CN113217463A - Single-stage axial flow type turbo-charging mechanism - Google Patents

Single-stage axial flow type turbo-charging mechanism Download PDF

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Publication number
CN113217463A
CN113217463A CN202110681884.1A CN202110681884A CN113217463A CN 113217463 A CN113217463 A CN 113217463A CN 202110681884 A CN202110681884 A CN 202110681884A CN 113217463 A CN113217463 A CN 113217463A
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axial flow
rotor
airfoil
stator
rotating shaft
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Inventor
孙杨
熊步先
戴维
全勇
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Northwestern Polytechnical University
Taicang Yangtze River Delta Research Institute of Northwestern Polytechnical University
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Northwestern Polytechnical University
Taicang Yangtze River Delta Research Institute of Northwestern Polytechnical University
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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
    • F04D29/26—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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • 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
    • F04D29/40—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
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Abstract

The invention relates to a single-stage axial flow type turbo-charging mechanism, belonging to the field of engines; the device comprises an air inlet channel, an axial flow turbine rotor, an axial flow turbine stator and a power rotating shaft; one end of the power rotating shaft penetrates through the axial flow turbine stator to be coaxially connected with the axial flow turbine rotor, and the other end of the power rotating shaft is connected with a power source to obtain rotating power; the air inlet channel is an outer envelope surface of the whole single-stage axial flow type turbocharger mechanism; the axial flow turbine rotor is positioned at one end of an inlet of the air inlet channel and comprises a rotor fairing and a plurality of rotor blades, and the plurality of rotor blades are uniformly distributed on the peripheral surface of the fairing along the circumferential direction; the axial flow turbine stator comprises stator blades and a supporting structure; the plurality of stator blades are uniformly distributed on the annular wall between the supporting structure and the air inlet channel along the circumferential direction and are used for supporting the internal structure; the rotor mechanism rotates under the driving of the power rotating shaft, and the rotor blades do work on free incoming flow, so that the pressure intensity of the incoming flow is increased, and the flow speed is accelerated. The accelerated free incoming flow passes through the stator vanes, the speed is reduced, and the pressure is further increased.

Description

Single-stage axial flow type turbo-charging mechanism
Technical Field
The invention belongs to the field of engines, and particularly relates to a single-stage axial flow type turbocharger mechanism.
Background
The power device of the unmanned aerial vehicle can be divided into a turbofan engine, a motor, a piston type internal combustion engine and the like. The turbofan engine is suitable for the medium-short range high-altitude high-speed unmanned aerial vehicle, has higher requirements on cost and technical threshold, and is mainly used in the military field; the motor is suitable for the small low-altitude micro unmanned aerial vehicle with short endurance time, is low in cost and convenient to control, and is mainly used in the consumption field; the piston type internal combustion engine is suitable for long-endurance medium-high and medium-low speed unmanned aerial vehicles, has the characteristics of low cost, high reliability, good universality and wide application field, and is suitable for military and civil fields. At present, about 80% of medium and low altitude unmanned aerial vehicles in long endurance adopt piston type internal combustion engines.
Along with the rise of the flying height of the unmanned aerial vehicle, the atmospheric pressure and the temperature gradually fall, the air density is reduced, the content of oxygen is reduced, and the performance of the piston engine is seriously influenced. According to the standard atmospheric table, when the altitude rises from sea level to 3000m, the air density is from 1.225kg/m3The pressure is reduced to 0.9093kg/m3Only 74% of the air density at sea level; and when raised to an altitude of 7000m, the air density is only 43% of the air density at sea level. Under the working condition of high altitude, the quality of air sucked into the cylinder by the piston engine is seriously reduced, the oxygen content in the cylinder is low, the combustion condition in the cylinder of the engine is worsened, the fuel is insufficiently combusted, the afterburning loss is serious, the power performance of the engine is greatly reduced, the acceleration time is prolonged, and the maneuverability of the unmanned aerial vehicle is seriously influenced; the fuel economy is poor, the fuel consumption is obviously increased, the flight time of the unmanned aerial vehicle is shortened, and the piston engine is difficult to meet the requirements of China on the flight height of the unmanned aerial vehicle of more than 6000m and the long flight time.
