TW202405312A - Centrifugal compressor - Google Patents
Centrifugal compressor Download PDFInfo
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- TW202405312A TW202405312A TW111126750A TW111126750A TW202405312A TW 202405312 A TW202405312 A TW 202405312A TW 111126750 A TW111126750 A TW 111126750A TW 111126750 A TW111126750 A TW 111126750A TW 202405312 A TW202405312 A TW 202405312A
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- 238000002347 injection Methods 0.000 claims abstract description 73
- 239000007924 injection Substances 0.000 claims abstract description 73
- 238000009792 diffusion process Methods 0.000 claims description 7
- 238000010992 reflux Methods 0.000 abstract 3
- 239000012530 fluid Substances 0.000 description 92
- 239000003570 air Substances 0.000 description 19
- 230000006835 compression Effects 0.000 description 7
- 238000007906 compression Methods 0.000 description 7
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 239000003507 refrigerant Substances 0.000 description 5
- 230000002093 peripheral effect Effects 0.000 description 4
- 229910002092 carbon dioxide Inorganic materials 0.000 description 3
- 239000001569 carbon dioxide Substances 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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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
- 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
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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
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
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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
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- 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
- F05D2240/127—Vortex generators, turbulators, or the like, for mixing
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
本發明是有關於一種離心式壓縮機,且特別是有關於一種二級離心式壓縮機。The present invention relates to a centrifugal compressor, and in particular to a two-stage centrifugal compressor.
常見的二級離心式壓縮機包括第一級葉輪及第二級葉輪,其中第一級葉輪位於流道的上游,且第二級葉輪位於流道的下游。首先,第一流體(例如氣態冷媒、空氣或二氧化碳等)係自進口導葉沿著驅動軸的長軸方向流向第一級葉輪,接著,第一級葉輪對第一流體加壓,並驅使第一流體沿著離心方向流入流道。接著,第一流體在流道的第一轉折段產生轉向,並沿著向心方向往第二級葉輪流動。詳細而言,第二級葉輪對應流道的第二轉折段配置,且節能器噴入通道連通於流道的第二轉折段,以將第二流體(例如氣態冷媒、空氣或二氧化碳等)注入流道的第二轉折段,使得第一流體及第二流體在流道的第二轉折段形成第三流體。之後,第三流體流向第二級葉輪,並經第二級葉輪的加壓沿著離心方向流向蝸殼流道。A common two-stage centrifugal compressor includes a first-stage impeller and a second-stage impeller. The first-stage impeller is located upstream of the flow channel, and the second-stage impeller is located downstream of the flow channel. First, the first fluid (such as gaseous refrigerant, air or carbon dioxide, etc.) flows from the inlet guide vane along the long axis direction of the drive shaft to the first-stage impeller. Then, the first-stage impeller pressurizes the first fluid and drives the second-stage impeller. A fluid flows into the flow channel along the centrifugal direction. Then, the first fluid turns in the first turning section of the flow channel and flows toward the second-stage impeller along the centripetal direction. Specifically, the second-stage impeller is configured corresponding to the second turning section of the flow channel, and the economizer injection channel is connected to the second turning section of the flow channel to inject the second fluid (such as gaseous refrigerant, air or carbon dioxide, etc.) The second turning section of the flow channel allows the first fluid and the second fluid to form a third fluid in the second turning section of the flow channel. After that, the third fluid flows to the second-stage impeller, and is pressurized by the second-stage impeller and flows to the volute flow channel along the centrifugal direction.
一般而言,第一級葉輪與第二級葉輪之間可設置有回流導葉底座,且來自節能器的第二流體係經由回流導葉底座上的多個回流翼的引導,以注入流道的第二轉折段。進一步而言,相鄰的任二個回流翼之間形成一個回流通道,且第二流體在回流通道中容易產生紊流,導致第一流體與第二流體無法均勻混合,並衍生出流體壓損增加及空氣動力效率下滑等問題,從而影響到離心式壓縮機的性能表現。Generally speaking, a return guide vane base can be provided between the first-stage impeller and the second-stage impeller, and the second flow system from the economizer is guided by a plurality of return wings on the return guide vane base to be injected into the flow channel. The second turning point. Furthermore, a return channel is formed between any two adjacent return wings, and the second fluid easily generates turbulence in the return channel, resulting in the inability of the first fluid and the second fluid to mix uniformly, and resulting in fluid pressure loss. Increase and decline in aerodynamic efficiency, etc., thus affecting the performance of centrifugal compressors.
