drain of the NMOS transistor after passing through a current-limiting resistor. The positive electrode of the other diode in the rectification component is directly connected or connected to the source of the NMOS transistor after passing through a current-limiting resistor. The positive and negative electrodes of the two diodes in the rectification component are connected in series and then connected to the output end of the active winding rotor.

[0029] In a possible design, the receiving circuit includes: a photosensitive diode, the positive electrode of the photosensitive diode is connected to the gate of the NMOS transistor, and the negative electrode is connected to the drain of the NMOS transistor after passing through a current-limiting resistor.

[0030] In a possible design, the light-emitting diode controls its light-emitting state according to the control signal, and sends the control signal outward through a light control method, so that the photosensitive diode is turned on and off according to the light-emitting state of the light-emitting diode, so that the NMOS transistor is turned on and off, thereby controlling the on and off of the current loop of the active winding rotor.

[0031] In a possible design, the turbine engine further includes: a flow sensor, which is used to collect the flow rate of the fluid flowing through the stator vane row of the compressor turbine, and transmit the flow rate to a control computer. The control computer gives a rotational speed adapted to the flow rate according to the flow rate to control the rotational speed of the compressor turbine to operate within the design boundary.

[0032] According to another aspect of the embodiments of the present invention, a turbine engine is provided, and the turbine engine includes the turbine engine rotor assembly as described in any embodiment of the present application.

[0033] Compared with the related art, a turbine engine rotor assembly and a turbine engine provided by an embodiment of the present invention install the turbine bearing on the engine main shaft, and the compressor turbine sleeve is floatingly installed on the engine main shaft through the turbine bearing. The permanent magnet motor is arranged between the engine main shaft and the compressor turbine to transmit the torque of the engine main shaft to the compressor turbine to drive the compressor turbine to rotate. By adopting the above structure to control the working state of the compressor turbine, the occurrence of surge phenomenon can be prevented, the whole turbine engine can have a wider surge margin, and the turbine engine can have a faster power response speed. In addition, since the compressor turbine of the present application adopts a single-rotor structure, the structure of the compressor turbine is simplified to simplify the structure of the turbine engine, the structural weight of the turbine engine is greatly reduced, the manufacturing difficulty of the turbine engine is reduced, and the overall cost of the turbine engine is reduced. At the same time, the turbine engine does not adopt the intermediate-stage air bleeding method, which can reduce the energy loss of the engine, further reduce the fuel consumption of the engine, and improve the fuel economy. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 FIG. 6 is a schematic structural diagram of an existing turbine engine rotor assembly;

[0035] Figure 2 FIG. 10 is a schematic structural diagram of a turbine engine rotor assembly provided by an embodiment of the present invention;

[0036] Figure 3 FIG. 14 is a schematic structural diagram of a control signal sending module of a turbine engine rotor assembly provided by an embodiment of the present invention;

[0037] Figure 4 FIG. 18 is a schematic circuit diagram of a control signal sending module of a turbine engine rotor assembly provided by an embodiment of the present invention;

[0038] Figure 5 FIG. 22 is a schematic structural diagram of a control signal receiving and driving module of a turbine engine rotor assembly provided by an embodiment of the present invention;

[0039] Figure 6 FIG. 26 is a schematic circuit diagram of a control signal receiving and driving module of a turbine engine rotor assembly provided by an embodiment of the present invention;

[0040] Figure 7 FIG. 30 is a schematic structural diagram of a turbine engine provided by an embodiment of the present invention.

[0041] The realization, functional features and advantages of the object of the present invention will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0042] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only for explaining the present invention and are not used to limit the present invention.

[0043] In subsequent descriptions, suffixes such as "module", "component" or "unit" used to represent elements are only for the convenience of describing the present invention, and they have no specific meaning in themselves. Therefore, "module", "component" or "unit" can be used interchangeably.

[0044] It should be noted that the terms "first", "second", etc. in the description and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily need to describe a specific order or sequence.

