WO2017063576A1 - 一种离心式压缩机补气结构及压缩机 - Google Patents

一种离心式压缩机补气结构及压缩机 Download PDF

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Publication number
WO2017063576A1
WO2017063576A1 PCT/CN2016/102040 CN2016102040W WO2017063576A1 WO 2017063576 A1 WO2017063576 A1 WO 2017063576A1 CN 2016102040 W CN2016102040 W CN 2016102040W WO 2017063576 A1 WO2017063576 A1 WO 2017063576A1
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Prior art keywords
air
air supply
centrifugal compressor
passage
return
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PCT/CN2016/102040
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English (en)
French (fr)
Inventor
蒋楠
张治平
钟瑞兴
蒋彩云
谢蓉
刘建飞
陈玉辉
黄保乾
张竞
周义
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珠海格力电器股份有限公司
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Application filed by 珠海格力电器股份有限公司 filed Critical 珠海格力电器股份有限公司
Priority to EP16854952.5A priority Critical patent/EP3364044B1/en
Priority to US15/768,371 priority patent/US10544799B2/en
Publication of WO2017063576A1 publication Critical patent/WO2017063576A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. 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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage 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
    • F04D29/42—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
    • F04D29/66—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
    • 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
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection

Definitions

  • the invention relates to the field of compressors, and in particular to a gas-filling structure of a centrifugal compressor and a compressor having the same.
  • the air supply method can be a single point of qi, or a 360° ring qi. Single point qi will cause local turbulent loss, resulting in a certain efficiency waste, the use range is relatively limited, and the 360° annular qi can be better integrated with the previous stage impeller to make the air flow more uniform, the maximum degree Reduce turbulence losses to improve cycle efficiency.
  • the present invention provides a plenum structure for a centrifugal compressor capable of effectively preventing mixing of a gas in a gas supply and a gas in an air passage to generate a turbulent flow loss.
  • An air-filling structure for a centrifugal compressor includes an annular air supply passage for introducing a supplemental airflow into an air passage of the compressor, wherein the annular air supply passage is provided with an air flow guiding assembly, and the air flow guiding assembly is used Adjusting a direction in which the inflating airflow flows into the air passage, so that an angle between a direction when the inflating airflow flows into the air passage and a direction of the airflow in the air passage is Set within the scope.
  • the preset range is -5° to 5°.
  • the airflow guiding assembly includes at least one set of guide vanes arranged along a circumferential direction of the annular supplemental passage.
  • the guide vane is in the shape of a flat plate whose inclination direction is the same as that of the return nozzle of the compressor;
  • the guide vanes are helical in shape and have the same direction of rotation as the return vanes of the compressor.
  • guide vanes are located outside the radial direction of the return vane as viewed in the axial direction of the impeller;
  • the guide vanes are disposed on a spiral extending outward in a spiral direction of the return vane, or the guide vanes are spaced apart from the return vane.
  • opposite sides of the guide vane are respectively connected to the inner wall of the annular air supply passage.
  • the thickness of the guide vanes is the same as the thickness of the return vanes.
  • the number of the guide vanes is the same as the number of the return vanes.
  • the air supply outlet of the air passage is disposed at an inlet curve of the return flow and/or an inlet of the lower stage impeller, and the guide vane is disposed adjacent to the air supply outlet.
  • the present invention also provides a compressor having high cycle efficiency, wherein the compressor has a qi structure as described above.
  • the air supply structure of the centrifugal compressor provided by the present invention is provided with an air flow guiding component in the annular air supply passage, and the airflow guiding component adjusts the direction of the inflating airflow flowing into the air passage, so that the inflating airflow flows into the air passage.
  • the angle between the direction and the direction of the airflow in the air passage is within a predetermined range, thereby maximally avoiding the turbulent loss generated when the two gases are fused, thereby improving the cycle efficiency.
