WO2018205632A1 - 扩压器叶片、压缩机结构和压缩机 - Google Patents

扩压器叶片、压缩机结构和压缩机 Download PDF

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Publication number
WO2018205632A1
WO2018205632A1 PCT/CN2017/118109 CN2017118109W WO2018205632A1 WO 2018205632 A1 WO2018205632 A1 WO 2018205632A1 CN 2017118109 W CN2017118109 W CN 2017118109W WO 2018205632 A1 WO2018205632 A1 WO 2018205632A1
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WIPO (PCT)
Prior art keywords
compressor
diffuser
benefit
blade
impeller
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Application number
PCT/CN2017/118109
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English (en)
French (fr)
Inventor
刘增岳
钟瑞兴
蒋楠
蒋彩云
陈玉辉
周义
雷连冬
欧阳鑫望
Original Assignee
格力电器（武汉）有限公司
珠海格力电器股份有限公司
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Application filed by 格力电器（武汉）有限公司, 珠海格力电器股份有限公司 filed Critical 格力电器（武汉）有限公司
Priority to EP17908929.7A priority Critical patent/EP3623639A4/en
Priority to US16/611,656 priority patent/US20210140446A1/en
Publication of WO2018205632A1 publication Critical patent/WO2018205632A1/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
    • 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
    • F04D29/26—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
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for 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
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—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
    • 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 present application relates to the field of compressors, and in particular to a diffuser vane, a compressor structure and a compressor.
  • the most widely used is a "two-stage compression intermediate incomplete cooling refrigeration cycle" with a flash steam separator (commonly known as an economizer).
  • the two-stage compression refrigeration cycle mixes the flash steam separated from the economizer with the exhaust gas from the low-stage compression, reduces the secondary compression intake air temperature, reduces the refrigerant gas specific volume, and reduces the compressor energy consumption.
  • the current air supply scheme causes a large airflow mixing loss and reduces the aerodynamic efficiency of the compressor.
  • the vane diffuser can effectively improve the aerodynamic performance of the compressor at the design point, but when the working condition deviates from the design point, the vane is larger due to the change of the inlet airflow angle of the diffuser vane.
  • the low-speed low-energy zone eventually leads to compressor stall and surge, reducing the stable operating range of the compressor.
  • a diffuser vane, a compressor structure and a compressor are provided to reduce the airflow mixing loss caused by the supplemental air, and/or reduce the suction surface generated by the diffuser vane when the compressor deviates from the design point. Low speed low energy zone.
  • an embodiment of the present application provides a diffuser blade, including: a blade body, a cavity is formed inside the blade body, and a plenum is formed on the blade body.
  • the air supply hole is provided on a suction side of the blade body.
  • the blade body is made by casting or machining.
  • the present application also provides a compressor structure including the above described diffuser vanes.
  • the compressor structure further includes a housing on which a gas supply passage is formed in communication with the cavity of the diffuser vane.
  • the compressor structure further includes a primary impeller and a secondary impeller, the output airflow of the primary impeller entering the secondary impeller through a primary diffuser provided with the diffuser vanes.
  • the output gas stream of the primary diffuser enters the secondary impeller through a return flow path.
  • the transition between the primary diffuser flow path and the return flow path is formed as a curve.
  • the output of the secondary impeller is fitted with a secondary diffuser.
  • the application also provides a compressor comprising the compressor structure described above.
  • the application can form a jet on the suction surface of the diffuser blade through the air-filled diffuser blade of the hollow structure and the air-filling hole of the back thereof, so as to blow off the low-speed low-energy region formed by the suction surface, thereby reducing the air supply.
  • the airflow mixing loss increases the aerodynamic efficiency of the centrifugal compressor and widens the compressor operating range while increasing the aerodynamic performance of the compressor design point.
  • FIG. 1 is a schematic view showing an axial force balance structure of a compressor rotor according to an embodiment of the present application
  • FIG. 2 is a schematic cross-sectional view of a diffuser blade of an embodiment of the present application
  • FIG. 3 is a schematic triangular view of the impeller exit speed of the embodiment of the present application.
  • the embodiment of the present application provides a diffuser blade, comprising: a blade body 1 , a cavity 2 is formed inside the blade body 1 , and a gas filling hole 3 is formed on the blade body 1 .
  • the air supply hole 3 is provided on a suction side of the blade body 1.
  • the blade body 1 is made by casting or machining.
  • the present application is designed to hollow out the diffuser vanes 4 and to provide a micro air inlet 3 in the back of the diffuser vanes 4. Therefore, the jet can be formed on the suction surface of the diffuser vane 4 by the supplemental air to blow off the low-speed low-energy region formed by the suction surface, thereby reducing the airflow mixing loss caused by the supplemental air, thereby improving the aerodynamic efficiency of the centrifugal compressor. It can also widen the operating range of the compressor while improving the aerodynamic performance of the compressor design point.
  • the position, angle and aperture size of the venting hole 3 that is, properly arranging the position, angle and jet velocity of the jet, it is possible to effectively suppress the separation of the suction surface of the diffuser blade at the non-design point operating condition.
  • the present application also provides a compressor structure including the diffuser vanes 4 described above.
  • the compressor structure further includes a housing on which a gas supply passage 5 communicating with the cavity 2 of the diffuser vane 4 is formed.
  • the stroke of the airflow in the first diffuser flow passage 9 is reduced, the friction and the like are reduced, and the total pressure recovery coefficient of the diffuser is improved.
  • the jet is formed on the suction surface of the diffuser vane 4 by the supplemental air, and the low-speed low-energy region formed by the suction surface is blown off, the airflow separation loss is reduced, and the aerodynamic efficiency of the compressor is improved.
  • the compressor structure further comprises a primary impeller 6 and a secondary impeller 7, the output airflow of the primary impeller 6 entering the secondary through a primary diffuser provided with the diffuser vane 4 Impeller 7.
  • the output gas stream of the primary diffuser enters the secondary impeller 7 through a return flow path 8.
  • the transition between the primary diffuser flow passage and the return flow passage 8 is formed as a curve.
  • the output of the secondary impeller 7 is fitted with a secondary diffuser.
  • the airflow passes through the first stage impeller 6, the first stage diffuser flow path 9, the return flow path 8, the secondary impeller 7, and the secondary diffuser flow path 11, and is discharged by the volute 13.
  • a secondary diffuser vane 12 is disposed in the secondary diffuser flow passage 11, and a return vane 10 is disposed in the return flow passage 8.
  • the back jet of the diffuser vane 4 can be used to supplement the air, which can effectively reduce the temperature and specific volume of the refrigerant at the outlet of the first impeller 6, and improve the aerodynamic efficiency of the secondary impeller.
  • the application also provides a compressor comprising the compressor structure described above.
  • the back jet of the diffuser vane 4 can effectively reduce the temperature and specific volume of the refrigerant at the outlet of the first impeller 6, and improve the aerodynamic efficiency of the secondary impeller.
  • the diffusing of the diffuser vane 4 can reduce the stroke of the airflow in the primary diffuser flow passage 9, reduce the loss of friction and the like, and improve the total pressure recovery coefficient of the diffuser.
  • the supplemental air can form a jet on the suction surface of the diffuser vane 4, blowing out the low-speed low-energy region formed by the suction surface, and reducing the airflow separation loss. Improve compressor aerodynamic efficiency.

