CN107420350B - Compressor and engine system of aerospace, aviation and ship engines - Google Patents

Compressor and engine system of aerospace, aviation and ship engines Download PDF

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Publication number
CN107420350B
CN107420350B CN201710826217.1A CN201710826217A CN107420350B CN 107420350 B CN107420350 B CN 107420350B CN 201710826217 A CN201710826217 A CN 201710826217A CN 107420350 B CN107420350 B CN 107420350B
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air
transition chamber
static pressure
air inlet
compressor
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CN107420350A (en
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朱振武
陈豪湘
冯哲佳
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Zhu Zhiyin
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Zhu Zhiyin
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/5806—Cooling the drive system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A compressor for space, aviation and ship engines is composed of air inlet channel, air-static pressure transition chamber, pressure air output pipeline and driver. One end of the air inlet channel is an air inlet. The other end of the air inlet channel is an air outlet. The air inlet channel is a tubular channel. The air inlet channel is arranged above the air static pressure transition chamber and is fixedly connected with the air static pressure transition chamber. The air outlet is communicated with the top of the air static pressure transition chamber. The air static pressure transition chamber is movably connected with the pressure air output pipeline. The bottom of the air static pressure transition chamber is provided with a transition chamber air outlet. The air outlet of the transition chamber is communicated with a pressure air output pipeline. The driving device is connected with and drives the aerostatic transition chamber. According to the compressor and the engine system, the air inlet of the whole compressor is arranged into the air inlets of the plurality of tubular channels, and the air inlets with different diameters are separated from each other, so that the problem that compressed air escapes due to large difference of the compressor to the air compression ratio can be effectively avoided.

Description

Compressor and engine system of aerospace, aviation and ship engines
Technical Field
The application relates to an air compression system and an engine system, in particular to a cyclone type air inlet compressor and an engine system and a use method thereof, and belongs to the field of mechanical power.
Background
Compressor (compressor): components in gas turbine engines that utilize high speed rotating blades to apply work to air to increase the air pressure. The air compressors can be divided into two main types, namely centrifugal type air compressors and axial type air compressors, wherein the centrifugal type air compressors consist of air guide wheels, impellers, diffusers and the like. Air enters the air compressor from the air inlet channel and enters the impeller through the guide of the air guide wheel rotating together with the impeller by the air compressor. Under the action of the high-speed rotating impeller, air is thrown to the outer edge of the impeller by centrifugal force from the center of the impeller, the pressure is gradually increased, the speed of the air flowing out of the impeller is reduced after the air enters the diffuser, the pressure is increased again, and finally the air flows out of the compressor through the air outlet pipe. The axial compressor air mainly flows in the axial compressor along the axial direction. It consists of two parts of rotor (also called running wheel) and stator (also called rectifier). The single-stage supercharging ratio is small, and a multistage structure is generally adopted to obtain a higher supercharging ratio. After the air is pressurized step by step in the compressor, the density and temperature are also increased step by step.
When the pressure ratio of the air compressor is increased to a certain value at a certain rotating speed, the air compressor enters an unstable working state, surge is easy to occur, the whole system generates low-frequency large-amplitude air flow axial pulsation, and even the phenomenon of instantaneous air flow backflow occurs. Compressor surge can lead to blade breakage, structural damage, excessive temperature of the combustion chamber, and engine stall.
A conventional low bypass ratio turbofan engine is employed. The turbofan engine has an inner culvert and an outer culvert, and the outer culvert fan is positioned in the air inlet channel of the aircraft and can work in transonic or supersonic speed flight, so that the turbofan engine has the advantage of high efficiency compared with a propeller engine. Turbofan engines have higher propulsive efficiency and greater thrust than turbojet engines. Moreover, the adoption of the turbofan engine can improve the heat efficiency without adversely affecting the propulsion efficiency. And the cold air of the outer duct can form a cold air film at the turbine part, so that the damage of high-temperature gas in front of the turbine to the turbine is reduced. And the outer duct air is mixed with the gas after the turbine, which is beneficial to increasing the thrust and reducing the noise.
In the prior art, most compressors are axial flow compressors. The air flow direction in the axial-flow compressor is approximately parallel to the working axle, and the advantage of adopting the compressor is that the air flow makes the compressor easy to organize multi-stage compression structurally, and the total supercharging pressure ratio of the compressor is higher with the lower whole pressure ratio of each stage. The pressure ratio of the pressurizing of each stage is between 1.15 and 1.35, so that the air does not need to change direction sharply when flowing through each stage of vane passage, and the flow loss is reduced, thereby the efficiency of the compressor is high. In particular, when the flow rate is high, the axial-flow compressor is easier to obtain higher compressor efficiency than other types of compressors, and the multistage axial-flow compressor also has the advantages of high flow rate, high efficiency and small windward side.
The drum-disc rotor is adopted, the bending rigidity of the drum-type rotor and the capability of the disc rotor for bearing large centrifugal load are both considered, in particular to the hybrid drum-disc rotor, and the rotor structure in the form has the advantages of the detachable rotor and the non-detachable rotor, has low requirements on manufacturing technology and technology, provides a wide selection space for a designer, and is convenient to check, maintain and replace.
The rotor blade adopts controllable diffusion blade profile, and the thickness and curvature of the blade profile are optimally distributed. Basically eliminates separation of boundary layers, increases the effective flow area of the compressor and improves the efficiency of the compressor. The chord of the blade profile is wider, thicker in front and back, and has better corrosion resistance and impact resistance. The tip over-bending blade body is used for reducing secondary loss caused by the surface layers of the two end walls of the blade, so that the tip end and the root of the blade body are specially bent around the front and the back. The new generation of high-efficiency blades further improves the stage efficiency and the characteristics of the compressor.
