WO2012077580A1 - Centrifugal turbomachine - Google Patents
Centrifugal turbomachine Download PDFInfo
- Publication number
- WO2012077580A1 WO2012077580A1 PCT/JP2011/077863 JP2011077863W WO2012077580A1 WO 2012077580 A1 WO2012077580 A1 WO 2012077580A1 JP 2011077863 W JP2011077863 W JP 2011077863W WO 2012077580 A1 WO2012077580 A1 WO 2012077580A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- diffuser
- blade
- hub
- distribution
- blades
- Prior art date
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Classifications
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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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
リーン:ディフューザ翼103のハブ101面に対する傾き度合いであり、以下に述べるスイープとダイヘドラルの複合とみなせる。
食い違い角(θSG):翼弦Cが半径方向(R方向)となす角(tanθSG=dC/
dR)。
スイープ(Δσ):図1中で一点鎖線で表した場合で、ディフューザ翼103の翼型104を、翼弦C方向へ平行移動させることで、下流側へ移動させる場合を正とする。
ダイヘドラル(Δδ):図1中で破線で表した場合で、ディフューザ翼103の翼型104を、翼弦Cに垂直な方向へ移動させることである。羽根車の回転方向とは逆方向へ移動させる場合を、正とする。 Chord (C): A line connecting the leading
Lean: Degree of inclination of the
Misalignment angle (θ SG ): Angle formed by the chord C and the radial direction (R direction) (tan θ SG = dC /
dR).
Sweep (Δσ): In the case represented by the one-dot chain line in FIG. 1, the case where the
Dihedral (Δδ): In the case represented by a broken line in FIG. 1, the
Claims (7)
- 同一の回転軸に、ハブとシュラウドとこれらハブとシュラウド間に周方向に間隔をおいて配置した複数の羽根とからなる少なくとも1個以上の羽根車を取り付け、この少なくとも1個の羽根車の少なくともいずれかの下流に羽根付きディフューザを備えた遠心型ターボ機械において、
前記羽根付きディフューザは、前記羽根車の下流側に形成される流路に複数の翼を周方向に間隔をおいて配置されたものであり、各々の前記翼は、基準となる翼を前記回転軸の軸方向である翼高さ方向に積み重ねた形状で形成されており、基準となる翼の前縁と後縁とを結ぶ翼弦方向に垂直な方向であって羽根車の回転方向とは逆の方向に移動させるのを正の移動とするダイヘドラル分布を、ハブ壁面側でハブ側端部から翼高さの中間部に向けて非一様としたことを特徴とする遠心型ターボ機械。 At least one impeller comprising a hub, a shroud, and a plurality of blades spaced circumferentially between the hub and the shroud is attached to the same rotating shaft, and at least one of the at least one impeller In a centrifugal turbomachine with a vaned diffuser on either downstream,
The vaned diffuser is configured such that a plurality of blades are arranged at intervals in a circumferential direction in a flow path formed on the downstream side of the impeller, and each of the blades rotates a reference blade. It is formed in a shape stacked in the blade height direction which is the axial direction of the shaft, and is the direction perpendicular to the chord direction connecting the leading edge and the trailing edge of the reference blade, and the rotation direction of the impeller A centrifugal turbomachine characterized in that a dihedral distribution in which the movement in the opposite direction is a positive movement is non-uniform from the hub side end toward the middle of the blade height on the hub wall surface side. - 前記ディフューザ翼の各々のダイヘドラル分布が、ハブ側端部から翼高さの中間部にむけて増大させる分布としたことを特徴とする請求項1に記載の遠心型ターボ機械。 The centrifugal turbomachine according to claim 1, wherein the dihedral distribution of each of the diffuser blades is a distribution that increases from a hub side end portion toward an intermediate portion of the blade height.
- 前記ディフューザ翼の各々は、その前縁部であってハブ側端部に仮想的に形成される平面とディフューザ翼の負圧面とが鈍角をなすことを特徴とする請求項2に記載の遠心型ターボ機械。 3. The centrifugal mold according to claim 2, wherein each of the diffuser blades has an obtuse angle between a plane virtually formed at a front end portion of the diffuser blade and at a hub side end portion and a suction surface of the diffuser blade. Turbo machine.
