CN107642382A - Radial turbine rotor and the method for producing it - Google Patents
Radial turbine rotor and the method for producing it Download PDFInfo
- Publication number
- CN107642382A CN107642382A CN201710594823.5A CN201710594823A CN107642382A CN 107642382 A CN107642382 A CN 107642382A CN 201710594823 A CN201710594823 A CN 201710594823A CN 107642382 A CN107642382 A CN 107642382A
- Authority
- CN
- China
- Prior art keywords
- turbine rotor
- radial turbine
- cavity structure
- rotor
- matrix
- 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.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 15
- 239000011159 matrix material Substances 0.000 claims abstract description 23
- 238000000034 method Methods 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims description 5
- 230000000717 retained effect Effects 0.000 claims description 3
- 230000002349 favourable effect Effects 0.000 description 5
- 230000001681 protective effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000001311 chemical methods and process Methods 0.000 description 1
- 208000002925 dental caries Diseases 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000003908 quality control method Methods 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
-
- 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
- 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
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
-
- 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
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- General Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Ceramic Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Materials Engineering (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Powder Metallurgy (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Method the present invention relates to radial turbine rotor and for producing it.Specifically, the present invention relates to a kind of radial turbine rotor (10), with rotor matrix (11)；And with the blade (12) being integrally formed on rotor matrix (11)；Wherein rotor matrix (11) has cavity structure (13).
Description
Technical field
Method the present invention relates to radial turbine rotor and for producing it.
Background technology
Fig. 1 is shown through from the section of radial turbine rotor 1 known in the art.Radial turbine rotor 1 has rotor
Matrix 2 and the multiple blades 3 being integrally formed on rotor matrix 2.Blade 3 has surface, is formed as suction side and on the pressure side,
It is used for the conduction flowed.From radial turbine rotor known to practice, the rotor matrix 2 of radial turbine rotor 1 is embodied as reality
Heart component.This rotor matrix 2 with integrally formed thereon blade 3 preferably by cast manufacture, particularly via
Casting method.
The content of the invention
Thus start, the problem of present invention is based on novel radial turbine rotor and method for manufacturing it is provided.
The problem is solved by radial turbine rotor according to claim 1.According to the present invention, rotor matrix has cavity knot
Structure.
Hollow structure is had according to the rotor matrix of the radial turbine rotor of the present invention.By means of this hollow structure, radial direction
The weight of turbine rotor can reduce compared to from radial turbine rotor known in the art.
Radial turbine rotor with compared with low weight significantly more quickly can accelerate and slow down.Therefore, radial turbine rotor or
Accordingly the dynamic of the turbine with radial turbine rotor can significantly improve.Especially when radial turbine rotor increases for exhaust driven gas turbine
It is favourable during the component part of depressor.In addition, the radial turbine rotor with lower quality allows the axle of radial turbine rotor
The design more advantageously fixed a price held.In addition, (it is intended to the situation in radial turbine rotor breaks to the so-called closed protective of turbine
Under prevent its fragment from reaching environment) less problem is provided.In the case of lighter radial turbine rotor, in the situation of its rupture
Under, energy to be absorbed is less so that closed protective can be implemented more simply and with more favourable cost.
According to the favourable further development of the present invention, cavity structure is strengthened by means of at least one web.Therefore, although
Weight saving, it is possible to provide the rigidity of the best-fit of radial turbine rotor.
According to the favourable further development of the present invention, it is open and the front side of rotor matrix is formed at outside stream guiding surface
And/or on rear side, cavity structure can be accessible from the outside via the opening.On the one hand these openings ensure that radial turbine rotor
Simple productibility, in addition, its roughness for being used on the inner surface of cavity set restriction.
According to the favourable further development of the present invention, the average roughness Ra of restriction is arranged on the inner surface of cavity structure
On, the roughness is between 2 microns to 10 microns.Mean roughness RA (itself and blade on the inner surface of cavity structure
Mean roughness RA on stream guiding surface deviates) it is special for providing the radial turbine rotor with optimal true operation characteristic
It is not preferable.
Limited in claim 6 according to the method for the radial turbine rotor of the present invention for manufacturing.
Brief description of the drawings
The present invention's preferably further develops and will show from dependent claims and from following description.By means of accompanying drawing more
It is described in detail by the exemplary embodiment of the present invention and is not limited to it.There is shown with：
Fig. 1：Through the section of the radial turbine rotor according to prior art；
Fig. 2：Through the section of the first radial turbine rotor according to the present invention；
Fig. 3：Through the section of the second radial turbine rotor according to the present invention；
Fig. 4：Through the section of the 3rd radial turbine rotor according to the present invention.
