CN111005768A - Electromagnetic counterweight device for rotor of aircraft engine - Google Patents
Electromagnetic counterweight device for rotor of aircraft engine Download PDFInfo
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- CN111005768A CN111005768A CN201911147569.XA CN201911147569A CN111005768A CN 111005768 A CN111005768 A CN 111005768A CN 201911147569 A CN201911147569 A CN 201911147569A CN 111005768 A CN111005768 A CN 111005768A
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- rotor
- electromagnet
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- aircraft engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
An electromagnetic counterweight device for an aircraft engine rotor belongs to the technical field of aircraft engines. The electromagnetic counterweight device for the aircraft engine rotor comprises a permanent magnet, an electromagnet and a self-adaptive current regulation controller; the permanent magnet is arranged at the root part of the rotor blade; the electromagnet is arranged outside the stator casing; the self-adaptive current regulation controller is connected with the aircraft engine and used for receiving vibration signals and rotating speed signals of the aircraft engine, and the self-adaptive current regulation controller is connected with the electromagnet and used for inputting current to the electromagnet. The electromagnetic counterweight device for the aircraft engine rotor adopts the electromagnetic virtual counterweight to replace a physical rotor counterweight disk, so that the weight of the engine rotor is greatly reduced, the stability of the rotation of the rotor is improved through an electromagnetic field, and the occurrence of vibration faults is reduced.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to an aero-engine rotor electromagnetic counterweight device.
Background
The interior of an aircraft engine rotor is generally provided with a counterweight plate to keep the engine stable and rotate at a high speed. However, the weight of the counterweight plate is large, so that the counterweight plate belongs to dead weight which does not contribute to the performance of the engine, the thrust-weight ratio of the engine is reduced, and the imbalance of the counterweight plate can cause large vibration of the whole engine and other technical problems.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides an electromagnetic counterweight device for an aircraft engine rotor, which adopts an electromagnetic virtual counterweight to replace a physical rotor counterweight disk, greatly reduces the weight of the engine rotor, improves the stability of the rotation of the rotor through an electromagnetic field, and reduces the occurrence of vibration faults.
In order to achieve the purpose, the technical scheme of the invention is as follows:
an electromagnetic counterweight device of an aircraft engine rotor comprises a permanent magnet, an electromagnet and a self-adaptive current regulation controller;
the permanent magnet is arranged at the root part of the rotor blade;
the electromagnet is arranged outside the stator casing;
the self-adaptive current regulation controller is connected with the aircraft engine and used for receiving vibration signals and rotating speed signals of the aircraft engine, and the self-adaptive current regulation controller is connected with the electromagnet and used for inputting current to the electromagnet.
The permanent magnet is embedded into the root of the rotor blade, and the electromagnet is embedded into the outer part of the stator casing.
The rotor of the aircraft engine is connected with the engine accessory casing through a driving shaft and is used for driving the engine accessory casing; the engine accessory case is connected with the alternating current generator, the alternating current generator is connected with the self-adaptive current regulation controller, and the engine accessory case transmits torque to the alternating current generator to generate power and supplies the power to the self-adaptive current regulation controller.
The invention has the beneficial effects that:
1) the permanent magnet and the electromagnet are matched to replace a counterweight plate with larger weight, so that the weight of the engine is reduced;
2) the working stability of the engine is ensured and the vibration level of the whole engine is reduced by controlling the current introduced into the electromagnet;
3) the invention is suitable for various aeroengines, gas turbines and the like, in particular to civil aviation aeroengines, and has wide market prospect;
4) through simulation calculation, the rotor electromagnetic counterweight device of the engine can reduce the weight of the rotor of the engine by more than 60 percent, further improve the thrust-weight ratio of the engine by more than 30 percent and reduce the oil consumption rate of the engine by about 20 percent, taking a CFM56 aircraft engine as an example, the oil consumption cost of each engine can be saved by about 0.4 ton per flying hour, and the flying cost of each thousand engines can be saved by about 153.6 billion yuan per 60 percent of attendance per year.
Additional features and advantages of the invention will be set forth in part in the detailed description which follows.
