CN102341602A - Axial centrifugal compressor with scalable rake angle - Google Patents
Axial centrifugal compressor with scalable rake angle Download PDFInfo
- Publication number
- CN102341602A CN102341602A CN2010800106788A CN201080010678A CN102341602A CN 102341602 A CN102341602 A CN 102341602A CN 2010800106788 A CN2010800106788 A CN 2010800106788A CN 201080010678 A CN201080010678 A CN 201080010678A CN 102341602 A CN102341602 A CN 102341602A
- Authority
- CN
- China
- Prior art keywords
- trailing edge
- blade
- root
- compressor
- angle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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
- F04D29/26—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
- F04D29/30—Vanes
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- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
- F01D5/048—Form or construction
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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
- F04D29/26—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
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a mobile wheel for a centrifugal or axial centrifugal compressor for a turbine engine, that comprises a base (2) on which a plurality of vanes (3) are attached at their feet (6) and extend between a leading edge (8) and a trailing edge (9), said trailing edge being inclined at the base (6) of the vane (3) by a slope angle a relative to the middle plane extending through the base thereof in the rotation direction of said compressor (1), characterized in that the trailing edge (9) has at the head (7) of the vane (3) a slope angle Beta smaller than the slope angle a at the vane base.
Description
Technical field
The field of the invention is the turbo machine field, has particularly comprised the turbocompressor field that at least one is centrifugal or mix (axial-centrifugal) compression stage.
Background technique
Aero-turbine, especially helicopter is used turbogenerator, generally all comprises the centrifugal or hybrid compressor compression stage as gas generator.These compressors all are to be made up of the driving wheel or the impeller that have cardinal principle axial admission mouth and radially outlet, and vanes fixed is on bell base, and this base is used as the guide element of air flow, and guides air-flow into the discharge direction from approach axis.So air-flow circulates between this base and compressor housing; Air-flow is compressed by each blade of impeller and promotes.
Vane tip is freely, and is positioned at the housing of occluded air pipeline--or the lid-the opposite.Trailing edge is lineal shape in the prior art, can be with respect to the meridian plane of the impeller that passes root of blade and tilt.The term of the angle that constitutes with this meridian plane is the tilt angle, or claims the inclination angle of trailing edge, and has constituted one of them interrelated geometrical parameters of describing the centrifugal impeller blade.
Selecting large inclined angle (for example, about 20 °) at centrifugal impeller trailing edge place is a kind of any means known that reduces root stress, particularly can cause these stress in the bending of centrifugal action lower blade.For this reason, need the high performance compressor of design, particularly should be able to:
When equal rotating speed, reduce the thickness of blade, thereby reduce the thickness of base housing, and then reduce rotor quality and inertia greatly;
Perhaps, at impeller equal quality and inertial time, improve rotational speed.
For example, the known document us US 5730582 of people has described a kind of centrifugal impeller of turbomachine compressor.In this impeller, it has the spiral shape of in cylinder, scribing, and the inclination angle is constant along trailing edge always.
For the lineal shape trailing edge, selecting the result of large inclined angle is exactly that with respect to this meridian plane, the angle of inclination of vane tip is identical with the angle of inclination of blade root.Between blade and lid, occur under the situation of accidental contact, if trailing edge is when the impeller sense of rotation tilts, the automatic interlock of metal (auto-engage) can appear in vane tip, and its risk is to cause performance to descend greatly.
In addition, the known document us US 4819884 of people has introduced a kind of ventilation plant, and it comprises a kind of impeller; In this impeller; The inclination angle continues to increase to its top from root of blade, and, in this impeller; Vane tip is fixed on the disk, thereby has avoided the risk of blade at this ventilation plant housing internal gearing.
Summary of the invention
The objective of the invention is to overcome these defectives; A kind of centrifugal or mixing axial-centrifugal compressor is provided; This compressor does not have some defective of the prior art, and, particularly; The trailing edge of this compressor has large inclined angle at its root, can not occur the phenomenon of the automatic interlock of vane tip at blade and lid when contacting.
