WO2008055397A1

WO2008055397A1 - Electric aero compressor

Info

Publication number: WO2008055397A1
Application number: PCT/CN2007/000786
Authority: WO
Inventors: Xueshi Yang
Original assignee: Beijing Afillip Air Suspension Train Technology Institute
Priority date: 2006-11-07
Filing date: 2007-03-12
Publication date: 2008-05-15
Also published as: CN1959120A

Abstract

An electric aero compressor is mainly comprised of an aero gas booster (1), a compressed gas duct (2) fixed on the end of the shell of the said aero gas booster (1), a transmission (5) and a motor (6) etc. An outlet flange (3) is provided on the said compressed gas duct (2). A rotating shaft (4) of the aero gas booster (1) is exposed on the outside of the said compressed gas duct (2). One end of the transmission (5) is connected to the rotating shaft (4), the other end is connected to the motor (6). The output power of the motor (6) is controlled by a control system (7). The range of the outlet gas flow rate of the electric aero compressor is 1.0-160 kg/sec. The range of the outlet gas pressure is 2.7-8kg/cm2. The outlet gas temperature is no higher than 100 Celsius degree.

Description

Electric aviation compressor

The invention relates to a type of electric aviation compressor, in particular to a non-combustion type high flow low pressure jet aerodynamic power plant. These products are characterized by small size, light weight, high strength, high jet pressure, high flow rate and low temperature. It is different from the ' turbojet engine' or ' turboprop engine' that generates jet-powered high-temperature combustion blasting. The energy of aircraft combustion equipment of high-temperature combustion blasting is aviation gasoline, which will cause air pollution and noise pollution. There is always a day of depletion of oil. The electric aviation compressor is characterized in that the compressed air jet is formed by sucking air and discharging air, without pollution and low noise, and the low temperature jet does not have a structural temperature rise and the strength is lowered. The electric aviation compressor product is used in the field of high-speed rail transportation powered by ground-based orbiters. Background technique

In the 1960s, after the developed countries of the world proposed the issue of high-speed railways, three technical approaches were developed at the same time: one was the maglev trains in Germany and Japan; the other was the high-speed wheel-rail, the French TGV train; Air cushion car developed in Europe and America. The principle of the air-cushion is the principle of the helicopter. Its power is based on the aviation gas jet engine. Because its high-temperature gas jet flows in the underside of the air-cushion, it does not affect or damage the structure of the air-cushion; However, there are problems of high energy consumption, large noise pollution, and poor operational stability; such problems are difficult to solve in engineering practice, and thus have not been correspondingly developed, and have to be dismissed. China's invention of high-speed orbiter ("air-floating vehicle" patent, ZL99100145. 1) proposed a method to overcome the shortcomings of air-cushion vehicles in order to reduce energy consumption, reduce noise, and maintain stable operation.

At present, the medium and low-altitude aircraft in the world, that is, the power equipment used in the aircraft, are all high-temperature gas turbine jet engines. The high-temperature gas jet of the turbojet engine is injected into the atmosphere, and will not It affects the structure of the aircraft, and its outlet pressure is low, slightly higher than the sea level atmospheric pressure. In terms of jet temperature alone, if such a high-temperature gas jet is injected into a certain structure of the aircraft, such as the chassis of a high-speed orbiter, it will cause serious problems and damage to the chassis structure. The use of electric aviation compressors to avoid high temperature gas damage to the aircraft structure. At the same time, the pressure required for the high-speed orbiter is much higher than the outlet pressure of the turbojet engine. Therefore, it is necessary to design and develop a new series of electric aviation compressors. That is to say, from the following aspects: the temperature requirements of power, export pressure, limited petroleum resources, air pollution, environmental noise, etc., the design and development of a new series of products suitable for aircraft has a large society. Meaning and economic value.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a type of non-combustion, high flow, high pressure, low temperature, cold jet, electric, air compressor for use in high speed orbital aircraft to provide compressed air power, as well as for civil use. Summary of the invention

In order to achieve the above objectives, an aviation compressor of an electric aviation compressor determines an aero-compressor that meets the technical requirements by extensively screening or redesigning existing similar products. Its technical requirements are: light weight, small size, high strength, large flow, good aerodynamic performance, low energy consumption, low noise, and less prone to surge. Its structure includes ducted casing, compressor blades, rotating shaft, three-point support frame, bearings and so on. The tail end of the ducted casing is cut at a certain angle and cut off by a certain angle of the compressed air guiding tube to form a turning combination, so that the compressor shaft protrudes beyond the compressed air guiding tube. A flange is provided at the outlet of the compressed air conduit for coupling to the compressed air inlet flange of the high speed orbiter chassis. The compressor shaft is coupled to one end of the transmission and the other end of the transmission is coupled to the motor. The output power of the motor is regulated and controlled by the control system. The control model and control software are patented by the prior invention patent "Air Float Gas Film Control Method" (Application No.:

200610057524. x) Guaranteed.

