CN109386312A - The turbine of the axial turbine of turbocharger flows into shell - Google Patents
The turbine of the axial turbine of turbocharger flows into shell Download PDFInfo
- Publication number
- CN109386312A CN109386312A CN201810877062.9A CN201810877062A CN109386312A CN 109386312 A CN109386312 A CN 109386312A CN 201810877062 A CN201810877062 A CN 201810877062A CN 109386312 A CN109386312 A CN 109386312A
- Authority
- CN
- China
- Prior art keywords
- turbine
- shell
- flows
- wall
- flank
- 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
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D9/00—Stators
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
- F01D25/265—Vertically split casings; Clamping arrangements therefor
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The present invention relates to the turbines of the axial turbine of turbocharger to flow into shell (10), it is with inflow entrance side end (11), the outer wall (13) that turbine flows into shell limits section as circular flow channel (15) at inflow entrance side end (11), with outflux side end (12), turbine flows into the outer wall (13) of shell and its inner wall (14) limits section as the flow channel (16) of annular at outflux side end, and there are flank (17), turbine flows into the outer wall (13) of shell and its inner wall (14) is connected to each other via flank (17).The jointing (22) of flank (17) is located in the region of inflow entrance side flange (11), and flank is connected to the outer wall (13) that turbine flows into shell using jointing (22).
Description
Technical field
The present invention relates to the turbines of the axial turbine of turbocharger to flow into shell.
Turbocharger includes the turbine for expanding first medium and the compressor for compressing second medium.Turbine
The turbine of booster includes turbine shroud and turbine rotor.The compressor of turbocharger includes that compressor housing and compressor turn
Son.Turbine rotor and compressor drum are connected with each other via axis, which is rotatably installed in the bear box of turbocharger
In.The bear box of turbocharger both is connected to turbine shroud and is also connected to compressor housing.Turbocharger
Turbine is implementable for axial turbine or radial turbine.Equally, it is axial compressor or diameter that the compressor of turbocharger is implementable
To compressor.The present invention relates to the turbines of the turbine shroud of the turbine for being designed as axial turbine of turbocharger to flow into shell.
Background technique
From the basic structure of the axial turbine of DE202014002981U1 known turbochargers.Therefore, the prior art
The turbine of turbine rotor and turbine shroud that turbine is shown in the form of extracts flows into shell.Here, turbine flows into shell
Outflux side end is shown in DE202014002981U1, turbine flow into shell (i.e. turbine flow into shell inner radial wall and
Radial outer wall) define that section is the flow channel of annular on it.It, can be by Jie to be expanded by means of the annular flow passage
Matter is supplied to the turbine rotor of axial turbine.
According to DE202014002981U1, nozzle ring is located in turbine rotor and turbine flows into the outflux side end of shell
Between.Nozzle ring is also described as guide device or guidance grid.
Summary of the invention
It is known that turbine flows into the inner radial wall of shell and its radial outer wall is connected to each other via flank, flank from practice
Extend through the annular flow passage that turbine flows on the outflux side end of shell.It is enclosed to be supplied to the medium flow field of turbine rotor
It is recycled around these flanks.
Known turbine flows into shell and is easy to rupture due to thermal cycle from practice.Therefore, turbine flows into the longevity of shell
Life is restricted.Other than forming crack, there are such problems in known turbine inflow shell in practice: being equally
Shell can be flowed into turbine due to thermal cycle and be mounted on the component (especially guide device or nozzle ring) flowed on shell
Between form relative motion, as a result, the gap realized during the operation that turbine flows between shell and guide device changes
Become.The turbine for needing to be not easy to due to thermal cycle and forming crack flows into shell.Furthermore, it is necessary to farthest reduce due to heat
The formation of the relative motion between the component that turbine flows into shell and is mounted on turbine inflow shell of circulation.Thus it opens
Begin, the present invention is based on the purposes for forming novel turbine inflow shell.
According to the first aspect of the invention, which flows into shell by turbine according to claim 1 and solves.According to
On the one hand, the jointing (flank is connected to the outer wall that turbine flows into shell using jointing) of flank is located in inflow entrance side
In the region of flange.
According to the second aspect of the invention, which flows into shell by turbine according to claim 5 and solves.According to
Two aspects, the cross section profile of flank are designed as drop shape.
