WO2019196919A1 - Lame de forme d'onde trigonométrique à corde ultra-large - Google Patents

Lame de forme d'onde trigonométrique à corde ultra-large Download PDF

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Publication number
WO2019196919A1
WO2019196919A1 PCT/CN2019/082396 CN2019082396W WO2019196919A1 WO 2019196919 A1 WO2019196919 A1 WO 2019196919A1 CN 2019082396 W CN2019082396 W CN 2019082396W WO 2019196919 A1 WO2019196919 A1 WO 2019196919A1
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WO
WIPO (PCT)
Prior art keywords
blade
waveform
cotangent
ultra
tangent
Prior art date
Application number
PCT/CN2019/082396
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English (en)
Chinese (zh)
Inventor
向兵
Original Assignee
深圳福世达动力科技有限公司
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Publication of WO2019196919A1 publication Critical patent/WO2019196919A1/fr

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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
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F04D29/386—Skewed 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/305—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the pressure side of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade

Definitions

  • the invention belongs to the field of fluid machinery, and relates to a blade of an impeller type compressor, in particular to an ultra-wide-string trigonometric waveform blade.
  • Impeller type compressors are generally divided into two types: radial flow type (ie centrifugal type) and axial flow type according to the direction of working fluid flow.
  • the centrifugal compressor has small volume, high impeller speed, high single-stage pressure ratio but low efficiency. It is usually suitable for medium and small flow applications and is widely used in power systems such as aviation and ships.
  • the axial flow compressor is compact in structure, easy to install more stages, single stage pressure is lower, and overall efficiency is higher, which is usually suitable for occasions with large flow.
  • the blades of the impeller compressor are usually divided into a moving blade and a stationary blade, wherein the moving blade rotates with the impeller, and the moving blade works on the gas working fluid to increase the pressure of the gaseous working fluid, and the stationary blade is stationary, and does not work on the gas working fluid.
  • the airflow working fluid is decelerated, diffused, and guided. Whether it is a moving blade or a stationary blade, its blade profile design has an important influence on the efficiency of the compressor.
  • the current axial flow compressor blade blade shape is usually a circular arc shape, and the blade blade is usually only suitable for working in Asia. With the speed of sound and transonic speed, as the Mach number of the working fluid gas rises, various flow losses such as separation of the surface layer in the flow channel increase rapidly, and the efficiency usually decreases rapidly, thereby limiting the further improvement of the single-stage pressure ratio.
  • the compressor has a long blade shape and is an ultra-wide-chord type.
  • the blade constructed with this type of blade belongs to an ultra-wide-chord blade.
  • the invention adopts a trigonometric function tangent or cotangent waveform curve surface to replace the traditional circular arc surface, and can obtain higher compression efficiency, and the axial flow compressor blade of the profile can obviously improve the single-stage compression ratio, and this
  • the profile is applied to the design of the bucket and diffuser blades of the centrifugal compressor, which can effectively improve the compression efficiency and has broad application prospects.
  • the blade can be regarded as being stacked by the blade type. Below we will first explain the blade shape of the blade, and then how to construct the blade from the blade shape.
  • An ultra-wide-string trigonometric waveform blade characterized in that the pressure surface of the blade leaf type is designed as a trigonometric tangent or a cotangent waveform curve structure, specifically whether the tangent or the cotangent is determined by the oblique direction of the airfoil, and the rightly inclined leaf
  • the type uses the cotangent waveform curve
  • the left-inclined leaf type uses the tangent waveform curve. Since the tangent or cotangent waveform curve is infinitely long and the length of the leaf type is limited, a section of the waveform curve is usually intercepted as a leaf type as needed.
  • the pressure surface; the tangent or cotangent waveform is periodic, the middle portion of each period is a curved arc, and the curvature of both sides is gradually reduced and gradually approaches the straight line.
  • the length of the tangential or cotangent waveform curve is intercepted from the middle of one cycle, and the lengths of the two ends are usually different. The interception is performed according to the design requirements. Generally, the higher the Mach number, the higher the curve.
  • the longer the back-end retention segment the smaller the folding angle of the inlet airflow to the outlet airflow becomes. The functional power will be reduced, so the length of the back-end reserved segment needs to strike a balance between power and efficiency.
  • the shape of the airfoil under the subsonic flow conditions and the shape of the airfoil under the supersonic flow conditions are also different.
