CN107461224A - Axial-flow turbine - Google Patents
Axial-flow turbine Download PDFInfo
- Publication number
- CN107461224A CN107461224A CN201710418306.2A CN201710418306A CN107461224A CN 107461224 A CN107461224 A CN 107461224A CN 201710418306 A CN201710418306 A CN 201710418306A CN 107461224 A CN107461224 A CN 107461224A
- Authority
- CN
- China
- Prior art keywords
- ring
- turbine
- axial
- bezel ring
- bezel
- 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
- 230000008859 change Effects 0.000 description 5
- 230000002349 favourable effect Effects 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
Classifications
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
- F01D1/20—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially axially
-
- 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
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
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- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/31—Retaining bolts or nuts
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/37—Retaining components in desired mutual position by a press fit connection
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The present invention relates to axial-flow turbine.Specifically, for a kind of axial-flow turbine (10) with the turbine wheel (11) in rotor-side, it includes movable vane piece (12)；With the turbine case (13) in stator side；With bezel ring, (20), it is not exclusively fastened to turbine case (13), side follows movable vane piece (12) to bezel ring, (20) radially outward, and radial clearance (22) is limited together with movable vane piece (12)；And carry centering ring (23), it is not exclusively connected to bezel ring, (20), so that the traction between centering ring (23) and bezel ring, (20) is more than the traction between bezel ring, (20) and turbine case (13), wherein centering ring (23) at least reaches in the groove (24) of turbine case (13) section, so that in the cold state of axial-flow turbine, centering ring (23) is felt relieved via its inner radial surface in the inner radial surface of groove (24), and in the Warm status of axial-flow turbine, centering ring (23) is felt relieved via its radially-outer surface on the radially-outer surface of groove (24).
Description
Technical field
The present invention relates to axial-flow turbine.In addition, the present invention relates to the exhaust turbine supercharger with this axial-flow turbine.
Background technology
Include the turbine wheel with movable vane piece on the rotor side and in stator side from axial-flow turbine known to practice
Turbine case.In addition, bezel ring, is not exclusively fastened to radially by turbine case, wherein bezel ring, by fastening bolt from practice is known
Movable vane piece is followed in outside, and radial clearance is limited together with movable vane piece.
From a kind of axial-flow turbine of exhaust turbine supercharger known to DE 102009045167A1, with turbine case including
The turbine wheel of movable vane piece and the bezel ring, for being fastened to turbine case.
During operation, turbine case and bezel ring, are by non-uniform heat flux, as a result, the radial clearance between movable vane piece and bezel ring,
Change.This radial clearance changed between bezel ring, and movable vane piece can cause the movable vane piece friction bezel ring, of turbine wheel.This is not
Profit.
Therefore a kind of axial-flow turbine is needed, in the case of the axial-flow turbine, the radial direction between movable vane piece and bezel ring,
Gap is during operation by less change.
The content of the invention
Since this, exhaust driven gas turbine of the present invention based on the axial-flow turbine for producing new type and with this axial-flow turbine
The purpose of booster.
This purpose solves by axial-flow turbine according to claim 1.Include using according to the axial-flow turbine of the present invention
In the centering ring of bezel ring, wherein centering ring is not exclusively connected to bezel ring, so that the traction between centering ring and bezel ring, is more than lid
Traction between ring and turbine case.In the groove for reaching turbine case, i.e. so that in axial-flow turbine centering ring at least section
Cold state in, centering ring is felt relieved via its inner radial surface in the inner radial surface of the groove of turbine case, and in axial-flow type
In the Warm status of turbine, centering ring is felt relieved via its radially-outer surface on the radially-outer surface of the groove of turbine case.
