CN102341602B - Axial centrifugal compressor with scalable rake angle - Google Patents
Axial centrifugal compressor with scalable rake angle Download PDFInfo
- Publication number
- CN102341602B CN102341602B CN201080010678.8A CN201080010678A CN102341602B CN 102341602 B CN102341602 B CN 102341602B CN 201080010678 A CN201080010678 A CN 201080010678A CN 102341602 B CN102341602 B CN 102341602B
- 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.)
- Expired - Fee Related
Links
Classifications
-
- 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
-
- 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
-
- 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
- F04D29/26—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
-
- 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 turbines, particularly includes at least one turbocompressor field that is centrifugal or mixing (axial-centrifugal) compression stage.
Background technique
Aero-turbine, especially helicopter turbogenerator, generally all comprise the centrifugal or hybrid compressor compression stage as gas generator.These compressors are all be made up of the driving wheel exported with cardinal principle axial admission mouth and radial direction or impeller, and blade is fixed on bell base, and this base is used as the guide element of air flowing, and guides air-flow into discharge direction from approach axis.So air-flow circulates between this base and compressor housing; Air-flow is undertaken compressing and promoting by each blade of impeller.
Vane tip is freely, and is positioned at the housing of enclosed air tube--or lid-opposite.Trailing edge is lineal shape in the prior art, can tilt relative to the meridian plane of the impeller through root of blade.The term of the angle formed with this meridian plane is tilt angle, or claims the inclination angle of trailing edge, and constitutes one of them interrelated geometrical parameters describing centrifugal impellers blades.
Select large inclined angle (such as, about 20 °) to be a kind of any means known reducing root stress at centrifugal impeller trailing edge place, particularly bend at centrifugal action lower blade and can cause these stress.For this reason, need to design high performance compressor, particularly should be able to:
When equal rotating speed, reduce the thickness of blade, thus reduce the thickness of base housing, and then greatly reduce rotor quality and inertia;
Or, at impeller equal quality and inertial time, improve rotational speed.
Such as, the known U.S. patent documents US of people 5730582 describes a kind of centrifugal impeller of turbomachine compressor.In this impeller, it is with the spiral shape scribed within the barrel, and inclination angle is constant along trailing edge always.
For lineal shape trailing edge, the result selecting large inclined angle is exactly that, relative to this meridian plane, the angle of inclination of vane tip is identical with the angle of inclination of blade root.When there is brought into incidental contact between blade and lid, if when trailing edge tilts along vane rotary direction, vane tip there will be metal auto-articulated (auto-engage), and its risk causes performance greatly to decline.
In addition, the known U.S. patent documents US of people 4819884 describes a kind of ventilation plant, it comprises a kind of impeller, in this impeller, inclination angle continues to increase from root of blade to its top, and, in this impeller, vane tip is fixed on a disk, thus avoids the risk of blade at this ventilation plant housing internal gearing.
Summary of the invention
The object of the invention is to overcome these defects, a kind of centrifugal or mixing axial-centrifugal compressor is provided, this compressor does not have some defect of the prior art, and, particularly, with large inclined angle, the phenomenon of vane tip auto-articulated can not be there is when blade contacts with lid in the trailing edge of this compressor at its root.
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, the multiple blades extended between leading edge and trailing edge are fixed on the base by its root, described trailing edge along described compressor sense of rotation root of blade relative to its root through the meridian plane of blade the angle that tilts, it is characterized in that, trailing edge is less than the inclination alpha at blade root place in the angle of inclination beta of vane tip.
Because roof inclination is less, the corner that trailing edge and vane tip are formed in more tangential, therefore, when occurring in brought into incidental contact situation, not too can pass housing relative to housing.
Preferably, the angle of inclination beta of trailing edge at vane tip place close to zero, or is exactly even zero.Even more preferably, the angle of inclination beta of trailing edge at vane tip place is negative value.These layouts provide larger guarantee, and namely the corner at trailing edge top is occurring can not penetrating in housing in brought into incidental contact situation.
In a specific embodiment, the curvature of trailing edge is constant between the root of edge and top in the rear.For this reason, the shape of trailing edge is circular arc.
In another embodiment, the curvature of trailing edge is transformable for continuing between the root of edge and top in the rear.