In order to enable the unmanned aerial vehicle to meet the task requirement of high altitude long voyage, the air intake of the engine needs to be pressurized, so that the air intake density of the engine is improved, and the air quality entering an engine cylinder is increased. Because the mass of air in the cylinder is increased, the volume of the cylinder is unchanged, and the density of oxygen is increased, the combustion in the cylinder is more sufficient, the fuel economy of the engine is improved, and the effective efficiency of the engine is improved. Although the supercharging mode is more, the exhaust turbocharging mode is most widely researched and applied. The exhaust gas turbocharging technology is realized by a turbocharger, the turbocharger mainly comprises a turbine and a gas compressor, the exhaust gas of the engine is expanded in the turbine to do work during the work, the turbine is pushed to rotate, the energy in the exhaust gas is converted into the mechanical energy of the turbine, the turbine drives the gas compressor to rotate to do work on the air flowing through the gas compressor, and the pressure energy and the internal energy of the inlet air of the engine are increased to realize the purpose of supercharging.
Patent CN201010624489.1 discloses a turbocharger system comprising a first, relatively small High Pressure (HP) turbocharger and a second, relatively large Low Pressure (LP) turbocharger. The turbine of the low-pressure turbocharger is connected in series downstream of the turbine of the high-pressure turbocharger. The first exhaust bypass flow path is disposed around a bypass flow path of the high pressure turbine. The second exhaust bypass flow path provides a bypass flow path around the low pressure turbine. The rotary valve is located at the intersection of the first and second bypass flow paths and the first exhaust flow path. The rotary valve includes a valve rotor that selectively rotates to allow or block airflow to the low pressure turbine and to allow or block airflow to the first and second bypass flow paths. Patent CN200880114582.9 is a turbocharger system comprising a first relatively small turbocharger and a second relatively large turbocharger connected in series, and an exhaust flow control valve. The exhaust flow control valve has: an inlet in communication with the exhaust gas flow upstream of the first turbine; a first exhaust port in communication with the exhaust stream downstream of the first turbine but upstream of the second turbine; a second exhaust port in communication with the exhaust stream downstream of the second turbine. The valve is operable to selectively allow or block flow through the first and second discharge ports.
From the prior patent, in order to realize the pressurization design, the pressurization design of a multistage centrifugal compressor is generally adopted in the prior art, and the multistage compressor is utilized to realize continuous pressurization. Although the multi-stage supercharging mode can realize supercharging, the prior art has the defects of more compressor cascade, more complex part mechanism and larger weight.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a single-stage axial flow type turbo-charging mechanism, which replaces multi-stage centrifugal type compression with axial flow type compression, realizes that the multi-stage centrifugal type compression is replaced with single-stage turbo-charging, reduces the number of compression stages, reduces the total amount of parts and components and simultaneously reduces the weight of the turbo-charging mechanism.
The technical scheme of the invention is as follows: a single-stage axial flow type turbo supercharging mechanism is characterized in that: the device comprises an air inlet channel, an axial flow turbine rotor, an axial flow turbine stator and a power rotating shaft; one end of the power rotating shaft penetrates through the axial flow turbine stator to be coaxially connected with the axial flow turbine rotor, and the other end of the power rotating shaft is connected with a power source to obtain rotating power;
the air inlet channel is an outer envelope surface of the whole single-stage axial flow type turbocharger mechanism, and comprises an axial flow turbine rotor, an axial flow turbine stator and a power rotating shaft, and the air inlet channel can provide an inlet for sucking air for the turbocharger mechanism;
the axial flow turbine rotor is positioned at one end of an inlet of the air inlet channel and comprises a rotor fairing and rotor blades; the rotor fairing is in a cone shape and is coaxially arranged at the front end of the power rotating shaft, and the power rotating shaft drives the axial flow turbine rotor to rotate around the shaft; the roots of the plurality of rotor blades are fixed on the rotor fairing and are uniformly distributed along the circumferential direction; the axial flow turbine rotor gives the incoming flow motion energy through the high-speed rotating blades, so that the incoming flow speed of the blades is increased, and the pressure intensity is increased;
the axial flow turbine stator comprises stator blades and a support structure; the supporting structure is a centrosymmetric geometric body, is fixedly connected with the air inlet channel through a plurality of stator blades arranged along the circumferential direction and is used for supporting an internal structure; the roots of the stator blades are connected with the supporting structure and are uniformly distributed along the circumferential direction.