本發明提供一種離心式壓縮機,有助於減少回流導葉底座之間的紊流產生,並提升壓縮效率。The present invention provides a centrifugal compressor, which helps reduce the turbulence between the bases of return guide vanes and improves compression efficiency.
本發明提出一種離心式壓縮機,包括進氣口、流道、第一級葉輪、第二級葉輪、回流導葉底座及節能器噴入通道。流道連通於進氣口,且具有第一擴壓段、連接第一擴壓段的第一轉折段、連接第一轉折段的回流段、連接回流段的第二轉折段、連接第二轉折段的第二擴壓段及連接第二擴壓段的蝸殼流道。第一級葉輪配置於進氣口與第一擴壓段之間。第二級葉輪配置於第二轉折段與第二擴壓段之間。回流導葉底座配置於第一級葉輪與第二級葉輪之間,且具有位於回流段內的多個回流翼及連通於回流段的多個注入孔。每一個回流翼具有第一翼部、第二翼部及將第一翼部與第二翼部分隔開來的狹縫。所述多個注入孔分別落在所述多個狹縫內。節能器噴入通道連通於所述多個注入孔。The invention proposes a centrifugal compressor, which includes an air inlet, a flow channel, a first-stage impeller, a second-stage impeller, a return guide vane base and an economizer injection channel. The flow channel is connected to the air inlet and has a first expansion section, a first turning section connected to the first expansion section, a return section connected to the first turning section, a second turning section connected to the return section, and a second turning section connected to the first turning section. The second expansion section of the section and the volute flow channel connecting the second expansion section. The first-stage impeller is arranged between the air inlet and the first diffusion section. The second stage impeller is arranged between the second turning section and the second expansion section. The return guide vane base is disposed between the first-stage impeller and the second-stage impeller, and has a plurality of return wings located in the return section and a plurality of injection holes connected to the return section. Each return wing has a first wing part, a second wing part and a slit separating the first wing part and the second wing part. The plurality of injection holes respectively fall into the plurality of slits. The economizer injection channel is connected to the plurality of injection holes.
在本發明的一實施例中,上述的回流翼的狹縫具有相對的二個出口,且所述二個出口之間的距離為D。注入孔與一個出口之間的距離介於1/4D至D之間。In an embodiment of the present invention, the above-mentioned slit of the return wing has two opposite outlets, and the distance between the two outlets is D. The distance between the injection hole and one outlet is between 1/4D and D.
在本發明的一實施例中,上述的回流翼的第一翼部具有相對於狹縫的外端部,且每一個回流翼的第二翼部具有相對於狹縫的內端部。第一翼部的外端部與第二翼部的內端部之間的距離為S,且狹縫與第二翼部的內端部之間的距離介於3/4S至1/2S之間。In an embodiment of the present invention, the first wing portion of the above-mentioned return wing has an outer end portion relative to the slit, and the second wing portion of each return wing has an inner end portion relative to the slit. The distance between the outer end of the first wing and the inner end of the second wing is S, and the distance between the slit and the inner end of the second wing is between 3/4S and 1/2S. between.
在本發明的一實施例中,上述的回流翼的翼型包括凹凸翼型、平凸翼型、對稱翼型、S形翼型及平板翼型。In an embodiment of the present invention, the airfoil of the above-mentioned return airfoil includes a concave and convex airfoil, a plano-convex airfoil, a symmetrical airfoil, an S-shaped airfoil and a flat airfoil.
在本發明的一實施例中,上述的離心式壓縮機更包括驅動軸,且第一級葉輪與第二級葉輪套設於驅動軸上。In one embodiment of the present invention, the above-mentioned centrifugal compressor further includes a drive shaft, and the first-stage impeller and the second-stage impeller are sleeved on the drive shaft.
在本發明的一實施例中,上述的注入孔的中心軸平行於驅動軸。In an embodiment of the present invention, the central axis of the above-mentioned injection hole is parallel to the driving shaft.