[0045] In one embodiment, as Figure 2 shown, the present invention provides a turbine engine rotor assembly. The turbine engine rotor assembly 100 includes: an engine main shaft 10, a permanent magnet motor 20, a turbine bearing 30, a gas turbine group 40, and a compressor turbine 50; wherein:

[0046] The gas turbine group 40 includes at least one gas turbine 41, and the gas turbine group 40 is installed at one end of the engine main shaft 10.

[0047] The turbine bearing 30 is installed at the other end of the engine main shaft 10.

[0048] The compressor turbine 50 is sleeved on the turbine bearing 30 and is floatingly installed on the engine main shaft 10 through the turbine bearing 30.

[0049] The permanent magnet motor 20 is arranged between the engine main shaft 10 and the compressor turbine 50, and is used to transmit the torque of the engine main shaft 10 to the compressor turbine 50 to drive the compressor turbine 50 to rotate.

[0050] In this embodiment, by mounting the turbine bearing 30 on the engine main shaft 10, the compressor turbine 50 is sleeved and floatingly mounted on the engine main shaft 10 through the turbine bearing 30. The permanent magnet motor 20 is disposed between the engine main shaft 10 and the compressor turbine 50 to transmit the torque of the engine main shaft 10 to the compressor turbine 50 to drive the compressor turbine 50 to rotate. By adopting the above structure to control the working state of the compressor turbine, the occurrence of surge can be prevented, the whole turbine engine can operate with a wider surge margin, and the turbine engine can have a faster power response speed. In addition, since the compressor turbine of the present application adopts a single-rotor structure, the structure of the rotor assembly of the turbine engine is simplified to simplify the structure of the turbine engine, the structural weight of the turbine engine is greatly reduced, the manufacturing difficulty of the turbine engine is reduced, and the overall cost of the turbine engine is reduced. At the same time, the turbine engine does not adopt the intermediate-stage air bleeding method, which can reduce the energy loss of the engine, further reduce the fuel consumption of the engine, and improve the fuel economy.

[0051] In one embodiment, as Figure 2 shown, the compressor turbine 50 includes a turbine disk 51 and a plurality of turbine blades 52. The plurality of turbine blades 52 are mounted on the outside of the turbine disk 51 in the circumferential direction.

[0052] The turbine bearing 30 is mounted at the center inside the turbine disk 51.

[0053] The compressor turbine 50 is sleeved on the turbine bearing 30 and is floatingly mounted on the engine main shaft 10 through the turbine bearing 30. That is, the compressor turbine 50 can rotate freely on the engine main shaft 10 and is not directly driven by the engine main shaft 10. This is different from the traditional compressor turbine. It is this structural feature that determines that the compressor turbine can be controlled to rotate independently, which is also the core of the compressor turbine of the present application to prevent surge.

[0054] In one embodiment, as Figure 2 shown, the permanent magnet motor 20 is disposed between the engine main shaft 10 and the compressor turbine 50 and is used to transmit the torque of the engine main shaft 10 to the compressor turbine 50 to drive the compressor turbine 50 to rotate.

[0055] The permanent magnet motor 20 includes an active winding rotor 21 and a driven permanent magnet rotor 22. The active winding rotor 21 is mounted on the engine main shaft 10, and the driven permanent magnet rotor 22 is mounted on the circumferential direction inside the turbine disk 51 of the compressor turbine 50. That is, part of the structure of the permanent magnet motor 20 is mounted on the engine main shaft 10, and part of the structure is mounted on the compressor turbine 50. Through the cooperation of the permanent magnet motor 20 composed of the active winding rotor 21 mounted on the engine main shaft 10 and the driven permanent magnet rotor 22 mounted inside the turbine disk 51 of the compressor turbine 50, the torque of the engine main shaft 10 is transmitted to the compressor turbine 50, thereby driving the compressor turbine 50 to rotate.

[0056] Preferably, the active winding rotor 21 is a winding rotor composed of iron core material.

[0057] Preferably, the driven permanent magnet rotor 22 is made of magnetic steel material.