The further technical scheme of the invention is as follows: and a central through hole is formed in a central shaft of the supporting structure and is used for penetrating through the power rotating shaft.
The further technical scheme of the invention is as follows: the other end of the power rotating shaft is connected with a turbine or a mechanical device driven by waste gas and used for obtaining rotary power.
The further technical scheme of the invention is as follows: the rotor fairing and the supporting structure are combined to form an ellipsoidal structure.
The further technical scheme of the invention is as follows: the number of rotor blades and stator blades shown is 8.
The further technical scheme of the invention is as follows: the rotor blade root airfoil and tip airfoil are shown as NACA4412 airfoils.
The further technical scheme of the invention is as follows: the size limiting method of the chord length of the rotor blade root airfoil and the tip airfoil comprises the following steps: the radius of the air inlet pipe is set to be R, the radius of the propeller hub is selected to be 0.15R-0.2R, the spanwise length is selected to be 0.5R-0.7R, the reference chord length of the root part is selected to be 0.6R-0.8R, and the chord length of the tip part is selected to be 0.8R-1.6R.
The further technical scheme of the invention is as follows: the method for setting the torsion angle between the root part and the tip part of the rotor blade comprises the following steps: setting the radius of a hub to be 0.2R, the span-wise length of a blade to be 0.7R and the free incoming flow velocity to be V;
(1) setting the angular speed in the working state as theta and the unit as rad/s;
(2) the radius of the hub is 0.2R, the rotation radius of the root part is 0.2R, the local rotation speed is 0.2R theta, the rotation radius of the tip part is 0.9R, and the local rotation speed is 0.9R theta;
(3) the local airflow angle at the root of the airfoil is arcsin (0.2R theta/V), and the local airflow angle at the tip of the airfoil is arcsin (0.9R theta/V);
(4) setting the local angle of attack alpha of the root1The range is limited to 2-4 degrees, and the local incidence angle alpha of the tip2The range is limited to 6-12 degrees;
(5) the local mounting angle calculation formula is as follows: root mounting angle psi1＝α1Arcsin (0.2R θ/V), root setting angle ψ2＝α2-arcsin(0.9Rθ/V)。
The further technical scheme of the invention is as follows: the chord length of the airfoil at the root part of the rotor blade is 0.168m, the installation angle is minus 6 degrees, the chord length from the airfoil at the tip part is 0.115m, the chord length from the airfoil at the tip part is 0.28m, the installation angle is minus 28 degrees, and the chord length from the airfoil at the root part is 0.6m from the rotation center.
Advantageous effects
The invention has the beneficial effects that: the single-stage axial flow type turbo-charging mechanism only adopts single-stage axial flow type turbo-charging and comprises an axial flow turbine rotor and an axial flow turbine stator. The rotor mechanism rotates under the driving of the power rotating shaft, and the rotor blades do work on free incoming flow, so that the pressure intensity of the incoming flow is increased, and the flow speed is accelerated. The accelerated free incoming flow passes through the stator vanes, the speed is reduced, and the pressure is further increased. The axial-flow type compressed air replaces multi-stage centrifugal compressed air, so that single-stage turbine compressed air replaces multi-stage centrifugal compressed air, the compressed air stage number is reduced, the total amount of parts is reduced, and the weight of a supercharging mechanism is reduced.
Different from the axial-flow compressor of the traditional large-scale aero-engine, the air inlet flow of the piston engine does not flow and burn in the combustion chamber, but burns and collides to do work in the cylinder, so the incoming flow speed is low. The single-stage axial flow supercharging mechanism provided by the scheme needs to be designed by matching the rotating blades aiming at the problems of low incoming flow speed, low flowing Reynolds number and the like. The specific design principle is as follows:
(1) blade root design principle: according to the motion characteristics of the rotating machinery, the linear velocity is smaller when the rotating machinery is closer to the rotating center under the premise that the angular velocities are the same. Under the condition of the same incoming flow speed, the local rotation linear speed is low, and the local effective attack angle is small, so that a small installation angle, preferably 2-4 degrees, is arranged at the root of the blade, and the chord length direction of the root of the blade is ensured to be consistent with the incoming flow as much as possible. In addition, the effective attack angle of the root is small, and the supercharging capacity of the root is limited, so that the small airfoil chord length is set, and the design requirement of structural rigidity is only required to be ensured.