Centering ring, wherein centering ring and bezel ring, and bezel ring, and turbine case difference are included according to the axial-flow turbine of the present invention
Not exclusively it is fastened to each other.Pass through the ratio between the traction between the traction between centering ring and bezel ring, and bezel ring, and turbine case
Rate, allow thermally-induced slip of the bezel ring, on turbine case in the heating of axial-flow turbine and cooling period during operation, so
And there is no corresponding relative motion between bezel ring, and centering ring.The groove (reaching wherein) of turbine case centering ring at least section
Inner radial surface and radially-outer surface define thermally-induced relative motion between bezel ring, and turbine case, and therefore limit movable vane
The change of radial clearance between piece and bezel ring,.Therefore the danger of the movable vane piece friction bezel ring, of turbine rotor can reduce.
According to favourable further development, bezel ring, and centering ring are not exclusively fastened to each other via the first fastening bolt,
And bezel ring, and turbine case are not exclusively fastened to each other via the second fastening bolt.Traction and bezel ring, between centering ring and bezel ring,
The ratio between traction between turbine case preferably by the first fastening bolt and the second fastening bolt screw-down torque and/or
Size and/or number determine.The ratio between the traction between traction and bezel ring, and turbine ring between centering ring and bezel ring, because
This can be particularly easy to and advantageously adjust, to allow the thermally-induced relative motion between bezel ring, and turbine case but to avoid bezel ring,
Corresponding relative motion between centering ring.
According to favourable further development, the traction between traction and bezel ring, and turbine case between centering ring and bezel ring, it
Between ratio determined in addition by the roughness of the friction surface between centering ring and bezel ring, and between bezel ring, and turbine case.Turbine
Therefore the ratio between the traction between traction and bezel ring, and turbine case between ring and bezel ring, easily and can be adjusted advantageously.
According to favourable further development, based on movable vane piece, turbine case is including on the shell sections on inflow side, inflow side
Shell sections on nozzle ring and outflow side, wherein bezel ring, are fastened in the shell sections on outflow side via the second fastening bolt,
And bezel ring, is clipped on turbine case by nozzle ring in addition.Especially when nozzle ring by bezel ring, be clipped on turbine case and so as to provide bezel ring, and
During a part for the traction between turbine case, the number of the second fastening bolt between bezel ring, and turbine case can reduce.
As modification, traction can also be completely taken over by nozzle ring.In this modification, it is relative that fastening bolt is done so as to its
Screw or be screwed on the collar in bottom, and gap is produced between bolt head and the supporting part of bezel ring,.Fastening bolt is therefore
" freedom ".As being for example not required on the further step described in expansion sleeve.Then fastening bolt is only used for assembling
Protection so that the bezel ring, with centering ring does not fall down during assembling/dismounting and is used as anti-rotation device.
Exhaust turbine supercharger limits in claim 12.
Brief description of the drawings
The preferably further development of the present invention obtains from dependent claims and following description.The exemplary implementation of the present invention
Example is illustrated in further detail by accompanying drawing, and not limited to this.Accompanying drawing is shown：
Fig. 1 is the first axial section through the axial-flow turbine according to the present invention；
Fig. 2 is the second axial section through the axial-flow turbine according to the present invention；
Fig. 3 is the 3rd axial section through the axial-flow turbine according to the present invention；
Fig. 4 is the details on end on observation direction according to the axial-flow turbine of the present invention；
Fig. 5 is Fig. 4 section V-V；And
Fig. 6 is Fig. 4 section VI-VI.
Reference numeral list
10 axial-flow turbines
11 turbine rotors
12 movable vane pieces
13 turbine cases
14 shell sections
15 nozzle rings
16 shell sections
17 clamp rings
18 fastening bolts
19 anti-rotation devices
20 bezel ring,s
21 fastening bolts
22 radial clearances
23 centering rings
24 fastening bolts
25 grooves
26 surfaces
27 surfaces
28 surfaces
29 surfaces
30 access openings
31 threaded holes
32 access openings
33 access openings
34 threaded holes
35 expansion sleeves
36 axial gaps.
