CN111622963A - Gas compressor based on impact type rotor-rotary stamping stator - Google Patents

Gas compressor based on impact type rotor-rotary stamping stator Download PDF

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Publication number
CN111622963A
CN111622963A CN202010452740.4A CN202010452740A CN111622963A CN 111622963 A CN111622963 A CN 111622963A CN 202010452740 A CN202010452740 A CN 202010452740A CN 111622963 A CN111622963 A CN 111622963A
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China
Prior art keywords
point
section
blade
arc
top surface
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CN202010452740.4A
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Chinese (zh)
Inventor
曹志远
贾明泽
宋澄
高玺
王楚旋
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Northwestern Polytechnical University
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Northwestern Polytechnical University
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Priority to CN202010452740.4A priority Critical patent/CN111622963A/en
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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
    • F04D19/00—Axial-flow pumps
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A gas compressor based on an impact rotor-rotary stamping stator is provided, wherein a hub is positioned in a casing. The impulse rotor blade row is formed by a plurality of impulse rotor blades on the side surface of the hub. Each baffle is positioned at one end of the air outlet of the casing. And an airflow compression block is fixed between the two baffle plates which are overlapped and staggered end to end. The stator of the invention takes the hub and the inner surface of the casing as the pneumatic action surfaces and divides the air flow by the clapboard. A row of impact rotors and a row of rotary punching stators form one stage of the ultrahigh pressure ratio compressor based on the impact rotors and the rotary punching stators. The invention utilizes the advantage of the adaptability of the rotary punching type stator to high incoming flow Mach number to carry out deceleration diffusion on the high air flow Mach number at the outlet of the punching type rotor, forms a shock wave system of a supersonic air inlet channel in the air inlet direction, and utilizes a multi-channel shock wave structure to carry out deceleration diffusion, thereby greatly improving the pneumatic performance of the stator.

Description

Gas compressor based on impact type rotor-rotary stamping stator
Technical Field
The invention relates to the field of gas compressors, in particular to an ultrahigh pressure ratio gas compressor based on an impact type rotor and a rotary stamping stator.
Background
The axial flow compressor is a machine which utilizes blades rotating at high speed to do work on gas to improve the gas pressure, and is widely applied to the fields of aeroengines, gas turbines, missiles and the like.
The modern aircraft design requires continuous improvement of the thrust-weight ratio of the aircraft engine, and the multistage axial-flow compressor occupies about 50% of the space of the aircraft engine in the axial length, so that reduction of the stage number of the multistage compressor has important significance for improvement of the thrust-weight ratio of the aircraft engine. On the premise that the total pressure ratio of the multistage axial flow compressor is kept unchanged, the stage number of the compressor is reduced, which means that the single-stage pressure ratio (or the stage pressure ratio) of the compressor needs to be greatly improved. Therefore, on the premise of ensuring that the efficiency and the stability margin of the compressor are not reduced basically, the stage pressure ratio of the compressor is gradually improved, and the method is the target pursued by modern aeroengine designers.
The stage pressure ratio of the subsonic axial flow compressor is below 1.3, and with the development of a full three-dimensional pneumatic design system of a modern compressor, the high-pressure ratio axial flow compressor becomes possible due to the appearance of the hypersonic compressor. The NASA is designed and tested in the last century to test a series of Stages 35-38 transonic speed unipolar axial flow compressors, wherein the stage ratio of Stages35 to 37 is 2.05, the stage ratio of Stages36 to Stages38 is 1.82, and the experimental efficiency of Stages37 rotors is 84.2%. The pressure ratio of the ATS-2 single-pole transonic compressor designed in China reaches 2.2, and the stage efficiency is 86.8%. However, as aircraft engines seek higher thrust-to-weight ratios, the stage pressure ratio of axial flow compressors will be further improved, and the design of higher stage pressure ratio axial flow compressors presents greater challenges for researchers.
In 1943 and 1946 Weise and Kantrowitz designed supersonic compressors, respectively. The impact compressor has not been studied continuously in order to obtain an ultra high load. Klapprath designed the first impulse supersonic compressor in the world. It features that the relative speed of the air flow at inlet and outlet of rotor is supersonic, the deflection angle of air flow in rotor is large, but the lifting of static pressure is small, so the lifting of static pressure is completed in stator. In supersonic fluid, because the downstream weak disturbance can not be transmitted upstream, the flow-pressure ratio curve of the compressor has constant flow under the working condition (supersonic speed) and is independent of the back pressure. The Klapprath compressor has high efficiency which can reach 89%, but under the working condition of 96% of the designed rotating speed, the stator loss of the Klapprath compressor is very large, so that the Klapprath compressor has the efficiency of only 63% -66% under the working condition of high pressure ratio. Supersonic compressors have been used as a long term research project at von karman hydromechanics institute (VKI) in europe and the Aachen university (RWTH Aachen) turbojet propulsion institute in germany.
The rotary punching compressor is firstly proposed by Ramgen power system company in America, and the punching rotor used by the rotary punching compressor is structurally characterized in that a series of small-angle binary supersonic air inlets are arranged at the edge part of the rotor, so that when supersonic air enters the air inlets, the air is continuously compressed, and the single-stage compression ratio is greatly improved. As a novel supersonic compressor, the supersonic compressor can realize discontinuous high-efficiency compression on airflow by utilizing shock waves, and has the advantages of compact structure, light weight, high pressure ratio and the like. Because complex flow phenomena such as shock wave-shock wave and mutual interference of shock wave-boundary layers exist in an internal flow field in the compression process, flow loss and performance reduction of the compressor can be caused. The current research direction is to reduce the loss and improve the performance of the compressor.