(2) Blade tip design principle: according to the motion characteristics of the rotating machinery, on the premise that the angular velocity is the same, the linear velocity is larger the farther away from the rotation center. Under the condition of the same incoming flow speed, the local rotating linear speed is low, and the local effective attack angle is large, so that a proper large installation angle, preferably 6-12 degrees, is arranged at the tip of the blade, and the local effective attack angle is guaranteed to be a positive value on one hand, and is guaranteed to be smaller than the stall attack angle on the other hand. In addition, the tip effective attack angle is large, and the supercharging capacity is high, so that the large airfoil chord length is set, but the structural rigidity and the elastic design requirements need to be ensured.
According to the design principle, the axial flow supercharging structure of the embodiment of the invention is provided, and the chord length of the airfoil at the root part of the rotating blade of the embodiment of the supercharging structure is 0.168m, the installation angle is-6 degrees and is 0.115m away from the rotation center, the chord length at the tip part is 0.28m, the installation angle is-28 degrees and is 0.6m away from the rotation center. When the rotation speed of the free incoming flow is 20m/sqie and is 500rpm, namely 1000 revolutions per minute, the local angular speed of the blade root is 25.6ad/s, the local rotation linear speed is 3m/s, the local effective attack angle is 3 degrees, the local angular speed of the blade tip is 25.6ad/s, the local rotation linear speed is 15.36m/s, and the local effective attack angle is 10 degrees. The airflow conditions of the blades all meet the design expectation and the design constraint.
The axial flow turbine can be subjected to parameter range selection according to the design principle aiming at different incoming flow conditions and structural dimensions, and four key parameters including the chord length of the blade root, the installation angle of the blade root, the chord length of the blade tip and the installation angle of the blade tip are mainly determined according to geometric dimensions.
In order to check the supercharging effect of the single-stage axial flow type turbocharger mechanism, the invention adopts a CFD numerical simulation method to calculate the supercharging performance of the turbocharger mechanism of the embodiment. Firstly, the ICEM CFD commercial software is adopted to divide the single-stage axial flow type turbocharger mechanism grids, and because turbocharging belongs to the problem of rotating machinery, the grid division adopts a division method of a rotating domain and a static domain, and non-mechanism grids are adopted for grid generation. The calculation tool adopts CFX commercial software, the control equation is an RANS equation, and the pneumatic calculation method of the rotary machine is an MRF method. The free incoming flow speed is 20m/s, and the rotating speed of the bladesAt 500rpm, and an atmospheric density of 1.225kg/m3Atmospheric pressure was 1 apm.
The simulation data is shown in table 1 and the flow field calculation results are shown in fig. 6. The calculation result shows that after the free incoming flow enters the air inlet port, the free incoming flow is accelerated to flow to the axial flow turbine rotor under the suction action of the axial flow turbine rotor, and before reaching the paddle disk, the speed is increased and the pressure is reduced. When the airflow contacts with the rotor blade, on one hand, the local effective attack angle of the airflow on the blade is a positive value, a low-pressure area is generated at the front edge of the blade, and a high-pressure area is formed at the rear edge of the blade, and on the other hand, the rotor blade actively applies work to the airflow under the driving of a rotary machine, the speed of the airflow is increased, and the pressure is increased, so that the rotor supercharging process is completed. Due to the arrangement of the torsion angle, the effective attack angle of each part of the blade is small, the effect of supporting is achieved, and the effective attack angle of the tip part of the blade is large, so that the air flow can be well acted. When the airflow flows through the rotor blades and flows into the stator blade area, the airflow is expanded in an isentropic mode, the speed is reduced, the pressure is increased, and the stator pressurization is completed. After two pressure increases, the gas flow increases from 1atm of free incoming flow to 1.4apm, reaching 1.6atm at the outlet, corresponding to a pressure coefficient Cp of 2. The pressure of the gas supplied to the intake port of the engine is increased, contributing to an improvement in the operating efficiency of the engine.