  • the compressor provided by the present invention greatly improves the cycle efficiency by adopting the above-mentioned air supply structure.
  • FIG. 1 is a schematic structural view of a gas-filling structure of a centrifugal compressor according to an embodiment of the present invention
  • FIG. 2 is a second structural schematic view of a gas-filling structure of a centrifugal compressor according to an embodiment of the present invention
  • FIG. 3 is a schematic view showing a positional relationship between a guide vane and a return vane blade on a plane perpendicular to a compressor axis according to an embodiment of the present invention
  • FIG. 4 is a second schematic view showing the positional relationship between the guide vane and the return vane on a plane perpendicular to the axis of the compressor according to an embodiment of the present invention
  • FIG. 5 is a view showing an angle range between a direction when a supplemental airflow flows into an air passage and a direction of a gas flow in an air passage in the air supply structure of the centrifugal compressor according to the embodiment of the present invention.
  • the present invention provides a centrifugal compressor air entrainment structure including an annular air supply passage for introducing a supplemental air flow into an air passage of the compressor, and an air flow guide assembly disposed in the annular air supply passage.
  • the gas passage is a passage through which the gas in the compressor flows.
  • the airflow guiding component adjusts the direction of the inflating airflow into the airway, so that the angle between the direction of the inflating airflow into the airway and the direction of the airflow in the airway is within a preset range, avoiding two paths
  • the turbulent flow loss generated when the gas is fused increases the circulation efficiency.
  • the smaller the preset range the more the turbulent flow loss can be reduced.
  • the preset angle between the direction when the inflating airflow flows into the air passage and the airflow direction b in the air passage is a range of -5 to 5, specifically, the air supply.
  • the angle between the deviation a in the direction of flowing into the air passage and the direction b of the air flow in the air passage is 5°, and the deviation c in the direction when the supplementary air flows into the air passage and the direction b in the air passage b The angle between them is -5°.
  • the airflow guiding assembly includes a set of guide vanes arranged in the circumferential direction of the annular supplemental passage.
  • the guide vanes are evenly arranged in the annular air supply passage, and a passage of the supplementary air flow is formed between the adjacent two guide vanes, and the direction of the supplementary air flow is changed under the guiding action of the adjacent two guide vanes.
  • the shape of the guide vanes may be, but not limited to, a flat plate shape or a spiral shape, and may have a guiding action to change the shape of the direction of the insufflation gas flow. Further, if the guide vane is in the shape of a flat plate, the direction of the tilt is the same as the direction of the return vane of the compressor. If the guide vane is spiral, the direction of rotation is the same as that of the return vane of the compressor. Very good diversion effect.
  • the compressor includes a casing 1 and an impeller 2, a diffuser 3, and a reflux unit 4 disposed in the casing 1, and is formed by the impeller 2, the diffuser 3, and the reflux unit 4.
  • Air passage 5 The annular air supply passage 6 communicates with the air passage 5 through the air supply outlet 62.
  • the air supply outlet 62 can be disposed at the inlet curve of the returning device 4 as shown in FIG.
  • the annular air supply passage 6 is disposed in the diffuser 3 and Between the returning devices 4, and by the wall surfaces of the outer casing 1, the diffuser 3 and the returning device 4, the air supply inlet 61 of the annular air supply passage 6 is disposed on the outer peripheral wall of the returning device 4, and the air supply flow is self-compensating.
  • the gas inlet 61 enters the annular air supply passage 6 and flows into the air passage 5 through the air supply outlet 62.
  • it may be disposed at the inlet of the lower stage impeller as shown in FIG. 2, and the air inlet 61 is disposed at the return air inlet 4.
  • the annular air supply passage 6 extends radially inward from the air supply inlet 61 to the air passage 5.
  • the guide vanes 7 are disposed close to the air supply outlet 62, and the guiding effect is better.
  • the number and arrangement of the guide vanes 7 are not limited, and the effect of adjusting the direction of the supplemental gas flow can be achieved.