In 2002, after experts of the U.S. department of energy, department of defense, aerospace agency and Ramgen power system company review on the rotary stamping compression technology, after comprehensively considering technical problems, time and economic cost, a rotary stamping gas turbine is consistently determined to replace a conventional gas compressor and is taken as a future key development direction.
In the invention and creation with patent number CN105626579A, a punching compression rotor is proposed, which is characterized in that a plurality of spiral partition plates are uniformly distributed on the outer wall of a wheel disc assembly, a gap between two adjacent partition plates forms an inlet flow channel, and each inlet flow channel is provided with an airflow compression section, a throat isolation section and a triangular outlet extension section from an inlet section to an outlet section. The rotor can compress the seven and six parts by a plurality of oblique shock waves generated by the compression section of the rotor after supersonic airflow enters the air inlet channel, so that a high pressure ratio is obtained. However, in order to make the air flow at the air inlet be supersonic, the condition can be achieved only by the continuous high-speed rotation of the rotor, and the power consumption of the compressor is increased.
The institute of engineering thermophysics of the Chinese academy of sciences xiao xiang in the text of analysis and research on the flow inside the punching impeller of the counter-rotating punching compressor, provides a structural scheme of the counter-rotating punching compressor, and the total pressure ratio is more than 10 by using two stages of counter-rotating blades in the compressor. The disadvantages of rotating the ram compressor are also evident in practice: the air flow is small, the requirement on the axial support of the compressor is high, and the like. A series of problems make it less desirable for use in high flow aircraft engines.
The conventional compressor rotor needs to work at a higher rotating speed, so the allowable flow rate is not too high generally; the stator design has the design difficulties of serious flow separation and low overall efficiency at present.
The Cao Shi far from the university in northwest of China teaches in the academic thesis "study on the influence of boundary layer suction on the flow control and performance of an axial flow compressor" and an invention patent (patent No. CN103967812B) that an axial flow compressor is provided, wherein the front end of an adopted impact type rotor blade adopts a pre-compression blade type, the camber is mainly concentrated on the second half section, and the camber of each section is more than 90 degrees. The design of the rotor ensures high efficiency and improves the working capacity of the rotor. However, the rotor used by the compressor has a small pressure-lifting effect on the air flow, and a stator capable of greatly improving the air flow pressure is lacked to improve the efficiency of the compressor.
Disclosure of Invention
The invention provides an air compressor based on an impact type rotor-rotary punching stator, aiming at overcoming the steps of small pressure lifting effect on air flow, low efficiency of the air compressor and serious flow separation of the stator in the prior art.
The invention comprises a casing, a hub, an impact type rotor blade, a partition plate and an airflow compression block. The hub is located within the case. A plurality of impact type rotor blades are circumferentially arranged on the side surface of the hub to form an impact type rotor blade row. When the rotor blades are arranged, the bottom surfaces of the impact rotor blades are fixed on the hub, and the front edges of the impact rotor blades are positioned in the direction of the air inlet of the casing. The top end of each of the impact rotor blades is spaced from the inner surface of the casing by 5mm, and the spacing between the adjacent surfaces of two adjacent impact rotor blades is 59.37 mm.
The baffle has three, is the arc lath of semicircle arcuation. The partition plates are positioned at one end of the air outlet of the casing, and the inner arc surface of each partition plate is fixed on the outer circumferential surface of the hub, so that the outer arc surface of each partition plate is fixedly connected with the inner circumferential surface of the casing at the position of the partition plate. When the partition boards are arranged, the two ends of each partition board are not positioned on the same vertical plane, and an included angle of 27.6 degrees is formed between a space connecting line between the two ends of each partition board and the vertical plane; the vertical plane is parallel to the end face of the hub. When the arrangement is carried out, the heads and the tails of the three clapboards are overlapped and staggered; the arc length of the overlapped and staggered heads and tails of the partition boards is 1/3 of the arc length of the inner circle of the partition board.
And an airflow compression block is arranged between the two partition plates which are overlapped and staggered end to end, is fixed on the outer circumferential surface of the hub, and ensures that two side edges of the airflow compression block are fixedly connected with the end or tail side surfaces of the two adjacent partition plates respectively. And the rotary punching stator of the gas compressor is formed by the partition plate and the gas flow compression block. The impact type rotor blade row and the rotary punching stator are sequentially arranged on the hub in parallel.
The impact rotor blade is an arc-shaped plate. The surface of the impact rotor blade adjacent to the surface of the casing is the blade top surface, and the surface matched with the outer surface of the hub is the blade bottom surface. The intersection point of the front edge of the impact type rotor blade and the top surface of the blade is called a top surface front edge point, and the intersection point of the rear edge and the top surface of the blade is called a top surface rear edge point; the intersection of the leading edge of an impulse rotor blade with the bottom surface of the blade is called the bottom leading edge point. The distance between the leading edge points of the top surfaces of two adjacent impulse rotor blades is 59.37 mm.
Making a curve passing through the top surface of the blade from the front edge to the rear edge of the top surface of the blade, wherein the curve is a top surface mean camber line; the top surface mean camber line is located at 1/2 of the blade thickness. The straight line obtained by connecting the two end points of the top surface mean camber line is the top surface chord length of the impact type rotor blade; and respectively making tangent lines of the camber line at two end points of the camber line in the top surface to respectively obtain a top surface front edge tangent line and a top surface rear edge tangent line.
The convex surface of the impact type rotor blade is a suction surface which consists of 3 sections of arc-shaped surfaces; the arcs are tangent at the junction. Making a connecting line between a boundary point of the suction surface at the position where the relative chord length x is 0.5 and the chord length of the top surface, and enabling the connecting line to be perpendicular to the chord length of the top surface; the length of the connecting line is y1；y 11/3 equal to the chord length of the top surface; the starting point of the first arc segment of the suction surface is a leading edge point, the end point is a first boundary point, and the first boundary point is positioned at the relative chord length xE＝0.21，yE＝0.5y1To (3). The starting point of the second arc section of the suction surface is the first dividing point, the end point is the second dividing point, and the second dividing point is positioned at the relative chord length xF＝0.6，yF＝1.05y1To (3). The starting point of the third arc segment of the suction surface is the second boundary point, and the end point is the trailing edge point.
