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JP2009281155A - Transonic two-stage centrifugal compressor - Google Patents

Transonic two-stage centrifugal compressor Download PDF

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Publication number
JP2009281155A
JP2009281155A JP2008131122A JP2008131122A JP2009281155A JP 2009281155 A JP2009281155 A JP 2009281155A JP 2008131122 A JP2008131122 A JP 2008131122A JP 2008131122 A JP2008131122 A JP 2008131122A JP 2009281155 A JP2009281155 A JP 2009281155A
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blade
impeller
transonic
stage
diffuser
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JP5319958B2 (en
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Ryosuke Mito
良介 三戸
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Mitsubishi Heavy Industries Ltd
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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
    • F04D29/68—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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • 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
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

<P>PROBLEM TO BE SOLVED: To prevent stalling and surging of an impeller and a diffuser blade over an entire operating region from a subsonic region to a supersonic region. <P>SOLUTION: In an operating method of this transonic two-stage centrifugal compressor 10 having a first bleed port 21 disposed at a position near a front end of a front stage intermediate blade 12, and a second bleeding port 22 disposed at a wake flow side of a front stage return blade 14 and at the upstream side of a rear stage impeller 15, in the subsonic region, 0-20% of the entire air flow rate from the first bleeding port 21 is extracted, in a transonic region, 0-8% of the entire air flow rate from the second bleed port 22 is extracted, and in the supersonic region, extraction is not performed at all. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

本発明は、航空用ガスタービン、産業用ガスタービン、舶用過給機、自動車用過給機等に用いられる遷音速二段遠心圧縮機に関するものである。   The present invention relates to a transonic two-stage centrifugal compressor used for an aeronautical gas turbine, an industrial gas turbine, a marine supercharger, an automobile supercharger, and the like.

二段遠心圧縮機としては、例えば、特許文献１に開示されたものが知られている。   As the two-stage centrifugal compressor, for example, the one disclosed in Patent Document 1 is known.

特開平８−２８４８９２号公報JP-A-8-284892

ところで、二段遠心圧縮機のうち、遷音速域に設計点を有するものを遷音速二段遠心圧縮機というが、このような圧縮機では、亜音速域において上流側に位置する前段インペラでストール（失速）が発生し、遷音速域において下流側に位置する後段インペラでストールが発生し、超音速領域では後段ディフューザでストールが発生してしまうといった問題点があった。   By the way, of the two-stage centrifugal compressors, those having a design point in the transonic range are called transonic two-stage centrifugal compressors. In such a compressor, the front impeller located upstream in the subsonic range is stalled. There is a problem that stall occurs in the rear impeller located on the downstream side in the transonic region, and stall occurs in the rear diffuser in the supersonic region.

本発明は、上記の事情に鑑みてなされたもので、亜音速域から超音速域の全ての運転領域にわたって、インペラおよびディフューザ翼のストールおよびサージングを防止することができる遷音速二段遠心圧縮機を提供することを目的とする。   The present invention has been made in view of the above circumstances, and a transonic two-stage centrifugal compressor capable of preventing impeller and diffuser blades from stalling and surging over the entire operating range from the subsonic range to the supersonic range. The purpose is to provide.

本発明は、上記課題を解決するため、以下の手段を採用した。
本発明に係る遷音速二段遠心圧縮機は、二段の蛇行形状に形成された空気流路に上流側から前段中間羽根を有する前段インペラと、前段ディフューザ翼と、前段リターン翼と、後段中間羽根を有する後段インペラと、後段ディフューザ翼とが配設され、前記前段中間羽根の前縁近傍位置に、第１の抽気口が配置され、前記前段リターン翼の後流側であって、かつ、前記後段インペラの上流側に、第２の抽気口が配置されているとともに、前記後段ディフューザ翼のスロート部と対向するディフューザシュラウドに、スロットがそれぞれ設けられている遷音速二段遠心圧縮機であって、亜音速域において前記第１の抽気口から全空気流量の０〜２０％が抽気され、遷音速域において前記第２の抽気口から全空気流量の０〜８％が抽気されるとともに、超音速域においては抽気が一切行われないように構成されている。 The present invention employs the following means in order to solve the above problems.
The transonic two-stage centrifugal compressor according to the present invention includes a front impeller having a front intermediate blade from an upstream side in a two-stage meandering air passage, a front diffuser blade, a front return blade, and a rear intermediate A rear impeller having blades and a rear diffuser blade are disposed; a first extraction port is disposed at a position in the vicinity of the front edge of the front intermediate blade; and on the downstream side of the front stage return blade; A transonic two-stage centrifugal compressor in which a second bleed port is disposed upstream of the rear impeller, and a slot is provided in each of the diffuser shrouds facing the throat portion of the rear diffuser blade. When 0 to 20% of the total air flow rate is extracted from the first extraction port in the subsonic speed range, and 0 to 8% of the total air flow rate is extracted from the second extraction port in the transonic range. To, and is configured to bleed is not performed at all in the supersonic range.