在本發明的一實施例中,上述的注入孔的中心軸垂直於回流段。In an embodiment of the present invention, the central axis of the above-mentioned injection hole is perpendicular to the return section.
在本發明的一實施例中,上述的注入孔包括錐孔、直孔或錐孔及直孔的組合。In one embodiment of the present invention, the above-mentioned injection hole includes a tapered hole, a straight hole, or a combination of a tapered hole and a straight hole.
在本發明的一實施例中,上述的回流翼的狹縫包括弧形狹縫或線性狹縫。In an embodiment of the present invention, the slits of the above-mentioned return wing include arc-shaped slits or linear slits.
在本發明的一實施例中,上述的回流導葉底座具有位於回流段內的第一表面及相對於第一表面的第二表面,且所述多個注入孔貫通第一表面與第二表面。In one embodiment of the present invention, the above-mentioned return guide vane base has a first surface located in the return section and a second surface opposite to the first surface, and the plurality of injection holes penetrates the first surface and the second surface. .
在本發明的一實施例中,上述的回流翼的第一翼部及第二翼部凸出於第一表面。In an embodiment of the present invention, the first wing portion and the second wing portion of the above-mentioned return wing protrude from the first surface.
在本發明的一實施例中,上述的注入孔具有連通於狹縫的第一開口及相對於第一開口的第二開口,且第一開口的孔徑小於第二開口的孔徑。In an embodiment of the present invention, the above-mentioned injection hole has a first opening connected to the slit and a second opening relative to the first opening, and the aperture of the first opening is smaller than the aperture of the second opening.
在本發明的一實施例中,上述的注入孔位於回流段鄰近第一轉折段處。In an embodiment of the present invention, the above-mentioned injection hole is located in the return section adjacent to the first turning section.
在本發明的一實施例中,上述的注入孔位於回流段離向第二轉折段處。In an embodiment of the present invention, the above-mentioned injection hole is located at the second turning section away from the return section.
在本發明的一實施例中,離心式壓縮機更包括節能器,連通節能器噴入通道並設置於離心式壓縮機外。In one embodiment of the present invention, the centrifugal compressor further includes an economizer, which is connected to the economizer injection channel and is arranged outside the centrifugal compressor.
在本發明的一實施例中,離心式壓縮機更包括進氣導葉,配置於進氣口。In an embodiment of the present invention, the centrifugal compressor further includes an air inlet guide vane, which is arranged at the air inlet.
在本發明的一實施例中,上述的回流導葉底座具有位於第一擴壓段內的第三表面及相對於第三表面的第四表面,且所述多個注入孔貫通第三表面與第四表面。In an embodiment of the present invention, the above-mentioned return guide vane base has a third surface located in the first expansion section and a fourth surface opposite to the third surface, and the plurality of injection holes penetrates the third surface and Fourth surface.
在本發明的一實施例中,上述的每一個回流翼的第一翼部及第二翼部凸出於第三表面。In an embodiment of the present invention, the first wing portion and the second wing portion of each of the above-mentioned return wings protrude from the third surface.
基於上述,在本發明的離心式壓縮機中,第二流體的注入位置落在流道的回流段內,使得第一流體與第二流體在流至第二級葉輪之前具有較長的流動路徑以均勻混合。另一方面,注入流道的回流段後的第二流體在狹縫中產生分流及進行第一次整流,接續,第二流體沿著回流翼的第二翼部的外周緣自回流段流向第二轉折段,並進行第二次整流,使回流段內的第二流體與第一流體的流向一致,並減少紊流的產生,使得第一流體與第二流體得以在流道內均勻混合,據以減少流體壓損並提升空氣動力效率,從而提升離心式壓縮機的壓縮效率。Based on the above, in the centrifugal compressor of the present invention, the injection position of the second fluid falls within the return section of the flow channel, so that the first fluid and the second fluid have a longer flow path before flowing to the second-stage impeller. to mix evenly. On the other hand, the second fluid injected into the return section of the flow channel splits in the slit and undergoes first rectification. Then, the second fluid flows from the return section to the third wing along the outer peripheral edge of the second wing of the return wing. The second turning section and the second rectification are carried out to make the flow direction of the second fluid in the return section consistent with that of the first fluid and reduce the generation of turbulence, so that the first fluid and the second fluid can be evenly mixed in the flow channel. This reduces fluid pressure loss and improves aerodynamic efficiency, thereby improving the compression efficiency of the centrifugal compressor.