  • the guide vanes 7 are located outside the radial direction of the return vane 41 as viewed in the axial direction of the impeller. .
  • the guide vanes 7 are disposed on a spiral extending outward in the spiral direction of the return vane 41, or as shown in FIG. 4, the guide vanes 7 are spaced apart from the return vane 41.
  • the spacing arrangement described herein means that the radially inward end of the guide vanes 7 is located between adjacent return vanes 41. Both of the above arrangement methods can achieve a good homogenization and guiding effect on the makeup gas flow.
  • the radially outward ends of the guide vanes 7 are all located on the same circle, and the radially inward ends of the guide vanes 7 are also located on the same circle.
  • the guide vanes 7 are disposed integrally with the returning device 4, and the opposite sides of the guide vanes 7 and the annular air supply passage 6 are respectively formed.
  • the inner wall connection can be used as the guide vane 7 and can also be used as a reinforcing rib to increase the structural strength and improve the reliability of the compressor.
  • the guide vanes 7 and the inner wall of the annular air supply passage 6 are smoothly transitioned by a curved surface to further improve the flow guiding effect and the reliability of the structure.
  • the guide vane 7 should not be too thick when casting, nor too thin, too thick will produce a large friction loss, and a large wake loss occurs at the tail of the blade, which has a great influence on performance, and is too thin to be cast.
  • the thickness of the guide vanes 7 is similar or identical to the thickness of the return vanes 41.
  • the number of guide vanes 7 should not be too much or too little, too much will increase the resistance of the inflated airflow, affecting the effect of supplemental air, and too little, the effect of diversion is poor.
  • the number of guide vanes 7 is from 12 to 18, generally in accordance with the number of return vanes 41. When the diameter is larger, the number of the guide vanes 7 takes a larger value, and vice versa.
  • the guide vanes are not limited to one group, and two or more sets of guide vanes may be provided in consideration of factors such as the effect of the diversion and the size of the compressor, and the setting manner is similar to that of the above-mentioned guide vanes, and no longer Narration.
  • the airflow guiding component is not limited to being a guide vane, and other structures capable of changing the direction of the inflating airflow, such as a bump, a guiding groove, and the like.
  • the present invention also provides a compressor having the air supply structure of the centrifugal compressor as described above, which greatly improves the cycle efficiency and structural reliability of the compressor.
  • first, second, third, etc. may be used to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be Terminology restrictions. These terms may be only used to distinguish one element, component, region, layer or section from another element, region, layer or section. Terms such as “first”, “second” and other numerical terms when used herein do not denote an order or order unless the context clearly dictates. Thus, a first element, component, region, layer or section discussed below may be referred to as a second element, component, region, layer or section without departing from the teachings of the example embodiments. Further, in the description of the present invention, the meaning of "a plurality" is two or more unless otherwise specified.
  • spatially related terms such as “inside”, “outside”, “below”, “below”, “lower”, “above”, “upper”, etc. are used herein to describe one of the examples illustrated in the figures.
  • the relationship of an element or feature to another element or feature may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures.
  • the example term “lower” can encompass both an orientation of the above and below.
  • the device may be oriented (rotated 90 degrees or at other orientations) in other ways, and the spatially related descriptors used herein should be interpreted accordingly.

