CN104105844A - Blade ring for axial turbomachine, and method for adjusting maximum flow rate of said blade ring - Google Patents
Blade ring for axial turbomachine, and method for adjusting maximum flow rate of said blade ring Download PDFInfo
- Publication number
- CN104105844A CN104105844A CN201280069005.9A CN201280069005A CN104105844A CN 104105844 A CN104105844 A CN 104105844A CN 201280069005 A CN201280069005 A CN 201280069005A CN 104105844 A CN104105844 A CN 104105844A
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- China
- Prior art keywords
- blade
- ring
- blade ring
- flow rate
- maximum flow
- 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.)
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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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
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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
- 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
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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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
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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
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2220/00—Application
- F05B2220/30—Application in turbines
- F05B2220/301—Application in turbines in steam turbines
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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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a blade ring for an axial turbomachine (1), comprising an outer surface (2) that is arranged on an outer ring (24) and faces radially inwards, and an inner surface (3) that is arranged on an inner ring (23) and faces radially outwards, said surfaces being arranged concentrically and parallel to one another and delimiting an annular flow channel (4) that tapers in the main flow direction (17) of the axial turbomachine (1), as well as at least one adjustment blade (7) that is arranged so as to be displaceable, in said flow channel (4), parallel to a surface line (6) of one of the surfaces (2, 3) by means of a guiding device (14, 15), and that is able to be fixed, in a predetermined position, to at least one of the rings (23, 24).
Description
Technical field
The present invention relates to a kind of blade ring for axial flow turbine, a kind of axial flow turbine with blade ring and a kind of for adjusting the method for the maximum flow rate of blade ring.
Background technique
In order to realize, move economically steam turbine importantly: can be by the process vapor stream decompression of the steam generator maximum possible in for example power station in steam turbine.The maximum process vapor stream that can transport by steam turbine is the conclusive parameter when design turbo machine and the maximum flow rate that is referred to as steam turbine.The rim of the guide blading of steam turbine has a plurality of guide vanes, and described guide vane arranges evenly distributedly on ring week, wherein between guide vane, forms blade path.Diametrically, blade path hub side by the wide gauge of hub wheel and in case side by housing profile gauge.The maximum flow rate of steam turbine is affected by the maximum flow rate of first rim of the guide blading fatefully, and described maximum flow rate substantially whole effectively integral body of cross sections of the blade path by first rim of the guide blading is determined.
The maximum flow rate of the steam turbine of coming of new is because manufacturing tolerances and the location tolerance of the member of steam turbine exist certain inexactness.In addition, maximum flow rate changes because member is aging.Therefore conventionally need to proofread and correct the maximum flow rate of steam turbine, so that steam turbine can move with rated condition again.For this reason, the guide vane existing when work is changed by having at the new guide vane of improved profile aspect the maximum flow rate of steam turbine.Conventionally, change whole guide vanes of relevant blade ring, however this be extremely expend and cost intensive.Alternative, in this, can shorten the trailing edge of guide vane.Therefore yet only can improve the maximum flow rate of the rim of the guide blading, and shorten and conventionally cause aerodynamic characteristic poorer and cause the mechanical strength of guide vane less.
Summary of the invention
The present invention is based on following object: realize a kind of blade ring for axial flow turbine, a kind of axial flow turbine with blade ring and a kind of for adjusting the method for the maximum flow rate of blade ring, wherein overcome the problems referred to above and especially can change in the mode of proofreading and correct the maximum flow rate of axial flow turbine.
For the blade ring according to the present invention of axial flow turbine have be arranged on outer shroud, radially towards inner outside and be arranged on interior ring, inner face towards the outside radially, described outside and described in the face of annular and along the flow channel gauge of the main flow direction convergent of axial flow turbine and arrange concentrically with respect to one another and abreast; And at least one adjusts blade, described adjustment blade in flow channel, by means of guiding device, in the mode that can be parallel to the bus of a face in face and move, arrange and at least one in ring on can be fixed in default position.
Bus be characterised in that its be arranged in these two faces one upper and directed towards the tip of the hypothesis of corresponding face.