本発明に係る遷音速二段遠心圧縮機の運転方法は、二段の蛇行形状に形成された空気流路に上流側から前段中間羽根を有する前段インペラと、前段ディフューザ翼と、前段リターン翼と、後段中間羽根を有する後段インペラと、後段ディフューザ翼とが配設され、前記前段中間羽根の前縁近傍位置に、第１の抽気口が配置され、前記前段リターン翼の後流側であって、かつ、前記後段インペラの上流側に、第２の抽気口が配置されているとともに、前記後段ディフューザ翼のスロート部と対向するディフューザシュラウドに、スロットがそれぞれ設けられている遷音速二段遠心圧縮機の運転方法であって、亜音速域において前記第１の抽気口から全空気流量の０〜２０％を抽気し、遷音速域において前記第２の抽気口から全空気流量の０〜８％を抽気することとし、超音速域においては抽気を一切行わないこととした。   The operation method of the transonic two-stage centrifugal compressor according to the present invention includes a front-stage impeller having a front-stage intermediate blade from an upstream side in an air passage formed in a two-stage meandering shape, a front-stage diffuser blade, a front-stage return blade, A rear impeller having a rear intermediate blade and a rear diffuser blade are disposed, and a first extraction port is disposed in the vicinity of the front edge of the front intermediate blade, on the downstream side of the front return blade. In addition, a second bleed port is disposed upstream of the rear stage impeller, and a transonic two-stage centrifugal compression is provided in which a slot is provided in each diffuser shroud facing the throat portion of the rear stage diffuser blade. The operation method of the machine, wherein 0 to 20% of the total air flow rate is extracted from the first bleed port in the subsonic region, and 0 to 8% of the total air flow rate from the second bleed port in the transonic region. It was decided to bleed, in the supersonic region was not carried out any bleed.

このような遷音速二段遠心圧縮機または遷音速二段遠心圧縮機の運転方法によれば、亜音速域から超音速域の全ての運転領域にわたって、前段インペラ、後段インペラ、前段ディフューザ翼、および後段ディフューザ翼のストールおよびサージングを防止することができて、圧縮機全体の効率を常に高効率に保つことができる。   According to the operation method of such a transonic two-stage centrifugal compressor or a transonic two-stage centrifugal compressor, the front-stage impeller, the rear-stage impeller, the front-stage diffuser blade, Stalling and surging of the rear diffuser blade can be prevented, and the efficiency of the entire compressor can always be kept high.

上記遷音速二段遠心圧縮機において、前記前段インペラの翼端前縁部と対向するインペラシュラウド、および前記後段インペラの翼端前縁部と対向するインペラシュラウドに、溝状のケーシングトリートメントが周方向に沿って形成されているとさらに好適である。   In the transonic two-stage centrifugal compressor, a grooved casing treatment is circumferentially disposed on the impeller shroud facing the blade front edge of the front impeller and the impeller shroud facing the blade front edge of the rear impeller. It is more preferable that it is formed along the line.

このような遷音速二段遠心圧縮機によれば、インペラの翼端漏れ流れが、ケーシングトリートメント内に吸い上げられ（吸い出され）、ケーシングトリートメント内を通って周方向に吐き出されることとなるので、インペラの翼端漏れ流れの上流側（前縁側）への逆流を抑制することができ、作動範囲を拡大させることができる。   According to such a transonic two-stage centrifugal compressor, the impeller blade tip leakage flow is sucked up (sucked out) into the casing treatment and discharged in the circumferential direction through the casing treatment. The backflow of the impeller blade tip leakage flow to the upstream side (front edge side) can be suppressed, and the operating range can be expanded.