For this reason; Target of the present invention is the driving wheel of the centrifugal or mixing axial-centrifugal compressor of a kind of turbo machine; It comprises base, crosses its root in a plurality of blade pass of extending between leading edge and the trailing edge and is fixed on this base, said trailing edge along said compressor sense of rotation at root of blade with respect to the meridian plane that passes blade at its root and the angle that tilts; It is characterized in that the inclination alpha that trailing edge is located less than blade root in the angle of inclination beta of vane tip.
Because the inclination angle, top is less, the corner that trailing edge and vane tip form is more tangential with respect to housing, therefore, accidental contact situation following time occurring, not too can pass housing.
Preferably, trailing edge is approaching zero in the angle of inclination beta at vane tip place, or even is exactly zero.Even more preferably, the angle of inclination beta of trailing edge at the vane tip place is negative value.These layouts provide bigger assurance, and promptly the corner at trailing edge top can not penetrate in the housing under accidental contact situation occurring.
In a specific embodiment, the curvature of trailing edge is constant between the root of said trailing edge and top.For this reason, trailing edge is shaped as circular arc.
Among another embodiment, the curvature of trailing edge is transformable for continuing between the root of said trailing edge and top.For this reason, this trailing edge is shaped as scroll.
In addition, the invention still further relates to a kind of turbo machine, it has comprised having the above-mentioned wherein compressor of a specific character.At last, this invention relates to a kind of aircraft that this turbo machine is housed.
Description of drawings
With reference to accompanying schematic figure; The following illustrated in detail property explanation of the embodiment of the invention that provides through complete illustrative and indefiniteness example; Can understand the present invention better, other purposes of the present invention, details, characteristic and advantage can more clearly display, and accompanying drawing is following:
Fig. 1 is the perspective view according to the Centrufugal compressor impeller of the embodiment of the invention;
Fig. 2 is the front elevation according to the centrifugal compressor trailing edge of existing technology; And
Fig. 3 is the front elevation according to the centrifugal compressor trailing edge of the embodiment of the invention.
Embodiment
With reference to Fig. 1, can see the centrifugal compressor 1 that comprises bell base 2, on said base, be fixed with the compressor blade 3 that is evenly distributed on base 2 peripheries.The end of base 2 is positioned at the cylinder that constitutes compressor wheel hub 4 at an upper portion thereof, and said top is corresponding with the compressed-air actuated plane of inlet of needs, and the other end of base is positioned at the disk 5 with respect to said compressor rotating shaft line radial direction in its underpart.Blade 3 is fixing by base 2 at its root 6; The top 7 of these blades is freely and can in the compressor housing (not shown), rotates.Along the air current flow direction, blade is extending in the leading edge 8 at wheel hub 4 places with between the trailing edge 9 at disk 5 places.
Referring now to Fig. 2, can see trailing edge 9 according to the compressor blade 3 of existing technology.This trailing edge at its root along sense of rotation with respect to the meridian plane that passes root and the angle [alpha] that tilts.This trailing edge 9 shape that is in line that is to say, this trailing edge 9 whole height from the root to top degree that tilts is identical, equals the tilting value α of root of blade.
On the contrary, in Fig. 3, the shape of trailing edge 9 highly can change along it.It along angle [alpha] of sense of rotation inclination, is defined as the tilt angle at blade 3 roots 6 places in the prior art, and still, this angle is upwards diminishing on the direction along trailing edge gradually, thereby reaches value β at 7 places, blade 3 tops, and this is worth less than α.This value β can be zero or or even negative value, that is to say that the vane tip opposite direction of edge and impeller rotation then tilts.