The diameter of flow channel declines towards direction inner face and outside convergent.If move at least one by means of guiding device along convergent direction, adjust blade, it declines apart from spacing of the blade of adjacent setting in blade ring at ring Zhou Fangxiang so, correspondingly declines thus for flowing through the obstruction increase of the flow channel of the fluid of flow channel and the maximum flow rate of blade ring.Similarly, by the mode at least one adjustment blade being moved in contrast to convergent direction by means of guiding device, improve maximum flow rate.Therefore, advantageously the in the situation that of operation guide device, can change simply the maximum flow rate of blade ring.For example, during process quality of steam stream that this for example can should be matched with the boundary conditions of change when the maximum flow rate when blade ring changes due to the part aging of axial flow turbine or in maximum flow rate, change, can need.In addition, can carry out the correction of maximum flow rate, to compensate location tolerance or the manufacturing tolerances of the axial flow turbine of coming of new.Can consider, interior ring is configured to dish.
Outside and inner face be conical surface preferably.As an alternative, outside and inner face preferably have identical radius of curvature in each cross section of the axis perpendicular to flow channel on some sections along corresponding bus, make the extension size of adjusting the radial clearance between blade and face when adjustment blade moves keep constant.At this, the round section that each of outside and inner face arranges by polygonal or by a plurality of direct neighbors respectively perpendicular to the cross section of the axis of flow channel forms.
Blade ring is the diagonal angle level of axial flow turbine preferably.Diagonal angle level advantageously has the flow channel by these two conical surface gauges.Preferably, blade ring is the rim of the guide blading with fixing, non-rotary guide vane and fixing, non-rotary inner face and outside.
One preferred embodiment in, blade ring has a plurality of blades, is wherein adjust blade and be placed in regularly outside and/or be placed in the blade on inner face blade alternate.Each blade of settling regularly together with interior ring and described outer shroud single type make, or together with the section of interior ring and the section single type of outer shroud make.Therefore advantageously obtain the high intensity of blade ring.By installing regularly every a blade ring, when manufacturing blade ring, advantageously for fabrication tool, obtain the good accessibility of blade ring.
Preferably, guiding device has chute and have bolt on the radial outside of adjusting blade and/or on the radially inner side of adjusting blade in interior ring and/or in outer shroud, and wherein bolt is incorporated in chute.Guiding device preferably at least one in chute the downstream in the main flow direction of axial flow turbine there is stop member, by described stop member, can be fixed in default position adjusting blade.At this, adjust blade and by fluid mobile in flow channel, compress stop member when axial flow turbine moves, realize thus and adjust the fixing of blade.Adjusting the location of blade in flow channel for example can be by being incorporated into spacer element on stop member and limiting.Spacer element for example can by countersunk head screw and/or outer shroud and/or interior ring on soldering point fix and be placed on interior ring.
Preferably, guiding device is configured to, and makes it possible to at least one adjustment blade of other adjustment blade exchanging.Therefore, can with have different aerodynamic characteristics other adjustment blade exchanging at least one adjust blade.For example, by making other adjustment blade have the mode of the profile that chord length is shorter or longer, the adaptation of maximum flow rate also can more bring execution by suitable.
Axial flow turbine according to the present invention has according to blade ring of the present invention.The maximum flow rate of axial flow turbine preferably limits by the maximum flow rate of blade ring.
For adjusting according to the method for the maximum flow rate of blade ring, there is following step: the expected value of the maximum flow rate of default blade ring; Determine the actual value of the maximum flow rate of blade ring; The actual value of the expected value of the maximum flow rate of blade ring and blade ring maximum flow rate is compared; By means of guiding device, be parallel to bus and move at least one adjustment blade, make the expected value of maximum flow rate identical with the actual value of maximum flow rate; By means of guiding device fixed adjustment blade.When the maximum flow rate by blade ring limits the maximum flow rate of axial flow turbine, can change by mobile at least one adjustment blade the maximum flow rate of axial flow turbine.
Accompanying drawing explanation
Below, according to appended schematic diagram, elaborate the present invention.Accompanying drawing illustrates according to the longitudinal section of the axial flow turbine of blade ring of the present invention with a preferred implementation.
Embodiment
As from accompanying drawing, axial flow turbine 1 has housing 22,, axle 21 and a plurality of blade ring 11 to 13.Fluid 25 can flow with main flow direction 17 within housing 22.In the accompanying drawings, first rim of the guide blading 11, rotor blade ring 12 and second rim of the guide blading 13 are shown, with this order, the main flow direction 17 along fluid 25 arranges for they.