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

Abstract

一种扩压器叶片、压缩机结构和压缩机，其中，扩压器叶片包括叶片本体（1），叶片本体（1）的内部形成有空腔（2），叶片本体（1）上形成有补气孔（3）。中空结构的扩压器叶片及其背部的补气孔，通过补气在扩压器叶片的吸力面形成射流，以吹除吸力面形成的低速低能区，降低了补气带来的气流掺混损失，进而提高了离心压缩机的气动效率，并可在提高压缩机设计点气动性能的同时扩宽压缩机运行范围。

Description

扩压器叶片、压缩机结构和压缩机
相关申请
本申请要求2017年05月11日申请的，申请号为201710330901.0，名称为“扩压器叶片、压缩机结构和压缩机”的中国专利申请的优先权，在此将其全文引入作为参考。
技术领域
本申请涉及压缩机领域，具体而言，涉及一种扩压器叶片、压缩机结构和压缩机。
背景技术
在离心压缩机中，由于气体经压缩后，温度会急剧上升，在高温下，气体比容很大，在保证相同制冷量的情况下，压缩机能耗将会急剧增大。为了降低压缩机耗功，提高制冷能力，常用多级压缩制冷循环。
目前使用最为广泛的是带有闪发蒸汽分离器(俗称经济器)的“双级压缩中间不完全冷却制冷循环”。双级压缩制冷循环，是将从经济器分离出来的闪发蒸汽与来自低级压缩的排气相混合，降低了二级压缩的进气温度，使制冷剂气体比容下降，压缩机能耗降低。但是当前的补气方案由于主流与补气流在气流速度大小及方向上的差别，导致补气产生较大气流掺混损失，降低压缩机气动效率。
此外，在离心压缩机中，采用叶片扩压器可以有效提高压缩机在设计点的气动性能，但是当工况偏离设计点时，由于扩压器叶片进口气流角的变化，导致叶片产生较大的低速低能区，最终导致压缩机失速及喘振，降低压缩机稳定运行范围。采用无叶扩压器虽然压缩机运行范围宽广，但是设计点性能偏低。
发明内容
本申请实施例中提供一种扩压器叶片、压缩机结构和压缩机，以降低补气带来的气流掺混损失、和/或降低压缩机偏离设计点时扩压器叶片吸力面产生的低速低能区。
为实现上述目的，本申请实施例提供一种扩压器叶片，包括：叶片本体，所述叶片本体的内部形成有空腔，所述叶片本体上形成有补气孔。
作为优选，所述补气孔设置在所述叶片本体的吸力面。
作为优选，所述叶片本体通过铸造或机加工制成。
本申请还提供了一种压缩机结构，包括上述的扩压器叶片。
作为优选，所述压缩机结构还包括壳体，所述壳体上形成与所述扩压器叶片的空腔连通的补气通道。
作为优选，所述压缩机结构还包括一级叶轮和二级叶轮，所述一级叶轮的输出气流经过设置有所述扩压器叶片的一级扩压器进入所述二级叶轮。
作为优选，所述一级扩压器的输出气流经过回流器流道进入所述二级叶轮。
作为优选，所述一级扩压器流道与所述回流器流道之间的过渡处形成为弯道。
作为优选，所述二级叶轮的输出端安装有二级扩压器。
本申请还提供了一种压缩机，包括上述的压缩机结构。
本申请可通过中空结构的扩压器叶片及其背部的补气孔，通过补气在扩压器叶片的吸力面形成射流，以吹除吸力面形成的低速低能区，降低了补气带来的气流掺混损失，进而提高了离心压缩机的气动效率，并可在提高压缩机设计点气动性能的同时扩宽压缩机运行范围。
附图说明
图1是本申请实施例的压缩机转子轴向力平衡结构示意图；
图2是本申请实施例的扩压器叶片的截面示意图；
图3是本申请实施例的叶轮出口速度三角形示意图。
附图标记说明：
1-叶片本体；
2-空腔；
3-补气孔；
4-扩压器叶片；
5-补气通道；