- 前記ダイヘドラル分布が、シュラウド側端部から翼高さの中間部に向けておよびハブ側端部から翼高さの中間部に向けて増大する分布であることを特徴とする請求項3に記載の遠心型ターボ機械。 4. The distribution according to claim 3, wherein the dihedral distribution is a distribution that increases from a shroud side end toward an intermediate portion of the blade height and from a hub side end toward an intermediate portion of the blade height. Centrifugal turbomachine.
- 前記ディフューザ翼の各々においては、その前縁部であってシュラウド側端部に仮想的に形成される平面とディフューザ翼の負圧面がなす角度およびハブ板とディフューザ翼の負圧面とがなす角度が鈍角であることを特徴とする請求項4に記載の遠心型ターボ機械。 In each of the diffuser blades, the angle formed by the plane formed virtually at the leading edge of the shroud side end and the suction surface of the diffuser blade and the angle formed by the hub plate and the suction surface of the diffuser blade are 5. The centrifugal turbomachine according to claim 4, wherein the centrifugal turbomachine has an obtuse angle.
- 前記ディフューザ翼の各々のダイヘドラル分布が、ハブ側端部から翼高さの中間部にむけて減少する分布とし、前記基準となる翼の翼弦方向に平行な方向であって下流側に移動させるのを正の移動とするスイープ分布を、ハブ側端部から翼高さの中間部にむけて減少させる分布としたことを特徴とする請求項1に記載の遠心型ターボ機械。 The dihedral distribution of each of the diffuser blades is a distribution that decreases from the hub side end portion toward the middle portion of the blade height, and is moved in a direction parallel to the chord direction of the reference blade and moved downstream. 2. The centrifugal turbomachine according to claim 1, wherein a sweep distribution with a positive movement is reduced from the hub side end toward an intermediate portion of the blade height.
- 前記ディフューザ翼の各々は、少なくともその翼の流れ方向前半部に前記ダイヘドラル分布と前記スイープ分布の少なくともいずれかが適用されていることを特徴とする請求項1ないし6のいずれか1項に記載の遠心型ターボ機械。 7. The diffuser blade according to claim 1, wherein at least one of the dihedral distribution and the sweep distribution is applied to at least a first half portion in the flow direction of the blade. 8. Centrifugal turbomachine.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201180058898.2A CN103314218B (en) | 2010-12-10 | 2011-12-01 | Centrifugal turbomachine |
US13/992,457 US20130309082A1 (en) | 2010-12-10 | 2011-12-01 | Centrifugal turbomachine |
EP11847208.3A EP2650546A1 (en) | 2010-12-10 | 2011-12-01 | Centrifugal turbomachine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2010-275839 | 2010-12-10 | ||
JP2010275839A JP5608062B2 (en) | 2010-12-10 | 2010-12-10 | Centrifugal turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012077580A1 true WO2012077580A1 (en) | 2012-06-14 |
Family
ID=46207070
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2011/077863 WO2012077580A1 (en) | 2010-12-10 | 2011-12-01 | Centrifugal turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130309082A1 (en) |
EP (1) | EP2650546A1 (en) |
JP (1) | JP5608062B2 (en) |
CN (1) | CN103314218B (en) |
WO (1) | WO2012077580A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10233758B2 (en) | 2013-10-08 | 2019-03-19 | United Technologies Corporation | Detuning trailing edge compound lean contour |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10527059B2 (en) | 2013-10-21 | 2020-01-07 | Williams International Co., L.L.C. | Turbomachine diffuser |
EP3412892B1 (en) | 2016-03-31 | 2020-03-18 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Rotary machine blade, supercharger, and method for forming flow field of same |
EP3564537B1 (en) * | 2017-03-28 | 2021-03-10 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Centrifugal compressor and turbocharger |
FR3065023B1 (en) * | 2017-04-07 | 2019-04-12 | Safran Aircraft Engines | REINFORCED AXIAL DIFFUSER |
US10760587B2 (en) * | 2017-06-06 | 2020-09-01 | Elliott Company | Extended sculpted twisted return channel vane arrangement |