According to the third aspect of the invention we, which flows into shell by turbine according to claim 7 and solves.According to
Three aspects, the flowing conduction of the flank extended between the inflow side and outflow side of corresponding flank and between outer wall and inner wall
Surface design profile in this way so that its initially diverging is simultaneously since inflow side is along the direction of the rollback point of flank profile
Then along the directionally focused of outflow side since rollback point, wherein the distance d of the flowing conduction surfaces in the region of rollback point
Ratio d/l between inflow side and outflow side distance l is greater than 0.4 and less than 1.0.
Aforementioned aspect of the present invention can be used alone or preferably it is in combination with one another.It therefore, can be above-mentioned by two or three
Aspect, which is combined with each other, to be utilized.Using all three aspects, turbine can be reduced and flow on shell the risk for forming crack.In addition, whirlpool
The risk for the relative motion that wheel flows into shell and is mounted between the component that turbine flows on shell can farthest reduce.Root
Multiple thermic load circulations can be born by flowing into shell according to turbine of the invention.
Detailed description of the invention
From dependent claims and it is described below and middle obtains preferred further development of the invention.It is more detailed by means of attached drawing
Exemplary embodiment of the present invention carefully is explained, without limited to this.It shows:
Fig. 1 is the axial cross section that shell is flowed by the turbine of the axial turbine of turbocharger according to the present invention.
Parts List
10 turbines flow into shell
11 inflow entrance side flanges
12 outflux side flanges
13 outer walls
14 inner walls
15 round entrance flow channels
16 ring exit flow channels
17 flanks
18 flowing conduction surfaces
19 flowing conduction surfaces
20 outflow sides
21 inflow sides
22 jointings
23 radial directions
24 longitudinal center axiss
25 rollback points
26 jointings
Specific embodiment
The turbine that Fig. 1 shows the axial turbine of turbocharger flows into shell 10.This turbine flows into shell 10
Inflow entrance side end with inflow entrance side flange 11 and the outflux side end with outflux side flange 12.
On inflow entrance side end, there is the medium expanded in the region for staying in axial turbine to enter turbine and flow into shell 10.
At outflux side end, which in axial direction leaves turbine and flows into shell 10, to be then in axial direction supplied to
The turbine rotor of axial turbine.Therefore, axis of export direction of the medium in the region of outflux side end 12 in axial turbine
It is upwardly extended to side.For this reason, axis is also described as by the section that turbine shown in Fig. 1 flows into shell 10 in Fig. 1
To section.
It includes outer wall 13 and inner wall 14 that turbine, which flows into shell 10,.At the inflow entrance side end that turbine flows into shell 10, outside
It is circular Inlet flow channel 15 that wall 13, which limits turbine and flows into the section of shell 10,.At outflux side end, outer wall 13 with
The section that inner wall 14 limits turbine inflow shell 10 together is ring-shaped flow pass 16.
In the region of inflow entrance side end, section is that circular flow channel 15 is limited by outer wall 13, and is being flowed out
In the region of mouth side end, annular flow passage 16 is limited by outer wall 13 and inner wall 14.Inner wall 14 is also been described as bell.
Flank 15 extends between outer wall 13 and inner wall 14, and wherein inner wall 14 is connected to outer wall 13 via flank 17.Here,
Flank 17 extends in the flow channel between ring exit side flow passages 16 and round entrance side flow passages 15.Flow through whirlpool
The medium flow field that wheel flows into shell 10 is recycled around flank 17.Medium flow field has inflow side 21, outflow around the flank 17 of its circulation
Side 20 and the flowing conduction surfaces 18,19 extended between outflow side 20 and inflow side 21.
According to the first aspect of the invention, the jointing 22 of flank 17 is provided, flank 17 is connected to turbine using it
The outer wall 13 of shell 10 is flowed into, jointing is located in the region of inflow entrance side flange 11 and extends to inflow entrance side flange 11
Region in.Therefore, the jointing 22 of flank to outer wall 13 is moved in the region of inflow entrance side end, and is therefore moved to
Turbine flows into the region of the inflow entrance side flange 11 of shell 10.
The specific jointing 26(flank 17 of flank 17 is connected to inner wall 14 via it) it is positioned to flow into shell compared with turbine
The inflow entrance side end of body flows into the outflux side of shell 10 closer to turbine.