Therefore, the invention reside in select at trailing edge 9 places blade root 6 places than large inclined angle α, then, on blade 3, use a curvature, thereby it is less even be zero or the inclination angle of negative value to find out vane tip.Use the flexural stress that can reduce root than large inclined angle α at blade root 6 places, the less angle of inclination beta at 7 places, top has then lowered the risk of the automatic interlock (auto-engagement) of unexpected contact situation lower blade 3 in housing between trailing edge 9 place's vane tips 7 and compressor housing.
The formation of this profile in trailing edge 9 places is based on a processing method (point machining method), and this method allows 3 dimension blade geometric shapes; On the contrary, previously used side milling processing (flank machining) has been adopted ruled surface (that is to say, by a large amount of rectilinear(-al)s) in the blade profile design, limited this possibility.
Obviously, this change to this profile geometries does not receive aerodynamic having a strong impact on.According to the use of blade 3 of the present invention even surprisingly, owing to dwindle, improved the performance of compressor on the contrary along trailing edge 9 height top rades.
Through the calculating to actual blade, checking is the result show, behind employing the present invention, can reduce the automatic interlock property of the stress and the vane tip of blade simultaneously.
Therefore, the present invention has saved quality and inertia, perhaps, adopting under equal in quality and the identical inertia situation, can improve rotational speed, and can not reduce performance when between blade 3 and housing, contact occurring.
About the curvature of the 9 adjustment blades 3 of the trailing edge place between root of blade 6 and top 7, estimate to have multiple multi-form.For example, this curvature can be constant, and trailing edge is shaped as circular arc, perhaps is continually varying, and then, the trailing edge profile is scroll.Curvature between root of blade and the top is selected according to its influence to the compressor aerodynamic performance.
Though top combination specific embodiment has been introduced the present invention, obviously, in any case the present invention is not limited only to this mode of execution, it has comprised and has belonged to interior said all the technical identical enforcement means of the scope of the invention and the combining form of these means.
Claims (8)
1. driving wheel that is used for the centrifugal or mixing axial-centrifugal compressor of turbo machine; Comprise base (2); The a plurality of blades (3) that between leading edge (8) and trailing edge (9), extend are fixed on this base through root of blade (6); Said trailing edge locates with respect to passing the meridian plane of blade at its root at blade (3) root (6) along said compressor (1) sense of rotation that the angle [alpha] that tilts is characterized in that, trailing edge (9) in the angle of inclination beta at blade (3) top (7) less than inclination alpha at the root of blade place.
2. driving wheel according to claim 1 is characterized in that, trailing edge (9) in the angle of inclination beta of vane tip near zero, perhaps even be exactly zero.
3. driving wheel according to claim 1 is characterized in that, trailing edge (9) is a negative value in the angle of inclination beta of vane tip.
4. according to claim 1 to 3 described driving wheel wherein, it is characterized in that the curvature of trailing edge (9) is constant between said trailing edge root (6) and top (7).
5. according to claim 1 to 3 described driving wheel wherein, it is characterized in that, the curvature of trailing edge (9) between said trailing edge root (6) and top (7) for continuing to change.
6. one kind has comprised according to claim 1 to 5 compressor of a described driving wheel wherein.
7. turbo machine that comprises compressor according to claim 6.