[0058] In this embodiment, when the engine main shaft 10 drives the active winding rotor 21 to rotate, the turbine blades 52 of the compressor turbine 50 equipped with the driven permanent magnet rotor 22 remain stationary or rotate at a low speed due to air resistance (the torque transmitted by bearing friction can be ignored), so that there is a speed difference between the active winding rotor 21 and the driven permanent magnet rotor 22. According to the principle of electromagnetic induction, an induced electromotive force will be generated on the active winding rotor 21. However, at this time, the torque power generated by the engine main shaft 10 cannot be transmitted to the compressor turbine 50. This situation is equivalent to power disconnection, and the turbine blades 52 of the compressor turbine 50 cannot rotate at high speed. If the output end of the active winding rotor 21 is short-circuited to form a closed loop at this time, a loop current will be formed on the active winding rotor 21. Since there is a force acting on the current in the magnetic field and the force is mutual, at this time, the rotating active winding rotor 21 transmits the torque to the driven permanent magnet rotor 22 through electromagnetic force, causing the driven permanent magnet rotor 22 to rotate at high speed, and then driving the turbine blades 52 of the compressor turbine 50 to rotate at high speed, thereby transmitting the torque power generated by the engine main shaft 10 to the compressor turbine 50, completing the power transmission. This situation is equivalent to power connection, and the turbine blades 52 of the compressor turbine 50 can rotate at high speed. The above is the mechanical torque transmission on and off completed by controlling the on and off of the current loop of the active winding rotor 21 in the compressor turbine proposed in this application, that is, the torque force transmission and adjustment are changed by the electromagnetic force change of controlling the on and off of the current loop of the active winding rotor 21 in the compressor turbine, so that the turbine engine can have a faster power response speed.

[0059] In one embodiment, as Figure 2 shown, the turbine engine rotor assembly 100 further includes: a control signal sending module 60 and a control signal receiving and driving module 70.

[0060] The control signal sending module 60 is configured to receive a control signal transmitted externally and send the control signal outward in a preset control manner, where the control signal is a signal for controlling power transmission between the engine main shaft 10 and the compressor turbine 50.

[0061] Wherein, the preset control manner includes one of the following: optical control, magnetic field Hall control, wireless electromagnetic wave control. Through one of the above control manners, the control signal for power transmission between the engine main shaft 10 and the compressor turbine 50 is sent outward. In the following embodiments, only the optical control manner is taken as an example to introduce the sending of the control signal for power transmission between the engine main shaft 10 and the compressor turbine 50, and other control manners are similar to the optical control manner and will not be elaborated herein.

[0062] The control signal receiving and driving module 70 is configured to receive the control signal and control the on / off of the current loop of the active winding rotor 21. If the output end of the active winding rotor 21 is short-circuited to connect the current loop and a loop current is formed on the active winding rotor 21, a closed loop is formed; if the output end of the active winding rotor 21 disconnects the current loop and no loop current is formed on the active winding rotor 21, no closed loop is formed.

[0063] As Figure 3 shown, the control signal sending module 60 includes a control signal sending circuit 61. The control signal sending circuit 61 includes a control signal input end 611 and a sending circuit 612. The control signal input end 611 is used to connect to an external control signal output end to receive the control signal transmitted externally. The sending circuit 612 is connected to the control signal input end 611 and is used to send the control signal outward.

[0064] Preferably, the control signal is a square wave control signal with an adjustable duty cycle.

[0065] As Figure 4 shown, the sending circuit 612 includes a light-emitting diode D8 and a third resistor R3. The positive electrode of the light-emitting diode D8 is connected to one end of the control signal input end 611, the negative electrode of the light-emitting diode D8 is connected to one end of the third resistor R3, and the other end of the third resistor R3 is connected to the other end of the control signal input end 611.

[0066] The light-emitting diode D8 sends out a control signal for controlling power transmission between the engine main shaft 10 and the compressor turbine 50 through a light control method. When the connected control signal input terminal 611 is powered on, the light-emitting diode D8 is powered on and emits light, and sends out the received control signal through the light control method. When the connected control signal input terminal 611 is powered off, the light-emitting diode D8 is powered on but does not emit light, and cannot send out the received control signal through the light control method.