In addition, the invention still further relates to a kind of turbo machine, that includes the compressor with above-mentioned wherein a kind of characteristic.Finally, this invention relates to a kind of aircraft that this turbo machine is housed.
Accompanying drawing explanation
With reference to accompanying schematic figure, the following indicative explaination in detail of the embodiment of the present invention provided by completely illustrative and indefiniteness example, the present invention may be better understood, and other objects of the present invention, details, characteristic and advantage can more clearly display, and accompanying drawing is as follows:
Fig. 1 is the perspective view of the Centrufugal compressor impeller according to the embodiment of the present invention;
Fig. 2 is the front elevation of the Centrifugal Compressor Blades trailing edge according to prior art; And
Fig. 3 is the front elevation of the Centrifugal Compressor Blades trailing edge according to the embodiment of the present invention.
Embodiment
With reference to Fig. 1, the centrifugal compressor 1 comprising bell base 2 can be seen, on described base, be fixed with the compressor blade 3 being evenly distributed on base 2 periphery.At an upper portion thereof, be positioned at the cylinder forming compressor wheel hub 4, described top is corresponding with the compressed-air actuated plane of inlet of needs, and the other end of base is in its underpart, is positioned at the disk 5 relative to described compressor rotating shaft line radial direction in the end of base 2.Blade 3 is fixed by base 2 at its root 6; The top 7 of these blades is freely and can rotates in compressor housing (not shown).Along air current flow direction, blade extends in the leading edge 8 at wheel hub 4 place with between the trailing edge 9 at disk 5 place.
Referring now to Fig. 2, the trailing edge 9 of the compressor blade 3 according to prior art can be seen.This trailing edge at its root along sense of rotation relative to the angle [alpha] that tilts through the meridian plane of root.This trailing edge 9 is in line shape, and that is, this trailing edge 9 whole height surface thereof degree from root to top is identical, equals the tilting value α of root of blade.
On the contrary, in figure 3, the shape of trailing edge 9 can change along its height.It to tilt an angle [alpha] along sense of rotation at blade 3 root 6 place, and be defined as tilt angle in the prior art, but this angle diminishes in an upward direction gradually along trailing edge, thus reach value β at blade 3 top 7 place, this value is less than α.This value β can be zero or or even negative value, that is, vane tip is then along tilting with the opposite direction of vane rotary.
Therefore, the invention reside in and select the comparatively large inclined angle α at blade root 6 place at trailing edge 9 place, then, blade 3 applies a curvature, thus find out vane tip less, be even the inclination angle of zero or negative value.The flexural stress of root can be reduced compared with large inclined angle α, the risk then reducing the auto-articulated (auto-engagement) of unexpected contact situation lower blade 3 in housing between trailing edge 9 place vane tip 7 and compressor housing compared with small inclination β at top 7 place in the application of blade root 6 place.
The formation of this profile in trailing edge 9 place is based on a processing method (point machining method), and this method allows 3 dimension blade geometric shapes; On the contrary, the Flank machining (flank machining) used in the past have employed ruled surface (that is, by a large amount of rectilinear(-al)) in blade profile design, limits this possibility.
Obviously, aerodynamic having a strong impact on is not subject to this change of this profile geometries.According to the use of blade 3 of the present invention even surprisingly, owing to reducing along trailing edge 9 height top rade, improve the performance of compressor on the contrary.
By the calculating to actual blade, the result shows, after adopting the present invention, can reduce the stress of blade and the auto-articulated of vane tip simultaneously.
Therefore, present invention saves quality and inertia, or, in employing equal in quality with in identical inertia situation, can rotational speed be improved, and can not performance be reduced when there is contact between blade 3 and housing.
Adjust the curvature of blade 3 about the trailing edge place 9 between root of blade 6 and top 7, expectation has multiple multi-form.Such as, this curvature can be constant, and trailing edge shape is circular arc, or is continually varying.Curvature between root of blade and top is selected the impact of compressor aerodynamic performance according to it.
Although describe the present invention in conjunction with specific embodiments above, obviously, in any case the present invention is not limited only to this mode of execution, it comprises the combining form belonging to described all technically identical enforcement means in the scope of the invention and these means.