The concave surface of the impact rotor blade is a pressure surface, and the distance from the boundary point at the position where the relative chord length x is 0.5 to the chord length of the pressure surface is recorded as y2，y 21/4 equal to the chord length of the top surface; the starting point of the front blade profile of the pressure surface is a leading edge point, and the end point is a third boundary point which is positioned at the relative chord length xG＝0.2，yG＝0.5y2At least one of (1) and (b); the starting point of the rear-section blade profile is the third boundary point, and the end point is the trailing edge point. The pressure surface of the front blade profile is made into a concave shape to reduce the wave front Mach number and reduce the shock wave loss, the blade profile is called as a pre-compression blade profile, and the relative chord length x of the pre-compression blade profileGThe precompression degree of the blade profile at the position of 0.2 is maximum; the rear section of the pressure surface consists of 3 sections of tangent circular arcs.
The functional relationship between y and x of the front-stage pre-compressed blade profile is as follows:
y＝-0.0004x2-0.6128x+0.5y2
the starting point of the first arc section of the pressure surface of the rear section arc profile is a third boundary point, the end point is a fourth boundary point, and the fourth boundary point is positioned at the relative chord length xH＝0.43，yH＝0.8y2At least one of (1) and (b); the starting point of the second circular arc section of the pressure surface is the fourth boundary point, the end point is the fifth boundary point, and the fifth boundary point is positioned at the relative chord length xI＝0.8，yI＝0.85y2At least one of (1) and (b); the starting point of the third arc segment of the pressure surface is the fifth boundary point, and the end point is the trailing edge point.
The suction surface and the pressure surface of the impact type rotor blade are connected by an arc at the intersection of the front edge, and the curvature radius of the arc is 0.1-3% of the chord length; the suction surface and the pressure surface of the impact type rotor blade are connected at the intersection of the rear edge by an arc, and the curvature radius of the arc is 0.1-3% of the chord length;
the connecting line between the front edge points of the impact type rotor blades distributed on the circumference of the hub is a top surface front edge frontal line; the connecting line between the trailing edge points of the impact rotor blades distributed on the circumference of the hub is called a top surface trailing edge frontal line; an acute angle formed by the frontal line of the top front edge and the tangent line of the top front edge is a geometric inlet angle alpha of the top; and an acute angle formed by the frontal line of the rear edge of the top surface and the tangent line of the rear edge of the top surface is a geometric outlet angle beta of the top surface. The angle formed by the intersection of the tangent of the front edge of the top surface and the tangent of the rear edge of the top surface is a top surface bending angle.
The line between the leading edge points of the individual impulse rotor blades distributed over the circumference of the hub is referred to as the frontal bottom edge line. The included angle between the bottom surface chord length and the frontal line of the bottom surface front edge is a blade root installation angle gamma; the setting angle γ of the blade root of each impulse rotor blade is 65.9 °.
There are 3 airflow compression blocks. The lower surface of the airflow compression block is an arc surface attached to the outer surface of the hub, the surfaces on the two sides are planes attached to the partition plate, the upper surface of the airflow compression block is arc-shaped and is processed into seven sections of inclined surfaces with different slopes, and the airflow entering the rotary punching stator is compressed to do work; the upper surface is divided into an ascending section and a descending section, of whichThe surface of the ascending section is processed into four sections of mutually jointed inclined planes, and the surface of the descending section is processed into three sections of mutually jointed inclined planes. The ascending section is an airflow inlet, and the descending section is an airflow outlet. In the ascending section, the included angle theta between the first section inclined plane of the airflow inlet and the horizontal plane1Is 63.6 degrees, and the included angle theta between the inclined surface of the second section and the horizontal plane2Theta is one half1The angle theta between the third section inclined plane and the horizontal plane3Theta is one half2Angle theta between the fourth inclined plane and the horizontal plane4Theta is one half3. The included angle between each section of inclined plane in the descending section and the horizontal plane is all positioned below the horizontal plane, so that each section of inclined plane is in a downward state, wherein the included angle theta between the fifth section of inclined plane connected with the fourth section of inclined plane in the ascending section and the horizontal plane5＝θ4(ii) a The sixth section of inclined surface is connected with the fifth section of inclined surface, and the included angle theta between the sixth section of inclined surface and the horizontal plane6＝2θ5(ii) a The seventh section of inclined surface is connected with the sixth section of inclined surface, and the included angle theta between the seventh section of inclined surface and the horizontal plane7＝2θ6。
The invention provides a high-pressure-ratio adsorption type compressor, which aims to achieve higher incoming flow Mach number, improve the stage pressure ratio and solve the design difficulties of serious stator flow separation and extremely low overall efficiency of a stamping type compressor.
The compressor is provided with an impact rotor and a rotary punching stator in sequence from an inlet to an outlet. The impact rotor is positioned in the casing and fixed on the circumferential surface of the hub; behind the impulse rotor blades are rotating stamped stators which are mounted in the same manner as the rotors and are fixed to the circumferential surface of the shaft. The stator is different from the traditional vane stator, the working mode does not use the suction surface and the pressure surface of the vane as pneumatic action surfaces any more, but uses the inner surfaces of the hub and the casing as the pneumatic action surfaces, and the partition plates on the surfaces are only devices required by the rotor for dividing airflow. A row of impact rotors and a row of rotary punching stators form one stage of the ultrahigh pressure ratio compressor based on the impact rotors and the rotary punching stators.