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

Abstract

一种离心式压缩机补气结构以及一种采用前述补气结构的压缩机，该离心式压缩机补气结构包括用于向压缩机的过气通道（5）内引入补气气流的环形补气通道（6），环形补气通道（6）内设置有气流导向组件，气流导向组件用于对所述补气气流流入所述过气通道（5）的方向进行调节，以使得补气气流流入过气通道（5）时的方向与过气通道（5）内的气流方向之间的夹角在一预设范围内，最大程度的避免两路气体融合时产生的紊流损失，从而提升循环效率。

Description

一种离心式压缩机补气结构及压缩机 技术领域
本发明涉及压缩机领域，具体涉及一种离心式压缩机补气结构及具有该补气结构的压缩机。
背景技术
为了提高双级或者多级离心式压缩机的循环效率，经常采用带有经济器的循环，经济器内闪发的气态制冷剂经补气通道进入下一级叶轮或者回流器弯道中进行补气。补气方式可以是单点补气，也可以是360°环形补气。单点补气由于会产生局部的紊流损失，造成一定的效率浪费，使用范围比较局限，而360°环形补气则可以更好的与前一级叶轮融合，使气流更加均匀，最大程度的减少紊流损失，从而更好的提高循环效率。
在360°环形补气结构的补气口位置，一般均未对该处做特殊处理，一旦补气位置气体相对扩压器通道内气体流速偏高或偏低时，会产生紊流损失而影响整个压缩机的循环效率。
针对上述问题，亟需提供一种新的离心式压缩机补气结构，以解决现有技术中存在的补气气体与压缩机过气通道内的气体混合产生紊流损失进而影响整个压缩机循环效率的问题。
发明内容
本发明提供一种能够有效防止补气气体与过气通道内的气体混合产生紊流损失的离心式压缩机补气结构。
为达此目的，本发明采用以下技术方案：
一种离心式压缩机补气结构，包括用于向压缩机的过气通道内引入补气气流的环形补气通道，所述环形补气通道内设置有气流导向组件，所述气流导向组件用于对所述补气气流流入所述过气通道的方向进行调节，以使得补气气流流入所述过气通道时的方向与所述过气通道内的气流方向之间的夹角在一预设范围内。
进一步地，所述预设范围为-5°至5°。
进一步地，所述气流导向组件包括沿所述环形补气通道的圆周方向布置的至少一组导流叶片。
进一步地，所述导流叶片呈平板形，其倾斜方向与所述压缩机的回流器叶片旋向相同；
或者，
所述导流叶片呈螺旋形，其旋向与压缩机的回流器叶片旋向相同。
进一步地，从叶轮的轴线方向上观察，所述导流叶片位于所述回流器叶片径向方向的外侧；
所述导流叶片设置于沿所述回流器叶片的螺旋方向向外延伸的螺旋线上，或者，所述导流叶片与所述回流器叶片间隔设置。
进一步地，所述导流叶片上相对的两侧面分别与所述环形补气通道的内壁连接。
进一步地，所述导流叶片的厚度与回流器叶片的厚度相同。
进一步地，所述导流叶片的数量与回流器叶片数量相同。
进一步地，所述过气通道的补气出口设置于回流器的进口弯道处和/或下一级叶轮的进口处，所述导流叶片靠近所述补气出口设置。
本发明还提供了一种循环效率高的压缩机，其中，该压缩机具有如上所述的补气结构。
本发明的有益效果是：
1、本发明提供的离心式压缩机补气结构在环形补气通道内设置有气流导向组件，通过气流导向组件调节补气气流流入过气通道的方向，从而使得补气气流流入过气通道时的方向与过气通道内的气流方向之间的夹角在一预设范围内，最大程度的避免两路气体融合时产生的紊流损失，从而提升循环效率。
2、本发明提供的压缩机由于采用了上述补气结构，大大提高了循环效率。
附图说明
通过以下参照附图对本发明实施例的描述，本发明的上述以及其它目的、特征和优点将更为清楚，在附图中：