First rim of the guide blading 11 has with being fixed on external conical shape ring 24 on housing 22 and having within tapered collar 24 outside with the inner conical ring 23 of taper inner face 3 towards the outside radially towards inner taper outside 2 radially.Taper outside 2 and taper inner face 3 arrange concentrically with respect to one another, have identical cone angle 18, are arranged in parallel with each other in each axial part section and to annular flow channel 4 gauges.As from accompanying drawing, inner conical ring 23 and external conical shape ring 24 are frusto-conical member.Yet also can consider that inner conical ring 23 comprises its cone tip part simultaneously.
The axis of cone line 26 of taper outside 2 and taper inner face 3 overlaps with axle axis 27.Conical surface 2,3 is oriented, and the outer diameter 28 (shown in the drawings half outer diameter 28) of flow channel 4 is declined along main flow direction 17.
As an alternative, inner conical ring 23 and external conical shape ring 24 are modified as, make taper inner face 3 and taper outside 2 in each cross section perpendicular to axle 21, on some sections, there is identical radius of curvature along corresponding bus 6 and along the width of adjusting blade 7, make, when adjustment blade 7 moves, in the extension size of adjusting the radial clearance between blade 7 and conical surface 2,3, to keep constant.For example can consider: radius of curvature is not infinitely-great, make each cross section perpendicular to axle 21 of conical surface 2,3 form respectively polygonal, wherein on polygonal each straightway section, be respectively arranged with blade.In the downstream of main flow direction 17, the length of polygonal each straightway section becomes shorter.
Can consider equally, perpendicular to each cross section of axle 21, by a plurality of round sections, be formed.The radius of curvature of these circle sections can be greater than and be less than the radius of flow channel 4 at this.In the downstream of main flow direction 17, the extension of each circle section becomes shorter, and on the contrary, it is constant that radius of curvature correspondingly keeps.
Not only can consider straightway or the circle section of the cross section of conical surface 2,3, and can consider other shape, the cross section of described shape does not change along bus 6.Similarly, can be thought of as taper outside 2 and taper inner face 3 different shapes is set, for example, for taper outside 2, polygonal is set, for taper inner face 3, round section is set.
Within flow channel 4, be provided with and adjust blade 7, described adjustment blade is arranged on taper outside 2 and is arranged on taper inner face 3 with its radially inner side 10 with its radial outside 9.Adjust blade 7 and there is respectively bolt 15 on its radially inner side 9 He on its radial outside 10, wherein bolt 15 join to respectively in inner conical ring 23 with external conical shape ring 24 in chute 14 in.Chute 14 arranges in parallel with each other and along the bus 6 of conical surface 2,3, stretches respectively, makes to adjust blade 7 and can be parallel to bus 6 and move.If adjust blade 7, along main flow direction 17, move, adjust so blade 7 spacing apart from its blade of adjacent setting in first rim of the guide blading 11 on ring Zhou Fangxiang and reduce, increase thus in first rim of the guide blading 11 obstruction for fluid 25.By the increase of blocking, reduce the maximum flow rate of first rim of the guide blading 11.On the contrary, can expand maximum flow rate by move adjustment blade towards the upstream of flow direction 17.The mobile route 8 of adjusting the maximum possible of blade 7 limits along the length of main flow direction 17 and the length of chute 14 by flow channel 4.In order to change maximum flow rate, can consider equally: by thering is the other adjustment blade of shorter or longer chord length, replace adjustment blade 7.
For chute 14 and bolt 15, can consider different shapes, for example the shape of T shape shape or swallow-tail form.Chute 14 in taper inner face 3 is by stop member 29 gauges in main flow direction 17, and it does not guide on the end that is positioned at downstream 5 of flow channel 4, makes to adjust blade 7 when axial flow turbine 1 operation and is pressed on stop member 29 by the mobile of fluid 25.Same feasible, the chute 14 in taper outside 2 along main flow direction 17 by stop member gauge or this two chutes 14 by stop member gauge.In the upstream of flow direction 17, not to chute 14 gauges, make to adjust blade 7 and can from circulation way 4, take out and can adjust blade exchanging by enough another.
As from accompanying drawing, for the position of adjusting blade 7 being fixed in chute 14, be provided with spacer element 16.Spacer element 16 is not only arranged in the side that is positioned at downstream of bolt 15, and is arranged in the side that is positioned at upstream of bolt 15.Feasible in principle, in the side of upstream, be not provided with spacer element 16 being positioned at, because adjust blade 7, when operation, compress the end of the spacer element 16 or the chute 14 that are positioned at downstream.While not being provided with spacer element 16 in the side that is being positioned at downstream, reach for the maximum flow rate of adjusting blade 7 minimum feasible.