為讓本發明的上述特徵和優點能更明顯易懂,下文特舉實施例,並配合所附圖式作詳細說明如下。In order to make the above-mentioned features and advantages of the present invention more obvious and easy to understand, embodiments are given below and described in detail with reference to the accompanying drawings.
圖1A是本發明一實施例的離心式壓縮機的剖面示意圖。圖1B是圖1A的區域R的放大示意圖。請參考圖1A及圖1B,在本實施例中,離心式壓縮機100可為二級離心式壓縮機,且包括進氣口110、流道120、進氣導葉140、驅動軸150、第一級葉輪160、第二級葉輪170、回流導葉底座180及節能器噴入通道190。進氣口110連通於流道120,其中進氣導葉140配置於進氣口110,且第一級葉輪160、第二級葉輪170、回流導葉底座180及節能器噴入通道190沿著流道120配置。另外,第一級葉輪160及第二級葉輪170套接於驅動軸150,以隨驅動軸150同步且同向旋轉。FIG. 1A is a schematic cross-sectional view of a centrifugal compressor according to an embodiment of the present invention. FIG. 1B is an enlarged schematic diagram of the region R in FIG. 1A . Please refer to FIGS. 1A and 1B . In this embodiment, the
詳細而言,流道120具有第一擴壓段121、第一轉折段122、回流段123、第二轉折段124、第二擴壓段125及蝸殼流道130,且第一擴壓段121、第一轉折段122、回流段123、第二轉折段124及第二擴壓段125依序排列於進氣口110與蝸殼流道130之間。In detail, the
進氣口110連通於第一擴壓段121,且第一級葉輪160配置於進氣口110與第一擴壓段121之間。第一轉折段122連接第一擴壓段121,且回流段123連接第一轉折段122。第二轉折段124連接回流段123,且第二擴壓段125連接第二轉折段124。第二級葉輪170配置於第二轉折段124與第二擴壓段125之間,且蝸殼流道130連接第二擴壓段125。The
在離心式壓縮機100運轉的過程中,第一流體F1(例如氣態冷媒)由進氣導葉140引導至進氣口110,並沿著軸向(例如平行於驅動軸150的長軸方向)流向第一級葉輪160。接著,第一級葉輪160對第一流體F1加壓,並驅使第一流體F1沿著離心方向(例如遠離驅動軸150的長軸方向)流入第一擴壓段121。接著,第一流體F1自第一擴壓段121流入第一轉折段122並產生轉向,以沿著向心方向(例如靠近驅動軸150的長軸方向)流入回流段123。另一方面,離心式壓縮機100更包括節能器(圖未示),節能器連通節能器噴入通道190並設置於離心式壓縮機100外。其中,節能器噴入通道190連通於回流段123,以將第二流體F2(例如氣態冷媒)注入回流段123,使得第一流體F1及第二流體F2在回流段123內形成第三流體F3。接著,第三流體F3自回流段123流入第二轉折段124。之後,第二級葉輪170對第三流體F3加壓,並驅使第三流體F3沿著離心方向流入第二擴壓段125,再自第二擴壓段125流入蝸殼流道130。During the operation of the
接續上述,第二流體F2的注入位置落在流道120的回流段123內,使得第一流體F1與第二流體F2在流至第二級葉輪170之前具有較長的流動路徑以均勻混合,據以提升離心式壓縮機100的壓縮效率。其中,第一流體F1與第二流體F2可為氣態冷媒、空氣、一氧化碳、二氧化碳、氧氣、氫氣或相關混合氣體等。Continuing from the above, the injection position of the second fluid F2 falls within the