图1是本发明具体实施方式提供的离心式压缩机补气结构的结构示意图之一；
图2是本发明具体实施方式提供的离心式压缩机补气结构的结构示意图之二；
图3是本发明具体实施方式提供的导流叶片以及回流器叶片在与压缩机轴线垂直的面上的位置关系示意图之一；
图4是本发明具体实施方式提供的导流叶片以及回流器叶片在与压缩机轴线垂直的面上的位置关系示意图之二；
图5是本发明具体实施方式提供的离心式压缩机补气结构内补气气流流入过气通道时的方向与过气通道内的气流方向之间的夹角范围图。
1、外壳；2、叶轮；3、扩压器；4、回流器；41、回流器叶片；5、过气通道；6、环形补气通道；61、补气进口；62、补气出口；7、导流叶片；a、补气气流流入过气通道时的方向上偏差；b、过气通道内的气流方向；c、补气气流流入过气通道时的方向下偏差。
具体实施方式
以下基于实施例对本发明进行描述，但是本发明并不仅仅限于这些实施例。在下文对本发明的细节描述中，详尽描述了一些特定的细节部分。对本领域技术人员来说没有这些细节部分的描述也可以完全理解本发明。为了避免混淆本发明的实质，公知的方法、过程、流程、元件并没有详细叙述。
本发明提供了一种离心式压缩机补气结构，其包括用于向压缩机的过气通道内引入补气气流的环形补气通道以及设置于环形补气通道内的气流导向组件。其中，过气通道为压缩机内气体流经的通道。通过气流导向组件调节补气气流流入过气通道的方向，从而使得补气气流流入过气通道时的方向与过气通道内的气流方向之间的夹角在一预设范围内，避免两路气体融合时产生的紊流损失，从而提升循环效率，当然，预设范围越小，越能够降低紊流损失。优选的，如图5所示，补气气流流入过气通道时的方向与过气通道内的气流方向b之间夹角的预设范围为-5°至5°，具体地，补气气流流入过气通道时的方向上偏差a与过气通道内的气流方向b之间夹角为5°，补气气流流入过气通道时的方向下偏差c与过气通道内的气流方向b之间夹角为-5°。
作为一种优选方式，气流导向组件包括沿环形补气通道的圆周方向布置的一组导流叶片。导流叶片均匀布置于环形补气通道内，相邻两导流叶片之间形成补气气流的通道，在相邻两导流叶片的导向作用下改变补气气流的方向。
导流叶片的形状可以但不局限于呈平板形或螺旋形，能够起到导向作用从而改变补气气流方向的形状均可。进一步的，若导流叶片为平板形，则其倾斜方向与压缩机的回流器叶片旋向相同，若导流叶片呈螺旋形，其旋向与压缩机的回流器叶片旋向相同，从而达到很好的导流效果。
具体的，如图1和图2所示，压缩机包括外壳1以及设置于外壳1内的叶轮2、扩压器3以及回流器4，由叶轮2、扩压器3和回流器4共同形成过气通道5。环形补气通道6经补气出口62与过气通道5连通，补气出口62可以如图1所示设置于回流器4的进口弯道处，环形补气通道6设置于扩压器3和回流器4之间，并由外壳1、扩压器3以及回流器4的壁面共同围成，环形补气通道6的补气进口61设置于回流器4的外周壁上，补气气流自补气进口61进入环形补气通道6内并由补气出口62流入过气通道5内；也可以如图2所示设置于下一级叶轮的进口处，补气进口61设置于回流器4的外周壁上，环形补气通道6自补气进口61沿径向向内延伸至过气通道5上。当然，其他方便补气的位置也可。导流叶片7靠近补气出口62设置，导向效果更好。
导流叶片7的数量和排布方式不限，能够达到调节补气气流方向的效果即可，优选的，从叶轮的轴线方向上观察，导流叶片7位于回流器叶片41径向方向的外侧。进一步优选的，如图3所示，导流叶片7设置于沿回流器叶片41的螺旋方向向外延伸的螺旋线上，或者如图4所示，导流叶片7与回流器叶片41间隔设置，此处所述的间隔设置指的是导流叶片7上径向向内的一端位于相邻两回流器叶片41之间。上述两种排布方式均能够对补气气流达到很好的匀化及导向作用。优选的，导流叶片7沿径向向外的一端均位于同一圆上，导流叶片7沿径向向内的一端也均位于同一圆上。