6-一级叶轮；
7-二级叶轮；
8-回流器流道；
9-一级扩压器流道；
10-回流器叶片；
11-二级扩压器流道；
12-二级扩压器叶片；
13-蜗壳。
具体实施方式
下面结合附图和具体实施例对本申请作进一步详细描述，但不作为对本申请的限定。
本申请的目的是降低补气带来的气流掺混损失，并可在提高设计点性能的同时扩宽压缩机运行范围。为此，本申请实施例提供一种扩压器叶片，包括：叶片本体1，所述叶片本体1 的内部形成有空腔2，所述叶片本体1上形成有补气孔3。优选地，所述补气孔3设置在所述叶片本体1的吸力面。优选地，所述叶片本体1通过铸造或机加工制成。
请参考图1-3，压缩机在设计点工况运行时，气体冷媒经过一级叶轮6后，由于冷媒随叶轮作圆周运动，气流绝对速度C由Cm和Ct组成。冷媒气流以绝对速度进入一级扩压器流道9，以较小攻角冲击叶片扩压。当未采用本申请中的扩压器叶片时，如果压缩机偏离设计点工况运行时，叶轮出口冷媒绝对气流角a减小，气流以较大的攻角冲击叶片，导致在叶片吸力面分离，出现较大的低速低能区，最终导致压缩机失速及喘振。在图3中，W为相对速度，U为旋转速度，C为绝对速度，且W+U＝C。
本申请通过将扩压器叶片4设计为中空，并在扩压器叶片4的背部设置微型的补气孔3。因此，可通过补气在扩压器叶片4的吸力面形成射流，以吹除吸力面形成的低速低能区，降低了补气带来的气流掺混损失，进而提高了离心压缩机的气动效率，并可在提高压缩机设计点气动性能的同时扩宽压缩机运行范围。
进一步地，通过合理设计补气孔3的位置、角度及孔径大小，即合理组织射流的位置、角度及射流速度，能够有效抑制非设计点工况扩压器叶片吸力面分离。
本申请还提供了一种压缩机结构，包括上述的扩压器叶片4。优选地，所述压缩机结构还包括壳体，所述壳体上形成与所述扩压器叶片4的空腔2连通的补气通道5。
在扩压器叶片的扩压作用下，降低了气流在一级扩压器流道9中的行程，降低了摩擦等损失，提高扩压器总压恢复系数。同时，通过补气在扩压器叶片4的吸力面形成射流，吹除了吸力面形成的低速低能区，减小了气流分离损失，提高了压缩机气动效率。
优选地，所述压缩机结构还包括一级叶轮6和二级叶轮7，所述一级叶轮6的输出气流经过设置有所述扩压器叶片4的一级扩压器进入所述二级叶轮7。优选地，所述一级扩压器的输出气流经过回流器流道8进入所述二级叶轮7。优选地，所述一级扩压器流道与所述回流器流道8之间的过渡处形成为弯道。优选地，所述二级叶轮7的输出端安装有二级扩压器。工作时，气流依次经过一级叶轮6、一级扩压器流道9、回流器流道8、二级叶轮7、二级扩压器流道11后，由蜗壳13排出。其中，在二级扩压器流道11中设置有二级扩压器叶片12，回流器流道8中设置有回流器叶片10。
通过上述设计，扩压器叶片4的背部射流补气，可以有效降低一级叶轮6出口冷媒的温度及比容，提高二级叶轮气动效率。
本申请还提供了一种压缩机，包括上述的压缩机结构。
通过本设计，扩压器叶片4的背部射流补气可以有效地降低一级叶轮6出口冷媒的温度及比容，提高二级叶轮气动效率。扩压器叶片4的扩压可降低气流在一级扩压器流道9中的行程，降低摩擦等损失，提高扩压器总压恢复系数。进一步地，通过扩压器叶片4的中空结构及背部的补气孔，可使补气在扩压器叶片4的吸力面形成射流，吹除吸力面形成的低速低能区，减小气流分离损失，提高压缩机气动效率。
当然，以上是本申请的优选实施方式。应当指出，对于本技术领域的普通技术人员来说，在不脱离本申请基本原理的前提下，还可以做出若干改进和润饰，这些改进和润饰也视为本申请的保护范围。