上記遷音速二段遠心圧縮機において、前記スロットの上流側に位置するディフューザシュラウドに、前記スロットから吸い出された作動流体を前記後段ディフューザ翼の前縁に向かって噴き出させる噴出口がそれぞれ設けられているとさらに好適である。   In the transonic two-stage centrifugal compressor, each of the diffuser shrouds located on the upstream side of the slot is provided with an outlet for ejecting the working fluid sucked from the slot toward the front edge of the rear diffuser blade. It is more preferable that it is used.

このような遷音速二段遠心圧縮機によれば、ストール域における後段ディフューザ翼１７への流入角がコントロールされることとなるので、後段ディフューザ翼１７のストールおよびサージングを防止することができる。   According to such a transonic two-stage centrifugal compressor, the inflow angle to the rear diffuser blade 17 in the stall region is controlled, so that stall and surging of the rear diffuser blade 17 can be prevented.

本発明によれば、亜音速域から超音速域の全ての運転領域にわたって、インペラおよびディフューザ翼のストールおよびサージングを防止することができるという効果を奏する。   According to the present invention, there is an effect that stall and surging of the impeller and the diffuser blade can be prevented over the entire operation range from the subsonic range to the supersonic range.

以下、本発明に係る遷音速二段遠心圧縮機の一実施形態について、図１から図６を参照しながら説明する。
図１は本実施形態に係る遷音速二段遠心圧縮機の断面図、図２から図４はそれぞれインペラの翼端と対向するインペラシュラウドをインペラの回転軸の側から見た展開図、図５（ａ）は後段ディフューザ翼が取り付けられているディフューザシュラウドを流路の中心側から見た平面図、図５（ｂ）は図５（ａ）のＶ−Ｖ矢視断面図、図６は抽気量を説明するためのグラフである。 Hereinafter, an embodiment of a transonic two-stage centrifugal compressor according to the present invention will be described with reference to FIGS. 1 to 6.
FIG. 1 is a cross-sectional view of a transonic two-stage centrifugal compressor according to the present embodiment, and FIGS. 2 to 4 are development views of an impeller shroud facing the impeller blade tip as seen from the side of the impeller rotating shaft. FIG. 5A is a plan view of a diffuser shroud to which a rear diffuser blade is attached as viewed from the center of the flow path, FIG. 5B is a cross-sectional view taken along the line V-V in FIG. 5A, and FIG. It is a graph for demonstrating quantity.

図１に示すように、本実施形態に係る遷音速二段遠心圧縮機１０は、二段の蛇行形状に形成された空気流路ｆに上流側から前段インペラ１１と、前段中間羽根１２と、前段ディフューザ翼１３と、前段リターン翼１４と、後段インペラ１５と、後段中間羽根１６と、後段ディフューザ翼１７とが配設されたものである。また、前段インペラ１１と前段中間羽根１２との中間位置には第１の抽気口２１が配置され、前段リターン翼１４の後流側であって、かつ、後段インペラ１５の上流側には第２の抽気口２２が配置されており、これら第１の抽気口２１および第２の抽気口２２から作動流体（例えば、空気）の一部が抽気される（吸い出される）ようになっている。   As shown in FIG. 1, the transonic two-stage centrifugal compressor 10 according to this embodiment includes a front-stage impeller 11, a front-stage intermediate blade 12, and an upstream air flow path f formed in a two-stage meandering shape, A front-stage diffuser blade 13, a front-stage return blade 14, a rear-stage impeller 15, a rear-stage intermediate blade 16, and a rear-stage diffuser blade 17 are provided. A first bleed port 21 is disposed at an intermediate position between the front stage impeller 11 and the front stage intermediate blade 12, on the downstream side of the front stage return blade 14 and on the upstream side of the rear stage impeller 15. A part of the working fluid (for example, air) is extracted (sucked out) from the first bleeder port 21 and the second bleeder port 22.

図６に示すように、本実施形態に係る遷音速二段遠心圧縮機１０では、亜音速域において抽気口２１から全空気流量の０〜２０％を抽気し、遷音速域において抽気口２２から全空気流量の０〜８％を抽気することとし、超音速域においては抽気を一切行わないこととした。   As shown in FIG. 6, in the transonic two-stage centrifugal compressor 10 according to this embodiment, 0 to 20% of the total air flow rate is extracted from the extraction port 21 in the subsonic region, and from the extraction port 22 in the transonic region. It was decided that 0 to 8% of the total air flow rate was extracted and no extraction was performed in the supersonic region.