It is observed from the axial cross section of Fig. 1, flank 17 is axially tilted relative to radial direction 23, that is, in this way
So that the longitudinal center axis 24 of corresponding flank 17 includes the angle [alpha] with radial direction 23, the angle is excellent between 45 ° and 85 °
It is selected between 60 ° and 80 °, particularly preferably between 60 ° and 70 °.Therefore, the flank 17 radially observed has relatively low
Height and therefore having relatively low radially extend.
Using these features, turbine can be increased and flow into the thermal resistance of shell 10 and therefore can increase the longevity that turbine flows into shell 10
Life.The risk that crack is formed in the region of flank 17 reduces.In addition, crack propagation behavior farthest reduces.Turbine flow
The risk for the relative motion for entering shell and being mounted between the component that turbine flows on shell equally reduces.
According to the second aspect of the invention, it is preferably used in combination with the first aspect of the present invention, the section of flank 17
Profile is designed as drop shape (referring to the details II of Fig. 1, showing section II-II).Here, flank 17 is preferably in this way
Profile is designed as drop shape, that is, so that the flowing conduction surfaces 18,19 of flank 17 are initially designed as the surface of drop shape in profile
It is dissipated since inflow side 21 on the direction of 18,19 rollback point 25, and after this, from these on the direction of outflow side 20
Rollback point 25 starts to assemble, wherein from outflow side 20 to the distance of rollback point 25 be greater than from inflow side 21 to rollback point 25 away from
From.Rollback point 25 is the specified point for flowing conduction surfaces 18,19, wherein the diverging route of flowing conduction surfaces 18,19 is merged into
In the convergence route for flowing conduction surfaces 18,19.Therefore, particularly advantageous flowing conduction is provided in the region of flank 17, it is special
Not, stream gently combines in the downstream of flank 17.Hatching effect farthest reduces.
It according to the third aspect of the invention we, can be sharp in conjunction with first aspect or second aspect or first and second aspect
With, provide the flowing conduction surfaces 18,19 in the region of rollback point 25 distance and inflow side 21 and outflow side 20 away from
It is greater than 0.4 and less than 1.0, preferably greater than 0.5 from the ratio d/l between l and less than 0.9, especially preferred more than 0.6 and is less than
0.8。
Especially when flank 17 is characterized in that such ratio d/l, thicken significantly, as a result increase thermal resistance and because
This increases the service life that turbine flows into shell 10.The risk that crack is formed in the region of flank 17 reduces.In addition, crack propagation
Behavior farthest reduces.Turbine flows into shell and is mounted on the wind for the relative motion that turbine flows between the component on shell
Danger is same to reduce.
Therefore, using the present invention, the novel turbine for proposing the axial turbine for turbocharger flows into shell 10.Root
According to all aspects of the invention for reducing due to thermic load circulation caused by cracking initiation risk.Furthermore, it is possible to provide maximum
The reduced crack propagation behavior in degree ground.Turbine, which flows into shell 10, can bear multiple duty cycles.Turbine flows into shell and installation
The risk that is not present relative motion is flowed between the component on shell in turbine.Furthermore, it is possible to provide uniform flowing is conducted and do not had
There is the risk of the vibrational excitation of downstream guidance grid.
Claims (11)
1. the turbine of the axial turbine of turbocharger flows into shell (10), there is inflow entrance side at inflow entrance side end (11)
Flange (11), the outer wall (13) that the turbine flows into shell limited at the inflow entrance side end (11) section as it is circular enter
Mouth flow channel (15),
There are outflux side flange (11) at outflux side end (12), the turbine flows into the outer wall (13) of shell and described
The inner wall (14) that turbine flows into shell limits section as annular outlet flow paths (16) at the outflux side end,
With flank (17), via the flank (17), the turbine flows into the outer wall (13) of shell and the turbine flows into shell
The inner wall (14) of body is connected to each other, which is characterized in that jointing (22) at least some sections of the flank (17) are located in
In the region of the inflow entrance side flange (11), the flank (17) is connected to the turbine flow using the jointing (22)
Enter the outer wall (13) of shell.
2. turbine according to claim 1 flows into shell, which is characterized in that the jointing (22) of the flank (17) prolongs
The inflow entrance side flange (11) is stretched, the flank is connected to the turbine using the jointing and flows into the outer of shell
Wall (13).