Such compressors have the following drawbacks: 1. because the blades of the compressor are longer, and the curvatures of the positions of the blades are different, the compression power of the air entering the positions of the blades of the whole compressor is different, the compression rate of the air passing through the blades is different, the air compression rate of the edge (periphery) of the blade is high, the air compression rate of the center (close to the center) of the blade is low, the air at the edge (periphery) of the blade is compressed and then moves to the center (close to the center) of the blade, and the air escapes from the center of the blade to the compressor, so that the actual efficiency of the compressor is low; 2. because the blades of the air compressor are longer, the surge is obvious, so that the unit generates strong vibration, the thrust tile is overloaded, and the damage of the air compressor can be caused in a short time; 3. between the rotor and stator of the compressor, such as between the top ends of rotor blades and a casing, between the inner ring of the rectifier and the rotor drum, and between the front and rear end surfaces of the rotor and the casing, there is leakage loss, which seriously affects the efficiency of the compressor.
Disclosure of Invention
Aiming at the problems in the prior art, the application provides the air compressor and the engine system, wherein the air inlet of the whole air compressor is provided with a plurality of air inlets with tubular channels, and the air inlets with different diameters are separated from each other independently, so that the problem that compressed air escapes due to large difference of the air compressor to the air compression rate can be effectively avoided; in addition, because the air inlet channel is a tubular channel, surge can be effectively avoided; the air collecting device is arranged at the connecting position of the components and is utilized, so that the problem of air leakage can be effectively solved.
According to a first embodiment of the present application, a compressor is provided.
The compressor comprises an air inlet channel, an air static pressure transition chamber, a pressure air output pipeline and a driving device. One end of the air inlet channel is an air inlet. The other end of the air inlet channel is an air outlet. The air inlet channel is a tubular channel. The air inlet channel is arranged above the air static pressure transition chamber and is fixedly connected with the air static pressure transition chamber. The air outlet is communicated with the top of the air static pressure transition chamber. The air static pressure transition chamber is movably connected with the pressure air output pipeline. The bottom of the air static pressure transition chamber is provided with a transition chamber air outlet. The air outlet of the transition chamber is communicated with a pressure air output pipeline. The driving device is connected with and drives the aerostatic transition chamber. Preferably, the driving device is a motor, preferably a torque hollow high-speed motor, which is sleeved on the periphery of the aerostatic transition chamber and drives the aerostatic transition chamber to rotate (rotate).
Preferably, the compressor further comprises a cooling device. The cooling device comprises a heat exchange condensing pipe and a cooling device shell. The cooling device shell wraps the air static pressure transition chamber, the front end of the pressure air output pipeline and the periphery of the outer side of the driving device. The heat exchange condenser tube is arranged in the shell of the cooling device. The shell of the cooling device is provided with a water inlet of a heat exchange condensing pipe and a water outlet of the heat exchange condensing pipe. The water inlet end of the heat exchange condensing pipe is connected with the water inlet of the heat exchange condensing pipe. The water outlet end of the heat exchange condensing pipe is connected with the water outlet of the heat exchange condensing pipe.
Preferably, the water inlet of the heat exchange condensing pipe is arranged at one end of the cooling device shell close to the air outlet of the transition chamber. The water outlet of the heat exchange condensing pipe is arranged at one end of the cooling device shell, which is close to the upper air outlet of the air inlet channel.
Preferably, 1 to 50 groups of air inlets, preferably 2 to 20 groups of air inlets, more preferably 3 to 10 groups of air inlets are arranged above the air static pressure transition chamber.
Preferably, each group of inlet channels comprises 1-50 inlet channels, preferably 2-20 inlet channels, more preferably 3-10 inlet channels. One end of each air inlet channel is independently an air inlet, and the other end of each air inlet channel is independently an air outlet.
Preferably, the top of the aerostatic transition chamber is circular.
Preferably, the air inlet direction of the air inlet channel is on the diameter or radial direction of the top of the air static pressure transition chamber. The air inlet channels are uniformly distributed on the periphery of the top of the air static pressure transition chamber.
Preferably, the air inlets in each group of air inlets are arranged from inside to outside along the diameter direction of the top of the air static pressure transition chamber.
Preferably, the distances between the air inlets of adjacent air inlets on the same circumference at the top of the air static pressure transition chamber are the same.
Preferably, each air inlet channel is arranged in an arc shape along the top circumference of the aerostatic transition chamber.
In the application, the air inlet channel is obliquely arranged above the air static pressure transition chamber.
Preferably, the included angle between the air inlet channel and the cross section of the top of the aerostatic transition chamber is 1-90 degrees, preferably 5-75 degrees, more preferably 10-60 degrees, and even more preferably 15-45 degrees.
In the present application, the angle between the air inlet and the cross section of the top of the aerostatic transition chamber is 1-90 degrees, preferably 15-85 degrees, more preferably 30-80 degrees, and even more preferably 45-75 degrees.
In the present application, the cross-sectional areas of all the air inlets are all the same, all different or partially the same.
In the present application, the cross-sectional areas of all the air outlets are all the same, all different or partially the same.
Preferably, the cross sections of the air outlets on the same circumference at the top of the air static pressure transition chamber are the same, and the cross sections of the air outlets on different circumferences at the top of the air static pressure transition chamber are different.
Preferably, the cross-sectional area of the air outlet close to the center of the top of the air static pressure transition chamber is smaller than the cross-sectional area of the air outlet far from the center of the top of the air static pressure transition chamber.
Preferably, the aerostatic transition chamber is connected to the pressurized air outlet line by means of bearings.
Preferably, the drive device is a motor, preferably a torque hollow high-speed motor.
Preferably, the air outlet is provided with an air inlet control valve.
Preferably, the cooling device shell is also provided with a condensed water outlet valve.
Preferably, the cooling device shell is also provided with an air outlet valve.
According to a second embodiment of the present application, an engine system is provided.
An engine system comprising a compressor and an engine as described in the first embodiment. The engine is provided with an engine intake. The end of the pressure air output pipeline is connected with an air inlet of the engine.
Preferably, the engine is a ramjet engine.
Preferably, the engine system further comprises an aerostatic chamber. The tail end of the pressure air output pipeline is connected with an air inlet of the air static pressure chamber, and an air outlet of the air static pressure chamber is connected with an air inlet of the engine.