  • the blade shape under subsonic flow conditions is generally slender, the thickness of the blade is usually not changed, and the waveform of the suction surface is similar or even the same.
  • the thickness of the leading edge of the blade is slightly thicker than the trailing edge. Generally designed as a small rounded structure, the trailing edge is generally designed as a pointed structure; the thickness of the blade type working under supersonic flow conditions is large, the first half of the blade is long and is designed as a sharp wedge structure.
  • the design can reduce the shock loss.
  • the thickness of the airfoil gradually increases from the leading edge to the middle. When the thickness is increased to the required thickness, the thickness of the downstream blade type generally decreases rapidly.
  • the pressure surface and suction surface of adjacent airfoils form a flow channel, and the shape of the airfoil under subsonic conditions and supersonic conditions is different, so the flow path will be different; under subsonic conditions
  • the flow channel is often designed as an expanded structure.
  • the inlet of the flow channel is a supersonic flow.
  • the first half of the flow path needs to be designed as a convergent structure, and the convergent flow channel is used to expand and lower the supersonic flow.
  • Speed when the incoming flow velocity is reduced to the speed of sound, the second half of the flow channel is designed as an expanded structure, which can further reduce the airflow velocity and further increase the static pressure. Therefore, the flow channel under the supersonic condition is first converged.
  • the expansion is a convergent expansion type flow passage, and the portion with the smallest flow area in the flow passage is generally called a throat. It should be noted that the convergent expansion type flow passage is mainly realized by changing the thickness of the blade type, and therefore, the height of the blade can be maintained. No change, or little change.
  • the design of the airfoil structure under subsonic conditions is relatively simple, because the thickness of the airfoil does not change much, and the waveforms of the suction and pressure surfaces of the blade are similar or even the same.
  • the suction surface design of the blade type under supersonic conditions is usually not unique. There are many different profile schemes, usually a smooth curve composed of multiple straight lines and arcs.
  • the pressure surface of the leaf type is the main working surface of the leaf type, and its profile is the main factor affecting the efficiency of the leaf type.
  • the suction has little influence on the efficiency, and there are various options available.
  • the pressure surface of the blade type of the present invention adopts a trigonometric function tangent or a cotangent waveform curve, the compression process of the airflow is smoother, so that a blade structure with high efficiency at subsonic speed can be designed; in the supersonic condition, the The waveform profile can avoid strong shock waves in the front-stage contraction flow channel, effectively reducing the negative factors such as shock-induced separation, eddy current, turbulence, etc., so it is also possible to design a high-efficiency airfoil structure under supersonic conditions; It is an ultra-wide-chord type, and the chord length is usually much longer than that of the existing axial-flow compressor, and it can work at a super-sonic condition with a higher Mach number, and the function can be greatly increased, so that the shaft can be
  • the suction side of the airfoil adopts another tangent or cotangent waveform of the same type as the pressure surface.
  • the period of this waveform is longer than the period of the pressure surface waveform, and there is a certain distance between the waveform of the pressure surface. If necessary, the angle of inclination can be different from the inclination angle of the waveform of the pressure surface.
  • the waveform of the suction surface and the waveform of the pressure surface are The leading and trailing edges of the leaf type intersect at two points. This design method of intersecting the two waveforms to obtain the airfoil can greatly reduce the complexity of the design of the suction surface of the airfoil, and the designed blade shape is generally more efficient.
  • the leaves are formed by stacking the leaves from the root to the tip of the blade. Since the line speeds of different leaf heights are different, the speed triangles will be different. Therefore, the installation angles of the leaf types at different leaf heights are usually different, and the leaf shapes can also be different. Therefore, the shape of the blades is usually distorted. .
  • One way to stack the leaf shape from the leaf root to the tip of the blade is to perform a straight line stacking.
  • This stacking method is relatively simple, and the leading edge of the blade is a straight line.
  • Another method is a curve stack, that is, there is a certain offset between the different leaf layers in the circumferential direction, and the leading edge of the blade is a curve.
  • a curve stack is employed, and specifically, the curve is a trigonometric sine or cosine waveform. From the root to the tip of the blade, the sine or cosine is usually stacked in a complete wave period. Considering the structural strength of the blade, the amplitude is usually not too large.