Embodiment
The present invention relates to axial-flow turbine, the particularly axial-flow turbine for exhaust turbine supercharger.Fig. 1 to Fig. 3 shows
Three different axial sections through axial-flow turbine 10 are gone out, it is biased in circumferential direction relative to each other, wherein showing
Having gone out axial-flow turbine 10 has the turbine rotor 11 with movable vane piece 12.In addition, Fig. 1 to Fig. 3 shows turbine case 13, wherein
In Fig. 1 into Fig. 3, multiple sections of turbine case 13 are shown, i.e. on shell sections 14 of the movable vane piece 12 on inflow side, same
Nozzle ring 15 of the sample on inflow side and the shell sections on outflow side 16.In the exemplary embodiment that Fig. 1 is shown into Fig. 3
In, the nozzle ring 15 on inflow side is arranged in the shell sections 14 on inflow side via clamp ring 17 and fastening bolt 18, wherein anti-
Rotating device 19 prevents rotating against between the shell sections 14 on nozzle ring 15 and inflow side on inflow side.
In addition, Fig. 1 shows the bezel ring, 20 in stator side.Bezel ring, 20 is in the shell sections 16 on the outflow side of turbine case 13
Turbine case 13 (that is, in Fig. 1 into Fig. 3) is fastened to (that is, via visible fastening bolt 21 in Fig. 3).These fastening bolts 21
For bezel ring, 20 to be not exclusively fastened on to the shell sections 16 of turbine case 13.
Bezel ring, 12 is positioned to the movable vane piece 12 of the adjoining of side radially outward turbine rotor 11, and with the movable vane of turbine rotor 11
Piece 12 defines radial clearance 22 together.
Centering ring 23 for bezel ring, 20 is included according to the axial-flow turbine 10 of the present invention, it is not exclusively arranged on bezel ring,
On 20, i.e. via visible fastening bolt 24 in Fig. 2.Here, the traction between centering ring 23 and bezel ring, 20 is more than the He of bezel ring, 20
Traction between turbine case 13 so that allow relative motion caused by the temperature between bezel ring, 20 and turbine case 13, but anti-fastening
Corresponding thermally-induced relative motion between thimble 23 and bezel ring, 20.
Reach (that is, its shell sections 16) groove 25 of turbine case 13 with being connected to the section of centering ring 23 of bezel ring, 20
In, i.e. so that in the cold state of axial-flow turbine 10, centering ring 23 is via inner radial surface 26 in the inside table in the footpath of groove 25
Felt relieved on face 27, and in the Warm status of axial-flow turbine, centering ring 23 is outside in the footpath of groove 25 via radially-outer surface 28
Felt relieved on surface 29.The cold state of axial-flow turbine means the state that axial-flow turbine is cooled wherein, and axial-flow type whirlpool
The Warm status of wheel 10 means the state that axial-flow turbine is heated wherein during operation.
Therefore the radial surface 27,29 of the groove 25 of the shell sections 16 of turbine case 13 limits bezel ring, 20 relative to turbine case 13
Relative motion, i.e. pass through the groove of corresponding radial surface 26,28 and the turbine case 13 of the centering ring 23 for being fastened to bezel ring, 20
The interaction of 25 corresponding radial surface 27,29.
As has already been discussed, bezel ring, 20 and centering ring 23 are fastened to each other via fastening bolt 24 (see Fig. 2), wherein
These fastening bolts 24 BE hereinafter described as the first fastening bolt.These first fastening bolts 24 are extended through in bezel ring, 20
Corresponding access opening 30 and it is bonded in the threaded hole 31 of centering ring 23.
Bezel ring, 20 is fastened to the shell sections 16 of turbine case 13, wherein these fastening bolts via fastening bolt 21 (see Fig. 3)
21 BE hereinafter described as the second fastening bolt.These the second fastening bolts 21 extend through the passage of bezel ring, 20 and centering ring 23
Hole 32,33 and it is joined in the threaded hole 34 of turbine case 13.
As has already been discussed, the traction between bezel ring, and centering ring 23 is more than leading between bezel ring, and turbine case 13
Draw.
The ratio between the traction between traction and bezel ring, 20 and turbine case 13 between centering ring 23 and bezel ring, 20 is special
Ground is determined by the screw-down torque and/or size and/or number of fastening bolt 21,24.