Preferably, the engine system is a lattice full informatization engine system. The lattice full informatization engine system comprises n compressors and engines. The tail ends of the pressure air output pipelines of the n compressors are connected with an air inlet of the engine. Preferably n is 2 to 200, preferably 5 to 150, more preferably 10 to 100.
According to a third embodiment of the present application, a method of compressing air in a compressor is provided.
A method of compressing air by a compressor or using the compressor of the first embodiment, the method comprising the steps of:
1) Starting a driving device;
2) The driving device drives the air static pressure transition chamber to rotate, air enters the air inlet channel from the air inlet of the air inlet channel, flows along the air inlet channel and is compressed, and enters the air static pressure transition chamber from the air outlet of the air inlet channel;
3) The compressed air enters a pressure air output pipeline through an air static pressure transition chamber;
4) In the working process of the driving device, the cooling device cools the driving device, and water generated by cooling is discharged from the condensed water outlet valve; and the air leakage at the joint of the air static pressure transition chamber and the pressure air output pipeline is cooled in the cooling device, cooling water is discharged from the condensed water outlet valve, and cooling air is discharged from the air outlet valve.
Preferably, the method further comprises:
5) The compressed air enters the air static pressure chamber from the pressure air output pipeline and is then conveyed to the air inlet of the engine.
According to a fourth embodiment of the present application there is provided a use of a compressor or engine system.
The compressor or engine system of the application is used for equipment in the aerospace or navigation field, and the compressor can also be used for military or civil engines according to the requirement. The system of the application is used in the fields of aerospace, aviation or navigation and the like. For example: the system of the application is used for equipment such as airplanes, ships and the like.
In the application, the air inlet channel is a tubular channel, only one end is provided with an air inlet, the other end is provided with an air outlet, and other positions are of a closed structure. The design of a total air inlet in the prior art is changed, the air inlet is changed into a plurality of air inlets, and each air inlet is independently provided with an air inlet and an air outlet. The plurality of air inlets can be divided into a plurality of groups, that is, a plurality of independent air inlets are arranged at the upper part (or the top part) of the air static pressure transition chamber as a group. And the arrangement direction of each air inlet channel is along the top circumference of the aerostatic transition chamber. According to the kinematic principle and the flow direction characteristics of wind, the direction of the air inlet of each air inlet channel is on the diameter or radial direction of the top of the air static pressure transition chamber, so that air (or wind) can enter the air inlet channel more smoothly. The air inlet channels are uniformly distributed on the periphery of the top of the air static pressure transition chamber, which means that: the air inlet channel is arranged above the top of the air static pressure transition chamber and is close to the outer side, the center of the top of the air static pressure transition chamber is a flat plate or a cylinder with a hemispherical top, and the design can play a role in guiding air so that wind enters the air inlet channel. A group of air inlet channels may comprise one or more individual air inlet channels, if a plurality of air inlet channels are included, which are arranged from inside to outside along the diameter of the top of the aerostatic transition chamber, that is to say the lengths of the air inlet channels are different, the length of the air inlet channel closer to the outer side of the diameter of the top of the aerostatic transition chamber is longer, and the length of the air inlet channel closer to the inner side of the diameter of the top of the aerostatic transition chamber is shorter. Preferably, one or more air inlets can be arranged on the same circumference of the top of the aerostatic transition chamber, and the distances between adjacent air inlets are the same on the same circumference. That is, the multiple groups of air inlets are uniformly distributed on the top of the air static pressure transition chamber, and the air inlets on the same circumference are uniformly distributed on the top of the air static pressure transition chamber. Each air inlet channel is arranged in an arc shape along the top circumference direction of the air static pressure transition chamber, namely the direction of the air inlet channel is arc-shaped, and air enters the air static pressure transition chamber along with the rotation of the air static pressure transition chamber in the air inlet channel due to the circular motion of the air static pressure transition chamber, so that the air compression effect is improved. The air compressor cuts the whole air inlet into a plurality of independent small air inlets, and air enters the air inlet channel from different air inlets (air inlets) on different diameters or radial directions of the air static pressure transition chamber and is conveyed to the air static pressure transition chamber, so that the problem that air compression power or air compression rate is different due to different diameters of the air inlets is avoided. Because the air inlet is cut into a plurality of independent small air inlets, the diameter (or the sectional area) of the single air inlet is smaller, and the difference of air compression power or air compression rate at different positions can be greatly reduced because the difference of the positions of air entering the air compressor is smaller.
In the application, the air inlet channel is obliquely arranged above the air static pressure transition chamber, and the air outlet of the air inlet channel is communicated with the air static pressure transition chamber because the air inlet of the air inlet channel is arranged above the air static pressure transition chamber, so that the air in the air inlet channel smoothly flows to the air static pressure transition chamber. The included angle (or inclination angle) between the air inlet channel and the top of the air static pressure transition chamber is not limited, and the air inlet channel and the top of the air static pressure transition chamber are designed according to actual needs. The included angle between the air inlet and the top of the air static pressure transition chamber is not limited, and the air static pressure transition chamber is designed according to actual needs.
In the present application, the direction of the air inlet refers to the direction of the plane in which the air inlet is located. The included angle between the air inlet and the top of the air static pressure transition chamber is the included angle between the plane of the air inlet and the plane of the top of the air static pressure transition chamber.
In the present application, the cross-sectional areas of all the air inlets (several) are all the same, all different or partially the same. In general, in order to make the air compression ratio the same, the cross-sectional areas of all the air inlets (several) are the same.