前段インペラ１１の翼端前縁部と対向するインペラシュラウド（ケーシングの内周面）３１、および後段インペラ１５の翼端前縁部と対向するインペラシュラウド（ケーシングの内周面）３２には、例えば、図２から図４に示すような溝状のケーシングトリートメント３３が周方向に沿って形成されている。
ケーシングトリートメント３３は、本実施形態に係る遷音速二段遠心圧縮機１０を小流量側で運転した場合に、インペラ１１，１５の前縁部に発生する離脱衝撃波の背後で、翼端漏れ流れと主流とが干渉することによって、インペラ１１，１５の約１０〜１５％コード長の位置に形成されるBlockage（阻害）領域の上流側（例えば、インペラ１１，１５の約５〜１０％コード長）に形成されている。
また、ケーシングトリートメント３３の幅はインペラ１１，１５の約２〜５％コード長に設定され、ケーシングトリートメント３３の深さはチップクリアランス（翼端とインペラシュラウドとの隙間）の約２倍に設定されている。 An impeller shroud (inner peripheral surface of the casing) 31 facing the blade front edge of the front impeller 11 and an impeller shroud (inner peripheral surface of the casing) 32 facing the front edge of the rear impeller 15 are, for example, A groove-like casing treatment 33 as shown in FIGS. 2 to 4 is formed along the circumferential direction.
When the transonic two-stage centrifugal compressor 10 according to the present embodiment is operated on the small flow rate side, the casing treatment 33 has a blade tip leakage flow behind the separation shock wave generated at the front edge of the impellers 11 and 15. The upstream side of the blockage area formed at the position of about 10-15% code length of the impellers 11, 15 due to interference with the mainstream (for example, about 5-10% code length of the impellers 11, 15) Is formed.
The width of the casing treatment 33 is set to about 2 to 5% cord length of the impellers 11 and 15, and the depth of the casing treatment 33 is set to about twice the tip clearance (the gap between the blade tip and the impeller shroud). ing.

そして、このようなケーシングトリートメント３３を設けることにより、インペラ１１，１５の翼端漏れ流れが、ケーシングトリートメント３３内に吸い上げられ（吸い出され）、ケーシングトリートメント３３内を通って周方向に吐き出されることとなるので、インペラ１１，１５の翼端漏れ流れの上流側（前縁側）への逆流を抑制することができ、作動範囲を拡大させることができる。   By providing such a casing treatment 33, the wing tip leakage flow of the impellers 11 and 15 is sucked up (sucked out) into the casing treatment 33 and discharged through the casing treatment 33 in the circumferential direction. Therefore, the reverse flow to the upstream side (front edge side) of the blade tip leakage flow of the impellers 11 and 15 can be suppressed, and the operating range can be expanded.

一方、後段ディフューザ翼１７のスロート部と対向するディフューザシュラウド（ケーシングの内周面）４１には、例えば、図５（ａ）および図５（ｂ）に示すようなスロット４２がそれぞれ設けられており、スロット４２の上流側に位置するディフューザシュラウド４１には、例えば、図５（ｂ）に示すような噴出口４３がそれぞれ設けられている。
スロット４２および噴出穴４３はそれぞれ、ディフューザシュラウド４１を板厚方向に貫通する平面視略矩形状を有する貫通穴であり、すべてのスロット４２および噴出穴４３は、周方向に沿って配置されたマニホールド４４を介して連通している。
また、噴出穴４３は、この噴出穴４３から噴き出される作動流体の向きが、後段ディフューザ翼１７の圧力面側のメタル角よりも法線方向を向くように形成されている。
さらに、スロット４２を介してマニホールド４４内に流入した作動流体は、噴出穴４３を介して後段ディフューザ翼１７の前縁よりも上流側で後段インペラ１５（図１参照）よりも下流側に噴き出され、再び主流に合流しても良い。 On the other hand, the diffuser shroud (inner peripheral surface of the casing) 41 facing the throat portion of the rear diffuser blade 17 is provided with slots 42 as shown in FIGS. 5A and 5B, for example. The diffuser shroud 41 positioned on the upstream side of the slot 42 is provided with, for example, a spout 43 as shown in FIG.
Each of the slots 42 and the ejection holes 43 is a through hole having a substantially rectangular shape in plan view that penetrates the diffuser shroud 41 in the plate thickness direction, and all the slots 42 and the ejection holes 43 are manifolds arranged along the circumferential direction. 44.
Further, the ejection hole 43 is formed so that the direction of the working fluid ejected from the ejection hole 43 is in the normal direction to the metal angle on the pressure surface side of the rear diffuser blade 17.
Further, the working fluid that has flowed into the manifold 44 via the slot 42 is ejected via the ejection hole 43 upstream of the front edge of the rear diffuser blade 17 and downstream of the rear impeller 15 (see FIG. 1). It is possible to join the mainstream again.