Electric aviation compressors are a series of models. Each model is segmented by flow The electric aviation compressor of each flow provides power with different load carrying capacity; the invention of the electric aviation compressor focuses on the compressor not surging, the high power and miniaturization of the system, the high strength, the large flow, the compressed air outlet Low temperature, high pressure, controllability of static control and dynamic control, control stability, etc.; Energy is powered by battery and grid; Battery has large capacity and miniaturization; At the same time, electric aviation compressor has stable multiple starts. Features. The electric aviation compressor draws in air and then discharges the air, which will not pollute the environment, nor cause high temperature damage to the high-speed orbiter chassis structure; its exhaust port is a gap formed by the gas film, and the turbojet engine cannot be heard. The sound of the blast, only the buzz.

The realization of this series of products is the development of electric aviation engines, which lays a good foundation for the development of electric aviation engines for aircrafts once the fuel-powered aircraft has to be grounded once the earth's petroleum resources are exhausted. BRIEF DESCRIPTION OF THE DRAWINGS

Figure 1 Schematic diagram of electric aviation compressor

Figure 2 Block diagram of an electric aviation compressor system

First, develop the components of the aviation compressor that meet the technical requirements of the aviation compressor. The tail end duct casing of the aero-compressor 1 is cut off at a certain angle, and a certain angle with the compressed air guiding tube 2 is fixed by welding to form a turning combination, so that the compressor rotating shaft 4 is exposed outside the compressed air guiding tube 2. . The flange 3 is welded at the outlet of the compressed air conduit for coupling to the compressed air inlet flange of the high speed orbiter chassis. The aero-compressor shaft 4 is further processed, and the compressor shaft 4 is coupled to one end of the transmission 5. The other end of the transmission 5 is coupled to the motor 6. The flow rate of the electric aviation compressor is different for different high speed orbiter operating speeds. After the compressor is selected, the output pressure of the motor 6 is regulated by the control system 7. The control model and control software are already guaranteed by invention patents. The manufacture of the electric aviation compressor hardware was completed by solidifying the various components described above. Carry out running tests and test design parameters; stereotypes; design drawings delivered to the factory plus Main parameters of production:

The compressed air tank of the electric aviation compressor is the chassis of the orbiter. The legged chassis is operated at different speeds. According to the changing air leakage function, the pressure required to generate the gas film is different, so the pressure is controlled. . The minimum pressure of the first type of electric aviation compressor according to the flow segment is the minimum flow rate of 1.0 kg / sec, up to the maximum. The flow rate is 160 kg / sec; the compressed air outlet temperature is not more than 100 degrees Celsius. The electric aviation compressor has multiple parking and starting functions during operation. Control process:

After the power is turned on, the control target parameter, ie the film thickness, is fed back to the control program. The film thickness has a function relationship with the compressed air flow, and the outlet pressure detection parameter is also fed back to the control program. At this point, the control program starts to solve two second-order partial differentials. A distributed parameter control system consisting of equations. When it is judged that the solution result does not coincide with the target parameter, the flow command is changed according to the corresponding function relationship between the thickness and the flow, and according to the relationship between the flow rate and the pressure, the command changes the control parameter at the inner boundary, that is, the pressure. For the new boundary conditions, the distributed parameter control system composed of two second-order partial differential equations is solved again. This is repeated until the film thickness determined by the flow rate satisfies the requirements. When the running speed is at a constant speed, the temperature equations in the two second-order partial differential equations of the distributed parameter control system disappear, and only one pressure equation remains, and the control program is greatly simplified.

For the hardware, the control parameters of the aforementioned control software, that is, the adjustment of the pressure, are achieved by adjusting the motor speed.

Claims

Claim

1. A type of electric aviation compressor; the electric aviation compressor is a series of products, each of the series of electric aviation compressors comprises an aviation compressor 1, and the end of the outer end of the air compressor 1 is fixed a compressed air guiding tube 2, an outlet flange 3 of the compressed air guiding tube 2; a rotating shaft 4 of the aviation compressor 1 exposed outside the compressed air guiding tube 2; The shaft 4 is coupled to one end of the transmission 5; the other end of the transmission 5 is coupled to the motor 6; the output power of the motor 6 is achieved by the control system 7.

2. An electric aviation compressor according to claim 1, characterized in that the outlet flange 3 of the compressed air conduit 2 is coupled to the compressed air inlet flange of the orbiter chassis.

An electric aviation compressor according to claim 1, wherein said aero-compressor shaft 4 is exposed outside said compressed air conduit 2.

4. An electric aviation compressor according to claim 3, wherein said aero-compressor shaft 4 is coupled to said transmission 5 - end.

An electric aviation compressor according to claim 4, wherein the other end of said transmission 5 is coupled to said electric motor 6.

6. An electric aviation compressor according to claim 5, characterized in that the output of said electric motor 6 is effected by said control system 7.

The electric aviation compressor according to claim 1, wherein the outlet air flow rate of the compressed air ranges from 1. 0 kg / sec to 160 kg / sec.

8, Air compressor motor as claimed in claim 1, characterized in that the compressed gas outlet pressure range between 2.7 kg / cm ² ~ 8 kg / cm ^2;

The electric aviation compressor according to claim 1, wherein said compressed air outlet gas temperature does not exceed 100 degrees Celsius.