圖2A至圖2C是本發明一實施例的回流導葉底座在不同視角下的示意圖。請參考圖1B、圖2A及圖2B,在本實施例中,回流導葉底座180配置於第一級葉輪160與第二級葉輪170之間,且具有位於回流段123內的多個回流翼181及連通於回流段123的多個注入孔182。所述多個回流翼181呈放射狀排列,且每一個回流翼181對應設有一個注入孔182。詳細而言,每一個回流翼181具有第一翼部183、第二翼部184及位於第一翼部183與第二翼部184之間的狹縫185,且第一翼部183與第二翼部184被狹縫185分隔開來。另外,注入孔182落在狹縫185內,其中節能器噴入通道190連通於注入孔182,且注入孔182透過狹縫185連通於回流段123,故第二流體F2可經由注入孔182及狹縫185注入回流段123。2A to 2C are schematic views of the return guide vane base from different viewing angles according to an embodiment of the present invention. Please refer to FIG. 1B , FIG. 2A and FIG. 2B . In this embodiment, the return
如圖1A及圖1B所示,注入孔182的中心軸平行於驅動軸150,且實質上垂直於回流段123,故第二流體F2可沿軸向直噴進入回流段123。在其他實施例中,注入孔182的中心軸傾斜於回流段123,故第二流體F2可斜噴進入回流段123。As shown in FIGS. 1A and 1B , the central axis of the
請參考圖1B、圖2A、圖2B及圖2C,在本實施例中,回流翼181的翼型為凹凸翼型,且每一個回流翼181的狹縫185為弧形狹縫。另一方面,回流導葉底座180具有位於回流段123內的第一表面186及相對於第一表面186的第二表面187,且所述多個注入孔182貫通第一表面186與第二表面187。具體而言,每一個回流翼181的第一翼部183及第二翼部184凸出於第一表面186,當第二流體F2自注入孔182流入狹縫185時,第二流體F2可在狹縫185內產生分流及進行第一次整流,以分別沿著第二翼部184的相對兩翼面流動,藉由近壁效應(near-wall effect )達到第二次整流的效果,並自回流段123流向第二轉折段124。Please refer to FIG. 1B , FIG. 2A , FIG. 2B and FIG. 2C . In this embodiment, the airfoil of the
如圖1B、圖2B及圖2C所示,每一個注入孔182具有連通於狹縫185的第一開口188及相對於第一開口188的第二開口189,其中第一開口188連接第一表面186,且第二開口189連接第二表面187。詳細而言,來自節能器噴入通道190的第二流體F2自第二開口189流向第一開口188,再自第一開口188流入狹縫185。由於第一開口188的孔徑A1小於第二開口189的孔徑A2,因此有助於提高第二流體F2注入狹縫185或回流段123時,減少第二流體F2的壓力損失。As shown in FIGS. 1B , 2B and 2C , each
如圖1B所示,在本實施例中,注入孔182可為錐孔,且孔徑由第二表面187往第一表面186漸減。在另一實施例中,注入孔182可為直孔,且孔徑由第二表面187往第一表面186保持一致。在又一實施例中,注入孔182可為錐孔與直孔的組合,其中錐孔連接第二表面187,且直孔連接第一表面186。As shown in FIG. 1B , in this embodiment, the
如圖2C所示,在本實施例中,每一個回流翼181的狹縫185具有相對的二個出口185a,其中所述二個出口185a之間的距離為D(即狹縫185的長度),且注入孔182(例如注入孔182的第一開口188)與一個出口185a之間的距離D1介於1/4D至D之間。舉例來說,注入孔182的位置可以是落在回流翼181的重心處。As shown in Figure 2C, in this embodiment, the
