Background
At present, an accessory case is arranged on an aeroengine, and a power extraction shaft and a gear train thereof are connected with a high-voltage shaft of the aeroengine to extract power for power generation, so that electric equipment on an airplane is supplied.
With the rapid development of artificial intelligence, computer science and communication navigation technology, more and more electric equipment is carried on an aircraft, and the required power is larger and larger, so that more shaft power is required to be extracted from an aeroengine to generate electricity.
Based on the current form of setting up accessory cartridge receiver extraction power on aeroengine and carrying out electricity generation, draw more power from aeroengine and carry out electricity generation, need to thicken the power extraction axle and increase the gear train, this kind of design has following defect:
1) The power extraction shaft of the accessory case is difficult to thicken greatly due to the limitation of the space in the aero-engine, the power consumption requirement of electric equipment on an aircraft is difficult to meet, the size of the accessory case is enlarged due to the increase of the gear train, the overall outline size of the aero-engine is enlarged, the difficulty of installing the aero-engine on the aircraft is increased, and high technical risks exist;
2) The power extraction shaft is thickened and the gear train is increased, so that the loss of power extraction of the accessory case from the aeroengine is increased, the power generation efficiency is reduced, the complexity of the accessory case is increased, the reliability of the accessory case is reduced, the difficulty of maintenance work is increased, and the weight of the aeroengine is increased as a whole;
3) The power extraction shaft is thickened, the gear train is increased, the accessory casing is required to be redesigned, test and examination are carried out, the modification difficulty is high, and the cost is uncontrollable.
The present application has been made in view of the above-described technical drawbacks.
Disclosure of Invention
The application aims to provide an aeroengine with a built-in superconducting generator and a control method thereof, which overcome or alleviate at least one technical defect of the prior art.
The technical scheme of the application is as follows:
one aspect provides an aeroengine with a built-in superconducting starter generator, which comprises the superconducting starter generator and a liquid nitrogen storage tank;
The superconducting starter generator is arranged in an intermediate casing of the aeroengine and comprises a motor rotor, a motor stator and a superconducting coil, wherein the motor rotor is sleeved on a high-voltage shaft of the aeroengine, the motor stator is sleeved on the periphery of the motor rotor and is connected in the intermediate casing through a bracket, an annular containing cavity is formed in the motor stator, liquid helium is filled in the annular containing cavity, and the superconducting coil is arranged in the annular containing cavity;
the liquid nitrogen storage tank is arranged outside the aeroengine;
The outer side and the inner side of the motor stator are provided with annular cooling cavities, and the annular cooling cavities at the outer side are communicated with the annular cooling cavities at the inner side at the front end and the rear end of the motor stator through annular cooling channels;
the annular cooling cavity outside the motor stator is communicated with a liquid nitrogen storage tank through a liquid nitrogen pipeline, and is respectively communicated with a compressor inlet of the aeroengine and a high-pressure turbine guide vane cooling air supply cavity through a gas nitrogen pipeline by utilizing a conversion valve.
Optionally, in the aeroengine with the built-in superconducting generator, an annular partition plate is arranged in an annular cooling cavity at the outer side of the stator of the motor, and the annular partition plate is positioned between the liquid nitrogen pipeline and the gas nitrogen pipeline.
Optionally, in the aeroengine with the built-in superconducting generator, the interface of the liquid nitrogen pipeline in the annular cooling cavity outside the motor stator is located before the interface of the gas nitrogen pipeline in the annular cooling cavity outside the motor stator.
Optionally, in the aeroengine with the built-in superconducting generator, a flow regulating valve is arranged on a liquid nitrogen pipeline.
Another aspect provides a method for controlling an aero-engine with a built-in superconducting starter generator, configured to control the aero-engine with a built-in superconducting starter generator, including:
When the exhaust temperature T6 of the aero-engine is not higher than the safety temperature threshold TS, controlling the conversion valve to enable the gas nitrogen flowing out of the gas nitrogen pipeline to flow to the inlet of the gas compressor;
when the exhaust temperature T6 of the aeroengine is higher than the safety temperature threshold TS, the conversion valve is controlled to enable the gas nitrogen flowing out of the gas nitrogen pipeline to flow to the high-pressure turbine guide vane cooling air supply cavity.
Optionally, in the method for controlling an aeroengine with a built-in superconducting starter generator, the safety temperature threshold TS is set to 800 ℃ to 900 ℃.
The application has at least the following beneficial technical effects:
The utility model provides an aeroengine of built-in superconductive starter generator and control method thereof sets up superconductive starter generator in aeroengine, has carried out integrated design to starter, generator, replaces accessory casket and starter, the generator that set up in aeroengine outside, can reduce the whole outline size of aeroengine, reduce the degree of difficulty that aeroengine installed on the aeroengine, and can reduce aeroengine's weight, and can adopt ripe superconductive motor and wire rod, design repacking degree of difficulty is little, in addition, superconductive starter generator lug connection is on aeroengine's high-voltage shaft, can reduce power transmission loss, can have higher generating efficiency.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only a portion related to the present application is shown in the drawings, and other related portions may refer to a general design.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. As used in this description of the application, the word "comprising" means that the element preceding the word covers the elements listed after the word and equivalents thereof without excluding other associated elements.