EP3460255A1 (en) | 2017-09-20 | 2019-03-27 | Siemens Aktiengesellschaft | Throughflow assembly |
EP3460257A1 (en) | 2017-09-20 | 2019-03-27 | Siemens Aktiengesellschaft | Throughflow assembly |
EP3460256A1 (en) * | 2017-09-20 | 2019-03-27 | Siemens Aktiengesellschaft | Throughflow assembly |
WO2019073551A1 (en) | 2017-10-11 | 2019-04-18 | 三菱重工エンジン&ターボチャージャ株式会社 | Impeller for centrifugal rotating machine, and centrifugal rotating machine |
JP7005393B2 (en) * | 2018-03-09 | 2022-01-21 | 三菱重工業株式会社 | Diffuser vane and centrifugal compressor |
US11098730B2 (en) * | 2019-04-12 | 2021-08-24 | Rolls-Royce Corporation | Deswirler assembly for a centrifugal compressor |
EP3760871A1 (en) | 2019-07-04 | 2021-01-06 | Siemens Aktiengesellschaft | Diffuser for a turbomachine |
EP3760876A1 (en) | 2019-07-04 | 2021-01-06 | Siemens Aktiengesellschaft | Diffuser for a turbomachine |
EP3805572A1 (en) | 2019-10-07 | 2021-04-14 | Siemens Aktiengesellschaft | Diffuser, radial turbocompressor |
KR20210071373A (en) * | 2019-12-06 | 2021-06-16 | 엘지전자 주식회사 | apparatus for both humidification and air cleaning |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2004092482A (en) | 2002-08-30 | 2004-03-25 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor, diffuser blade and its manufacturing method |
US20070053779A1 (en) * | 2005-09-05 | 2007-03-08 | Volker Guemmer | Blade of a turbomachine with block-wise defined profile skeleton line |
US20070140837A1 (en) * | 2005-12-19 | 2007-06-21 | Volker Guemmer | Turbomachine with variable stator |
JP2008138679A (en) * | 2006-11-30 | 2008-06-19 | General Electric Co <Ge> | Advanced booster system |
JP2009504974A (en) | 2005-08-09 | 2009-02-05 | プラクスエア・テクノロジー・インコーポレイテッド | Lean type centrifugal compressor airfoil diffuser |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3482668B2 (en) * | 1993-10-18 | 2003-12-22 | 株式会社日立製作所 | Centrifugal fluid machine |
EP1873402A1 (en) * | 2006-06-26 | 2008-01-02 | Siemens Aktiengesellschaft | Compressor in particular for turbocharger |
-
2010
- 2010-12-10 JP JP2010275839A patent/JP5608062B2/en not_active Expired - Fee Related
-
2011
- 2011-12-01 EP EP11847208.3A patent/EP2650546A1/en not_active Withdrawn
- 2011-12-01 WO PCT/JP2011/077863 patent/WO2012077580A1/en active Application Filing
- 2011-12-01 CN CN201180058898.2A patent/CN103314218B/en not_active Expired - Fee Related
- 2011-12-01 US US13/992,457 patent/US20130309082A1/en not_active Abandoned
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2004092482A (en) | 2002-08-30 | 2004-03-25 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor, diffuser blade and its manufacturing method |
JP2009504974A (en) | 2005-08-09 | 2009-02-05 | プラクスエア・テクノロジー・インコーポレイテッド | Lean type centrifugal compressor airfoil diffuser |
US20070053779A1 (en) * | 2005-09-05 | 2007-03-08 | Volker Guemmer | Blade of a turbomachine with block-wise defined profile skeleton line |
US20070140837A1 (en) * | 2005-12-19 | 2007-06-21 | Volker Guemmer | Turbomachine with variable stator |
JP2008138679A (en) * | 2006-11-30 | 2008-06-19 | General Electric Co <Ge> | Advanced booster system |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10233758B2 (en) | 2013-10-08 | 2019-03-19 | United Technologies Corporation | Detuning trailing edge compound lean contour |
Also Published As
Publication number | Publication date |
---|---|
CN103314218A (en) | 2013-09-18 |
EP2650546A1 (en) | 2013-10-16 |
JP5608062B2 (en) | 2014-10-15 |
JP2012122443A (en) | 2012-06-28 |
US20130309082A1 (en) | 2013-11-21 |
CN103314218B (en) | 2016-03-09 |
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