Claims (8)
1. the driving wheel of an or mixing axial-centrifugal compressor centrifugal for turbo machine, comprise base (2), the multiple blades (3) extended between leading edge (8) and trailing edge (9) are fixing on the base by root of blade (6), described trailing edge along described compressor (1) sense of rotation at blade (3) root (6) place relative to its root through the meridian plane of blade the angle [alpha] that tilts, it is characterized in that, trailing edge (9) is less than the inclination alpha at root of blade place in the angle of inclination beta at blade (3) top (7).
2. driving wheel according to claim 1, is characterized in that, trailing edge (9) close to zero, or is exactly even zero in the angle of inclination beta of vane tip.
3. driving wheel according to claim 1, is characterized in that, trailing edge (9) is negative value in the angle of inclination beta of vane tip.
4. according to the driving wheel of Claim 1-3 wherein described in one, it is characterized in that, the curvature of trailing edge (9) is constant between edge root (6) and top (7) in the rear.
5. according to the driving wheel of Claim 1-3 wherein described in one, it is characterized in that, the curvature of trailing edge (9) is continue change in the rear between edge root (6) and top (7).
6. one kind includes the compressor according to the driving wheel of claim 1 to 5 wherein described in one.
7. one kind includes the turbo machine of compressor according to claim 6.
8. one kind is equipped with the aircraft of turbo machine described in foregoing Claims.
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 CN102341602A (en) | 2012-02-01 |
| CN102341602B true 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) |
Families Citing this family (15)
| 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 |
| WO2014102981A1 (en) * | 2012-12-27 | 2014-07-03 | 三菱重工業株式会社 | Radial turbine rotor blade |
| JP5705945B1 (en) * | 2013-10-28 | 2015-04-22 | ミネベア株式会社 | Centrifugal fan |
| WO2015104282A1 (en) * | 2014-01-07 | 2015-07-16 | Nuovo Pignone Srl | Centrifugal compressor impeller with non-linear blade leading edge and associated design method |
| CN103758783B (en) * | 2014-02-17 | 2016-04-27 | 南通大通宝富风机有限公司 | A kind of control rod drive mechanisms (CRD) cooling blower blade reducing root bending stress |
| 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 |
| 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 |
| JP6992504B2 (en) * | 2017-12-27 | 2022-01-13 | トヨタ自動車株式会社 | Impeller manufacturing method |
Citations (4)
| 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 |
| 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 |
Family Cites Families (8)
| 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 |
| DE4403224A1 (en) * | 1994-02-03 | 1995-08-10 | Vorwerk Co Interholding | Radial fan wheel |
| US6338610B1 (en) * | 1998-01-14 | 2002-01-15 | Ebara Corporation | Centrifugal turbomachinery |
| US7563074B2 (en) * | 2005-09-13 | 2009-07-21 | Ingersoll-Rand Company | Impeller for a centrifugal compressor |
| 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 EP EP10707910A patent/EP2406500A1/en not_active Withdrawn
- 2010-03-10 CN CN201080010678.8A patent/CN102341602B/en not_active Expired - Fee Related
- 2010-03-10 KR KR1020117024047A patent/KR101746870B1/en active IP Right Grant
- 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 RU RU2011141460/06A patent/RU2011141460A/en unknown
- 2010-03-10 WO PCT/EP2010/053057 patent/WO2010103055A1/en active Application Filing
- 2010-03-10 JP JP2011553449A patent/JP5687215B2/en not_active Expired - Fee Related
Patent Citations (4)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20110129465A (en) | 2011-12-01 |
| JP2012520412A (en) | 2012-09-06 |
| FR2943103A1 (en) | 2010-09-17 |
| US20110318188A1 (en) | 2011-12-29 |
| KR101746870B1 (en) | 2017-06-14 |
| CN102341602A (en) | 2012-02-01 |
| WO2010103055A1 (en) | 2010-09-16 |
| CA2755017C (en) | 2017-04-04 |
| FR2943103B1 (en) | 2011-05-27 |
| JP5687215B2 (en) | 2015-03-18 |
| CA2755017A1 (en) | 2010-09-16 |
| EP2406500A1 (en) | 2012-01-18 |
| RU2011141460A (en) | 2013-04-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150701 Termination date: 20200310 |
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| CF01 | Termination of patent right due to non-payment of annual fee |