In addition, the words used in the description of the present application to indicate directions are merely used to indicate relative directions or positional relationships, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed accordingly. It should also be noted that, unless explicitly stated or limited otherwise, terms such as "mounted," "connected," and the like, as used in the description of the present application, should be construed broadly, and may be, for example, fixedly connected, detachably connected, mechanically connected, electrically connected, directly connected, or indirectly connected through an intermediate medium, as would be understood by one of ordinary skill in the art in view of the specific meaning of the present application.
The superconducting motor has the characteristics of high power density and higher power generation capacity, is applied to a plurality of industrial fields, has mature technology and controllable cost, and based on the characteristics, the embodiment of the application provides an aero-engine with a built-in superconducting generator, which is shown in figure 1 and comprises the superconducting generator 1 and a liquid nitrogen storage tank 2.
The superconductive generator 1 is arranged in an intermediate casing of the aeroengine 3 and comprises a motor rotor 4, a motor stator 5 and a superconductive coil 6, as shown in fig. 2, wherein the motor rotor 4 is sleeved on a high-voltage shaft of the aeroengine 3, the motor stator 5 is sleeved on the periphery of the motor rotor 4, the motor stator is connected in the intermediate casing through a bracket 7, an annular containing cavity is formed in the motor stator 5, liquid helium is filled in the annular containing cavity, and the superconductive coil 6 is arranged in the annular containing cavity.
The aero-engine with the built-in superconducting starter generator disclosed in the embodiment can be provided with the superconducting starter generator 1 in an electric mode when being started, and supplies power to the superconducting starter generator 1, so that the superconducting starter generator 1 drives the high-voltage shaft to rotate, and further the aero-engine 3 is ignited, so that the aero-engine 3 is started, after the aero-engine 3 is started, the superconducting starter generator 1 can be provided in a power generation mode, the high-voltage shaft power of the aero-engine 3 is extracted to generate power, and the power is supplied to electric equipment on an aircraft for use, thereby meeting the power requirement of the electric equipment on the aircraft.
The aero-engine with the built-in superconducting starter generator disclosed by the embodiment above is characterized in that the superconducting starter generator 1 is arranged in the aero-engine 3, the starter and the generator are integrated, an accessory casing arranged outside the aero-engine 3, the starter and the generator are replaced, the overall outline size of the aero-engine 3 can be reduced, the difficulty in installing the aero-engine 3 on an airplane is reduced, the weight of the aero-engine 3 can be reduced, a mature superconducting motor and wires thereof can be adopted, the design and modification difficulty is low, in addition, the superconducting starter generator 1 is directly connected to a high-voltage shaft of the aero-engine 3, the power transmission loss can be reduced, and the power generation efficiency can be higher.
The liquid nitrogen reservoir 2 is arranged outside the aircraft engine 3, in particular connectable to an external casing of the aircraft engine 3.
The outer side and the inner side of the motor stator 5 are provided with annular cooling cavities, and the annular cooling cavities at the outer side and the annular cooling cavities at the inner side are communicated with each other at the front end and the rear end of the motor stator 5 through annular cooling channels.
The annular cooling cavity outside the motor stator 5 is communicated with the liquid nitrogen storage tank 2 through a liquid nitrogen pipeline 8, and is respectively communicated with a gas compressor inlet 13 of the aeroengine 3 and a high-pressure turbine guide vane cooling and air supplying cavity 14 through a gas nitrogen pipeline 9 by utilizing a conversion valve 11, and the liquid nitrogen pipeline 8 and the gas nitrogen pipeline 9 penetrate through the intermediary case.
When the aeroengine with the built-in superconducting generator disclosed by the embodiment works, the liquid nitrogen storage tank 2 can be used for introducing liquid nitrogen into the annular cooling cavities at the outer side and the inner side of the motor stator 5 through the liquid nitrogen pipeline 8, absorbing heat accumulated by liquid helium in the annular containing cavity through heat conduction and cooling the liquid helium of the motor stator 5, so that a low-temperature environment required by superconducting coils 6 is maintained, gasification can occur after the liquid nitrogen absorbs the heat, and then the liquid nitrogen can flow to the air compressor inlet 13 or the high-pressure turbine guide vane cooling air supply cavity 14 through the air nitrogen pipeline 9.