Drawings
FIG. 1 is a schematic structural view of a prior art aircraft engine rotor counterweight plate;
FIG. 2 is a schematic structural diagram of an electromagnetic counterweight device for an aircraft engine rotor, provided by an embodiment of the invention;
fig. 3 is a connection block diagram of an aircraft engine rotor electromagnetic counterweight device provided by an embodiment of the invention.
Reference numerals in the drawings of the specification include:
1-rotor counterweight plate, 2-rotor blade, 3-stator blade, 4-stator casing, 5-shaft neck, 6-bearing, 7-permanent magnet and 8-electromagnet.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
In the description of the present invention, unless otherwise specified and limited, it is to be noted that the terms "mounted," "connected," and "connected" are to be interpreted broadly, and may be, for example, a mechanical connection or an electrical connection, a communication between two elements, a direct connection, or an indirect connection via an intermediate medium, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
In order to solve the problems in the prior art, as shown in fig. 1 to 3, an embodiment of the present invention provides an electromagnetic counterweight device for an aircraft engine rotor, which uses an electromagnetic virtual counterweight to replace a physical rotor counterweight disk 1, so as to greatly reduce the weight of the engine rotor, improve the stability of the rotor rotation through an electromagnetic field, and reduce the occurrence of vibration faults.
As shown in fig. 1 and 2, an electromagnetic counterweight device for an aircraft engine rotor comprises a permanent magnet 7, an electromagnet 8 and an adaptive current regulation controller; the permanent magnet 7 is arranged at the root part of the rotor blade 2; the electromagnet 8 is disposed outside the stator case 4. The invention replaces the structure of the prior aeroengine rotor counterweight disc 1, other structures of the aeroengine such as a stator blade 3, a shaft neck 5, a bearing 6 and the like are not changed, a permanent magnet 7 is embedded in the root part of the aeroengine rotor blade 2, an electromagnet 8 is embedded in the position corresponding to the permanent magnet outside a stator casing 4, when the engine works, the current of the electromagnet 8 is adjusted, further the centripetal force at the root part of the rotor blade 2 is adjusted, and the counterweight disc of the engine rotor blade 2 is simulated through the interaction of magnetic force. When the engine works, corresponding current is introduced to the electromagnet 8 along with the difference of the rotating speed, so that the electromagnetic force meets the counterweight requirement of the rotating speed, when the rotor of the engine is unstable in rotation and large in vibration, the current introduced to the electromagnet 8 embedded in the outer part of the stator case 4 is increased by a small amplitude, the centripetal force of the rotor is increased, the stability of the rotor is enhanced, and the vibration level of the whole engine is reduced.
As shown in fig. 3, the adaptive current regulation controller is connected to the aircraft engine and configured to receive a vibration signal and a rotation speed signal of the aircraft engine, and the adaptive current regulation controller is connected to the electromagnet 8 and configured to input a current to the electromagnet 8. The rotor of the aircraft engine is connected with the engine accessory casing through a driving shaft and is used for driving the engine accessory casing; the engine accessory case is connected with the alternating current generator, the alternating current generator is connected with the self-adaptive current regulation controller, and the engine accessory case transmits torque to the alternating current generator to generate power and supplies the power to the self-adaptive current regulation controller. The self-adaptive current regulation controller adopts the prior art, for example, a full-authority digital electronic control technology, the self-adaptive current regulation controller automatically regulates output current to the electromagnet 8 according to a vibration signal and a rotating speed signal of an engine, a vibration sensor for collecting the vibration signal and a rotating speed sensor for collecting the rotating speed signal are arranged in the conventional aircraft engine, the self-adaptive current regulation controller realizes signal receiving through the vibration sensor and the rotating speed sensor, and meanwhile, the electromagnet 8 regulates an electromagnetic field interacting with the permanent magnet 7 according to the magnitude of the input current so as to regulate a virtual centripetal force generated by the electromagnetic virtual counterweight permanent magnet 7.