由于补气出口62一般较窄，单独增设导流叶片7比较困难，因此将导流叶片7设置为与回流器4一体铸造成型，导流叶片7上相对的两侧面分别与环形补气通道6的内壁连接，如此即可作为导流叶片7，又可作为加强筋增加结构强度，提高压缩机的使用可靠性。优选的，导流叶片7与环形补气通道6的内壁通过平滑的曲面过渡，进一步提高导流效果以及结构的可靠性。
导流叶片7铸造时不能太厚，也不能太薄，太厚会产生较大的摩擦损失，并在叶片尾部产生较大的尾迹损失，对性能影响较大，太薄则不易铸造。优选的，导流叶片7的厚度与回流器叶片41厚度相近或相同。
导流叶片7数量不宜过多或过少，过多会增加补气气流的阻力，影响补气效果，过少则导流效果差。优选的，导流叶片7的数量为12至18片，一般与回流器叶片41数量保持一致。直径较大时，导流叶片7数量取较大值，反之则取较小值。
其中，导流叶片不局限于一组，考虑到导流效果、压缩机尺寸等因素，可以设置两组或多组导流叶片，设置方式与上述导流叶片的设置方式类似，在此不再赘述。另外，气流导向组件也不局限于是导流叶片，其他能够改变补气气流方向的结构均可，如凸块、导向凹槽等等。
针对上述补气结构，本发明还提供了一种压缩机，其具有如上所述的离心式压缩机补气结构，大大提高了压缩机的循环效率和结构的可靠性。
此外，本领域普通技术人员应当理解，在此提供的附图都是为了说明的目的，并且附图不一定是按比例绘制的。
同时，应当理解，示例实施例被提供，以使本公开是全面的，并将其范围充分传达给本领域技术人员。很多特定细节(例如特定部件、设备和方法的示例)被给出以提供对本公开的全面理解。本领域技术人员将明白，不需要采用特定细节，示例实施例可以以很多不同的形式被实施，并且示例实施例不应被理解为限制本公开的范围。在一些示例实施例中，众所周知的工艺、众所周知的设备结构以及众所周知的技术没有详细描述。
在此使用的术语仅用于描述特定示例实施例的目的，并非意欲为限制性的。如在此使用的，单数形式的“一”、“一个”和“所述”也可意欲包括复数形式，除非上下文以另外的方式明确指出。术语“包括”、“包含”、“含有”和“具有”为包含性的并因此明确说明所述特 征、整体、步骤、操作、元件和/或部件的存在，但是不排除存在或增加一个或更多其它特征、整体、步骤、操作、元件、部件和/或其组合。在此描述的方法步骤、工艺和操作将不被理解为必然要求它们以所讨论或例示的特定顺序被执行，除非明确说明为执行的顺序。还将理解可采用另外的或替代的步骤。
当一元件或层被提及为在另一元件或层“上”、“被接合到”、“被连接到”或“被联接到”另一元件或层时，其可直接在另一元件或层上、被直接接合、连接或联接到另一元件或层，或者可存在中间元件或层。相比之下，当一元件被提及为“直接”在另一元件或层“上”、“直接被接合到”、“直接被连接到”或“直接被联接到”另一元件或层时，可不存在中间元件或层。用于描述元件之间关系的其它词语应该以相似方式被解释(例如，“之间”与“直接在之间”，“邻近”与“直接邻近”等)。如在此使用的，术语“和/或”包括一个或更多关联的所列项目中的任一或全部组合。
虽然术语第一、第二、第三等在此可被用于描述各个元件、部件、区域、层和/或区段，但是这些元件、部件、区域、层和/或区段不应该被这些术语限制。这些术语可仅用于将一个元件、部件、区域、层或区段与另一元件、区域、层或区段区分开。诸如“第一”、“第二”的术语和其它数值术语当在此使用时不意味着次序或顺序，除非上下文明确指出。因而，下面讨论的第一元件、部件、区域、层或区段可被称为第二元件、部件、区域、层或区段，而不背离示例实施例的教导。此外，在本发明的描述中，除非另有说明，“多个”的含义是两个或两个以上。