In the present application, the cross-sectional areas of all the air outlets are all the same, all different or partially the same. Preferably, the cross sections of the air outlets on the same circumference at the top of the aerostatic transition chamber are the same, and the cross sections of the air outlets on different circumferences at the top of the aerostatic transition chamber are different. Because the air inlet channel at the top of the air static pressure transition chamber is arranged on different circumferences, the diameters of the circumferences are different, the lengths of the air inlet channels are different, meanwhile, the radians of the air inlet channels are also different, and the sectional areas of the air outlets are set to be different sizes, so that the air pressure of the air entering the air static pressure transition chamber from each air outlet is ensured to be the same, the pressure difference of the air entering the inner hole of the air static pressure transition chamber is overcome, and the escape of compressed air is avoided. The sectional areas of the air outlets on the circumferences with different diameters are designed according to actual requirements; generally, the smaller the cross-sectional area of the air outlet near the center of the top of the air static pressure transition chamber, the larger the cross-sectional area of the air outlet far from the center of the top of the air static pressure transition chamber. The specific design requirements are as follows: the air pressure of each air outlet entering the air static pressure transition chamber is ensured to be the same. The air pressure of each air outlet entering the air static pressure transition chamber can be changed by changing the sectional area of the air outlet. Generally, the cross-sectional area of the air outlet near the center of the top of the air static pressure transition chamber is smaller than the cross-sectional area of the air outlet far from the center of the top of the air static pressure transition chamber.
In the present application, the air inlet duct is fixedly connected with the aerostatic transition chamber, for example, by welding, bonding, or the like. The air inlet channel is communicated with the air static pressure transition chamber through an air outlet. The aerostatic transition chamber is movably connected with the pressure air output pipeline, for example, through a bearing. In the operation process, the driving device drives the air static pressure transition chamber to rotate, and the air inlet channel is fixedly connected with the air static pressure transition chamber, so that the air inlet channel and the air static pressure transition chamber synchronously rotate, the pressure air output pipeline is kept static and is relatively static with the driving device shell, and the air static pressure transition chamber does not rotate. The air inlet rotates to enable air to enter the air inlet from the air inlet to be compressed, and then enter the air static pressure transition chamber.
In the present application, the cooling device functions as: because the driving device continuously outputs power, and the air static pressure transition chamber and the pressure air output pipeline move relatively, heat is generated at the connecting position of the air static pressure transition chamber and the pressure air output pipeline, and the cooling device cools the connecting positions of the driving device, the air static pressure transition chamber and the pressure air output pipeline, the whole compressor and the system are ensured to work normally for a long time. Meanwhile, due to air compression, after the heat exchange condensation pipe in the cooling device is contacted with air outside the condensation pipe, water is generated, and the water is collected and discharged through a condensed water outlet valve, so that the condensed water can be used as a water source of the whole engine system for other purposes; for example, into a heat exchange condenser tube as a cooling medium. Preferably, the cooling device is a sealing device, and is wrapped around the air static pressure transition chamber, the front end of the pressure air output pipeline and the outer side of the driving device, so that air leakage at the connection position of the air static pressure transition chamber and the pressure air output pipeline directly enters the cooling device, condensed water and air (or air) are formed after the air leakage or air leakage exchanges heat in the cooling device, the condensed water is also discharged through a condensed water outlet valve, and the air (or air) is discharged from an air outlet valve on the shell of the cooling device. The water inlet of the heat exchange condensation pipe is arranged at one end of the cooling device shell, which is close to the air outlet of the transition chamber, and the water outlet of the heat exchange condensation pipe is arranged at one end of the cooling device shell, which is close to the air outlet of the air inlet channel, and the purpose of the water outlet of the heat exchange condensation pipe is as follows: because the air enters the air static pressure transition chamber after being compressed by the air inlet channel and then enters the pressure air output pipeline, the design ensures that the flow direction of condensed water is from the air outlet close to the transition chamber to the air outlet close to the upper air outlet of the air inlet channel; thus, the whole flow direction of the condensed water is opposite to the flow direction of the air (or the compressed air), convection is formed, and the cooling effect is increased.
When the compressor is used, air independently enters respective air inlets from a plurality of air inlets on different circumference diameters or radial directions, and then enters the air static pressure transition chamber from respective independent air outlets along the air inlets; by controlling the sectional area of the air outlets, the air pressure of the air outlets entering the air static pressure transition chamber is ensured to be the same, and the effective working efficiency of the air compressor is improved while the air escape is placed.
Compared with the prior art, the device and the system have the following beneficial technical effects:
1. the air compressor cuts the whole air inlet into a plurality of independent small air inlets, and air enters the air inlet channel from different air inlets (air inlets) on different diameters or radial directions of the air static pressure transition chamber and is conveyed to the air static pressure transition chamber, so that the problem of different air compression power or air compression rate caused by different diameters of the air inlets is avoided;
2. the air inlet is cut into a plurality of independent small air inlets, the diameter (or the sectional area) of each air inlet is smaller, and the difference of air compression power or air compression rate at different positions can be greatly reduced due to smaller difference of the positions of air entering the air compressor;
3. the compressor of the application can effectively avoid surging because the air inlet channel is a tubular channel;
4. the air compressor is provided with the cooling device, so that the air leakage of the device can be realized while the cooling effect is achieved, and the air leakage problem can be effectively solved by utilizing the cooling device.
Drawings
Fig. 1 is a front view of a compressor according to the present application;
FIG. 2 is a top view of a compressor according to the present application;
FIG. 3 is a cross-sectional view taken at the A-A position of FIG. 2;
FIG. 4 is a schematic view of a compressor with a cooling device according to the present application;
FIG. 5 is a schematic diagram of an engine system according to the present disclosure;
FIG. 6 is a schematic diagram of a lattice full informatization engine system according to the present application;
FIG. 7 is a front view of a compressor having two sets of inlet ports according to the present application;
FIG. 8 is a top view of a compressor having two sets of inlet ports according to the present application;
FIG. 9 is a top view of a compressor having three inlet ports according to the present application;
fig. 10 is a front view showing a three-dimensional structure of a compressor according to the present application;
FIG. 11 is a schematic perspective view of a compressor according to the present application;
fig. 12 is a front view showing another design of a compressor according to the present application;
fig. 13 is a front view showing a third design of a compressor according to the present application;
fig. 14 is a schematic perspective view of a compressor according to the present application.