In Fig. 4 in shown exemplary embodiment, (it is used for the tight of bezel ring, 20 and centering ring 23 to the first fastening bolt 24
Gu) number be the second fastening bolt 21 (it is used for fastening of the bezel ring, 20 in the shell sections 16 of turbine case 13) number two
Times.Although in Fig. 4, the diameter of fastening bolt 21,24 is equal, it is also possible to make the diameter of the first fastening bolt 24 relative
In the diameter increase of the second fastening bolt 21.
Because the fact that the second fastening bolt 21 is extended in turbine case 13, the length of the second fastening bolt 21 is more than first
The length of fastening bolt 24.
In addition, the screw-down torque of the first fastening bolt 24 is preferably greater than the screw-down torque of the second fastening bolt 21, preferably
At least 1.3 times, particularly preferably at least 1.5 times, most preferably at least 1.8 times.
As has already been discussed, the second fastening bolt 21 is used to bezel ring, 20 being fastened on turbine case 13.Due in axle
Allow the thermally-induced relative motion between bezel ring, 20 and turbine case 13, the second fastening bolt 21 during the operation of steam turbines 10
Bent during operation.In order to which these can safely bear corresponding bending force, the second fastening bolt 21, which has, to be adapted to
Length, wherein in the illustrated exemplary embodiment, its own is supported on bezel ring, by fastening bolt 21 via expansion sleeve 35
On 20.However, these expansion sleeves 35 are optional components.In order to bear the corresponding length of the second fastening bolt 21, turbine
The threaded hole 34 of shell 13 can also be implemented accordingly longer.
The ratio between the traction between traction and bezel ring, 20 and turbine case 13 between centering ring and bezel ring, 20 can also be through
By the coarse of on the one hand between the centering ring 23 and bezel ring, 20 and on the other hand friction surface between bezel ring, 20 and turbine case 13
Degree adjustment.Here, the friction surface between bezel ring, 20 and centering ring 23 is compared to the friction table between bezel ring, 20 and turbine case 13
Face preferably selects larger roughness.
In the exemplary embodiment that Fig. 1 is shown into Fig. 3, axial gap is formed between nozzle ring 13 and bezel ring, 20
36.In the case, the traction between bezel ring, 20 and turbine case 13 only adjusts via the first fastening bolt 21.In contrast to this,
It is still possible that bezel ring, 20 is clipped in turbine case 13 by nozzle ring 15, wherein between bezel ring, 20 and nozzle ring 15 and then it is not present
Axial gap 36.In the case, a part for the traction between bezel ring, 20 and turbine case 13 by nozzle ring 15 by being applied to
Clamping force on bezel ring, 20 is provided so that then the number of the second fastening bolt 21 can be reduced.In the case, bezel ring, 20 and whirlpool
Between hub 13 traction (itself then via nozzle ring 15 clamping force and determined by the bolt power of the second fastening bolt 21)
Less than the traction between bezel ring, 23 and centering ring 23.
Using the present invention, the thermally-induced relative motion between bezel ring, 20 and turbine case 13 is restricted.Bezel ring, 20 is via fixed
Thimble 23 is felt relieved on turbine case 13.Radial clearance 22 between movable vane piece 12 and bezel ring, 20 can be therefore more accurate during operation
Really adjust, even with the different heat expansion of the component of correlation.Compared with prior art, it can reduce or even reduce completely dynamic
The friction bezel ring, 20 of blade 12.
The exhaust turbine supercharger of compressor and axial-flow turbine is preferably comprised according to the axial-flow turbine of the present invention
A part.
Because the tolerance of rotor portion and various shells, orientation and alignment error, uneven between turbo blade and bezel ring,
Gap may occur in which during assembly.
In order to correct this uneven gap, bezel ring, is not felt relieved in a position-stable manner but in a manner of adjustable, and therefore
Installed via frictional connection.
However, the frictional connection only between bezel ring, and shell always causes the one side of bezel ring, mobile and therefore passes through component
Different heating and the friction damage of temperature change and gap change.