The impact type rotor 3 comprises 27 blades which are uniformly distributed on a hub along the circumferential direction, the installation angle of the blade root of each rotor blade is 65.9 degrees, the chord lengths of different blade heights are all about 120mm, the inlet geometric angle is 40.18 degrees, and the outlet geometric angle is 12.71 degrees. In order to adapt to the airflow direction, the rotor blades are streamline blades with large bending angles, the bending angles of the rotor blades from the air inlet to the air outlet are larger than 90 degrees from the blade root to the blade tip, each blade is designed by a wide chord blade, namely, on the premise that the total bending angle is larger than 90 degrees, the chord length of the blade is widened, the bending angle of each blade is smaller, so that the whole channel is streamline, airflow is not easy to block when flowing, and the flow loss is reduced. The impulse force of the impact rotor mainly comes from the impact force of the airflow to the blades, the rotor rotates to pressurize the airflow, the working principle is that when the airflow enters a channel between the guide blades formed between two adjacent inlet guide blades, the airflow speed is still supersonic, the inlet Mach number is about 1.2, the impulse force is different from that of a conventional compressor, the airflow angle of different blade span inlets is about 60 degrees due to the fact that the included angle between the rear-row stator inlet airflow and the axial direction is large, and the secondary flow of the airflow at the blade walls of the end faces of the blades is controlled by the bent blades.
The rotary punching stator is formed by fixing three partition plates which have the arc length which is half of the circular circumference of the top surface of the hub and cross the side surface on the side surface of the hub. Viewed in the axial direction, the overlapping portion of each two baffles is 1/3 of its arc length. A plurality of stepped airflow channels similar to a binary supersonic air inlet channel are arranged on the wheel rim in the overlapped part of the two partition plates at a small angle, the partition plates are used as the wall surfaces of the air inlet channel, and the channels and the casing together form the air inlet channel of the stator. The front half part of the channel is in ascending trend, and the included angle between the inclined surface and the wheel rim is gradually reduced; the latter half is in a downward trend and the angle between the inclined surface and the rim is also gradually reduced. The working principle is that the front half part of the air flow is compressed in the stepped channel, so that the speed of the air flow is continuously increased and the Mach number at the top is 1; in the latter half, the air flow velocity reaches supersonic speed, and the air flow velocity is continuously increased due to the continuous expansion of the cross section of the air inlet. An air inlet channel similar to a Laval nozzle is formed in the channel and used for compressing and applying work to the air flow and increasing the energy of the air flow.
In order to ensure high efficiency and simultaneously improve the pressure ratio of the rotor, the axial flow compressor rotor adopts a large-bend-angle impact type rotor; the rotor of the invention has higher incoming flow Mach number and larger air flow turning angle, so the rotor pressure ratio can be as high as 5.7, while the conventional transonic speed rotor is only about 2.0; the impact design makes the air flow in the rotor have smaller diffusion degree, i.e. the diffusion load is lower, so that the efficiency can still keep higher despite the rotor has larger turning angle, and the efficiency can reach 87%.
The advantage of the adaptability of the rotary punching type stator to the high incoming flow Mach number is utilized to carry out speed reduction and diffusion on the high air flow Mach number at the outlet of the punching type rotor; the stator of the type is provided with an airflow compression section similar to an air inlet channel type in the air inlet direction, a shock wave system similar to a supersonic speed air inlet channel is sequentially formed, a multi-channel shock wave structure is utilized for speed reduction and pressure expansion, and compared with a conventional vane type stator, the pneumatic performance of the stator can be greatly improved. Verification proves that the total pressure loss of the airflow after the airflow passes through the shock wave system is far smaller than that of the airflow after the airflow passes through only one normal shock wave, and the verification proves that the total pressure loss of the airflow is smaller as more oblique shock waves pass through under the condition that the total deflection angles of the airflow are the same.
Drawings
FIG. 1 is a three-dimensional view of the present invention as viewed from the air intake direction;
FIG. 2 is a three-dimensional view of the present invention as viewed from the direction of gas egress;
FIG. 3 is an axial two-dimensional cross-sectional view of the present invention;
FIG. 4 is a three-dimensional view of an assembly of an impulse rotor-rotating punch stator
FIG. 5 is a side view of an impulse rotor-rotating punch stator;
FIG. 6 is an assembly view of the impulse rotor-rotating punch stator as viewed from the intake direction;
FIG. 7 is an assembled view of the impulse rotor-rotating punch stator as viewed from the air outlet direction;
FIG. 8 is a three-dimensional view of an impulse rotor blade;
FIG. 9 is a top view of an impulse rotor blade;
FIG. 10 is a top cross-sectional view of an impulse rotor blade;
FIG. 11 is a bottom cross-sectional view of an impulse rotor blade;
FIG. 12 is a schematic illustration of the geometric inlet angle and geometric outlet angle of the top surface of an impingement rotor blade;
FIG. 13 is a schematic view of an impingement rotor blade stagger angle.
FIG. 14 is a three-dimensional view of an airflow compression block;
FIG. 15 is a cross-sectional view of the gas flow constriction block;
FIG. 16 is a cross-sectional view of a rotating ram stator airflow channel;
fig. 17 is a schematic view of the shock wave formed by the rotating ram stator airflow channel.