Reference numerals:
1: an air inlet channel; 101: an air inlet; 102: an air outlet; 103: an inlet control valve; 2: an aerostatic transition chamber; 201: a transition chamber air outlet; 3: a pressurized air output duct; 4: a driving device; 5: a cooling device; 501: a heat exchange condenser tube; 502: a cooling device housing; 50201: a water inlet of a heat exchange condensing pipe; 50202: a water outlet of the heat exchange condensing pipe; 6: a bearing; 7: a condensed water outlet valve; 8: an air outlet valve; 9: an engine; 901: an engine intake; 10: an aerostatic chamber.
Detailed Description
According to a first embodiment of the present application, a compressor is provided.
The compressor comprises an air inlet channel 1, an air static pressure transition chamber 2, a pressure air output pipeline 3 and a driving device 4. One end of the intake duct 1 is an intake port 101. The other end of the air inlet channel 1 is an air outlet 102. The air inlet channel 1 is a tubular channel. The air inlet channel 1 is arranged above the air static pressure transition chamber 2 and is fixedly connected with the air static pressure transition chamber 2. The air outlet 102 communicates with the top of the aerostatic transition chamber 2. The air static pressure transition chamber 2 is movably connected with the pressure air output pipeline 3. The bottom of the aerostatic transition chamber 2 is provided with a transition chamber air outlet 201. The transition chamber outlet 201 communicates with the pressurized air outlet conduit 3. The drive device 4 is connected to and drives the aerostatic transition chamber 2.
Preferably, the compressor further comprises a cooling device 5. The cooling device 5 includes a heat exchange condenser pipe 501 and a cooling device housing 502. The cooling device housing 502 is wrapped around the aerostatic transition chamber 2, the front end of the pressure air output pipe 3 and the outside of the driving device 4. The heat exchange condenser pipe 501 is provided in the cooling device housing 502. The cooling device housing 502 is provided with a heat exchange condenser water inlet 50201 and a heat exchange condenser water outlet 50202. The water inlet end of the heat exchange condenser pipe 501 is connected with a water inlet 50201 of the heat exchange condenser pipe. The water outlet end of the heat exchange condenser pipe 501 is connected with a heat exchange condenser pipe water outlet 50202.
Preferably, the heat exchange condenser water inlet 50201 is disposed at an end of the cooling device housing 502 adjacent to the transition chamber air outlet 201. The heat exchange condenser pipe water outlet 50202 is arranged at one end of the cooling device housing 502 near the air outlet 102 on the air inlet channel 1.
Preferably, 1-50 groups of air inlets 1, preferably 2-20 groups of air inlets 1, more preferably 3-10 groups of air inlets 1 are arranged above the air static pressure transition chamber 2.
Preferably, each group of inlet channels 1 comprises 1-50 inlet channels 1, preferably 2-20 inlet channels 1, more preferably 3-10 inlet channels 1. One end of each air inlet channel 1 is independently provided with an air inlet 101, and the other end of each air inlet channel 1 is independently provided with an air outlet 102.
Preferably, the top of the aerostatic transition chamber 2 is circular.
Preferably, the direction of the air inlet 101 of the air inlet channel 1 is on the diameter or radial direction of the top of the aerostatic transition chamber 2. The air inlet channels 1 are uniformly distributed on the periphery of the top of the air static pressure transition chamber 2.
Preferably, the air inlets 1 in each group of air inlets 1 are arranged from inside to outside along the diameter direction of the top of the air static pressure transition chamber 2.
Preferably, the distances between the air inlets 101 of adjacent air inlets 1 on the same circumference on the top of the aerostatic transition chamber 2 are the same.
Preferably, each air inlet channel 1 is arranged in an arc shape along the top circumference of the aerostatic transition chamber 2.
In the present application, the air intake duct 1 is disposed obliquely above the aerostatic transition chamber 2.
Preferably, the included angle between the air inlet channel 1 and the cross section of the top of the aerostatic transition chamber 2 is 1-90 degrees, preferably 5-75 degrees, more preferably 10-60 degrees, still more preferably 15-45 degrees.
In the present application, the angle between the air inlet 101 and the cross section of the top of the aerostatic transition chamber 2 is 1-90 degrees, preferably 15-85 degrees, more preferably 30-80 degrees, still more preferably 45-75 degrees.
In the present application, the sectional areas of all the air inlets 101 are all the same, all different, or partially the same.
In the present application, the cross-sectional areas of all of the air outlets 102 are all the same, all different, or partially the same.
Preferably, the cross-sectional areas of the air outlets 102 on the same circumference at the top of the aerostatic transition chamber 2 are the same, and the cross-sectional areas of the air outlets 102 on different circumferences at the top of the aerostatic transition chamber 2 are different.
Preferably, the cross-sectional area of the air outlet 102 near the center of the top of the air static pressure transition chamber 2 is smaller than the cross-sectional area of the air outlet 102 far from the center of the top of the air static pressure transition chamber 2.
Preferably, the aerostatic transition chamber 2 is connected to the pressurized air outlet line 3 via a bearing 6.
Preferably, the driving device 4 is a motor, preferably a torque hollow high-speed motor.
Preferably, an inlet control valve 103 is provided at the outlet 102.
Preferably, the cooling device housing 502 is further provided with a condensed water outlet valve 7.
Preferably, the cooling device housing 502 is further provided with an air outlet valve 8.
According to a second embodiment of the present application, an engine system is provided.
An engine system comprising a compressor and an engine 9 as described in the first embodiment. The engine 9 is provided with an engine intake 901. The end of the pressurized air output pipe 3 is connected to an engine intake 901.
Preferably, the engine 9 is a ramjet engine.
Preferably, the engine system further comprises an aerostatic chamber 10. The end of the pressure air output pipeline 3 is connected with an air inlet of the air static pressure chamber 10, and an air outlet of the air static pressure chamber 10 is connected with an engine air inlet 901.