[0067] When a square-wave control signal with an adjustable duty cycle is connected to the light-emitting diode D8, the rotational speed of the compressor turbine 50 can be correspondingly changed. That is, when the light-emitting diode D8 is powered on, the power of the compressor turbine 50 is turned on, and when the light-emitting diode D8 is powered off, the power of the compressor turbine 50 is interrupted.

[0068] In this embodiment, through the above method, an effective means can be provided for the electronic control of preventing the compressor turbine from surging, the working state of the compressor turbine can be effectively controlled, the occurrence of the surging phenomenon can be prevented, the whole turbine engine can operate with a wider surging margin, the turbine engine can have a faster power response speed, and at the same time, a direct electronic control method can be adopted to make the turbine engine more intelligent and efficient.

[0069] In one embodiment, as Figure 5 shown, the control signal receiving and driving module 70 includes a control signal receiving and driving circuit 71, and the control signal receiving and driving circuit 71 includes: a receiving circuit 711, a bridge rectifier circuit 712, and a driving circuit 713. Among them:

[0070] The bridge rectifier circuit 712 is used to rectify the induced electromotive force generated on the active winding rotor 21 into a DC voltage and load the DC voltage onto the driving circuit 713.

[0071] The receiving circuit 711 is used to receive the control signal sent by the control signal sending module 60.

[0072] The driving circuit 713 is used to control the on-off of the current loop of the active winding rotor 21 according to the control signal and the DC voltage.

[0073] Specifically, as Figure 6 shown, the driving circuit 713 includes: an NMOS transistor Q1. In this embodiment, the NMOS transistor is taken as an example to illustrate the driving circuit 713, but a PMOS transistor, a triode, or an element or circuit that realizes a similar current driving function can also be used to form the driving circuit, which will not be elaborated here.

[0074] The bridge rectifier circuit 712 includes a plurality of diodes. Every two diodes are connected in series to form a rectification component. The negative electrode of one diode in the rectification component is directly connected or connected to the drain of the NMOS transistor Q1 after passing through a current-limiting resistor. The positive electrode of the other diode in the rectification component is directly connected or connected to the source of the NMOS transistor Q1 after passing through a current-limiting resistor. The positive and negative electrodes of the two diodes in the rectification component are connected in series and then connected to the output terminal of the active winding rotor 21.

[0075] For example, as Figure 6 shown, the bridge rectifier circuit 712 is composed of 6 diodes, namely diode D1, diode D2, diode D3, diode D4, diode D5 and diode D6. The 6 diodes form three rectification components. That is, diode D1 and diode D2 are connected in series to form the first rectification component, diode D3 and diode D4 are connected in series to form the second rectification component, and diode D5 and diode D6 are connected in series to form the third rectification component; the negative electrode of diode D1 in the first rectification component is used as the negative electrode of the first rectification component, the positive electrode of diode D1 is connected in series with the negative electrode of diode D2 (series connection C), and the positive electrode of diode D2 is used as the positive electrode of the first rectification component; the negative electrode of diode D3 in the second rectification component is used as the negative electrode of the second rectification component, the positive electrode of diode D3 is connected in series with the negative electrode of diode D4 (series connection point B), and the positive electrode of diode D4 is used as the positive electrode of the second rectification component; the negative electrode of diode D5 in the third rectification component is used as the negative electrode of the third rectification component, the positive electrode of diode D5 is connected in series with the negative electrode of diode D6 (series connection point A), and the positive electrode of diode D6 is used as the positive electrode of the third rectification component; the positive electrodes of the first rectification component, the second rectification component and the third rectification component are connected together and then directly connected to the source of the NMOS transistor Q1. The negative electrodes of the first rectification component, the second rectification component and the third rectification component are connected together and then connected to the drain of the NMOS transistor Q1 after passing through the current-limiting resistor R1.