FIG. 18 is a schematic illustration of a blade profile split point of an impulse rotor blade
In the figure: 1. a case; 2. a hub; 3. an impulse rotor blade; 4. a partition plate; 5. an airflow compression block; 6. a blade top surface; 7. a blade bottom surface; 8. a top surface mean camber line; 9. the top surface chord length; 10. a top surface leading edge tangent; 11. a top surface trailing edge tangent; 12. a top surface corner piece; 13. a bottom surface mean camber line; 14. the chord length of the bottom surface; 15. a bottom surface leading edge tangent line; 16. a bottom surface trailing edge tangent line; 17. a bottom surface corner; 18. a rising ramp; 19. a descending ramp; 20. a top leading edge frontal line; 21. a leading edge; 22. a trailing edge; 23. the frontal line of the rear edge of the bottom surface; 24. frontal line of the bottom front edge; A. a top surface trailing edge point; B. a top leading edge point; C. a bottom trailing edge point; D. a bottom leading edge point; E. a first demarcation point; F. a second demarcation point; G. a third division point; H. a fourth demarcation point; I. a fifth demarcation point; α, geometric entrance angle; beta. geometric exit angle; and gamma, a mounting angle.
Detailed Description
The embodiment is an air compressor based on an impact rotor-rotating punching stator, and the air compressor comprises a casing 1, a hub 2, impact rotor blades 3, a partition plate 4 and an airflow compression block 5. The hub 2 is located inside the casing 1. The plurality of impulse rotor blades 3 are circumferentially arranged on the side surface of the hub 2 to form an impulse rotor blade row. When the rotor blades are arranged, the blade bottom surfaces 7 of the impact rotor blades are fixed on the hub, and the front edges of the impact rotor blades are located in the direction of the air inlet of the casing 1. The top end of each of the impact rotor blades 3 is spaced from the inner surface of the casing 1 by 5mm, and the spacing between the adjacent surfaces of two adjacent impact rotor blades is 59.37 mm.
The partition plates 4 are three arc-shaped battens which are semi-circular arc-shaped. The clapboards are positioned at one end of the air outlet of the casing 1, and the inner arc surface of each clapboard is fixed on the outer circumferential surface of the hub, so that the outer arc surface of each clapboard is fixedly connected with the inner circumferential surface of the casing at the position. When the partition boards 4 are arranged, the two ends of each partition board 4 are not on the same vertical plane, and an included angle of 27.6 degrees is formed between a space connecting line between the two ends of each partition board and the vertical plane; said vertical plane being parallel to the end face of the hub 2. When the arrangement is carried out, the heads and the tails of the three clapboards 4 are overlapped and staggered; the arc length of the overlapped and staggered heads and tails of the partition boards 4 is 1/3 of the arc length of the inner circle of the partition board 4. In this embodiment, the inner arc length of each partition board is 725mm, and the arc length of two adjacent partition boards overlapped and staggered is 242 mm.
And an airflow compression block 5 is arranged between two partition plates which are overlapped and staggered end to end, the airflow compression block 5 is fixed on the outer circumferential surface of the hub 2, and two side edges of the airflow compression block 5 are respectively and fixedly connected with the end or tail side surfaces of two adjacent partition plates. And the rotary punching stator of the air compressor is formed by the partition plate and the airflow compression block 5. The impact type rotor blade row and the rotary punching stator are sequentially arranged on the hub 2 in parallel.
The impact rotor blade 3 is an arc-shaped plate. The surface of the impulse rotor blade 3 adjacent to the casing surface is the blade top surface 6 and the surface cooperating with the outer surface of the hub 2 is the blade bottom surface 7. The intersection point of the leading edge of the impact rotor blade 3 and the blade top surface 6 is called a top surface leading edge point B, and the intersection point of the trailing edge and the blade top surface 6 is called a top surface trailing edge point A; the intersection of the leading edge of the impulse rotor blade 3 with the blade base 7 is called the base leading edge point C. The distance between the top surface leading edge points B of two adjacent impact type rotor blades is 59.37 mm.
Making a curve through the blade top surface 6 from the leading edge to the trailing edge of the top surface, the curve being a top surface mean camber line 8; the top surface mean camber line is located at 1/2 of the blade thickness. The straight line connecting the two end points of the top surface mean camber line 8 is the top surface chord length 9 of the impulse rotor blade 3; tangents to the top surface mean camber line 8 are respectively made at two end points of the camber line, and a top surface leading edge tangent line 10 and a top surface trailing edge tangent line 11 are respectively obtained.
The connecting line between the front edge points C of the impact rotor blades 3 distributed on the circumference of the hub 2 is a top surface front edge frontal line 20; the connecting line between the trailing edge points a of the individual impulse rotor blades 3 distributed over the circumference of the hub 2 is referred to as the top trailing edge frontal line 23; the acute angle formed by the frontal line 20 of the top front edge and the tangent line 10 of the top front edge is the geometric inlet angle alpha of the top surface; the acute angle enclosed by the top surface rear edge frontal line 23 and the top surface rear edge tangent line 11 is the top surface geometric exit angle β. The top surface front edge tangent line 10 and the top surface rear edge tangent line 11 intersect to form a top surface corner angle 12.
In the present embodiment, the length of the top chord 9 of the impulse rotor blade is 120.48mm, the length of the bottom chord 14 is 115.39mm, and the distance between the blade top surface 6 and the blade bottom surface 7 is 54.18 mm.
The distance from each point constituting the boundary of the top surface of the impulse rotor blade to the chord length 9 of the top surface is denoted y, and the percentage of the chord length of the top surface to the distance from the projection of each point on the chord length of the top surface to the leading edge point B is denoted as the relative chord length x. Let the relative chord length of each dividing point be xE、xF、xG、xH、xI(ii) a The distances from the dividing points to the top chord length 9 are respectively recorded as yE、yF、yG、yH、yI。
The convex surface of the impact type rotor blade is a suction surface, and an arc-shaped surface is adopted, so that 3 sections of arcs are totally formed; the arcs are tangent at the junction. A connecting line between a boundary point of the suction surface at the position where the relative chord length x is 0.5 and the top surface chord length 9 is recorded, and the connecting line is perpendicular to the top surface chord length; the length of the connecting line is y1；y 11/3 equal to the chord length of the top surface; the starting point of the first arc section of the suction surface is a front edge point B, the end point is a first boundary point E, and the first boundary point E is positioned at a relative chord length xE＝0.21，yE＝0.5y1To (3). The starting point of the second arc section of the suction surface is a dividing point E, the end point is a second dividing point F, and the second dividing point F is positioned at the relative chord length xF＝0.6，yF＝1.05y1To (3). The starting point of the third arc segment of the suction surface is the second dividing point F, and the end point is the trailing edge point A.