Preferably, the engine system is a lattice full informatization engine system, the lattice full informatization engine system comprises n compressors and an engine 9, and the tail end of a pressure air output pipeline 3 of the n compressors is connected with an engine air inlet 901. Preferably n is 2 to 200, preferably 5 to 150, more preferably 10 to 100.
According to a third embodiment of the present application, a method of compressing air in a compressor is provided.
A method of compressing air by a compressor or using the compressor of the first embodiment, the method comprising the steps of:
1) Starting the driving device 4;
2) The driving device 4 drives the air static pressure transition chamber 2 to rotate, air enters the air inlet channel 1 from the air inlet 101 of the air inlet channel 1, flows along the air inlet channel 1 and is compressed, and enters the air static pressure transition chamber 2 from the air outlet 102 of the air inlet channel 1;
3) The compressed air enters a pressure air output pipeline 3 through an air static pressure transition chamber 2;
4) In the working process of the driving device 4, the cooling device 5 cools the driving device 4, and water generated by cooling is discharged from the condensed water outlet valve 7; the air leakage at the joint of the air static pressure transition chamber 2 and the pressure air output pipeline 3 is cooled in the cooling device 5, cooling water is discharged from the condensed water outlet valve 7, and cooling air is discharged from the air outlet valve 8.
Preferably, the method further comprises:
5) The compressed air enters the air static pressure chamber 10 from the pressure air output pipe 3 and is then sent to the engine air inlet 901.
Example 1
As shown in fig. 1-3 and 8, the compressor comprises an air inlet channel 1, an air static pressure transition chamber 2, a pressure air output pipeline 3 and a driving device 4. And 3 groups of air inlet channels 1 are arranged above the air static pressure transition chamber 2, and each group of air inlet channels 1 comprises 4 air inlet channels 1. One end of the intake duct 1 is an intake port 101. The other end of the air inlet channel 1 is an air outlet 102. The air inlet channel 1 is a tubular channel. The air inlet channel 1 is arranged above the air static pressure transition chamber 2 and is fixedly connected with the air static pressure transition chamber 2. The air outlet 102 communicates with the top of the aerostatic transition chamber 2. The aerostatic transition chamber 2 is connected with the pressure air output pipeline 3 through a bearing 6. The bottom of the aerostatic transition chamber 2 is provided with a transition chamber air outlet 201. The transition chamber outlet 201 communicates with the pressurized air outlet conduit 3. The drive device 4 is connected to and drives the aerostatic transition chamber 2.
The top of the aerostatic transition chamber 2 is circular. The direction of the air inlet 101 of the air inlet channel 1 is on the diameter or radial direction of the top of the air static pressure transition chamber 2. The air inlet channels 1 are uniformly distributed on the periphery of the top of the air static pressure transition chamber 2. The air inlets 1 in each group of air inlets 1 are arranged from inside to outside along the diameter direction of the top of the air static pressure transition chamber 2. The distances between the air inlets 101 of the adjacent air inlets 1 on the same circumference at the top of the air static pressure transition chamber 2 are the same. Each air inlet channel 1 is arranged in an arc shape along the top circumference direction of the aerostatic transition chamber 2. The air inlet channel 1 is obliquely arranged above the air static pressure transition chamber 2, and an included angle between the air inlet channel 1 and the top of the air static pressure transition chamber 2 is 10 degrees. The angle between the air inlet 101 and the top of the aerostatic transition chamber 2 is 80 degrees.
The cross-sectional areas of all the air inlets 101 are the same, the cross-sectional areas of the air outlets 102 on the same circumference at the top of the aerostatic transition chamber 2 are the same, and the cross-sectional areas of the air outlets 102 on different circumferences at the top of the aerostatic transition chamber 2 are different. The cross-sectional area of the air outlet 102 near the center of the top of the air static pressure transition chamber 2 is smaller than the cross-sectional area of the air outlet 102 far from the center of the top of the air static pressure transition chamber 2.
The driving device 4 is a torque hollow high-speed motor.
Example 2
As shown in fig. 4, example 1 is repeated except that the apparatus further comprises a cooling device 5. The cooling device 5 includes a heat exchange condenser pipe 501 and a cooling device housing 502. The cooling device housing 502 is wrapped around the air static pressure transition chamber 2, the front end of the pressure air output pipeline 3 and the outer side of the torque hollow high-speed motor 4. The heat exchange condenser pipe 501 is provided in the cooling device housing 502. The cooling device housing 502 is provided with a heat exchange condenser water inlet 50201 and a heat exchange condenser water outlet 50202. The water inlet end of the heat exchange condenser pipe 501 is connected with a water inlet 50201 of the heat exchange condenser pipe. The water outlet end of the heat exchange condenser pipe 501 is connected with a heat exchange condenser pipe water outlet 50202. The heat exchange condenser water inlet 50201 is disposed at one end of the transition chamber air outlet 201 of the cooling device housing 502. The heat exchange condenser pipe water outlet 50202 is arranged at one end of the cooling device housing 502 near the air outlet 102 on the air inlet channel 1.
Example 3
Example 2 was repeated except that the inlet duct 1 was inclined above the aerostatic transition chamber 2, and the angle between the inlet duct 1 and the top of the aerostatic transition chamber 2 was 20 degrees. The angle between the air inlet 101 and the top of the aerostatic transition chamber 2 is 85 degrees.
Example 4
Example 2 was repeated except that the inlet duct 1 was inclined above the aerostatic transition chamber 2, and the angle between the inlet duct 1 and the top of the aerostatic transition chamber 2 was 30 degrees. The angle between the air inlet 101 and the top of the aerostatic transition chamber 2 is 60 degrees.
Example 5
Example 2 was repeated except that the cross-sectional areas of all the air inlets 101 were all the same and the cross-sectional areas of all the air outlets 102 were also all the same.
Example 6
Example 2 was repeated except that the cooling device case 502 was further provided with a condensate outlet valve 7, and the cooling device case 502 was further provided with an air outlet valve 8.