The working principle of the electromagnetic counterweight device for the rotor of the aircraft engine is as follows:
when the engine works, the engine rotor drives the engine accessory casing through the driving shaft, the engine accessory casing transmits torque to the alternating current generator for power generation and supplies the torque to the self-adaptive current regulation controller, the self-adaptive current regulation controller receives a vibration signal and a rotating speed signal of the engine and automatically regulates output current to the electromagnet 8 according to the vibration signal and the rotating speed signal of the engine, and magnetic force generated by the electromagnet 8 interacts with the permanent magnet 7 embedded into the root part of the rotor blade 2 through magnetic force to generate centripetal force on the rotor; the electromagnet 8 adjusts an electromagnetic field interacting with the permanent magnet 7 according to the magnitude of the input current, and further adjusts a virtual centripetal force generated by the electromagnetic virtual counterweight permanent magnet 7;
when the rotating speed of the engine is low, the required virtual counterweight is small, the current input to the electromagnet 8 by the self-adaptive current regulation controller is small, when the rotating speed of the engine is increased, the required virtual counterweight is gradually increased, the current input to the electromagnet 8 by the self-adaptive current regulation controller is increased, the current introduced to the electromagnet 8 is increased along with the increase of the rotating speed, the electromagnetic force strength is further increased, the centripetal force of the rotor is increased, and the rotor is stabilized by simulating the rotor counterweight disc 1;
when the vibration of the engine is small, the rotor rotates stably, the required additional virtual counterweight is small, and the current input to the electromagnet 8 is small; when the engine vibration increases, need bigger virtual counter weight to stabilize the rotation of rotor, the electric current grow to 8 inputs of electro-magnet this moment, increase the electric current that lets in to electro-magnet 8, and then increase the stability of rotor, reduce complete machine vibration level.
When the engine works, the input current of the electromagnet 8 is superposed under the influence of the vibration and the rotating speed of the engine, the larger the input current is, the more the stable rotation of the rotor is facilitated, but the more the consumed electric energy is, the self-adaptive current regulation controller can judge the input vibration signal and the rotating speed signal according to the preset logic, and therefore the most economical current capable of meeting the work of the engine can be automatically output.
When the electromagnetic device is adopted, cables, electrical accessories on all aircraft engines, relevant electrical accessories on airplanes and the like have necessary electromagnetic compatibility, so that the electromagnetic compatibility is processed, and the electromagnetic device can be prevented from generating interference on control signals. In addition, the individual parts of the external conduit and the bracket of the engine are provided with bond wires to carry out voltage equalization on the voltage generated by electromagnetism, and when the equalized voltage of related components is accumulated to a certain degree, point discharge is needed to be carried out to release electric energy, so that the airplane, the engine, pilots and ground maintainers are protected from electric shock.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (3)
1. An electromagnetic counterweight device of an aircraft engine rotor is characterized by comprising a permanent magnet, an electromagnet and a self-adaptive current regulation controller;
the permanent magnet is arranged at the root part of the rotor blade;
the electromagnet is arranged outside the stator casing;
the self-adaptive current regulation controller is connected with the aircraft engine and used for receiving vibration signals and rotating speed signals of the aircraft engine, and the self-adaptive current regulation controller is connected with the electromagnet and used for inputting current to the electromagnet.
2. An aircraft engine rotor electromagnetic counterweight according to claim 1 and characterized in that said permanent magnets are embedded in the root of the rotor blade and said electromagnets are embedded outside the stator casing.