3. turbine according to claim 1 or 2 flows into shell, which is characterized in that the rib seen in axial cross section
Portion (17) is axially tilted relative to radial direction (23).
4. turbine according to claim 3 flows into shell, which is characterized in that seen in axial cross section, the corresponding flank
(17) longitudinal center axis (24) includes the angle (α) with radial direction (32), and the angle is between 45 ° and 85 °, preferably
Between 60 ° and 80 °, particularly preferably between 60 ° and 70 °.
5. turbine according to any one of claim 1 to 4 flows into shell, which is characterized in that the turbine flows into shell
Further developed according to any one of claim 6 to 10.
6. the turbine of the axial turbine of turbocharger flows into shell (10), there is inflow entrance side flange at inflow entrance side (11)
(11), the outer wall (13) that the turbine flows into shell limits section as circular Inlet flow channel at the inflow entrance side
(15), there are outflux side flange (11) at outflux side end (12), the turbine flows into outer wall (13) and the institute of shell
It states turbine and flows into the inner wall (14) of shell and limits section at the outflux side end as annular outlet flow paths (16),
With flank (17), the turbine flows into the outer wall (13) of shell and the turbine flows into the inner wall (14) of shell via the rib
Portion (17) is connected to each other, which is characterized in that the cross section profile of the flank (17) is designed as drop shape.
7. turbine according to claim 6 flows into shell, which is characterized in that the flank (17), in the corresponding rib
Extend between the inflow side (21) and outflow side (20) in portion (17) and between the outer wall (13) and the inner wall (14)
Flow the drop profile that conduction surfaces (18,19) limit the flank (17).
8. turbine according to claim 7 flows into shell, which is characterized in that the flowing conduction surfaces of the flank (17)
(18,19) are initially dissipated since the inflow side (21) are along the direction of the rollback point (25) of the drop profile, and herein it
Afterwards, it is assembled since the rollback point (25) is along the direction of the outflow side (20), wherein from the outflow side (20) described in
The distance of rollback point (25) is greater than the distance from the inflow side (21) to the rollback point.
9. the turbine of the axial turbine of turbocharger flows into shell (10), there is inflow entrance side at inflow entrance side end (11)
Flange (11), the outer wall (13) that the turbine flows into shell limit section as circular entrance stream at the inflow entrance side end
Dynamic channel (15),
With outflux side flange (11) and outflux side end (12), the outer wall (13) of the turbine inflow shell and the whirlpool
The inner wall (14) that wheel flows into shell limits section as the outlet flow paths (16) of annular at the outflux side end, has
Flank (17), the inner wall (14) that the turbine flows into the outer wall (13) of shell and the turbine flows into shell connect each other via flank
Connect, which is characterized in that the flank (17), between the inflow side (21) and outflow side (20) of the corresponding flank (17) with
And the flowing conduction surfaces (18,19) extended between the outer wall (13) and the inner wall (14), initially from the inflow side
(21) direction along the rollback point (25) of flank profile starts to dissipate, and after this, from the rollback point (25) along the stream
The direction of side starts to assemble out, wherein the flowing conduction surfaces (18,19) in the region of the rollback point (25) away from
Ratio d/l between d and inflow side (21) and outflow side (20) distance l is greater than 0.4 and less than 1.0.