Claims (10)

  1. 一种扩压器叶片，其特征在于，包括：叶片本体(1)，所述叶片本体(1)的内部形成有空腔(2)，所述叶片本体(1)上形成有补气孔(3)。
  2. 根据权利要求1所述的扩压器叶片，其特征在于，所述补气孔(3)设置在所述叶片本体(1)的吸力面。
  3. 根据权利要求1所述的扩压器叶片，其特征在于，所述叶片本体(1)通过铸造或机加工制成。
  4. 一种压缩机结构，其特征在于，包括权利要求1至3中任一项所述的扩压器叶片(4)。
  5. 根据权利要求4所述的压缩机结构，其特征在于，所述压缩机结构还包括壳体，所述壳体上形成与所述扩压器叶片(4)的空腔(2)连通的补气通道(5)。
  6. 根据权利要求4所述的压缩机结构，其特征在于，所述压缩机结构还包括一级叶轮(6)和二级叶轮(7)，所述一级叶轮(6)的输出气流经过设置有所述扩压器叶片(4)的一级扩压器进入所述二级叶轮(7)。
  7. 根据权利要求6所述的压缩机结构，其特征在于，所述一级扩压器的输出气流经过回流器流道(8)进入所述二级叶轮(7)。
  8. 根据权利要求7所述的压缩机结构，其特征在于，所述一级扩压器流道与所述回流器流道(8)之间的过渡处形成为弯道。
  9. 根据权利要求7所述的压缩机结构，其特征在于，所述二级叶轮(7)的输出端安装有二级扩压器。
  10. 一种压缩机，其特征在于，包括权利要求4至9中任一项所述的压缩机结构。
PCT/CN2017/118109 2017-05-11 2017-12-22 扩压器叶片、压缩机结构和压缩机 WO2018205632A1 (zh)

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CN113829015B (zh) * 2021-10-25 2023-10-27 重庆江增船舶重工有限公司 扇形扩压器的加工方法
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