TABLE 1 CFD simulation datasheet for single-stage axial-flow turbocharger mechanism
Parameter name Air inlet In front of the rotor Behind the rotor Behind the stator An outlet
Coefficient of pressure 1atm 0.9atm 1.2atm 1.4atm 1.6atm
Drawings
FIG. 1 is a schematic diagram of a single stage axial flow turbocharger mechanism employed in an embodiment of the present invention;
FIG. 2 is a three-view illustration of a single stage axial flow turbocharger mechanism employed in an embodiment of the present invention; wherein, a is a front view, b is a side view, and c is a top view;
FIG. 3 is a three-dimensional view of an axial turbine rotor employed in an embodiment of the present invention; wherein a is a front view, b is a side view, and c is a top view;
FIG. 4 is a three-dimensional view of an axial flow turbine stator employed in an embodiment of the present invention; wherein a is a front view, b is a side view, and c is a top view;
FIG. 5 is a CFD computational grid used in the embodiments of the present invention, where a is a rotating domain computational grid and b is a stationary domain computational grid;
fig. 6 is a CFD numerical simulation result of the single-stage axial flow turbocharger mechanism employed in the embodiment of the present invention, where a is a velocity field cloud chart and b is a pressure coefficient cloud chart.
Description of the figures: 1. an axial flow turbine rotor; 2. an air inlet channel; 3. an axial flow turbine stator; 4. a power shaft; 5. a rotor fairing; 6. a rotor blade; 7. a stator vane; 8. a support structure.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
Referring to the drawings, the single-stage axial flow turbocharger mechanism of the present embodiment is an axisymmetric mechanism. The intake duct is the cylinder, and entry and export cross-section are circular, intake duct cylinder generating line and booster mechanism symmetry coincidence. The axial flow turbine rotor is an axisymmetric geometric body and comprises a rotor fairing and eight rotor blades, and the symmetry axis of the axial flow turbine rotor is coincided with the symmetry axis of the supercharging mechanism. The axial flow turbine stator is an axisymmetrical geometric body and comprises a supporting structure and eight stator blades, and the symmetric axis of the axial flow turbine stator is coincided with the symmetric axis of the supercharging mechanism. The power rotating shaft is a cylinder, and a power rotating shaft bus coincides with a symmetrical axis of the supercharging mechanism.
Different from the axial-flow compressor of the traditional large-scale aero-engine, the air inlet flow of the piston engine does not flow and burn in the combustion chamber, but burns and collides to do work in the cylinder, so the incoming flow speed is low. The single-stage axial flow supercharging mechanism provided by the scheme needs to be designed by matching the rotating blades aiming at the problems of low incoming flow speed, low flowing Reynolds number and the like. The specific design principle is as follows:
(1) blade root design principle: according to the motion characteristics of the rotating machinery, the linear velocity is smaller when the rotating machinery is closer to the rotating center under the premise that the angular velocities are the same. Under the condition of the same incoming flow speed, the local rotation linear speed is low, and the local effective attack angle is low, so that a small installation angle is arranged at the root of the blade, generally 2-4 degrees, and the chord length direction of the root of the blade is ensured to be consistent with the incoming flow as much as possible. In addition, the effective attack angle of the root is small, and the supercharging capacity of the root is limited, so that the small airfoil chord length is set, and the design requirement of structural rigidity is only required to be ensured.
(2) Blade tip design principle: according to the motion characteristics of the rotating machinery, on the premise that the angular velocity is the same, the linear velocity is larger the farther away from the rotation center. Under the condition of the same incoming flow speed, the local rotating linear speed is low, and the local effective attack angle is large, so that a large installation angle with a proper angle is arranged at the tip of the blade, generally 6-12 degrees, on one hand, the local effective attack angle is guaranteed to be a positive value, and on the other hand, the local attack angle is guaranteed to be smaller than the stall attack angle. In addition, the tip effective attack angle is large, and the supercharging capacity is high, so that the large airfoil chord length is set, but the structural rigidity and the elastic design requirements need to be ensured.