10. turbine according to claim 9 flows into shell, which is characterized in that the ratio d/l is greater than 0.5 and is less than
0.9。
11. turbine according to claim 9 flows into shell, which is characterized in that the ratio d/l is greater than 0.6 and is less than
0.8。
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102017117783.3A DE102017117783A1 (en) | 2017-08-04 | 2017-08-04 | Turbine inlet housing of an axial turbine of a turbocharger |
| DE102017117783.3 | 2017-08-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109386312A true CN109386312A (en) | 2019-02-26 |
Family
ID=65019821
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810877062.9A Pending CN109386312A (en) | 2017-08-04 | 2018-08-03 | The turbine of the axial turbine of turbocharger flows into shell |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JP2019031972A (en) |
| KR (1) | KR20190015107A (en) |
| CN (1) | CN109386312A (en) |
| CH (2) | CH714062B1 (en) |
| DE (1) | DE102017117783A1 (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0575659A1 (en) * | 1992-06-26 | 1993-12-29 | Asea Brown Boveri Ag | Inlet casing for a steam turbine |
| CN102022180A (en) * | 2009-09-11 | 2011-04-20 | 曼柴油机和涡轮机欧洲股份公司 | Exhaust gas turbocharger arrangement, attached driving system and design method of driving system |
| CN103206272A (en) * | 2012-01-12 | 2013-07-17 | 通用电气公司 | Gas turbine exhaust diffuser having plasma actuator |
| CN113389600A (en) * | 2020-03-13 | 2021-09-14 | 通用电气公司 | Nozzle assembly with alternating guide vanes for a turbine engine |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6341592Y2 (en) * | 1984-10-16 | 1988-11-01 | ||
| JP2000320361A (en) * | 1999-05-10 | 2000-11-21 | Niigata Eng Co Ltd | Internal combustion engine with supercharger |
| JP2000328906A (en) * | 1999-05-19 | 2000-11-28 | Ishikawajima Harima Heavy Ind Co Ltd | Axial-flow turbine |
| CN201090252Y (en) * | 2007-07-06 | 2008-07-23 | 大连经济技术开发区泽通机械有限公司 | Improvement of turbine inlet casing dowel plate of axial-flow turbine supercharger |
| CN201428510Y (en) * | 2009-07-07 | 2010-03-24 | 大连恒通机车配件有限公司 | Turbocharger for diesel engine |
| US8672620B2 (en) * | 2010-08-17 | 2014-03-18 | Hamilton Sundstrand Corporation | Air turbine starter turbine nozzle airfoil |
| JP5687641B2 (en) * | 2012-02-20 | 2015-03-18 | 株式会社東芝 | Axial exhaust turbine |
| US20140137533A1 (en) * | 2012-11-19 | 2014-05-22 | General Electric Company | Exhaust gas diffuser for a gas turbine |
| JP6129580B2 (en) * | 2013-02-22 | 2017-05-17 | 三菱重工業株式会社 | gas turbine |
| JP5922685B2 (en) * | 2014-01-31 | 2016-05-24 | 三菱重工業株式会社 | Exhaust turbine device, supercharger and exhaust energy recovery device |
| DE202014002981U1 (en) | 2014-04-08 | 2014-04-16 | Man Diesel & Turbo Se | Axial turbine for an exhaust gas turbocharger |
-
2017
- 2017-08-04 DE DE102017117783.3A patent/DE102017117783A1/en active Pending
-
2018
- 2018-07-03 CH CH00831/18A patent/CH714062B1/en unknown
- 2018-07-03 CH CH70265/21A patent/CH717806B1/en unknown
- 2018-07-24 KR KR1020180085866A patent/KR20190015107A/en not_active Application Discontinuation
- 2018-07-30 JP JP2018142234A patent/JP2019031972A/en active Pending
- 2018-08-03 CN CN201810877062.9A patent/CN109386312A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0575659A1 (en) * | 1992-06-26 | 1993-12-29 | Asea Brown Boveri Ag | Inlet casing for a steam turbine |
| CN102022180A (en) * | 2009-09-11 | 2011-04-20 | 曼柴油机和涡轮机欧洲股份公司 | Exhaust gas turbocharger arrangement, attached driving system and design method of driving system |
| CN103206272A (en) * | 2012-01-12 | 2013-07-17 | 通用电气公司 | Gas turbine exhaust diffuser having plasma actuator |
| CN113389600A (en) * | 2020-03-13 | 2021-09-14 | 通用电气公司 | Nozzle assembly with alternating guide vanes for a turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CH714062B1 (en) | 2022-02-28 |
| KR20190015107A (en) | 2019-02-13 |
| JP2019031972A (en) | 2019-02-28 |
| CH717806B1 (en) | 2022-04-14 |
| DE102017117783A1 (en) | 2019-02-07 |
| CH714062A2 (en) | 2019-02-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| CB02 | Change of applicant information |
Address after: Augsburg Applicant after: MAN ENERGY SOLUTIONS SE Address before: Augsburg Applicant before: Man Diesel & Turbo SE |
|
| CB02 | Change of applicant information | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190226 |
|
| WD01 | Invention patent application deemed withdrawn after publication |