8. aircraft that is equipped with the said turbo machine of front claim.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0951604A FR2943103B1 (en) | 2009-03-13 | 2009-03-13 | AXIALO-CENTRIFUGAL COMPRESSOR WITH AN EVOLVING RAKE ANGLE |
| FR0951604 | 2009-03-13 | ||
| PCT/EP2010/053057 WO2010103055A1 (en) | 2009-03-13 | 2010-03-10 | Axial centrifugal compressor with scalable rake angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102341602A true CN102341602A (en) | 2012-02-01 |
| CN102341602B CN102341602B (en) | 2015-07-01 |
Family
ID=41057639
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201080010678.8A Expired - Fee Related CN102341602B (en) | 2009-03-13 | 2010-03-10 | Axial centrifugal compressor with scalable rake angle |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US20110318188A1 (en) |
| EP (1) | EP2406500A1 (en) |
| JP (1) | JP5687215B2 (en) |
| KR (1) | KR101746870B1 (en) |
| CN (1) | CN102341602B (en) |
| CA (1) | CA2755017C (en) |
| FR (1) | FR2943103B1 (en) |
| RU (1) | RU2011141460A (en) |
| WO (1) | WO2010103055A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103758783A (en) * | 2014-02-17 | 2014-04-30 | 南通大通宝富风机有限公司 | Control rod drive mechanism cooling fan blade capable of reducing root bending stress |
| CN106164496A (en) * | 2014-01-07 | 2016-11-23 | 诺沃皮尼奥内股份有限公司 | The Centrufugal compressor impeller with non-linear blade inlet edge and the method for designing being associated |
| CN110573745A (en) * | 2017-10-11 | 2019-12-13 | 三菱重工发动机和增压器株式会社 | Impeller of centrifugal rotary machine and centrifugal rotary machine |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8951009B2 (en) * | 2011-05-23 | 2015-02-10 | Ingersoll Rand Company | Sculpted impeller |
| US9476355B2 (en) * | 2012-02-29 | 2016-10-25 | Siemens Energy, Inc. | Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section |
| US8997486B2 (en) | 2012-03-23 | 2015-04-07 | Bullseye Power LLC | Compressor wheel |
| EP2940271B2 (en) | 2012-12-27 | 2023-06-14 | Mitsubishi Heavy Industries, Ltd. | Radial turbine rotor blade |
| JP5705945B1 (en) * | 2013-10-28 | 2015-04-22 | ミネベア株式会社 | Centrifugal fan |
| JP6532215B2 (en) * | 2014-11-10 | 2019-06-19 | 三菱重工サーマルシステムズ株式会社 | Impeller and centrifugal compressor |
| JP6210459B2 (en) * | 2014-11-25 | 2017-10-11 | 三菱重工業株式会社 | Impeller and rotating machine |
| JP6627175B2 (en) * | 2015-03-30 | 2020-01-08 | 三菱重工コンプレッサ株式会社 | Impeller and centrifugal compressor |
| JP2017186914A (en) * | 2016-04-01 | 2017-10-12 | 株式会社日立製作所 | Radial impeller and centrifugal fluid machine including the same |
| FR3062431B1 (en) | 2017-01-27 | 2021-01-01 | Safran Helicopter Engines | WHEEL BLADE FOR TURBOMACHINE, INCLUDING A VANE AT ITS TOP AND ATTACKING EDGE |
| RU2667251C1 (en) * | 2017-10-05 | 2018-09-18 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Box of drive units |
| JP6992504B2 (en) * | 2017-12-27 | 2022-01-13 | トヨタ自動車株式会社 | Impeller manufacturing method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2354653A (en) * | 1940-06-11 | 1944-08-01 | Gen Electric | Impeller |
| US4819884A (en) * | 1985-01-31 | 1989-04-11 | Microfuel Corporation | Means of pneumatic comminution |
| CN1123050A (en) * | 1994-02-03 | 1996-05-22 | 沃维克股份有限公司 | Radial impeller |
| US5730582A (en) * | 1997-01-15 | 1998-03-24 | Essex Turbine Ltd. | Impeller for radial flow devices |
| CN1386983A (en) * | 2002-06-06 | 2002-12-25 | 孙敏超 | Efficient propeller with blades curled backward for centrifugal propeller machinery |