In this embodiment, the radius of curvature of first circular arc section is infinitely great, and the first circular arc section of suction surface is a straight line promptly, the radius of curvature of suction surface second circular arc section is 408.9mm, and the radius of curvature of suction surface third circular arc section is 140 mm.
The concave surface of the impact rotor blade is a pressure surface, and the distance from the boundary point at the position where the relative chord length x is 0.5 to the chord length 9 of the top surface is represented as y2，y 21/4 equal to the chord length of the top surface; the starting point of the pressure surface front blade profile is a leading edge point B, the end point is a third boundary point G, and the third boundary point G is positioned at a relative chord length xG＝0.2，yG＝0.5y2At least one of (1) and (b); the starting point of the rear-section blade profile is the third boundary point G, and the end point is the trailing edge point A. The pressure surface of the front blade profile is made into a concave shape to reduce the wave front Mach number and reduce the shock wave loss, the blade profile is called as a pre-compression blade profile, and the relative chord length x of the pre-compression blade profileGThe precompression degree of the blade profile at the position of 0.2 is maximum; the rear section of the pressure surface adopts an arc profile and consists of 3 sections of tangent arcs.
The functional relationship between y and x of the front-stage pre-compressed blade profile is as follows:
y＝-0.0004x2-0.6128x+0.5y2
the starting point of the first arc section of the pressure surface of the rear section arc profile is a demarcation point G, and the end point of the first arc section of the pressure surface of the rear section arc profile is a fourth demarcation point H; the fourth demarcation point H is located at the relative chord length xH＝0.43，yH＝0.8y2At least one of (1) and (b); the starting point of the second circular arc section of the pressure surface is the fourth dividing point H, the end point is a fifth dividing point I, and the fifth dividing point I is positioned at the relative chord length xI＝0.8，yI＝0.85y2At least one of (1) and (b); the starting point of the third arc segment of the pressure surface is a demarcation point I, and the end point is a trailing edge point A.
In this embodiment, the radius of curvature of the first arc segment of the pressure surface is 356.4mm, and the radius of curvature of the second arc segment of the pressure surface is 204.5 mm; the radius of curvature of the third circular arc section of the pressure surface is 140 mm.
The suction surface and the pressure surface of the impact type rotor blade are connected by an arc at the intersection of the front edge, and the curvature radius of the arc is 0.1-3% of the chord length; the suction surface and the pressure surface of the impact type rotor blade are connected at the intersection of the rear edge by an arc, and the curvature radius of the arc is 0.1-3% of the chord length;
the line between the leading edge points B of the individual impulse rotor blades 3 distributed over the circumference of the hub 2 is called the base leading edge frontal line 24. The included angle between the bottom surface chord length 14 and the frontal line 24 of the bottom surface front edge is a blade root installation angle gamma; the setting angle γ of the blade root of each impulse rotor blade 3 is 65.9 °. In the present embodiment, the length of the top chord 9 is 120.48mm, and the length of the bottom chord 14 is 115.39 mm. The geometric inlet angle α is 42 ° and the geometric outlet angle β is 63 °.
In order to adapt to the direction of the air flow, the impact rotor blade 3 is a streamlined blade with a large bending angle, i.e. a bending angle greater than 90 °. In the present exemplary embodiment, the top corner 12 of the impact rotor blade 3 is 94.5 °, and the bottom corner 17 is 100.6 °. The impulse rotor blade 3 is a wide chord blade. The wide chord blades enable airflow channels between two adjacent blades to be streamline, airflow is not easy to block when flowing, and meanwhile flow loss is reduced.
The number of the airflow compression blocks 5 is 3, and the airflow compression blocks are block-shaped. The lower surface of the airflow compression block 5 is an arc surface attached to the outer surface of the hub 2, the two side surfaces are planes attached to the partition plate 4, the upper surface is arc-shaped and is processed into seven sections of inclined surfaces with different slopes, and the airflow entering the rotary punching stator is compressed to do work; the upper surface is divided into an ascending section 21 and a descending section 22, wherein the surface of the ascending section is processed into four sections of mutually connected inclined surfaces, and the surface of the descending section is processed into three sections of mutually connected inclined surfaces. The ascending section is an airflow inlet, and the descending section is an airflow outlet. In the ascending section, the included angle theta between the first section inclined plane of the airflow inlet and the horizontal plane1Is 63.6 degrees, and the included angle theta between the inclined surface of the second section and the horizontal plane2Theta is one half1The angle theta between the third section inclined plane and the horizontal plane3Theta is one half2Angle theta between the fourth inclined plane and the horizontal plane4Theta is one half3. The included angle between each section of inclined plane in the descending section and the horizontal plane is all positioned below the horizontal plane, so that each section of inclined plane is in a downward state, wherein the included angle theta between the fifth section of inclined plane connected with the fourth section of inclined plane in the ascending section and the horizontal plane5＝θ4(ii) a The sixth section of inclined surface is connected with the fifth section of inclined surface, and the included angle theta between the sixth section of inclined surface and the horizontal plane6＝2θ5(ii) a The seventh section of inclined surface is connected with the sixth section of inclined surface, and the included angle theta between the seventh section of inclined surface and the horizontal plane7＝2θ6. In the present embodiment, θ1＝63.6°，θ2＝36.75°，θ3＝18.36°，θ4＝9.18°，θ5＝-9.18°，θ6＝-18.36°，θ7＝-36.72°。
The projection lengths of the inclined surface sections in the ascending section 21 in the circumferential direction of the hub 2 are the same, and are 29.42mm in the embodiment; the projection lengths of the inclined surface sections in the descending section 22 in the circumferential direction of the hub 2 are the same, and are all 26.33mm in the embodiment.