[0076] The receiving circuit 711 includes: a photosensitive diode D7. The positive electrode of the photosensitive diode D7 is connected to the gate of the NMOS transistor Q1, and the negative electrode of the photosensitive diode D7 is connected to the drain of the NMOS transistor Q1 after passing through a current-limiting resistor R1.

[0077] In Figure 6 it, the active winding rotor 21 is a three-phase star winding rotor (it can also be single-phase. In this embodiment, the three-phase is taken as an example for illustration). The output terminal of each phase is respectively connected to the series connection points A, B, and C of the positive and negative electrodes of two diodes in each rectification component. The gate of the NMOS transistor Q1 is connected to the source of the NMOS transistor Q1 after passing through the second resistor R2.

[0078] The induced electromotive force generated by the active winding rotor 21 is rectified into a DC voltage after passing through the bridge rectifier circuit 712 composed of six diodes (as Figure 6 shown, the upper is the positive voltage and the lower is the negative voltage), and the DC voltage is directly or through the current-limiting resistor R1 loaded to the source and drain of the NMOS transistor Q1.

[0079] The light-emitting diode D8 controls the light-emitting state according to the control signal, and sends the control signal outward through the optical control method, so that the photodiode D7 is turned on and off according to the light-emitting state of the light-emitting diode D8, so as to turn on and off the NMOS transistor Q1, thereby controlling the on and off of the current loop of the active winding rotor 21. Specifically:

[0080] When Figure 4 the control signal input terminal 611 connected in Figure 6 is powered off, the light-emitting diode D8 is powered on but does not emit light, and cannot send the received control signal outward through the optical control method, so that

[0081] the photodiode D7 in Figure 4 is not illuminated by the light-emitting diode D8. At this time, the gate voltage of the NMOS transistor Q1 is zero, and the NMOS transistor Q1 is turned off. At this time, it is equivalent to the active winding rotor 21 being open, and mechanically it is equivalent to the power being cut off.

[0081] When Figure 4 the control signal input terminal 611 connected in Figure 6 is powered on, the light-emitting diode D8 is powered on and emits light, and sends the received control signal outward through the optical control method, so that Figure 6 the photodiode D7 in Figure 6 is illuminated by the light-emitting diode D8. At this time, the positive voltage breaks down the photodiode D7 and is loaded to the gate of the NMOS transistor Q1, so that the gate voltage of the NMOS transistor Q1 is close to the power supply voltage, and the NMOS transistor Q1 is turned on, and a loop is formed between the positive and negative, and there is current flowing through. At this time, it is equivalent to the active winding rotor 21 being short-circuited, and mechanically it is equivalent to the power being turned on. That is, when the light-emitting diode D8 is powered on and emits light, the photodiode D7 is illuminated, so as to transfer the torque power generated by the engine main shaft 10 to the compressor turbine 50 to turn on the power of the compressor turbine 50. When the light-emitting diode D8 is powered off and does not emit light, the photodiode D7 cannot be illuminated, so that the torque power generated by the engine main shaft 10 cannot be transferred to the compressor turbine 50, and the power of the compressor turbine 50 is interrupted.

[0082] In this embodiment, through the above method, an effective means can be provided for the electronic control of the prevention of compressor turbine surge, which can effectively control the working state of the compressor turbine, prevent the occurrence of surge phenomenon, enable the entire turbine engine to have a wider surge margin, enable the turbine engine to have a faster power response speed, and at the same time, a direct electronic control method can be adopted to make the turbine engine more intelligent and efficient.

[0083] In one embodiment, the turbine engine rotor assembly 100 further includes: a flow sensor (not shown), which is installed at each stage of the stator vane cascade (not shown) of the compressor turbine, and is used to collect the flow rate of the fluid flowing through the stator vane cascade of the compressor turbine, and transmit the flow rate to a control computer. The control computer calculates or looks up a table according to the flow rate, and gives a rotational speed adapted to the flow rate to control the rotational speed of the compressor turbine to operate within the design boundary.