List of reference characters
1 radial turbine rotor
2 rotor matrix
3 blades
10 radial turbine rotors
11 rotor matrix
12 blades
13 cavity structures
14 webs
15 front sides
16 rear sides
17 openings
18 openings
19 inner surfaces.
Embodiment
The present invention relates to a kind of radial turbine rotor, particularly the radial turbine rotor for turbocharger.The present invention
Further relate to a kind of method for producing this radial turbine rotor.
Fig. 2 is shown through the section of the radial turbine rotor 10 according to the present invention.Radial turbine rotor 10 has rotor
Matrix 11 and the multiple blades 12 being integrally formed on rotor matrix 11.In the sense that the invention proposed herein, cavity knot
Structure 13 is introduced into the rotor matrix 11 of radial turbine rotor 10.The cavity structure 13 can be formed by single cavity, or by passing through
Multiple cavitys that web or partition wall are separated from each other are formed.
Fig. 3 is shown through the section of another radial turbine rotor 10 according to the present invention, wherein in figure 3, cavity
Structure 13 is strengthened by the web 14 in axial direction extended.The web 14 is in figure 3 in axial direction in the footpath according to the present invention
Extend between the front side 15 of the rotor matrix 11 of turbine rotor 10 and rear side 16.
Additionally or alternatively cavity structure 13 can be strengthened in the web 14 in axial direction extended, web in addition, it can be horizontal
Xiang Yu, extend in particular perpendicular to web 14.
In Fig. 4 exemplary embodiment, radial turbine rotor 10 is shown, wherein in the front side 15 of rotor matrix 11
Region is neutralized in the region of rear side 16, the formation opening 17 on non-streaming guiding surface, and 18, therefore outside stream guiding surface, cavity
Structure 13 can be accessible from the outside via the opening.This opening 17,18 has the system with the radial turbine rotor 10 according to the present invention
Make or correspond to the advantages of production is relevant.
According to a preferred embodiment of the invention, it is set to the roughness of restriction being arranged on the inner surface 19 of cavity structure 13
On, wherein average roughness Ra is between 2 microns to 10 microns.
The invention further relates to a kind of method for producing this radial turbine rotor 10.Rotor matrix 11 with rotor base
The feelings that the blade 12 being integrally formed on body 11 is formed in the case where cavity structure 13 is formed with Fig. 4 split sheds 17,18 together
Integrated support structure is produced as via generation manufacture method under condition, wherein generation manufacture method is also appointed as increasing material manufacturing method.
In the retained material occurred in generating manufacture method (so in cavity structure 13 for example during manufacture method is generated
The residual particles of the powder bed of middle collection) it can be discharged via opening 17,18 from cavity structure 13.Opening 17,18 also is used as examining
Opening is looked into, to check material character or accordingly to carry out quality control.Opening 17,18 can be again switched off after inspection.
In addition, opening 17,18 is suitable to the inner surface 19 that the average roughness Ra of restriction is then arranged on to cavity structure 13
On.Therefore, roughness can be set by means of mechanical means, so for example be ground via sliding, wherein, abrasive body and then via opening
Mouth 17,18 introduces and drawn cavity structure 13.In addition, roughness can be set by means of physico-chemical process, wherein in order to set
Mean roughness on the inner surface 19 of cavity structure 13, liquid medium is introduced into cavity structure 13 and therefrom via opening 17
Draw.
The present invention correspondingly proposes a kind of radial turbine rotor 10, and its rotor matrix 11 has cavity structure 13.Here,
Cavity structure 13 can be strengthened by means of at least one web 14.Hole 17,18 on the non-streaming guiding surface of radial turbine rotor 10
(cavity structure 13 can be accessible from the outside via its) is used to remove retained material and for the inner surface in cavity structure 13
The roughness limited is set.
Claims (9)
1. a kind of radial turbine rotor (10), carries
Rotor matrix (11);
The blade (12) being integrally formed on the rotor matrix (11);
Characterized in that,
The rotor matrix (11) has cavity structure (13).
2. radial turbine rotor according to claim 1, it is characterised in that the cavity structure (13) has one or more
Individual cavity.
3. the radial turbine rotor according to claim 1 or claim 2, it is characterised in that the cavity structure (13)
Strengthened by least one web (14).
4. the radial turbine rotor according to any one of claim 1 to claim 3, it is characterised in that opening (17,
16) it is formed at outside stream guiding surface on the front side (15) and/or rear side (16) of the rotor matrix (11), the cavity structure
(13) can be accessible from the outside via the opening.
5. the radial turbine rotor according to any one of claim 1 to claim 4, it is characterised in that restriction is put down
Equal roughness Ra is arranged on the inner surface (19) of the cavity structure (13), and the roughness is between 2 microns to 10 microns.
A kind of 6. side for being used to produce the radial turbine rotor (10) according to any one of claim 1 to claim 5
Method, it is characterised in that the radial turbine rotor is produced as integrated support structure by means of generating manufacture method.