Example 7
As shown in fig. 6 and 7, example 2 was repeated except that the compressor was provided with two sets of air intake passages.
Example 8
As shown in fig. 5, an engine system includes the compressor and the engine 9 described in embodiment 2. The engine 9 is provided with an engine intake 901. The end of the pressurized air output pipe 3 is connected to an engine intake 901. The engine 9 is a ramjet engine.
Example 9
Example 8 is repeated except that the engine system further includes an aerostatic chamber 10. The end of the pressure air output pipeline 3 is connected with an air inlet of the air static pressure chamber 10, and an air outlet of the air static pressure chamber 10 is connected with an engine air inlet 901.
Example 10
Example 9 was repeated except that the engine system was a lattice full informatization engine system including 50 compressors and an engine 9, and the ends of the pressure air output pipes 3 of the 50 compressors were connected to the engine intake port 901.
Use example 1
A method of using the compressor described in example 2, the method comprising the steps of:
1) Starting the torque hollow high-speed motor 4;
2) The torque hollow high-speed motor 4 drives the air static pressure transition chamber 2 and rotates, air enters the air inlet channel 1 from the air inlet 101 of the air inlet channel 1, flows along the air inlet channel 1 and is compressed, and enters the air static pressure transition chamber 2 from the air outlet 102 of the air inlet channel 1;
3) The compressed air enters a pressure air output pipeline 3 through an air static pressure transition chamber 2;
4) In the working process of the moment hollow high-speed motor 4, the cooling device 5 cools the moment hollow high-speed motor 4, and water generated by cooling is discharged from the condensed water outlet valve 7; the air leakage at the joint of the air static pressure transition chamber 2 and the pressure air output pipeline 3 is cooled in the cooling device 5, cooling water is discharged from the condensed water outlet valve 7, and cooling air is discharged from the air outlet valve 8;
5) The compressed air enters the air static pressure chamber 10 from the pressure air output pipe 3 and is then sent to the engine air inlet 901.
Use of example 2
The procedure of example 1 was repeated using the compressor procedure described in example 3.
Use of example 3
The procedure of example 1 was repeated using the compressor procedure described in example 4.
Use example 4
The procedure of example 1 was repeated using the compressor procedure described in example 5.
Comparative example 1
And (3) performing air compression by using an NC type axial-flow compressor produced by a certain manufacturer.
The total pressure ratio of the air compressor is the ratio of the total pressure of the air at the outlet of the air compressor to the total pressure of the air at the inlet of the air compressor; the compressor efficiency is the volume or weight of compressed air per unit time.

Claims (22)

1. The air compressor of an aerospace, aviation and marine engine comprises an air inlet channel (1), an aerostatic transition chamber (2), a pressure air output pipeline (3) and a driving device (4); one end of the air inlet channel (1) is an air inlet (101), and the other end of the air inlet channel (1) is an air outlet (102); the air inlet channel (1) is a tubular channel; the air inlet channel (1) is arranged above the air static pressure transition chamber (2) and is fixedly connected with the air static pressure transition chamber (2), and the air outlet (102) is communicated with the top of the air static pressure transition chamber (2); the air static pressure transition chamber (2) is movably connected with the pressure air output pipeline (3), a transition chamber air outlet (201) is arranged at the bottom of the air static pressure transition chamber (2), and the transition chamber air outlet (201) is communicated with the pressure air output pipeline (3); the driving device (4) is connected with and drives the aerostatic transition chamber (2);
2-50 groups of air inlets (1) are arranged above the air static pressure transition chamber (2); each group of air inlets (1) comprises 2-50 air inlets (1), one end of each air inlet (1) is independently provided with an air inlet (101), and the other end of each air inlet (1) is independently provided with an air outlet (102); the top of the aerostatic transition chamber (2) is round; the direction of an air inlet (101) of the air inlet channel (1) is in the radial direction of the top of the air static pressure transition chamber (2), and the air inlet channel (1) is uniformly distributed on the periphery of the top of the air static pressure transition chamber (2); the air inlet channels (1) in each group of air inlet channels (1) are distributed from inside to outside along the diameter direction of the top of the air static pressure transition chamber (2); each air inlet channel (1) is arranged in an arc shape along the top circumference direction of the air static pressure transition chamber (2); the cross sections of the air outlets (102) on the same circumference at the top of the air static pressure transition chamber (2) are the same, and the cross sections of the air outlets (102) on different circumferences at the top of the air static pressure transition chamber (2) are different; the cross section area of the air outlet (102) close to the center of the top of the air static pressure transition chamber (2) is smaller than the cross section area of the air outlet (102) far away from the center of the top of the air static pressure transition chamber (2).
2. The compressor as set forth in claim 1, wherein: the compressor also comprises a cooling device (5), wherein the cooling device (5) comprises a heat exchange condensing pipe (501) and a cooling device shell (502), and the cooling device shell (502) is wrapped around the air static pressure transition chamber (2), the front end of the pressure air output pipeline (3) and the outer side of the driving device (4); the heat exchange condenser pipe (501) is arranged in the cooling device shell (502), and a heat exchange condenser pipe water inlet (50201) and a heat exchange condenser pipe water outlet (50202) are arranged on the cooling device shell (502); the water inlet end of the heat exchange condensation pipe (501) is connected with the water inlet (50201) of the heat exchange condensation pipe; the water outlet end of the heat exchange condensation pipe (501) is connected with a water outlet (50202) of the heat exchange condensation pipe.
3. The compressor as set forth in claim 2, wherein: the water inlet (50201) of the heat exchange condensing pipe is arranged at one end, close to the air outlet (201) of the transition chamber, of the cooling device shell (502), and the water outlet (50202) of the heat exchange condensing pipe is arranged at one end, close to the air outlet (102) of the air inlet channel (1), of the cooling device shell (502).
4. The compressor as set forth in claim 1, wherein: 2-20 groups of air inlets (1) are arranged above the air static pressure transition chamber (2);
each group of air inlet channels (1) comprises 2-20 air inlet channels (1).