| WO2007033274A2 (en) * | 2005-09-13 | 2007-03-22 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB587514A (en) * | 1942-09-03 | 1947-04-29 | Power Jets Ltd | Improvements relating to centrifugal compressors, pumps and the like |
| FR2393176A1 (en) * | 1977-06-01 | 1978-12-29 | Alsthom Atlantique | High-pressure centrifugal compressor - has rotor with round concave surface and slightly curved vanes |
| US4502837A (en) * | 1982-09-30 | 1985-03-05 | General Electric Company | Multi stage centrifugal impeller |
| US4923370A (en) * | 1988-11-28 | 1990-05-08 | Allied-Signal Inc. | Radial turbine wheel |
| DE69932408T2 (en) * | 1998-01-14 | 2007-03-08 | Ebara Corp. | RADIAL FLOW MACHINE |
| WO2009065030A2 (en) * | 2007-11-16 | 2009-05-22 | Borgwarner Inc. | Low blade frequency titanium compressor wheel |
-
2009
- 2009-03-13 FR FR0951604A patent/FR2943103B1/en not_active Expired - Fee Related
-
2010
- 2010-03-10 WO PCT/EP2010/053057 patent/WO2010103055A1/en active Application Filing
- 2010-03-10 RU RU2011141460/06A patent/RU2011141460A/en unknown
- 2010-03-10 KR KR1020117024047A patent/KR101746870B1/en active IP Right Grant
- 2010-03-10 EP EP10707910A patent/EP2406500A1/en not_active Withdrawn
- 2010-03-10 JP JP2011553449A patent/JP5687215B2/en not_active Expired - Fee Related
- 2010-03-10 CA CA2755017A patent/CA2755017C/en not_active Expired - Fee Related
- 2010-03-10 US US13/256,371 patent/US20110318188A1/en not_active Abandoned
- 2010-03-10 CN CN201080010678.8A patent/CN102341602B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2354653A (en) * | 1940-06-11 | 1944-08-01 | Gen Electric | Impeller |
| US4819884A (en) * | 1985-01-31 | 1989-04-11 | Microfuel Corporation | Means of pneumatic comminution |
| CN1123050A (en) * | 1994-02-03 | 1996-05-22 | 沃维克股份有限公司 | Radial impeller |
| US5730582A (en) * | 1997-01-15 | 1998-03-24 | Essex Turbine Ltd. | Impeller for radial flow devices |
| CN1386983A (en) * | 2002-06-06 | 2002-12-25 | 孙敏超 | Efficient propeller with blades curled backward for centrifugal propeller machinery |
| WO2007033274A2 (en) * | 2005-09-13 | 2007-03-22 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106164496A (en) * | 2014-01-07 | 2016-11-23 | 诺沃皮尼奥内股份有限公司 | The Centrufugal compressor impeller with non-linear blade inlet edge and the method for designing being associated |
| US10634157B2 (en) | 2014-01-07 | 2020-04-28 | Nuovo Pignone Srl | Centrifugal compressor impeller with non-linear leading edge and associated design method |
| CN103758783A (en) * | 2014-02-17 | 2014-04-30 | 南通大通宝富风机有限公司 | Control rod drive mechanism cooling fan blade capable of reducing root bending stress |
| CN110573745A (en) * | 2017-10-11 | 2019-12-13 | 三菱重工发动机和增压器株式会社 | Impeller of centrifugal rotary machine and centrifugal rotary machine |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2010103055A1 (en) | 2010-09-16 |
| CN102341602B (en) | 2015-07-01 |
| FR2943103B1 (en) | 2011-05-27 |
| KR20110129465A (en) | 2011-12-01 |
| CA2755017C (en) | 2017-04-04 |
| FR2943103A1 (en) | 2010-09-17 |
| JP2012520412A (en) | 2012-09-06 |
| JP5687215B2 (en) | 2015-03-18 |
| EP2406500A1 (en) | 2012-01-18 |
| US20110318188A1 (en) | 2011-12-29 |
| CA2755017A1 (en) | 2010-09-16 |
| KR101746870B1 (en) | 2017-06-14 |
| RU2011141460A (en) | 2013-04-20 |
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Granted publication date: 20150701 Termination date: 20200310 |
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| CF01 | Termination of patent right due to non-payment of annual fee |