The working principle of the airflow compression block 5 is that after the airflow enters the rotary punching stator, a series of shock waves formed by the shape of the airflow compression block 5 are used for decelerating and pressurizing the incoming flow. The shaping forms an air inlet channel similar to a Laval nozzle in the channel, and is used for compressing and applying work to air flow and increasing the energy of the air flow.
The casing 1 is a housing, the inner surface of which is connected with the partition plate 4, the circumferential diameter of the side end surface of the impact rotor in the embodiment is 462.04mm, and the circumferential diameter of the side end surface of the rotary stamping stator is 458.04 mm.
The rotating stamping stator in the embodiment is different from the traditional blade type stator, the action mode does not use the suction surface and the pressure surface of the blade as pneumatic action surfaces any more, but uses the outer circumferential surface of the hub 2 and the inner surface of the casing 1 as the pneumatic action surfaces, the partition plate 6 fixed on the surface of the hub 2 is only a device required by the hub for dividing airflow, and the airflow compression work is completed by utilizing the shape of the airflow compression block 5. Each row of impulse rotor blades and rotating punch stator constitutes a stage of the compressor, and the superhigh pressure ratio compressor based on impulse rotor-rotating punch stator is composed of a plurality of such stages, a hub 2 and a casing 1.
The driving force of the rotor used by the gas compressor mainly comes from the impact force of the airflow on the impact type rotor blades, so that the impact type rotor rotates to pressurize the airflow, the working principle is that when the airflow enters a channel between guide vane blades formed between two adjacent impact type rotor blades 3, the airflow speed is still supersonic, the inlet Mach number is 1.2, the angle between the airflow at the outlet of a rotary punching stator and the axial direction is 60-70 degrees, and the secondary flow of the airflow at the blade end face blade wall is controlled by adopting a bent blade.

Claims (7)

1. A gas compressor based on an impact type rotor-rotary punching stator is characterized by comprising a casing, a hub, impact type rotor blades, a partition plate and a gas flow compression block; the hub is positioned in the casing; a plurality of impact type rotor blades are circumferentially distributed on the side surface of the hub to form an impact type rotor blade row; when the rotor blades are arranged, the bottom surfaces of the impact rotor blades are fixed on the hub, and the front edges of the impact rotor blades are positioned in the direction of the air inlet of the casing; the distance between the top end of each impact type rotor blade and the inner surface of the casing is 5mm, and the distance between the adjacent surfaces of two adjacent impact type rotor blades is 59.37 mm;
the three partition plates are arc-shaped battens in a semicircular arc shape; the clapboards are positioned at one end of the air outlet of the casing, and the inner arc surface of each clapboard is fixed on the outer circumferential surface of the hub, so that the outer arc surface of each clapboard is fixedly connected with the inner circumferential surface of the casing at the position of the clapboard; when the partition boards are arranged, the two ends of each partition board are not positioned on the same vertical plane, and an included angle of 27.6 degrees is formed between a space connecting line between the two ends of each partition board and the vertical plane; the vertical plane is parallel to the end face of the hub; when the arrangement is carried out, the heads and the tails of the three clapboards are overlapped and staggered; the arc length of the overlapped and staggered heads and tails of the partition boards is 1/3 of the arc length of the inner circle of the partition board;
an airflow compression block is arranged between the two partition plates which are overlapped and staggered end to end, the airflow compression block is fixed on the outer circumferential surface of the hub, and two side edges of the airflow compression block are fixedly connected with the end or tail side surfaces of the two adjacent partition plates respectively; the rotary punching stator of the gas compressor is formed by the partition plate and the gas flow compression block; the impact type rotor blade row and the rotary punching stator are sequentially arranged on the hub in parallel.
2. The impulse rotor-rotating punch stator based compressor as claimed in claim 1, wherein said impulse rotor blades are arc-shaped plates; the surface of the impact type rotor blade adjacent to the surface of the casing is a blade top surface, and the surface matched with the outer surface of the hub is a blade bottom surface; the intersection point of the front edge of the impact type rotor blade and the top surface of the blade is called a top surface front edge point, and the intersection point of the rear edge and the top surface of the blade is called a top surface rear edge point; the intersection point of the leading edge of the impact rotor blade and the bottom surface of the blade is called a bottom surface leading edge point; the distance between the leading edge points of the top surfaces of two adjacent impulse rotor blades is 59.37 mm.
3. The impulse rotor-rotating punch stator-based compressor as claimed in claim 1, wherein a curve passing through the blade tip surface is made from the leading edge to the trailing edge of the blade tip surface, the curve being a tip surface mean camber line; the top surface mean camber line is located at 1/2 of the blade thickness; the straight line obtained by connecting the two end points of the top surface mean camber line is the top surface chord length of the impact type rotor blade; and respectively making tangent lines of the camber line at two end points of the camber line in the top surface to respectively obtain a top surface front edge tangent line and a top surface rear edge tangent line.