Whole blades in the first rotor blade ring 11 are all configured to be adjusted blade 7 and then forms movably.As an alternative, blade can alternately form and form in the mode being placed in regularly on conical surface 2,3 as adjusting blade 7.At this, can consider, the blade of inner conical ring 23, external conical shape ring 24 and fixed in position is made by single-piece.Can consider equally, respectively the blade of fixed in position is made by single-piece together with each section of inner conical ring 23 and external conical shape ring 24, and then first rim of the guide blading 11 be comprised of a plurality of sections.
Can consider, be similarly rotor blade ring adjustment blade 7 is set.At this, inner conical ring 23 is fixedly connected with axle 21, and adjustment blade 7 is arranged on inner conical ring 23 movably with its radially inner side 10.Therefore inner conical ring 23 and adjustment blade 7 are the rotary components of axial flow turbine 1.In taper outside 2 with movably can be provided with gap between the radial outside 9 of blade 7.Adjusting blade 7 can engage with external conical shape ring 24 with its radial outside 9 equally.Under latter event, external conical shape ring 24 is rotary component equally.
The adjustment of the maximum flow rate of first rim of the guide blading 11 is as the execution of getting off: the expected value of the maximum flow rate of default blade ring 11; Determine the actual value of the maximum flow rate of blade ring 11; The actual value of the maximum flow rate of the expected value of the maximum flow rate of blade ring 11 and blade ring 11 is compared; By means of guiding device, be parallel to bus 6 and move at least one adjustment blade 7, make the expected value of maximum flow rate identical with the actual value of maximum flow rate; By means of guiding device fixed adjustment blade 7.
Although at length set forth and describe the present invention by preferred embodiment, however the present invention by disclosed example, do not limited, and those skilled in the art can therefrom derive other variations, and do not depart from protection scope of the present invention.
Claims (13)
1. the blade ring for axial flow turbine (1), it has: be arranged on outer shroud (24), radially towards inner outside (2) and be arranged on interior ring (23), inner face (3) towards the outside radially, described outside and described in the face of annular and along flow channel (4) gauge of main flow direction (17) convergent of described axial flow turbine (1) and arrange concentrically with respect to one another and abreast; And at least one adjusts blade (7), described adjustment blade in described flow channel (4) by means of guiding device (14,15) can be parallel to face (2,3) the mobile mode of the bus (6) of a face in arrange and at least one in ring (23,24) on can be fixed in default position.
2. blade ring according to claim 1, wherein said outside (2) and described inner face (3) are conical surfaces.
3. blade ring according to claim 1, wherein said outside (2) and described inner face (3) on some sections have identical radius of curvature at each in perpendicular to the cross section of the axis of described flow channel (4) along corresponding described bus (6), make the extension size of radial clearance between described adjustment blade (7) and described (2,3) when described adjustment blade (7) is mobile keep constant.
4. blade ring according to claim 3, the round section that each cross section perpendicular to the axis of described flow channel (4) of wherein said outside (2) and described inner face (3) arranges by polygonal or by a plurality of direct neighbors respectively forms.
5. according to the blade ring described in any one in claim 1 to 4, wherein said blade ring (11) is the diagonal angle level of described axial flow turbine (1).
6. according to the blade ring described in any one in claim 1 to 5, wherein said blade ring (11) has a plurality of blades, and wherein said blade alternate ground is described adjustment blade (7) and is placed in regularly described outside (2) and/or is placed in the blade on described inner face (3).
7. blade ring according to claim 6, wherein each described blade of settling regularly together with described interior ring (23) and described outer shroud (24) single type make, or together with the section of described interior ring (23) and the section single type of described outer shroud (24) make.
8. according to the blade ring described in any one in claim 1 to 7, wherein said guiding device has chute (14) and have bolt (15) on the radial outside (9) of described adjustment blade (7) and/or on radially inner side (10) in described interior ring (23) and/or in described outer shroud (24), wherein said bolt (15) joins in described chute (14).
9. blade ring according to claim 8, downstream in the main flow direction (17) of described axial flow turbine (1) at least one in described chute (14) of wherein said guiding device has stop member (29), by described stop member, described adjustment blade (7) can be fixed in default position.