In order to avoid such situation, in the past, the also partly amplification and therefore efficiency reduction of bezel ring, gap.
Where this is the present invention, its in order to bias this uneven gap by bezel ring, and centering ring implement into two parts for
The purpose of adjustment.
This adjustability is realized between bezel ring, and centering ring.Bezel ring, has to enough gaps of shell in external diameter.
The advantages of being invented by this be exactly reduce friction damage (movable vane piece and bezel ring) and reduction gap possibility and because
This increase efficiency.
Claims (12)
1. a kind of axial-flow turbine (10), carries
Turbine wheel (11) in rotor-side, it includes movable vane piece (12)；
Turbine case (13) in stator side；
Bezel ring, (20), it is not exclusively fastened to the turbine case (13), the bezel ring, (20) radially outward side follow it is described
Movable vane piece (12), and radial clearance (22) is limited together with the movable vane piece (12)；
Characterized in that,
Centering ring (23), it is not exclusively connected to the bezel ring, (20) so that the centering ring (23) and the bezel ring, (20)
Between traction be more than traction between the bezel ring, (20) and the turbine case (13), wherein the centering ring (23) at least area
In the groove (24) for reaching to section the turbine case (13) so that in the cold state of the axial-flow turbine, the centering
Ring (23) is felt relieved via its inner radial surface in the inner radial surface of the groove (24), and in the heat of the axial-flow turbine
In state, the centering ring (23) is felt relieved via its radially-outer surface on the radially-outer surface of the groove (24).
2. axial-flow turbine according to claim 1, it is characterised in that the turbine case (13) is based on the movable vane piece
(12) shell sections (14), the nozzle ring (15) on inflow side and the shell sections (16) on outflow side on inflow side are included, its
Described in bezel ring, (20) be fastened to shell sections (16) on the outflow side.
3. the axial-flow turbine according to claim 1 or claim 2, it is characterised in that the bezel ring, (20) and described
Centering ring (23) is not exclusively fastened to each other via the first fastening bolt (24).
4. the axial-flow turbine according to any one of claim 1 to claim 3, it is characterised in that the bezel ring,
(20) not exclusively it is fastened to each other via the second fastening bolt (21) with the turbine case (13).
5. according to the axial-flow turbine described in claim 2 and claim 4, it is characterised in that the nozzle ring (15) is in addition
The bezel ring, (20) is clipped on the turbine case.
6. axial-flow turbine according to claim 5, it is characterised in that the bolt power of second fastening bolt (21) and
The clamping force sum of the nozzle ring (15) limits the traction between the bezel ring, (20) and the turbine case (13).
7. the axial-flow turbine according to any one of claim 3 to claim 6, it is characterised in that the centering ring
(23) ratio between the traction between the traction between the bezel ring, (20) and the bezel ring, (20) and the turbine case (13)
Rate is true by the screw-down torque and/or size and/or number of first fastening bolt (24) and second fastening bolt (21)
It is fixed.
8. axial-flow turbine according to claim 7, it is characterised in that the number of first fastening bolt (24) is more than
The number of second fastening bolt (21).
9. according to the axial-flow turbine described in claim 7 or claim 8, it is characterised in that first fastening bolt
(24) screw-down torque is more than the screw-down torque of second fastening bolt (21).
10. the axial-flow turbine according to any one of claim 7 to claim 9, it is characterised in that described first is tight
The diameter of fixing bolt (24) is more than the diameter of second fastening bolt (21).
11. the axial-flow turbine according to any one of claim 1 to claim 10, it is characterised in that the centering
Between the traction between traction and the bezel ring, (20) and the turbine case (13) between ring (23) and the bezel ring, (20)
Ratio is by between the centering ring (23) and the bezel ring, (20) and between the bezel ring, (20) and the turbine case (13)
The roughness of friction surface determines.