  • the sinusoidal or cosine wave blade structure is beneficial for converting the energy of the radial high-frequency wave in the working fluid in the blade channel into the static pressure of the working medium, and avoiding the multiple high-frequency radial waves being reflected and reflected between the top and bottom walls of the channel. For heat energy, the compression efficiency of the blade can be improved.
  • this swept-back blade design can effectively reduce the shock loss at the leading edge of the blade, while improving the performance of the blade strength and vibration.
  • the flow path formed by the ramjet inlet (diffuser), the aeroengine supersonic inlet and the impeller-type compressor impeller is similar. Therefore, the design of the supersonic inlet can be used for reference.
  • the design method of the profile in the present invention for example, when designing the profile structure of the rectangular inlet, two tangential or cotangent waveform curves can be used as the upper and lower profiles of the supersonic inlet, by changing the two waveforms. By changing the distance and phase difference between the two waveforms, the area of the inlet and the throat can be changed, and the requirements of different Mach numbers can be adapted.
  • the ultra-wide-string trigonometric waveform has high compression efficiency.
  • the application of such blades in axial flow and diagonal flow compressors can significantly improve the single-stage pressure ratio and reduce the number of compressor stages.
  • the ultra-wide-string trigonometric waveform blade can be used as the bucket and diffuser blades of the centrifugal compressor, which is beneficial to improve the efficiency of the centrifugal compressor.
  • the tangent or cotangent waveform curve surface used in the present invention can be applied not only to the impeller type compressor, but also to the ramjet intake port (diffuser) and the aeroengine supersonic inlet profile. designing.
  • FIG. 1 is a schematic view showing the structure of a blade leaf type of the present invention.
  • FIG. 2 is a schematic view showing the structure of a cascade of the present invention.
  • a blade type of a blade that can operate under supersonic flow conditions is provided.
  • the blade pressure face 2 and the leaf suction face 3 are two trigonometric cotangent waveforms.
  • the period of the waveform of the air pressure surface 2 is longer than the period of the waveform of the suction surface of the airfoil, and there is a certain distance between the two cotangent waveforms, both of which are inclined to the right and the two waveforms intersect.
  • the portion of the pressure surface 2 and the front of the suction surface 3 that are retained in the front is longer, and the two form a sharp wedge shape, which can be reduced.
  • the loss caused by the supersonic airflow shock is suitable for working under supersonic conditions.
  • Figure 2 shows a cascade structure formed by a plurality of leaf patterns in Figure 1, in which the pressure surface and the suction surface of the adjacent air type constitute a flow path, and the flow path includes the first half of the flow path 6,
  • the throat 7 and the second half of the flow passage 8 are three parts, wherein the first half of the flow passage 6 is convergent, that is, the flow area of the flow passage is gradually smaller, and the throat 7 is the portion with the smallest flow passage area, after the flow passage
  • the half section 8 is of the expansion type, that is, the flow area is gradually enlarged, and the first half of the flow passage 6, the throat 7, and the second half of the flow passage 8 constitute a convergent expansion type flow passage.
  • the pressure surface of the airfoil will work on the gas working fluid, and the total pressure of the gas working fluid will increase.
  • the gas working medium is compressed by the pressure surface of the contracting flow channel and the suction surface, and the supersonic gas flow medium usually passes through the converging flow channel.
  • Multiple weak shock waves ideally using isoltropic shock waves to perform isentropic compression on the airflow medium
  • the flow rate is gradually reduced, the static pressure is gradually increased, the speed at the throat 7 is reduced to the speed of sound, and then into the second half of the flow path.
  • the flow rate is further lowered and the static pressure is further increased.
  • the leaf shapes at different leaf heights are designed, and then these leaf shapes are stacked from the blade root to the tip of the blade, and stacked into a sinusoidal waveform. Because it is a supersonic blade, The leading edges of the blades are stacked into a swept-back structure, and the height of the blades is gradually increased to reduce the shock loss of the leading edge of the blades. After the stacking of the blades is completed, the leading edge of the blade is swept back. From the axial direction, the pressure surface and the suction surface of the blade are cotangent waveforms, and the blades are sinusoidal waveforms when viewed from the radial direction. For the second half of the blade, because the blade is thicker, in order to reduce the weight, the inner part of the blade is hollowed out while ensuring the strength of the pressure surface and the suction surface of the blade.