[0084] In this embodiment, by installing a flow sensor at each stage of the stator vane cascade of the compressor turbine, collecting the flow rate of the fluid flowing through the stator vane cascade of the compressor turbine, and transmitting the flow rate to a control computer, the control computer gives a rotational speed adapted to the flow rate according to the flow rate, and controls the rotational speed of the compressor turbine to operate within the design boundary. Thus, a direct electronic control method can be adopted to make the turbine engine more intelligent and efficient.

[0085] In one embodiment, as Figure 7 shown, the present invention provides a turbine engine, which includes the turbine engine rotor assembly 100 described in any of the above embodiments.

[0086] Among them, the structure and function of the turbine engine rotor assembly 100 in this embodiment are the same as those of the turbine engine rotor assembly 100 described in any of the above embodiments, and will not be elaborated here.

[0087] It should be noted that the above turbine engine embodiment and the turbine engine rotor assembly embodiment belong to the same concept. The specific implementation process can be seen in the turbine engine rotor assembly embodiment, and the technical features in the turbine engine rotor assembly embodiment are all correspondingly applicable in the turbine engine embodiment, and will not be repeated here.

[0088] In this embodiment, when the turbine engine is started by bleeding air, the duty ratio of the connection between the compressor and the turbine in the compressor turbine can be reduced first. At this time, due to the small inertia of the compressor, it does not need a large amount of power to drive the gas turbine, and the speed increases quickly, which can quickly raise the pressure in the combustion chamber to the ignition condition. Then fuel is injected and ignited, and the gas pushes the turbine to the starting speed, making the engine start performance better.

[0089] When the engine accelerates rapidly, the turbine speed and thrust increase rapidly. The compressor turbine will increase its speed according to the incoming air flow rate to adapt to the increase in flight speed. Phenomenally, the speed increase of the compressor turbine is "half a beat slower" than that of the gas turbine. This avoids the compressor turbine entering the surge zone due to excessive acceleration, thereby reducing the limitation on acceleration and giving the engine better acceleration performance. Since the present application adopts a single-rotor structure but realizes the functions of a dual-rotor or triple-rotor, the structural weight can be reduced significantly, the manufacturing difficulty can be decreased, and the overall cost of the engine can also be reduced. At the same time, without adopting the intermediate-stage air bleeding method, the energy loss of the engine can be reduced, and the fuel consumption of the engine can be further decreased, improving fuel economy.

[0090] In this embodiment, a turbine engine is provided by s. By changing the tangential speed of the turbine blade to change the angle of attack, the technical means of any of the above embodiments are adopted to achieve the controllable speed regulation of the active winding rotor and realize the complete decoupling from the turbine. During the operation of the engine, the rotational speeds of each stage of the compressor can be adjusted according to the values of the flow rate sensors at each stage, so that the control of each stage can be automatically controlled by a computer, making the engine more intelligent.

[0091] It should be noted that in this article, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article or device including that element.

[0092] The serial numbers of the above embodiments of the present invention are only for description and do not represent the advantages or disadvantages of the embodiments.

[0093] The embodiments of the present invention have been described above in conjunction with the accompanying drawings. However, the present invention is not limited to the above specific embodiments. The above specific embodiments are merely illustrative and not restrictive. Under the inspiration of the present invention, those of ordinary skill in the art can also make many forms without departing from the spirit and scope protected by the present invention and the claims. All of these fall within the protection scope of the present invention.

Claims

1. A turbine engine rotor assembly, characterized in that, The turbine engine rotor assembly includes: an engine main shaft, a permanent magnet motor, a turbine bearing, a gas turbine group, and a compressor turbine; wherein: The gas turbine group includes at least one gas turbine, and the gas turbine group is installed at one end of the engine main shaft; The turbine bearing is installed at the other end of the engine main shaft; The compressor turbine is sleeved on the turbine bearing and is floatingly installed on the engine main shaft through the turbine bearing; The permanent magnet motor is arranged between the engine main shaft and the compressor turbine and is used to transmit the torque of the engine main shaft to the compressor turbine to drive the compressor turbine to rotate.