The size limiting method comprises the following steps: the radius of the pipeline is set to be R, the radius of the propeller hub is selected to be 0.15R-0.2R, the spanwise length is selected to be 0.5R-0.7R, the reference chord length of the root part is selected to be 0.6R-0.8R, and the chord length of the tip part is selected to be 0.8R-1.6R.
The torsion angle setting method comprises the following steps: setting the radius of a hub to be 0.2R, the span-wise length of a blade to be 0.7R and the free incoming flow velocity to be V;
(1) setting the angular speed in the working state as theta and the unit as rad/s;
(2) the radius of the hub is 0.2R, the rotation radius of the root part is 0.2R, the local rotation speed is 0.2R theta, the rotation radius of the tip part is 0.9R, and the local rotation speed is 0.9R theta;
(3) the local airflow angle at the root of the airfoil is arcsin (0.2R theta/V), and the local airflow angle at the tip of the airfoil is arcsin (0.9R theta/V);
(4) setting the local angle of attack alpha of the root1The range is limited to 2-4 degrees, and the local incidence angle alpha of the tip2The range is limited to 6-12 degrees;
(5) the local mounting angle calculation formula is as follows: root mounting angle psi1＝α1Arcsin (0.2R θ/V), root setting angle ψ2＝α2-arcsin(0.9Rθ/V)。
According to the design principle and the calculation method, the axial flow supercharging structure of the embodiment of the invention is provided, and the chord length of the airfoil at the root part of the rotating blade of the supercharging structure of the embodiment is 0.168m, the installation angle is-6 degrees, the distance from the rotating center is 0.115m, the chord length at the tip part is 0.28m, the installation angle is-28 degrees, and the distance from the rotating center is 0.6 m. When the free incoming flow is 20m/s and the rotating speed is 500rpm, namely 1000 revolutions per minute, the local angular velocity of the blade root is 25.6ad/s, the local rotating linear velocity is 3m/s, the local effective attack angle is 3 degrees, the local angular velocity of the blade tip is 25.6ad/s, the local rotating linear velocity is 15.36m/s, and the local effective attack angle is 10 degrees. The airflow conditions of the blades all meet the design expectation and the design constraint.
The axial flow turbine can be subjected to parameter range selection according to the design principle aiming at different incoming flow conditions and structural dimensions, and four key parameters including the chord length of the blade root, the installation angle of the blade root, the chord length of the blade tip and the installation angle of the blade tip are mainly determined according to geometric dimensions.
In this embodiment, the foremost point of the rotor fairing is taken as the origin of the coordinate system and is denoted as O. And establishing a right-hand coordinate system for describing geometric parameters of the single-stage axial flow type turbocharger mechanism at a point O, wherein an x axis is positioned in a symmetrical plane of the turbocharger mechanism, a vector direction points to the center of a circle of an outlet section from the center of a circle of an inlet section, a z axis is positioned in the symmetrical plane of the turbocharger mechanism and is vertically upward, and a y axis is perpendicular to an x-z plane and points to the right side of the turbocharger mechanism and meets the right-hand rule.
The intake duct is the cylinder, and entry and export cross-section are circular, intake duct cylinder generating line and booster mechanism symmetry coincidence. The radius of the cylinder of the air inlet channel is 0.8m, the length of the generatrix is 2m, the inlet and outlet cross sections of the air inlet channel are parallel to a y-z plane, and the center coordinate of the inlet cross section of the air inlet channel is (-0.2,0,0) and the generatrix of the air inlet channel is coincident with the axis of Ox.