A kind of 12. exhaust turbine supercharger, with compressor and according to any one of claim 1 to claim 11
Axial-flow turbine.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102016209911.6A DE102016209911A1 (en) | 2016-06-06 | 2016-06-06 | axial turbine |
| DE102016209911.6 | 2016-06-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107461224A true CN107461224A (en) | 2017-12-12 |
Family
ID=60327794
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710418306.2A Pending CN107461224A (en) | 2016-06-06 | 2017-06-06 | Axial-flow turbine |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JP2017219046A (en) |
| KR (1) | KR20170138037A (en) |
| CN (1) | CN107461224A (en) |
| CH (1) | CH712548B1 (en) |
| DE (1) | DE102016209911A1 (en) |
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|---|---|---|---|---|
| CN101220757A (en) * | 2007-01-09 | 2008-07-16 | 株式会社东芝 | Steam turbine |
| US20120014778A1 (en) * | 2010-07-14 | 2012-01-19 | Hitachi, Ltd. | Sealing Device for Steam Turbines and Method for Controlling Sealing Device |
| CN204402580U (en) * | 2014-12-31 | 2015-06-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine turbine moving-stator blade axial clearance adjust structure |
| US20170306796A1 (en) * | 2016-04-22 | 2017-10-26 | United Technologies Corporation | Stator Arrangement |
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| US3062497A (en) * | 1958-11-24 | 1962-11-06 | Ford Motor Co | Gas turbine engine |
| EP0116160B1 (en) * | 1983-01-18 | 1987-12-23 | BBC Brown Boveri AG | Turbocharger having bearings at the ends of its shaft and an uncooled gas conduit |
| DE60113826T2 (en) * | 2001-07-06 | 2006-04-27 | Electro-Motive Diesel Inc., Lagrange | Turbocharger with vane ring coupling |
| DE102006039064B4 (en) * | 2006-08-19 | 2020-06-25 | Man Energy Solutions Se | Exhaust gas turbocharger for an internal combustion engine |
| DE102009045167A1 (en) | 2009-09-30 | 2011-04-07 | Man Diesel & Turbo Se | Turbine i.e. axial turbine, for use in exhaust-gas turbocharger to turbocharge large diesel engine, has diffuser divided into two segments in circumferential direction, where side of each segment is extended in radial direction |
| DE102010064047A1 (en) * | 2010-12-23 | 2012-06-28 | Man Diesel & Turbo Se | Fluid flow machine has housing with fluid guiding housing and bearing housing that is connected with fluid guiding housing, where impeller is mounted in fluid guiding housing over central impeller shaft in rotating manner |
| JP5889266B2 (en) * | 2013-11-14 | 2016-03-22 | 三菱重工業株式会社 | Turbine |
-
2016
- 2016-06-06 DE DE102016209911.6A patent/DE102016209911A1/en active Pending
-
2017
- 2017-05-08 CH CH00616/17A patent/CH712548B1/en unknown
- 2017-05-16 KR KR1020170060489A patent/KR20170138037A/en active IP Right Grant
- 2017-06-05 JP JP2017110642A patent/JP2017219046A/en not_active Ceased
- 2017-06-06 CN CN201710418306.2A patent/CN107461224A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101220757A (en) * | 2007-01-09 | 2008-07-16 | 株式会社东芝 | Steam turbine |
| US20120014778A1 (en) * | 2010-07-14 | 2012-01-19 | Hitachi, Ltd. | Sealing Device for Steam Turbines and Method for Controlling Sealing Device |
| CN204402580U (en) * | 2014-12-31 | 2015-06-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine turbine moving-stator blade axial clearance adjust structure |
| US20170306796A1 (en) * | 2016-04-22 | 2017-10-26 | United Technologies Corporation | Stator Arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2017219046A (en) | 2017-12-14 |
| DE102016209911A1 (en) | 2017-12-07 |
| CH712548B1 (en) | 2021-02-15 |
| CH712548A2 (en) | 2017-12-15 |
| KR20170138037A (en) | 2017-12-14 |
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Address after: Augsburg Applicant after: Mann Energy Solutions Ltd. Address before: Augsburg Applicant before: Man Diesel & Turbo SE |
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Application publication date: 20171212 |