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

Abstract

L'invention concerne une lame de forme d'onde trigonométrique à corde ultra-large. La surface de pression du profil de pale de la pale est conçue sous la forme d'une structure de courbe de forme d'onde de tangente ou de cotangente trigonométrique. La courbe de forme d'onde tangente ou cotangente est utilisée comme surface du profil de lame, de telle sorte que non seulement la structure de lame dans une condition de travail subsonique peut être conçue, mais également la structure de lame dans une condition de travail supersonique peut être conçue. En particulier dans la condition de travail supersonique, des ondes de choc fortes dans un trajet d'écoulement d'un compresseur de gaz et de grandes pertes d'écoulement ainsi provoquées peuvent être efficacement évitées.
PCT/CN2019/082396 2018-04-12 2019-04-12 Lame de forme d'onde trigonométrique à corde ultra-large WO2019196919A1 (fr)

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CN201810324003.9A CN108425887A (zh) 2018-04-12 2018-04-12 超宽弦三角函数波形叶片
CN201810324003.9 2018-04-12

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Families Citing this family (6)

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Publication number Priority date Publication date Assignee Title
CN108425887A (zh) * 2018-04-12 2018-08-21 深圳福世达动力科技有限公司 超宽弦三角函数波形叶片
CN110864485A (zh) * 2019-12-20 2020-03-06 海信容声(广东)冰箱有限公司 一种低温储藏装置
CN111594277B (zh) * 2020-05-29 2023-02-10 安徽九州云箭航天技术有限公司 一种超音速涡轮用喷嘴叶片及其设计方法
CN114382727A (zh) * 2022-01-19 2022-04-22 集美大学 一种超音速轴流压气机及其叶片设计方法
CN115182788B (zh) * 2022-09-13 2022-12-20 中国航发沈阳发动机研究所 一种航空发动机单级涡轮气动构型
CN116753190B (zh) * 2023-08-23 2024-03-22 江苏乐科节能科技股份有限公司 一种带有中间静叶栅的串列式离心式压缩机叶轮

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US6164919A (en) * 1997-12-12 2000-12-26 Vanmoor; Arthur Propeller and impeller blade configuration
CN102509340A (zh) * 2011-10-09 2012-06-20 东华理工大学 一种基于变形的叶脉可视化造型方法
CN107480392A (zh) * 2017-08-25 2017-12-15 北京航空航天大学 一种基于椭圆非均匀变形的叶片造型方法
EP3256697A1 (fr) * 2015-02-09 2017-12-20 Safran Aircraft Engines Ensemble de redressement d'air de turbomachine à performances aerodynamiques améliorées
CN108425887A (zh) * 2018-04-12 2018-08-21 深圳福世达动力科技有限公司 超宽弦三角函数波形叶片
CN208138201U (zh) * 2018-04-12 2018-11-23 深圳福世达动力科技有限公司 超宽弦三角函数波形叶片

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US6095457A (en) * 1998-12-14 2000-08-01 Vanmoor; Arthur Airfoil and wing configuration
US6899525B2 (en) * 2002-07-22 2005-05-31 Arthur Vanmoor Blade and wing configuration
CN101182784B (zh) * 2007-12-03 2011-05-11 南京航空航天大学 应用于航空发动机的风扇/压气机的转子超声叶型的设计方法

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Publication number Priority date Publication date Assignee Title
US6164919A (en) * 1997-12-12 2000-12-26 Vanmoor; Arthur Propeller and impeller blade configuration
CN102509340A (zh) * 2011-10-09 2012-06-20 东华理工大学 一种基于变形的叶脉可视化造型方法
EP3256697A1 (fr) * 2015-02-09 2017-12-20 Safran Aircraft Engines Ensemble de redressement d'air de turbomachine à performances aerodynamiques améliorées
CN107480392A (zh) * 2017-08-25 2017-12-15 北京航空航天大学 一种基于椭圆非均匀变形的叶片造型方法
CN108425887A (zh) * 2018-04-12 2018-08-21 深圳福世达动力科技有限公司 超宽弦三角函数波形叶片
CN208138201U (zh) * 2018-04-12 2018-11-23 深圳福世达动力科技有限公司 超宽弦三角函数波形叶片

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