The axial flow turbine rotor is an axisymmetric geometric body and comprises a rotor fairing and eight rotor blades, and the symmetry axis of the axial flow turbine rotor is coincided with the symmetry axis of the supercharging mechanism. The coordinates of the most front end points of the rotor fairing are (0,0,0), the cross sections along the y-z direction are all circular, the coordinates of discrete points of a profile curve along the x-z direction are shown in the table, and the rotor fairing is in an axisymmetric pattern, so that the geometry of the rotor fairing can be formed by rotating the curve. The eight rotor blades are axisymmetrically distributed with respect to the rotor fairing, and therefore, only one of them will be described in this embodiment, and the remaining blades can be rotated by the current blade. The rotor blade is formed by dividing a rotor blade wing by a rotor fairing. The blade wing is a wing containing a torsion angle, and has no sweepback angle, dihedral angle and mounting angle. The section airfoil profile close to one side of the fairing and the section airfoil profile far away from one side of the fairing both adopt NACA4412 airfoil profiles, the coordinates of the leading edge point of the airfoil profile close to one side of the rotor fairing of the blade are (0.0954,01176,0), the chord length of the airfoil profile close to one side of the fairing of the rotor blade is 0.16m, and the chord length of the section airfoil profile far away from one side of the fairing is 0.28 m. The spanwise length of the rotor blade is 0.48m, the leading edge line of the blade airfoil is in the x-y plane of the straight line and the vector direction is parallel to the Oy axis. The torsion angle of the profile airfoil on the side far away from the fairing relative to the profile airfoil on the side close to the fairing is-35 degrees. The trailing edge of the blade wing is formed by adopting a sample line, and the molded surface is formed by adopting a multi-section curved surface.
TABLE 2 coordinate data table of longitudinal section of rotor fairing
Figure BDA0003123173530000091
Figure BDA0003123173530000101
The axial flow turbine stator is an axisymmetrical geometric body and comprises a supporting structure and eight stator blades, and the symmetric axis of the axial flow turbine stator is coincided with the symmetric axis of the supercharging mechanism. The cross sections of the supporting structures along the y-z direction are circular, and the coordinates of the circle center of the circular cross section at the foremost end are (0.36,0, 0). The coordinates of the discrete points of the cross-sectional curve of the support structure in the x-z direction are shown in table 2, and since the support structure is an axisymmetric figure, the support structure can be rotated from the curve. The 8 stator blades are distributed axisymmetrically with respect to the support structure, so that only one of them will be described in this embodiment, and the remaining blades can be obtained by the current blade rotation. The stator blade is obtained by dividing a stator blade wing by a supporting structure, and the stator blade wing is a straight wing without a torsion angle, a sweep angle, a dihedral angle and a mounting angle. The point coordinates of the leading edge of the profile airfoil on the side close to the supporting structure are (0.452, 0.269-0.000037), the chord length of the profile airfoil on the side close to the supporting structure of the stator blade wing is 0.24m, and the chord length of the profile airfoil on the side far from the supporting structure is 0.24 m. The spanwise length of the stator vane machine is 0.36m, the leading edge line of the vane wing is in a straight line x-y plane, and the vector direction is parallel to the Oy axis. The trailing edge of the blade wing is formed by adopting a sample line, and the molded surface is formed by adopting a multi-section curved surface.
Table 3 longitudinal section coordinate data table of support structure
Figure BDA0003123173530000111
Figure BDA0003123173530000121
Figure BDA0003123173530000131
Figure BDA0003123173530000141
The power rotating shaft is a cylindrical rod with the diameter of 8mm, the front end of the power rotating shaft is connected with the axial flow turbine rotor, the middle of the power rotating shaft penetrates through the axial flow turbine stator, and the rear end of the power rotating shaft is connected with the exhaust gas turbine.