如圖1B及圖2C所示,每一個回流翼181的第一翼部183較第二翼部184遠離第二轉折段124,其中第一翼部183具有相對於狹縫185的外端部183a,且第二翼部184具有相對於狹縫185的內端部184a。每一個回流翼181的狹縫185位於第一翼部183的外端部183a與第二翼部184的內端部184a之間,且內端部184a較狹縫185靠近第二轉折段124。每一個回流翼181的第一翼部183的外端部183a與第二翼部184的內端部184a之間的距離為S(即回流翼181的長度),且狹縫185與第二翼部184的內端部184a之間的距離S1介於3/4S至1/2S之間,也就是狹縫185設置於回流翼181的重心處。此外,第一流體F1於回流段123沿著相鄰兩回流翼181之間進行整流,而注入回流段123後的第二流體F2在狹縫185中產生分流及進行第一次整流,接續,第二流體F2沿著回流翼181的第二翼部184外周緣進行第二次整流並與第一流體F1匯流。其中,落在回流翼181內的注入孔182位於回流段123鄰近第一轉折段122處,且離向(或稱遠離)第二轉折段124處,使得第一流體F1與第二流體F2在流至第二級葉輪170之前具有較長的流動路徑以均勻混合,據以提升離心式壓縮機100的壓縮效率。As shown in FIGS. 1B and 2C , the
如圖1B及圖2A所示,第二流體F2沿著軸向(例如平行於驅動軸150的長軸方向)注入流道120,且第二流體F2的注入位置落在流道120的回流段123內。在第二流體F2注入回流段123之後,第二流體F2在狹縫185中產生分流及進行第一次整流,接續,第二流體F2沿著回流翼181的第二翼部184的外周緣自回流段123流向第二轉折段124,以進行第二次整流並與第一流體F1匯流,使回流段123內的第二流體F2與第一流體F1的流向一致,並減少紊流的產生,使得第一流體F1與第二流體F2得以在流道120內均勻混合形成第三流體F3,據以減少流體壓損並提升空氣動力效率,從而提升離心式壓縮機100的壓縮效率。As shown in FIG. 1B and FIG. 2A , the second fluid F2 is injected into the
請參考圖1B,回流導葉底座180的第二表面187鄰接密封空間101,其中節能器噴入通道190透過密封空間101連通注入孔182,且回流導葉底座180、第二級葉輪170及機殼之間設有密封件102,以防止第二流體F2外洩。Please refer to FIG. 1B , the
圖3至圖7是本發明其他實施例的回流導葉底座的俯視示意圖。如圖3所示,圖2C所示的回流翼181的狹縫185為弧形狹縫,不同的是,本實施例的回流翼181a的狹縫1851為線性狹縫,且線性狹縫是以中心圓的切線方向延伸。如圖4所示,圖2C所示的回流翼181的翼型為凹凸翼型,不同的是,本實施例的回流翼181b的翼型為平凸翼型。如圖5所示,圖2C所示的回流翼181的翼型為凹凸翼型,不同的是,本實施例的回流翼181c的翼型為S形翼型。如圖6所示,圖2C所示的回流翼181的翼型為凹凸翼型,不同的是,本實施例的回流翼181d的翼型為對稱翼型。如圖7所示,圖2C所示的回流翼181的翼型為凹凸翼型,不同的是,本實施例的回流翼181e的翼型為平板翼型。3 to 7 are schematic top views of the return guide vane base in other embodiments of the present invention. As shown in Figure 3, the
舉例來說,依不同設計需求,圖2C至圖7所示的回流翼的狹縫可為弧形狹縫、線性狹縫或弧形狹縫與線性狹縫的組合,並且,回流導葉底座上的回流翼的翼型可為圖2C至圖7所示的多種翼型的其中一者或至少二者以上的組合。另外,因應實際工況需求,注入孔可設計為直孔、錐孔或是直孔與錐孔的組合。For example, depending on different design requirements, the slits of the return vanes shown in Figures 2C to 7 can be arc slits, linear slits, or a combination of arc slits and linear slits, and the return guide vane base The airfoil of the return airfoil on the airfoil may be one of the various airfoils shown in FIGS. 2C to 7 or a combination of at least two or more of them. In addition, in response to actual working conditions, the injection hole can be designed as a straight hole, a tapered hole, or a combination of a straight hole and a tapered hole.