そして、このようなスロット４２およびマニホールド４４を設けることにより、後段ディフューザ翼１７のスロート部における圧力分布が、周方向に均一化されることとなるので、後段ディフューザ翼１７のストールおよびサージングを防止することができる。
また、このような噴出穴４３を設けることにより、ストール域における後段ディフューザ翼１７への流入角がコントロールされることとなるので、後段ディフューザ翼１７のストールおよびサージングを防止することができる。 By providing the slot 42 and the manifold 44 as described above, the pressure distribution in the throat portion of the rear diffuser blade 17 is made uniform in the circumferential direction, thereby preventing stall and surging of the rear diffuser blade 17. be able to.
In addition, by providing such an ejection hole 43, the inflow angle to the rear diffuser blade 17 in the stall region is controlled, so that the stall and surging of the rear diffuser blade 17 can be prevented.

本実施形態に係る遷音速二段遠心圧縮機１０によれば、亜音速域から超音速域の全ての運転領域にわたって、インペラ１１，１５およびディフューザ翼１３，１７のストールおよびサージングを防止することができて、圧縮機全体の効率を常に高効率に保つことができる。   According to the transonic two-stage centrifugal compressor 10 according to the present embodiment, stalling and surging of the impellers 11 and 15 and the diffuser blades 13 and 17 can be prevented over the entire operation region from the subsonic region to the supersonic region. In this way, the efficiency of the entire compressor can always be kept high.

なお、本発明は上述した実施形態に限定されるものではなく、本発明の技術的思想を逸脱しない範囲内で適宜必要に応じて変形実施、変更実施、および組合せ実施可能である。   Note that the present invention is not limited to the above-described embodiments, and modifications, changes, and combinations can be appropriately made as necessary without departing from the technical idea of the present invention.

本発明の一実施形態に係る遷音速二段遠心圧縮機の断面図である。It is sectional drawing of the transonic two-stage centrifugal compressor which concerns on one Embodiment of this invention. インペラの翼端と対向するインペラシュラウドをインペラの回転軸の側から見た展開図である。It is the expanded view which looked at the impeller shroud which opposes the blade tip of an impeller from the rotating shaft side of the impeller. インペラの翼端と対向するインペラシュラウドをインペラの回転軸の側から見た展開図である。It is the expanded view which looked at the impeller shroud which opposes the blade tip of an impeller from the rotating shaft side of the impeller. インペラの翼端と対向するインペラシュラウドをインペラの回転軸の側から見た展開図である。It is the expanded view which looked at the impeller shroud which opposes the blade tip of an impeller from the rotating shaft side of the impeller. （ａ）は後段ディフューザ翼が取り付けられているディフューザシュラウドを流路の中心側から見た平面図、（ｂ）は（ａ）のＶ−Ｖ矢視断面図である。(A) is the top view which looked at the diffuser shroud where the back | latter stage diffuser blade | wing is attached from the center side of a flow path, (b) is VV arrow sectional drawing of (a). 抽気量を説明するためのグラフである。It is a graph for demonstrating the amount of extraction.

符号の説明Explanation of symbols

１０ 遷音速二段遠心圧縮機
１１ 前段インペラ
１２ 前段中間羽根
１３ 前段ディフューザ翼
１４ 前段リターン翼
１５ 後段インペラ
１６ 後段中間羽根
１７ 後段ディフューザ翼
２１ 第１の抽気口
２２ 第２の抽気口
３１ インペラシュラウド
３２ インペラシュラウド
３３ ケーシングトリートメント
４１ ディフューザシュラウド
４２ スロット
４３ 噴出口
ｆ 空気流路 DESCRIPTION OF SYMBOLS 10 Transonic two-stage centrifugal compressor 11 Front stage impeller 12 Front stage intermediate blade 13 Front stage diffuser blade 14 Front stage return blade 15 Rear stage impeller 16 Rear stage intermediate blade 17 Rear stage diffuser blade 21 First extraction port 22 Second extraction port 31 Impeller shroud 32 Impeller shroud 33 Casing treatment 41 Diffuser shroud 42 Slot 43 Spout f Air flow path

Claims (4)