The single-stage axial flow type turbo-charging mechanism replaces centrifugal air compression with axial flow air compression, and only is suitable for the single-stage air compression mechanism to realize turbo-charging. After the free incoming flow passes through the rotor, the rotor applies work to the free incoming flow, so that the incoming flow speed is accelerated, and the pressure intensity is increased. Furthermore, the air current gets into the stator behind the rotor, because the stator appearance is the shrink form, consequently, the flow tube is the expansion state, and the air current flows through the expansion pipeline, further speed reduction pressure boost, after twice pressure boost, has reached better pressure boost effect. The single-stage axial flow type turbo supercharging mechanism only adopts one-stage vorticity supercharging, has the advantages of single-stage air compression, simplicity and portability, and effectively solves the defects of multiple stages, complex mechanism and larger weight of an air compression mechanism in the prior patents such as CN201010624489.1 and the like.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims (9)

1. A single-stage axial flow type turbo supercharging mechanism is characterized in that: the device comprises an air inlet channel, an axial flow turbine rotor, an axial flow turbine stator and a power rotating shaft; one end of the power rotating shaft penetrates through the axial flow turbine stator to be coaxially connected with the axial flow turbine rotor, and the other end of the power rotating shaft is connected with a power source to obtain rotating power;
the air inlet channel is an outer envelope surface of the whole single-stage axial flow type turbocharger mechanism, and comprises an axial flow turbine rotor, an axial flow turbine stator and a power rotating shaft, and the air inlet channel can provide an inlet for sucking air for the turbocharger mechanism;
the axial flow turbine rotor is positioned at one end of an inlet of the air inlet channel and comprises a rotor fairing and rotor blades; the rotor fairing is in a cone shape and is coaxially arranged at the front end of the power rotating shaft, and the power rotating shaft drives the axial flow turbine rotor to rotate around the shaft; the roots of the plurality of rotor blades are fixed on the rotor fairing and are uniformly distributed along the circumferential direction; the axial flow turbine rotor gives the incoming flow motion energy through the high-speed rotating blades, so that the incoming flow speed of the blades is increased, and the pressure intensity is increased;
the axial flow turbine stator comprises stator blades and a support structure; the supporting structure is a centrosymmetric geometric body, is fixedly connected with the air inlet channel through a plurality of stator blades arranged along the circumferential direction and is used for supporting an internal structure; the roots of the stator blades are connected with the supporting structure and are uniformly distributed along the circumferential direction.
2. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: and a central through hole is formed in a central shaft of the supporting structure and is used for penetrating through the power rotating shaft.
3. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the other end of the power rotating shaft is connected with a turbine or a mechanical device driven by waste gas and used for obtaining rotary power.
4. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the rotor fairing and the supporting structure are combined to form an ellipsoidal structure.
5. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the number of rotor blades and stator blades shown is 8.
6. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the rotor blade root airfoil and tip airfoil are shown as NACA4412 airfoils.
7. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the size limiting method of the chord length of the rotor blade root airfoil and the tip airfoil comprises the following steps: the radius of the air inlet pipe is set to be R, the radius of the propeller hub is selected to be 0.15R-0.2R, the spanwise length is selected to be 0.5R-0.7R, the reference chord length of the root part is selected to be 0.6R-0.8R, and the chord length of the tip part is selected to be 0.8R-1.6R.
8. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the method for setting the torsion angle between the root part and the tip part of the rotor blade comprises the following steps: setting the radius of a hub to be 0.2R, the span-wise length of a blade to be 0.7R and the free incoming flow velocity to be V;
(1) setting the angular speed in the working state as theta and the unit as rad/s;
(2) the radius of the hub is 0.2R, the rotation radius of the root part is 0.2R, the local rotation speed is 0.2R theta, the rotation radius of the tip part is 0.9R, and the local rotation speed is 0.9R theta;
(3) the local airflow angle at the root of the airfoil is arcsin (0.2R theta/V), and the local airflow angle at the tip of the airfoil is arcsin (0.9R theta/V);
(4) setting the local angle of attack alpha of the root1The range is limited to 2-4 degrees, and the local incidence angle alpha of the tip2The range is limited to 6-12 degrees;
(5) the local mounting angle calculation formula is as follows: root mounting angle psi1＝α1Arcsin (0.2R θ/V), root setting angle ψ2＝α2-arcsin(0.9Rθ/V)。
9. The single-stage axial flow turbocharger mechanism according to claim 1, characterized in that: the chord length of the airfoil at the root part of the rotor blade is 0.168m, the installation angle is minus 6 degrees, the chord length from the airfoil at the tip part is 0.115m, the chord length from the airfoil at the tip part is 0.28m, the installation angle is minus 28 degrees, and the chord length from the airfoil at the root part is 0.6m from the rotation center.
CN202110681884.1A 2021-06-19 2021-06-19 Single-stage axial flow type turbo-charging mechanism Pending CN113217463A (en)

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CN114491805A (en) * 2022-01-14 2022-05-13 成都飞机工业（集团）有限责任公司 Method for designing intersection point hole of non-normal columnar joint of partition frame of airplane

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