圖8是本發明另一實施例的離心式壓縮機的局部放大示意圖。請先參考圖1B,本實施例的回流導葉底座180包括第一回流導葉底座180a及第二回流導葉底座180b,其中第一回流導葉底座180a位於第二級葉輪170與第二回流導葉底座180b之間,且第二回流導葉底座180b位於第一回流導葉底座180a與第一級葉輪160之間。第一回流導葉底座180a的第一表面186面對第二回流導葉底座180b的第一表面1861,且第一回流導葉底座180a的第一表面186及第二回流導葉底座180b的第一表面1861均位於回流段123內。回流翼181凸出於第一回流導葉底座180a的第一表面186,並接觸第二回流導葉底座180b的第一表面1861。Figure 8 is a partially enlarged schematic diagram of a centrifugal compressor according to another embodiment of the present invention. Please refer to FIG. 1B first. The return
接著,請參考圖8,不同於上述實施例,本實施例的回流翼181凸出於第二回流導葉底座180b的第一表面1861,並接觸第一回流導葉底座180a的第一表面186。另一方面,注入孔182位於第一回流導葉底座180a,並對準位於第二回流導葉底座180b的回流翼181的狹縫185。Next, please refer to Figure 8. Different from the above embodiment, the
圖9是本發明又一實施例的離心式壓縮機的局部放大示意圖。請參考圖9,同理,更可依不同工況需求,將回流翼181’和注入孔182’設置於第一擴壓段121內,使回流翼181’凸出於第二回流導葉底座180b中遠離第一表面1861的第三表面186’,且與第一擴壓段121和第一級葉輪160對應設置。具體來說,第二回流導葉底座180b具有位於第一擴壓段121內的第三表面186’及相對於第三表面186’的第四表面187’,且所述多個注入孔182’貫通第三表面186’與第四表面187’。另外,每一個回流翼181’的第一翼部183’及第二翼部184’凸出於第三表面186’。Figure 9 is a partially enlarged schematic diagram of a centrifugal compressor according to yet another embodiment of the present invention. Please refer to Figure 9. Similarly, the return wing 181' and the injection hole 182' can be arranged in the
第二流體F2的注入位置落在流道120的第一擴壓段121內,在第二流體F2注入第一擴壓段121之後,第二流體F2在狹縫185’中產生分流及進行第一次整流,接續,第二流體F2沿著回流翼181’的第二翼部184’的外周緣自第一擴壓段121流向第一轉折段122,以進行第二次整流並與第一流體F1匯流,使第一擴壓段121內的第二流體F2與第一流體F1的流向一致,並減少紊流的產生,使得第一流體F1與第二流體F2得以在流道120內均勻混合形成第三流體F3,據以減少流體壓損並提升空氣動力效率,從而提升離心式壓縮機100的壓縮效率。The injection position of the second fluid F2 falls within the
綜上所述,在本發明的離心式壓縮機中,第二流體的注入位置落在流道的回流段(或第一擴壓段)的前端內,使得第一流體與第二流體在流至第二級葉輪之前具有較長的流動路徑以均勻混合。另一方面,注入流道的回流段(或第一擴壓段)後的第二流體在狹縫中產生分流及進行第一次整流,接續,第二流體沿著回流翼的第二翼部外周緣自回流段流向第二轉折段,並進行第二次整流,使回流段(或第一擴壓段)內的第二流體與第一流體的流向一致,並減少紊流的產生,使得第一流體與第二流體得以在流道內均勻混合,據以減少流體壓損並提升空氣動力效率,從而提升離心式壓縮機的壓縮效率。To sum up, in the centrifugal compressor of the present invention, the injection position of the second fluid falls within the front end of the return section (or first expansion section) of the flow channel, so that the first fluid and the second fluid are in the flow path. There is a longer flow path before the second stage impeller for uniform mixing. On the other hand, the second fluid injected into the return section (or first expansion section) of the flow channel splits in the slit and undergoes first rectification. Then, the second fluid flows along the second wing of the return wing. The outer peripheral edge flows from the return section to the second turning section, and performs a second rectification, so that the second fluid in the return section (or first expansion section) is consistent with the flow direction of the first fluid, and reduces the generation of turbulence, so that The first fluid and the second fluid can be evenly mixed in the flow channel, thereby reducing fluid pressure loss and improving aerodynamic efficiency, thereby improving the compression efficiency of the centrifugal compressor.
雖然本發明已以實施例揭露如上,然其並非用以限定本發明,任何所屬技術領域中具有通常知識者,在不脫離本發明的精神和範圍內,當可作些許的更動與潤飾,故本發明的保護範圍當視後附的申請專利範圍所界定者為準。Although the present invention has been disclosed above through embodiments, they are not intended to limit the present invention. Anyone with ordinary knowledge in the technical field may make some modifications and modifications without departing from the spirit and scope of the present invention. Therefore, The protection scope of the present invention shall be determined by the appended patent application scope.