5. The compressor as set forth in claim 4, wherein: 3-10 groups of air inlets (1) are arranged above the air static pressure transition chamber (2);
each group of air inlet channels (1) comprises 3-10 air inlet channels (1).
6. The compressor as set forth in claim 1, wherein: the distances between the air inlets (101) of the adjacent air inlets (1) on the same circumference at the top of the air static pressure transition chamber (2) are the same.
7. The compressor according to any one of claims 1-6, wherein: the air inlet channel (1) is obliquely arranged above the air static pressure transition chamber (2); the included angle between the air inlet channel (1) and the cross section of the top of the air static pressure transition chamber (2) is 1-90 degrees; and/or
The included angle between the air inlet (101) and the cross section of the top of the air static pressure transition chamber (2) is 1-90 degrees.
8. The compressor as set forth in claim 7, wherein: the included angle between the air inlet channel (1) and the cross section of the top of the air static pressure transition chamber (2) is 5-75 degrees; and/or
The included angle between the air inlet (101) and the cross section of the top of the air static pressure transition chamber (2) is 15-85 degrees.
9. The compressor as set forth in claim 8, wherein: the included angle between the air inlet channel (1) and the cross section of the top of the air static pressure transition chamber (2) is 10-60 degrees; and/or
The included angle between the air inlet (101) and the cross section of the top of the air static pressure transition chamber (2) is 30-80 degrees.
10. The compressor as set forth in claim 9, wherein: the included angle between the air inlet channel (1) and the cross section of the top of the air static pressure transition chamber (2) is 15-45 degrees; and/or
The included angle between the air inlet (101) and the cross section of the top of the air static pressure transition chamber (2) is 45-75 degrees.
11. The compressor according to any one of claims 1-6, wherein: the air static pressure transition chamber (2) is connected with the pressure air output pipeline (3) through a bearing (6); and/or
The driving device (4) is a torque hollow high-speed motor; and/or
An air inlet channel control valve (103) is arranged at the air outlet (102).
12. The compressor as set forth in claim 2, wherein: a condensed water outlet valve (7) is also arranged on the cooling device shell (502); and/or
The cooling device shell (502) is also provided with an air outlet valve (8).
13. An engine system comprising a compressor according to claim 12 and an engine (9), the engine (9) being provided with an engine inlet (901), the end of the pressure air outlet conduit (3) being connected to the engine inlet (901).
14. The engine system of claim 13, wherein: the engine (9) is a ramjet engine.
15. The engine system of claim 14, wherein: the engine system further comprises an air static pressure chamber (10), the tail end of the pressure air output pipeline (3) is connected with an air inlet of the air static pressure chamber (10), and an air outlet of the air static pressure chamber (10) is connected with an engine air inlet (901).
16. The engine system according to any one of claims 13-15, characterized in that: the engine system is a lattice full informatization engine system, and the lattice full informatization engine system comprises n compressors and an engine (9), wherein the tail ends of pressure air output pipelines (3) of the n compressors are connected with an engine air inlet (901); n is 2-200.
17. The engine system of claim 16, wherein: n is 5-150.
18. The engine system of claim 17, wherein: n is 10-100.
19. A method of using the engine system of claim 15, the method comprising the steps of:
1) Starting the driving device (4);
2) The driving device (4) drives the air static pressure transition chamber (2) to rotate, air enters the air inlet channel (1) from the air inlet port (101) of the air inlet channel (1), flows along the air inlet channel (1) and is compressed, and enters the air static pressure transition chamber (2) from the air outlet port (102) of the air inlet channel (1);
3) The compressed air enters a pressure air output pipeline (3) through an air static pressure transition chamber (2);
4) In the working process of the driving device (4), the cooling device (5) cools the driving device (4), and water generated by cooling is discharged from the condensed water outlet valve (7); the air leakage at the joint of the air static pressure transition chamber (2) and the pressure air output pipeline (3) is cooled in the cooling device (5), cooling water is discharged from the condensed water outlet valve (7), and cooling air is discharged from the air outlet valve (8).
20. The method according to claim 19, wherein: the method further comprises the steps of:
5) The compressed air enters the air static pressure chamber (10) from the pressure air output pipeline (3) and is conveyed to the air inlet (901) of the engine.
21. Use of a compressor according to any one of claims 1-12, characterized in that: the compressor is used for equipment in the aerospace or navigation field.
22. Use of an engine system according to any one of claims 13-15, characterized in that: the engine system is used for equipment in the aerospace or navigation field.
CN201710826217.1A 2017-09-14 2017-09-14 Compressor and engine system of aerospace, aviation and ship engines Active CN107420350B (en)

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101178072A (en) * 2006-11-09 2008-05-14 黎晔 Punching type air compressor
CN101440998A (en) * 2007-11-22 2009-05-27 海尔集团公司 Heat pump water heater
CN101498309A (en) * 2009-02-03 2009-08-05 王秀华 Centripetal pump and blade tube type impeller
CN101749257A (en) * 2009-12-29 2010-06-23 林钧浩 Circulating pressure pipeline compressor
WO2014180343A1 (en) * 2013-05-09 2014-11-13 Lin Junhao Pipeline wheel pressure boosting ventilation compressor
CN105298850A (en) * 2015-10-10 2016-02-03 黄敬易 Centripetal axial flow pipe

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101178072A (en) * 2006-11-09 2008-05-14 黎晔 Punching type air compressor
CN101440998A (en) * 2007-11-22 2009-05-27 海尔集团公司 Heat pump water heater
CN101498309A (en) * 2009-02-03 2009-08-05 王秀华 Centripetal pump and blade tube type impeller
CN101749257A (en) * 2009-12-29 2010-06-23 林钧浩 Circulating pressure pipeline compressor
WO2014180343A1 (en) * 2013-05-09 2014-11-13 Lin Junhao Pipeline wheel pressure boosting ventilation compressor
CN105298850A (en) * 2015-10-10 2016-02-03 黄敬易 Centripetal axial flow pipe

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