4. The compressor based on the impact type rotor-rotating punching stator as claimed in claim 1, wherein the convex surface of the impact type rotor blade is a suction surface, and the suction surface is composed of 3 sections of circular arc profiles; each arc is tangent at the joint; making a connecting line between the boundary point of the suction surface at the position where the relative chord length x is equal to 0.5 and the top surface chord length, and making the connecting line be perpendicular to the top surface chord lengthLength; the length of the connecting line is y1；y11/3 equal to the chord length of the top surface; the starting point of the first arc segment of the suction surface is a leading edge point, the end point is a first boundary point, and the first boundary point is positioned at the relative chord length xE＝0.21，yE＝0.5y1At least one of (1) and (b); the starting point of the second arc section of the suction surface is the first dividing point, the end point is the second dividing point, and the second dividing point is positioned at the relative chord length xF＝0.6，yF＝1.05y1At least one of (1) and (b); the starting point of the third arc segment of the suction surface is the second boundary point, and the end point is the trailing edge point;
the concave surface of the impact rotor blade is a pressure surface, and the distance from the boundary point at the position where the relative chord length x is 0.5 to the chord length of the pressure surface is recorded as y2，y21/4 equal to the chord length of the top surface; the starting point of the front blade profile of the pressure surface is a leading edge point, and the end point is a third boundary point which is positioned at the relative chord length xG＝0.2，yG＝0.5y2At least one of (1) and (b); the starting point of the rear-section blade profile is the third boundary point, and the end point is a trailing edge point; the pressure surface of the front blade profile is made into a concave shape to reduce the wave front Mach number and reduce the shock wave loss, the blade profile is called as a pre-compression blade profile, and the relative chord length x of the pre-compression blade profileGThe precompression degree of the blade profile at the position of 0.2 is maximum; the rear section of the pressure surface consists of 3 sections of tangent circular arcs;
the functional relationship between y and x of the front-stage pre-compressed blade profile is as follows:
y＝-0.0004x2-0.6128x+0.5y2
the starting point of the first arc section of the pressure surface of the rear section arc profile is a third boundary point, the end point is a fourth boundary point, and the fourth boundary point is positioned at the relative chord length xH＝0.43，yH＝0.8y2At least one of (1) and (b); the starting point of the second circular arc section of the pressure surface is the fourth boundary point, the end point is the fifth boundary point, and the fifth boundary point is positioned at the relative chord length x1＝0.8，y1＝0.85y2At least one of (1) and (b); the starting point of the third arc segment of the pressure surface is the fifth boundary point, and the end point is the trailing edge point.
5. The compressor based on the impact type rotor-rotating punching stator as claimed in claim 4, wherein the suction surface and the pressure surface of the impact type rotor blade are connected by an arc at the intersection of the front edge, and the radius of curvature of the arc is 0.1% -3% of the chord length; the suction surface and the pressure surface of the impact type rotor blade are connected by an arc at the intersection of the rear edge, and the curvature radius of the arc is 0.1-3% of the chord length.
6. The compressor based on the impulse rotor-rotating punching stator as claimed in claim 1, wherein the connecting line between the leading edge points of each impulse rotor blade distributed on the circumference of the hub is the frontal line of the leading edge of the top surface; the connecting line between the trailing edge points of the impact rotor blades distributed on the circumference of the hub is called a top surface trailing edge frontal line; an acute angle formed by the frontal line of the top front edge and the tangent line of the top front edge is a geometric inlet angle alpha of the top; an acute angle formed by the frontal line of the rear edge of the top surface and the tangent line of the rear edge of the top surface is a geometric outlet angle beta of the top surface; the angle obtained by the intersection of the tangent of the front edge of the top surface and the tangent of the rear edge of the top surface is a top surface bend angle;
the connecting line between the front edge points of the impact type rotor blades distributed on the circumference of the hub is called as a frontal line of the front edge of the bottom surface;
the included angle between the bottom surface chord length and the frontal line of the bottom surface front edge is a blade root installation angle gamma; the setting angle γ of the blade root of each impulse rotor blade is 65.9 °.
7. The compressor based on the impulse rotor-rotating punching stator as claimed in claim 1, wherein there are 3 said gas flow compression blocks; the lower surface of the airflow compression block is an arc surface attached to the outer surface of the hub, the surfaces on the two sides are planes attached to the partition plate, the upper surface of the airflow compression block is arc-shaped and is processed into seven sections of inclined surfaces with different slopes, and the airflow entering the rotary punching stator is compressed to do work; the upper surface is divided into an ascending section and a descending section, wherein the surface of the ascending section is processed into four sections of mutually connected inclined planes, and the surface of the descending section is processed into three sections of mutually connected inclined planes; the ascending section is an airflow inlet, and the descending section is an airflow outlet; in the ascending section, the included angle theta between the first section inclined plane of the airflow inlet and the horizontal plane1Is 63.6 degrees and is inclined at a second sectionAngle theta between the plane and the horizontal plane2Theta is one half1The angle theta between the third section inclined plane and the horizontal plane3Theta is one half2Angle theta between the fourth inclined plane and the horizontal plane4Theta is one half3(ii) a The included angle between each section of inclined plane in the descending section and the horizontal plane is all positioned below the horizontal plane, so that each section of inclined plane is in a downward state, wherein the included angle theta between the fifth section of inclined plane connected with the fourth section of inclined plane in the ascending section and the horizontal plane5＝θ4(ii) a The sixth section of inclined surface is connected with the fifth section of inclined surface, and the included angle theta between the sixth section of inclined surface and the horizontal plane6＝2θ5(ii) a The seventh section of inclined surface is connected with the sixth section of inclined surface, and the included angle theta between the seventh section of inclined surface and the horizontal plane7＝2θ6。
CN202010452740.4A 2020-05-26 2020-05-26 Gas compressor based on impact type rotor-rotary stamping stator Pending CN111622963A (en)

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CN113513500A (en) * 2021-07-14 2021-10-19 南京航空航天大学 Low-loss diffusion vane profile with negative outlet airflow angle
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