100:離心式壓縮機
101:密封空間
102:密封件
110:進氣口
120:流道
121:第一擴壓段
122:第一轉折段
123:回流段
124:第二轉折段
125:第二擴壓段
130:蝸殼流道
140:進氣導葉
150:驅動軸
160:第一級葉輪
170:第二級葉輪
180:回流導葉底座
180a:第一回流導葉底座
180b:第二回流導葉底座
181、181a~181e、181’:回流翼
182、182’:注入孔
183、183’:第一翼部
183a:外端部
184、184’:第二翼部
184a:內端部
185、1851、185’:狹縫
185a:開口
186、1861:第一表面
186’:第三表面
187:第二表面
187’:第四表面
188:第一開口
189:第二開口
190:節能器噴入通道
A1、A2:孔徑
D、D1、S、S1:距離
F1:第一流體
F2:第二流體
F3:第三流體
R:區域
100:Centrifugal compressor
101: Sealed space
102:Seals
110:Air inlet
120:Flow channel
121: First expansion section
122: The first turning point
123:Reflow section
124: The second turning point
125: Second expansion section
130: Volute runner
140:Inlet guide vane
150: Drive shaft
160:First stage impeller
170:Second stage impeller
180:Return
圖1A是本發明一實施例的離心式壓縮機的剖面示意圖。 圖1B是圖1A的區域R的放大示意圖。 圖2A至圖2C是本發明一實施例的回流導葉底座在不同視角下的示意圖。 圖3至圖7是本發明其他實施例的回流導葉底座的俯視示意圖。 圖8是本發明另一實施例的離心式壓縮機的局部放大示意圖。 圖9是本發明又一實施例的離心式壓縮機的局部放大示意圖。 FIG. 1A is a schematic cross-sectional view of a centrifugal compressor according to an embodiment of the present invention. FIG. 1B is an enlarged schematic diagram of the region R in FIG. 1A . 2A to 2C are schematic views of the return guide vane base from different viewing angles according to an embodiment of the present invention. 3 to 7 are schematic top views of the return guide vane base in other embodiments of the present invention. Figure 8 is a partially enlarged schematic diagram of a centrifugal compressor according to another embodiment of the present invention. Figure 9 is a partially enlarged schematic diagram of a centrifugal compressor according to yet another embodiment of the present invention.
100:離心式壓縮機 100:Centrifugal compressor
110:進氣口 110:Air inlet
120:流道 120:Flow channel
130:蝸殼流道 130: Volute runner
140:進氣導葉 140:Inlet guide vane
150:驅動軸 150: Drive shaft
160:第一級葉輪 160:First stage impeller
170:第二級葉輪 170:Second stage impeller
180:回流導葉底座 180:Return guide vane base
190:節能器噴入通道 190:Energy saver injection channel
F1:第一流體 F1: first fluid
F2:第二流體 F2: Second fluid
R:區域 R:Region
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JPH08284892A (en) * | 1995-04-10 | 1996-10-29 | Mitsubishi Heavy Ind Ltd | Diffuser of centrifugal compressor |
JP5167403B1 (en) * | 2011-12-08 | 2013-03-21 | 三菱重工業株式会社 | Centrifugal fluid machine |
CN103206389B (en) * | 2012-01-12 | 2015-10-14 | 珠海格力电器股份有限公司 | Multistage refrigeration compressor and second vapor injection structure thereof |
US11391289B2 (en) * | 2020-04-30 | 2022-07-19 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi-stage centrifugal compressors |
TWM634139U (en) * | 2022-07-15 | 2022-11-11 | 復盛股份有限公司 | Centrifugal compressor |
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2022
- 2022-07-15 TW TW111126750A patent/TWI827145B/en active
- 2022-08-15 CN CN202210974794.6A patent/CN117432637A/en active Pending
- 2022-08-15 CN CN202222138512.7U patent/CN218266395U/en active Active
Also Published As
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TWI827145B (en) | 2023-12-21 |
CN117432637A (en) | 2024-01-23 |
CN218266395U (en) | 2023-01-10 |
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