2. The turbine engine rotor assembly according to claim 1, wherein, The compressor turbine includes a turbine disk and a plurality of turbine blades, and the plurality of turbine blades are installed on the outside of the turbine disk in the circumferential direction.

3. The turbine engine rotor assembly according to claim 2, wherein The permanent magnet motor includes an active winding rotor and a driven permanent magnet rotor. The active winding rotor is installed on the engine main shaft, and the driven permanent magnet rotor is installed in the circumferential direction inside the turbine disk of the compressor turbine.

4. The turbine engine rotor assembly according to claim 3, wherein, The turbine engine rotor assembly further includes: a control signal sending module, which is used to receive a control signal transmitted externally and send the control signal outward in a preset control manner, wherein the control signal is a signal for controlling power transmission between the engine main shaft and the compressor turbine.

5. The turbine engine rotor assembly according to claim 4, wherein, The control signal sending module includes a control signal sending circuit, and the control signal sending circuit includes a control signal input end and a sending circuit; wherein: The control signal input end is used to be connected to an external control signal output end to receive the control signal transmitted externally; The sending circuit is connected to the control signal input end and is used to send the control signal outward.

6. The turbine engine rotor assembly according to claim 5, characterized in that, The sending circuit includes a light-emitting diode and a third resistor. The positive electrode of the light-emitting diode is connected to the control signal input end, and the negative electrode is connected to the third resistor.

7. The turbine engine rotor assembly according to claim 6, wherein, The turbine engine rotor assembly further includes: a control signal receiving and driving module, which is used to receive the control signal and control the on-off of the current loop of the active winding rotor.

8. The turbine engine rotor assembly according to claim 7, wherein, The control signal receiving and driving module includes a control signal receiving and driving circuit, and the control signal receiving and driving circuit includes: a receiving circuit, a bridge rectifier circuit, and a driving circuit, wherein: The bridge rectifier circuit is used to rectify the induced electromotive force generated on the active winding rotor into a DC voltage and load the DC voltage onto the driving circuit; The receiving circuit is used to receive the control signal sent by the control signal sending module; The driving circuit is used to control the on-off of the current loop of the active winding rotor according to the control signal and the DC voltage.

9. The turbine engine rotor assembly according to claim 8, characterized in that, The drive circuit includes an NMOS transistor; the bridge rectifier circuit includes a plurality of diodes. Each two diodes are connected in series to form a rectification component. The negative electrode of one diode in the rectification component is directly connected or connected to the drain of the NMOS transistor through a current-limiting resistor. The positive electrode of the other diode in the rectification component is directly connected or connected to the source of the NMOS transistor through a current-limiting resistor. The positive and negative electrodes of the two diodes in the rectification component are connected in series and then connected to the output end of the active winding rotor.

10. The turbine engine rotor assembly according to claim 9, characterized in that, The receiving circuit includes: a photosensitive diode. The positive electrode of the photosensitive diode is connected to the gate of the NMOS transistor, and the negative electrode is connected to the drain of the NMOS transistor through a current-limiting resistor.

11. The turbine engine rotor assembly according to claim 10, characterized in that, The light-emitting diode controls the light-emitting state according to the control signal, and sends the control signal outward through a light control method, so that the photosensitive diode is turned on and off according to the light-emitting state of the light-emitting diode, so that the NMOS transistor is turned on and off, thereby controlling the on and off of the current loop of the active winding rotor.

12. The turbine engine rotor assembly according to claim 1, wherein, The turbine engine rotor assembly further includes: a flow sensor, which is used to collect the flow rate flowing through the stator vane row of the compressor turbine, and transmit the flow rate to a control computer. The control computer gives a rotational speed adapted to the flow rate according to the flow rate to control the rotational speed of the compressor turbine to operate within the design boundary.

13. A turbine engine, characterized in that, The turbine engine includes the turbine engine rotor assembly according to any one of claims 1 to 12.

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