In order to avoid that the liquid nitrogen which is introduced into the annular cooling cavity outside the motor stator 5 through the liquid nitrogen pipeline 8 directly flows to the air compressor inlet 13 or the high-pressure turbine guide vane cooling air supply cavity 14 through the gas nitrogen pipeline 9, an annular partition plate 10 is arranged in the annular cooling cavity outside the motor stator 5, the annular partition plate 10 is positioned between the liquid nitrogen pipeline 8 and the interface of the annular cooling cavity outside the motor stator 5, the interface of the liquid nitrogen pipeline 8 in the annular cooling cavity outside the motor stator 5 can be specifically designed, and the liquid nitrogen which is positioned in front of the interface of the annular cooling cavity outside the motor stator 5 through the gas nitrogen pipeline 9, so that the liquid nitrogen which is introduced into the annular cooling cavity outside the motor stator 5 through the liquid nitrogen pipeline 8 is blocked by the annular partition plate 10, flows to the annular cooling cavity inside the motor stator 5 through the annular cooling channel at the front end of the motor stator 5, flows to the annular cooling cavity outside the motor stator 5 through the gas nitrogen pipeline 9, flows to the air compressor inlet 13 or the high-pressure turbine guide vane cooling air supply cavity 14, and accordingly, heat of the liquid helium can be fully absorbed by the heat of the liquid helium in the annular cooling cavity.
The exhaust temperature T6 of the aeroengine 3 can be obtained through detection, when the exhaust temperature T6 of the aeroengine 3 is higher than a safety temperature threshold TS, it indicates that the high-pressure turbine guide vane is in a severe high-temperature environment, at this time, the conversion valve 11 can be controlled to enable the gas nitrogen flowing out of the gas nitrogen pipeline 9 to flow to the high-pressure turbine guide vane cooling air supply cavity 14, so as to supply the high-pressure turbine guide vane for cooling, assist in reducing the temperature of the high-pressure turbine guide vane, prevent the high-pressure turbine guide vane from being ablated by high temperature, and the safety temperature threshold TS can be set to 800 ℃ to 900 ℃ generally.
The compression work consumed by the compressor to compress the gas is calculated as follows:
;
Wherein,The compression work consumed for the compressor to compress the gas,Is the gas mass flow; for the specific pressure and heat capacity of the gas,For the temperature of the compressor inlet 13,Is the pressure ratio of the air compressor,Is the specific heat ratio of the gas,Is compressor efficiency.
From the above, it can be seen that the ratio of the compressor pressureEfficiency of compressorReducing the temperature of the inlet 13 of the compressor under the condition of constant parametersCompression work consumed by the compressor for compressing gas can be reducedThus, when the exhaust temperature T6 of the aeroengine 3 is not higher than the safety temperature threshold TS, the switching valve 11 is controlled to enable the gas nitrogen flowing out of the gas nitrogen pipeline 9 to flow to the compressor inlet 13 so as to reduce the temperature of the compressor inlet 13Thereby reducing the compression work consumed by the compressor for compressing the gasThereby realizing the effective utilization of the gas nitrogen.
The liquid nitrogen pipeline 8 is provided with the flow regulating valve 12, so that the flow of liquid nitrogen which is introduced into the annular cooling cavity on the outer side and the inner side of the motor stator 5 through the liquid nitrogen pipeline 8 can be regulated in real time according to the heat dissipation requirement of the demand through the flow regulating valve 12, and the flow of the introduced liquid nitrogen can be determined by referring to the following steps:
Calculating the power generation requirement of the superconducting generator 1, specifically, a full-authority digital engine controller FADEC, calculating based on the power consumption requirement of electric equipment on an aircraft, and controlling the superconducting generator 1 to generate power according to the power generation requirement;
Based on the power generation power requirement of the superconducting generator 1, the liquid nitrogen flow requirement of liquid helium cooling in the annular containing cavity of the motor stator 5 is calculated, and specifically, the liquid nitrogen flow requirement can be calculated by a full-authority digital engine controller FADEC, and the opening of a valve 12 is regulated according to the liquid nitrogen flow requirement, so that the flow of liquid nitrogen introduced into the annular cooling cavities at the outer side and the inner side of the motor stator 5 through a liquid nitrogen pipeline 8 is regulated.
The aeroengine with the built-in superconducting starter generator disclosed in the above embodiment can be controlled by referring to the following method:
when the exhaust temperature T6 of the aero-engine 3 is not higher than the safety temperature threshold TS, controlling the switching valve 11 to enable the gas nitrogen flowing out of the gas nitrogen pipeline 9 to flow to the gas compressor inlet 13;
when the exhaust temperature T6 of the aeroengine 3 is higher than the safety temperature threshold TS, the conversion valve 11 is controlled to enable the gas nitrogen flowing out of the gas nitrogen pipeline 9 to flow to the high-pressure turbine guide vane cooling air supply cavity 14, so that the waste of the gas nitrogen can be avoided, the safety and the service life of the aeroengine 3 are ensured, and the effective circulating work of the aeroengine 3 is improved.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.