3. The aircraft engine rotor electromagnetic counterweight device of claim 1, wherein the aircraft engine rotor is connected to an engine accessory case by a drive shaft for driving the engine accessory case; the engine accessory case is connected with the alternating current generator, the alternating current generator is connected with the self-adaptive current regulation controller, and the engine accessory case transmits torque to the alternating current generator to generate power and supplies the power to the self-adaptive current regulation controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911147569.XA CN111005768A (en) | 2019-11-21 | 2019-11-21 | Electromagnetic counterweight device for rotor of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911147569.XA CN111005768A (en) | 2019-11-21 | 2019-11-21 | Electromagnetic counterweight device for rotor of aircraft engine |
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| CN111005768A true CN111005768A (en) | 2020-04-14 |
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| CN201911147569.XA Pending CN111005768A (en) | 2019-11-21 | 2019-11-21 | Electromagnetic counterweight device for rotor of aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113432789A (en) * | 2021-06-30 | 2021-09-24 | 中国大唐集团科学技术研究院有限公司华东电力试验研究院 | Online testing device and method for dynamic balance weight of rotary machine |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101592081A (en) * | 2009-06-05 | 2009-12-02 | 中国航空动力机械研究所 | A kind of gas turbine generating engine |
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN106030261A (en) * | 2013-12-23 | 2016-10-12 | 涡轮梅坎公司 | Turbine engine assembly for measuring the vibrations to which a rotating blade is subjected |
| CN107013410A (en) * | 2017-06-07 | 2017-08-04 | 曲阜师范大学 | A kind of vertical axis permanent magnet direct wind-driven generator and its control method |
| CN107313876A (en) * | 2017-07-04 | 2017-11-03 | 南京航空航天大学 | Contain fan outside a kind of magnetic suspension for aviation turbofan engine |
| CN107435591A (en) * | 2016-05-27 | 2017-12-05 | 中国航发商用航空发动机有限责任公司 | Aero-Engine Start system, starting method and aero-engine |
| CN108869558A (en) * | 2018-01-12 | 2018-11-23 | 至玥腾风科技投资集团有限公司 | A kind of control method of bearing, rotor-support-foundation system and bearing |
| CN109655270A (en) * | 2018-10-29 | 2019-04-19 | 中国航发贵阳发动机设计研究所 | A kind of installation of cantilever can high tachometric survey torque device |
| CN109690027A (en) * | 2016-09-08 | 2019-04-26 | 赛峰直升机发动机 | A kind of device for by multi-layer piezoelectric actuator control inlet guide vane |
| CN109989878A (en) * | 2019-04-28 | 2019-07-09 | 福州大学 | Electromagnetic type wind power generator impeller imbalance compensation device and method |
| CN209398455U (en) * | 2018-12-05 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | A kind of aero-engine and its blade |
-
2019
- 2019-11-21 CN CN201911147569.XA patent/CN111005768A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101592081A (en) * | 2009-06-05 | 2009-12-02 | 中国航空动力机械研究所 | A kind of gas turbine generating engine |
| CN106030261A (en) * | 2013-12-23 | 2016-10-12 | 涡轮梅坎公司 | Turbine engine assembly for measuring the vibrations to which a rotating blade is subjected |
| CN105571867A (en) * | 2016-01-21 | 2016-05-11 | 苏州东菱振动试验仪器有限公司 | Vibration control experiment platform for aero-engine |
| CN107435591A (en) * | 2016-05-27 | 2017-12-05 | 中国航发商用航空发动机有限责任公司 | Aero-Engine Start system, starting method and aero-engine |
| CN109690027A (en) * | 2016-09-08 | 2019-04-26 | 赛峰直升机发动机 | A kind of device for by multi-layer piezoelectric actuator control inlet guide vane |
| CN107013410A (en) * | 2017-06-07 | 2017-08-04 | 曲阜师范大学 | A kind of vertical axis permanent magnet direct wind-driven generator and its control method |
| CN107313876A (en) * | 2017-07-04 | 2017-11-03 | 南京航空航天大学 | Contain fan outside a kind of magnetic suspension for aviation turbofan engine |
| CN108869558A (en) * | 2018-01-12 | 2018-11-23 | 至玥腾风科技投资集团有限公司 | A kind of control method of bearing, rotor-support-foundation system and bearing |
| CN109655270A (en) * | 2018-10-29 | 2019-04-19 | 中国航发贵阳发动机设计研究所 | A kind of installation of cantilever can high tachometric survey torque device |
| CN209398455U (en) * | 2018-12-05 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | A kind of aero-engine and its blade |
| CN109989878A (en) * | 2019-04-28 | 2019-07-09 | 福州大学 | Electromagnetic type wind power generator impeller imbalance compensation device and method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113432789A (en) * | 2021-06-30 | 2021-09-24 | 中国大唐集团科学技术研究院有限公司华东电力试验研究院 | Online testing device and method for dynamic balance weight of rotary machine |
| CN113432789B (en) * | 2021-06-30 | 2024-04-02 | 中国大唐集团科学技术研究院有限公司华东电力试验研究院 | Online testing device and method for dynamic balance weight of rotary machine |
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Application publication date: 20200414 |
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