为易于说明，诸如“内”、“外”、“之下”、“下方”、“下部”、“上方”、“上部”等等的空间相关术语在此被用于描述图中例示的一个元件或特征与另一元件或特征的关系。将理解的是，空间相关术语可意欲包含设备在使用或操作中的除图中描绘的方位之外的不同的方位。例如，如果图中的设备被翻转，则被描述为在其它元件或特征“下方”或“之下”的元件于是将被定位为在该其它元件或特征“上方”。因而，示例术语“下方”能包含上方和下方的方位二者。设备可以以其它方式被定向(旋转90度或处于其它方位)，并且在此使用的空间相关描述词应该被相应地解释。
以上所述仅为本发明的优选实施例，并不用于限制本发明，对于本领域技术人员而言，本发明可以有各种改动和变化。凡在本发明的精神和原理之内所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。
以下基于实施例对本发明进行描述，但是本发明并不仅仅限于这些实施例。在下文对本发明的细节描述中，详尽描述了一些特定的细节部分。对本领域技术人员来说没有这些细节部分的描述也可以完全理解本发明。为了避免混淆本发明的实质，公知的方法、过程、流程、元件并没有详细叙述。

Claims (10)

  1. 一种离心式压缩机补气结构，包括用于向压缩机的过气通道(5)内引入补气气流的环形补气通道(6)，其特征在于：所述环形补气通道(6)内设置有气流导向组件，所述气流导向组件用于对所述补气气流流入所述过气通道(5)的方向进行调节，以使得补气气流流入所述过气通道(5)时的方向与所述过气通道(5)内的气流方向之间的夹角在一预设范围内。
  2. 根据权利要求1所述的离心式压缩机补气结构，其特征在于：所述预设范围为-5°至5°。
  3. 根据权利要求1所述的离心式压缩机补气结构，其特征在于：所述气流导向组件包括沿所述环形补气通道(6)的圆周方向布置的至少一组导流叶片(7)。
  4. 根据权利要求3所述的离心式压缩机补气结构，其特征在于：所述导流叶片(7)呈平板形，其倾斜方向与所述压缩机的回流器叶片(41)旋向相同；或者，所述导流叶片(7)呈螺旋形，其旋向与压缩机的回流器叶片(41)旋向相同。
  5. 根据权利要求4所述的离心式压缩机补气结构，其特征在于：从叶轮的轴线方向上观察，所述导流叶片(7)位于所述回流器叶片(41)径向方向的外侧；所述导流叶片(7)设置于沿所述回流器叶片(41)的螺旋方向向外延伸的螺旋线上，或者，所述导流叶片(7)与所述回流器叶片(41)间隔设置。
  6. 根据权利要求3至5任一项所述的离心式压缩机补气结构，其特征在于：所述导流叶片(7)上相对的两侧面分别与所述环形补气通道(6)的内壁连接。
  7. 根据权利要求3至5任一项所述的离心式压缩机补气结构，其特征在于：所述导流叶片(7)的厚度与所述回流器叶片(41)的厚度相同。
  8. 根据权利要求3至5任一项所述的离心式压缩机补气结构，其特征在于：所述导流叶片(7)的数量与所述回流器叶片(41)数量相同。
  9. 根据权利要求3至5任一项所述的离心式压缩机补气结构，其特征在于：所述过气通道(5)的补气出口(62)设置于回流器(4)的进口弯道处和/或下一级叶轮的进口处，所述导流叶片(7)靠近所述补气出口(62)设置。
  10. 一种压缩机，其特征在于：所述压缩机具有如权利要求1至9任一项所述的补气结构。
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