7. according to the method for claim 6, it is characterised in that the retained material occurred during the generation manufacture method
Discharged via the opening (17,18) from the cavity structure (13).
8. according to the method described in claim 6 or claim 7, it is characterised in that the average roughness Ra of the restriction is borrowed
The opening (17,18) helped on the inner surface (19) of the cavity structure (13) is set.
9. according to the method for claim 8, it is characterised in that the roughness is by means of mechanical means and/or physico
Method is set.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102016213238.5 | 2016-07-20 | ||
| DE102016213238.5A DE102016213238A1 (en) | 2016-07-20 | 2016-07-20 | Radial turbine rotor and method of making same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107642382A true CN107642382A (en) | 2018-01-30 |
Family
ID=60890285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710594823.5A Pending CN107642382A (en) | 2016-07-20 | 2017-07-20 | Radial turbine rotor and the method for producing it |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JP6843711B2 (en) |
| KR (1) | KR20180010151A (en) |
| CN (1) | CN107642382A (en) |
| CH (1) | CH712770B1 (en) |
| DE (1) | DE102016213238A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP7261668B2 (en) * | 2019-06-18 | 2023-04-20 | 株式会社小松製作所 | turbine wheel |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5620705A (en) * | 1979-07-30 | 1981-02-26 | Nissan Motor Co Ltd | Radial turbine rotor |
| JPS61215401A (en) * | 1985-03-20 | 1986-09-25 | Yanmar Diesel Engine Co Ltd | Turbine wheel for supercharger |
| CN101631940A (en) * | 2006-10-12 | 2010-01-20 | 曼柴油机欧洲股份公司 | Compressor for turbocharger and cooling method thereof |
| CN103567384A (en) * | 2012-08-02 | 2014-02-12 | 三星泰科威株式会社 | Method of manufacturing rotor |
| CN103670531A (en) * | 2012-09-07 | 2014-03-26 | 罗伯特·博世有限公司 | Impeller for a turbomachine and method for producing a turbine for a turbomachine |
| JP2016037901A (en) * | 2014-08-07 | 2016-03-22 | 日立金属株式会社 | Impeller |
| CN109661510A (en) * | 2016-07-20 | 2019-04-19 | 曼恩能源方案有限公司 | Turbine and method for producing it |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001349296A (en) * | 2000-06-06 | 2001-12-21 | Shimadzu Corp | Turbo wheel |
| DE102013226664A1 (en) * | 2013-12-19 | 2015-06-25 | Continental Automotive Gmbh | Turbine rotor and method of manufacturing the turbine rotor |
-
2016
- 2016-07-20 DE DE102016213238.5A patent/DE102016213238A1/en not_active Ceased
-
2017
- 2017-07-05 CH CH00871/17A patent/CH712770B1/en unknown
- 2017-07-18 KR KR1020170090958A patent/KR20180010151A/en not_active Application Discontinuation
- 2017-07-19 JP JP2017139762A patent/JP6843711B2/en active Active
- 2017-07-20 CN CN201710594823.5A patent/CN107642382A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5620705A (en) * | 1979-07-30 | 1981-02-26 | Nissan Motor Co Ltd | Radial turbine rotor |
| JPS61215401A (en) * | 1985-03-20 | 1986-09-25 | Yanmar Diesel Engine Co Ltd | Turbine wheel for supercharger |
| CN101631940A (en) * | 2006-10-12 | 2010-01-20 | 曼柴油机欧洲股份公司 | Compressor for turbocharger and cooling method thereof |
| CN103567384A (en) * | 2012-08-02 | 2014-02-12 | 三星泰科威株式会社 | Method of manufacturing rotor |
| CN103670531A (en) * | 2012-09-07 | 2014-03-26 | 罗伯特·博世有限公司 | Impeller for a turbomachine and method for producing a turbine for a turbomachine |
| JP2016037901A (en) * | 2014-08-07 | 2016-03-22 | 日立金属株式会社 | Impeller |
| CN109661510A (en) * | 2016-07-20 | 2019-04-19 | 曼恩能源方案有限公司 | Turbine and method for producing it |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20180010151A (en) | 2018-01-30 |
| DE102016213238A1 (en) | 2018-01-25 |
| JP6843711B2 (en) | 2021-03-17 |
| JP2018013127A (en) | 2018-01-25 |
| CH712770A2 (en) | 2018-01-31 |
| CH712770B1 (en) | 2021-12-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: Augsburg Applicant after: Mann Energy Solutions Ltd. Address before: Augsburg Applicant before: Man Diesel & Turbo SE |
|
| CB02 | Change of applicant information | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180130 |
|
| WD01 | Invention patent application deemed withdrawn after publication |