二段の蛇行形状に形成された空気流路に上流側から前段中間羽根を有する前段インペラと、前段ディフューザ翼と、前段リターン翼と、後段中間羽根を有する後段インペラと、後段ディフューザ翼とが配設され、
前記前段中間羽根の前縁近傍位置に、第１の抽気口が配置され、前記前段リターン翼の後流側であって、かつ、前記後段インペラの上流側に、第２の抽気口が配置されているとともに、
前記後段ディフューザ翼のスロート部と対向するディフューザシュラウドに、スロットがそれぞれ設けられている遷音速二段遠心圧縮機であって、
亜音速域において前記第１の抽気口から全空気流量の０〜２０％が抽気され、遷音速域において前記第２の抽気口から全空気流量の０〜８％が抽気されるとともに、超音速域においては抽気が一切行われないように構成されていることを特徴とする遷音速二段遠心圧縮機。 A front impeller having a front intermediate blade from the upstream side, a front diffuser blade, a front return blade, a rear impeller having a rear intermediate blade, and a rear diffuser blade are arranged in an air flow path formed in a two-stage meandering shape. Established,
A first bleed port is disposed in the vicinity of the front edge of the front intermediate blade, and a second bleed port is disposed on the downstream side of the front stage return blade and upstream of the rear impeller. And
A transonic two-stage centrifugal compressor in which slots are respectively provided in the diffuser shroud facing the throat portion of the rear diffuser blade,
In the subsonic region, 0 to 20% of the total air flow rate is extracted from the first bleed port, and in the transonic region, 0 to 8% of the total air flow rate is extracted from the second bleed port, and the supersonic speed is extracted. A transonic two-stage centrifugal compressor characterized in that no bleed is performed in the region. 前記前段インペラの翼端前縁部と対向するインペラシュラウド、および前記後段インペラの翼端前縁部と対向するインペラシュラウドに、溝状のケーシングトリートメントが周方向に沿って形成されていることを特徴とする請求項１に記載の遷音速二段遠心圧縮機。   A groove-like casing treatment is formed along the circumferential direction on the impeller shroud facing the blade front edge of the front impeller and the impeller shroud facing the blade front edge of the rear impeller. The transonic two-stage centrifugal compressor according to claim 1. 前記スロットの上流側に位置するディフューザシュラウドに、前記スロットから吸い出された作動流体を前記後段ディフューザ翼の前縁に向かって噴き出させる噴出口がそれぞれ設けられていることを特徴とする請求項１に記載の遷音速二段遠心圧縮機。   The diffuser shroud positioned on the upstream side of the slot is provided with an outlet for ejecting the working fluid sucked out of the slot toward the front edge of the rear diffuser blade. 2. A transonic two-stage centrifugal compressor according to 1. 二段の蛇行形状に形成された空気流路に上流側から前段中間羽根を有する前段インペラと、前段ディフューザ翼と、前段リターン翼と、後段中間羽根を有する後段インペラと、後段ディフューザ翼とが配設され、
前記前段中間羽根の前縁近傍位置に、第１の抽気口が配置され、前記前段リターン翼の後流側であって、かつ、前記後段インペラの上流側に、第２の抽気口が配置されているとともに、
前記後段ディフューザ翼のスロート部と対向するディフューザシュラウドに、スロットがそれぞれ設けられている遷音速二段遠心圧縮機の運転方法であって、
亜音速域において前記第１の抽気口から全空気流量の０〜２０％を抽気し、遷音速域において前記第２の抽気口から全空気流量の０〜８％を抽気することとし、超音速域においては抽気を一切行わないこととしたことを特徴とする遷音速二段遠心圧縮機の運転方法。 A front impeller having a front intermediate blade from the upstream side, a front diffuser blade, a front return blade, a rear impeller having a rear intermediate blade, and a rear diffuser blade are arranged in an air flow path formed in a two-stage meandering shape. Established,
A first bleed port is disposed in the vicinity of the front edge of the front intermediate blade, and a second bleed port is disposed on the downstream side of the front stage return blade and upstream of the rear impeller. And
The operation method of the transonic two-stage centrifugal compressor in which slots are respectively provided in the diffuser shroud facing the throat portion of the rear diffuser blade,
In the subsonic region, 0 to 20% of the total air flow rate is extracted from the first extraction port, and in the transonic region, 0 to 8% of the total air flow rate is extracted from the second extraction port. A method of operating a transonic two-stage centrifugal compressor, characterized in that no bleed is performed in the region.
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