10. according to the blade ring described in any one in claim 1 to 9, wherein said guiding device (14,15) is configured to, and makes to adjust the enough other adjustment blade exchangings of blade (7) energy described at least one.
11. 1 kinds of axial flow turbines, it has according to the blade ring (11) described in any one in claim 1 to 10.
12. axial flow turbines according to claim 11, the maximum flow rate of wherein said axial flow turbine (1) limits by the maximum flow rate of described blade ring (11).
13. 1 kinds for adjusting according to the method for the maximum flow rate of the blade ring (11) described in any one of claim 1 to 10, has following step:
The expected value of the maximum flow rate of-default described blade ring (11);
-determine the actual value of the maximum flow rate of described blade ring (11);
-actual value of the maximum flow rate of the expected value of the maximum flow rate of described blade ring (11) and described blade ring (11) is compared;
-by means of described guiding device (14,15), be parallel to that described bus (6) is mobile adjusts blade (7) described at least one, make the expected value of maximum flow rate identical with the actual value of maximum flow rate;
-by means of the fixing described adjustment blade (7) of described guiding device (14,15).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP12153630.4 | 2012-02-02 | ||
| EP12153630.4A EP2623717A1 (en) | 2012-02-02 | 2012-02-02 | Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring |
| PCT/EP2012/071992 WO2013113415A1 (en) | 2012-02-02 | 2012-11-07 | Blade ring for an axial turbomachine, and a method for adjusting the maximum flow rate of said blade ring |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104105844A true CN104105844A (en) | 2014-10-15 |
| CN104105844B CN104105844B (en) | 2016-03-16 |
Family
ID=47178653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280069005.9A Expired - Fee Related CN104105844B (en) | 2012-02-02 | 2012-11-07 | Blade ring for axial flow turbine and the method for the maximum flow rate that adjusts blade ring |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150030431A1 (en) |
| EP (2) | EP2623717A1 (en) |
| JP (1) | JP5855768B2 (en) |
| CN (1) | CN104105844B (en) |
| WO (1) | WO2013113415A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT201700061762A1 (en) * | 2017-06-06 | 2018-12-06 | Ansaldo Energia Spa | STATIC GROUP FOR A STAGE OF RADIAL-AXIAL EXPANSION OF STEAM TURBINE |
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| US20110247418A1 (en) * | 2010-04-08 | 2011-10-13 | General Electric Company | System and method for monitoring a compressor |
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2012
- 2012-02-02 EP EP12153630.4A patent/EP2623717A1/en not_active Withdrawn
- 2012-11-07 US US14/373,818 patent/US20150030431A1/en not_active Abandoned
- 2012-11-07 EP EP12786929.5A patent/EP2788586B1/en not_active Not-in-force
- 2012-11-07 CN CN201280069005.9A patent/CN104105844B/en not_active Expired - Fee Related
- 2012-11-07 WO PCT/EP2012/071992 patent/WO2013113415A1/en active Application Filing
- 2012-11-07 JP JP2014555097A patent/JP5855768B2/en not_active Expired - Fee Related
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| CN2709807Y (en) * | 2004-07-27 | 2005-07-13 | 天津市必尔得新技术开发有限公司 | Coal burner of reducing discharge of nitrogen oxide for cement kiln |
| CN101113678A (en) * | 2007-07-31 | 2008-01-30 | 孙敏超 | Outlet flowing intersecting surface changing adjustable turbo nozzle ring |
| WO2010108876A1 (en) * | 2009-03-26 | 2010-09-30 | Siemens Aktiengesellschaft | Axial turbomachine having an axially displaceable guide-blade carrier |
| GB2474344A (en) * | 2009-10-06 | 2011-04-13 | Cummins Ltd | Variable geometry turbine inlet |
| CN102242644A (en) * | 2010-05-12 | 2011-11-16 | 西门子公司 | Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2015506439A (en) | 2015-03-02 |
| EP2788586A1 (en) | 2014-10-15 |
| EP2623717A1 (en) | 2013-08-07 |
| JP5855768B2 (en) | 2016-02-09 |
| CN104105844B (en) | 2016-03-16 |
| WO2013113415A1 (en) | 2013-08-08 |
| EP2788586B1 (en) | 2016-01-20 |
| US20150030431A1 (en) | 2015-01-29 |
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