CN101089370A - System design and cooling method for lp steam turbines using last stage hybrid bucket - Google Patents
System design and cooling method for lp steam turbines using last stage hybrid bucket Download PDFInfo
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- CN101089370A CN101089370A CNA200710110090XA CN200710110090A CN101089370A CN 101089370 A CN101089370 A CN 101089370A CN A200710110090X A CNA200710110090X A CN A200710110090XA CN 200710110090 A CN200710110090 A CN 200710110090A CN 101089370 A CN101089370 A CN 101089370A
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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
- 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
- F01D5/10—Anti- vibration means
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
- 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
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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)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A steam turbine system for use in conjunction with hybrid last stage(s) LP buckets. The system is adapted to cool the bucket tip region during low VAN windage conditions whereby the beneficial design and efficiency outcomes of the use of hybrid blades can be realized.
Description
Technical field
The present invention relates to the turbine system design that the mixing composite blading (movable vane) in (a plurality of) final stage of steam turbine (typically being low pressure (LP) steam turbine part) uses.
Background technique
Turbine blade moves in they suffer the environment of high centrifugal force load and vibration stress.When the blade natural frequency become with running speed or other through overfrequency (upstream blade or nozzle counting, perhaps other main every/change characteristics) during resonance, vibration stress increases.The damping amount that exists in vibration stress amplitude when the blade resonant vibration and the system proportional (damping is made of material, aerodynamics and mechanical component and vibrational excitation level).For the blade of continuous joint, vibration frequency is the function of whole system of row's blade, and the function of individual blade in not necessarily should row.
In addition, for turbine blade or blade, the centrifugal force load is motion speed, leaf quality and the function of locating the radius of engine centerline from the quality place.When leaf quality increases, must increase in lower radial height place physical area or cross-section area, can not surpass tolerable stress for given material with the quality that can carry its top.Can cause the excessive mobile obstacle of root and cause lower performance thus in this increase long-pending than lower span place leaf cross-section.The weight of blade causes higher disk stress and therefore may reduce reliability.
Several existing U. S. Patent/applications relate to so-called " mixing " Blade Design, wherein by with airfoil surface configuration being the weight that the combination of metal and polymer packing material reduces aerofoil.Especially, one or more blades are formed in the airfoil portion, and fill with the polymer packing material.These existing patent/applications comprise U.S. Patent No. 6,854,959,6,364,616,6,139,278,6,042,338,5,931,641 and 5,720,597; The application No.10/913 that the application No.10/900222 that on July 28th, 2004 submitted and on August 7th, 2004 submit, 407; Open the quoting by this of each is included in herein in these patents and the application.
But another problem relevant with the mixed steam turbine blade relates to the conduct cost of the function of such temperature that blade suffers during use.For example in double-flow turbine, during partial load and full speed situation, there is serious air blast heating to the exhaust stage blade apex zone.Shield region behind the blade has water spray system to be cooled to the blast air of condenser.In this, water sprays and not to be used for cooled blade but cooling discharged steam and to remain in its material temperature limits will discharge housing seal in modular design.Typically, be the carbamate sealing between LP guard shield and condenser opening.Even spray run duration at water, cool stream can not move near the heating region the blade tip, and therefore, the cooling of blade tip is very little.Blade tip can reach and surpass 500 Fahrenheits during this situation, and during normal running, leaf temperature only reaches about 150 Fahrenheits.
Summary of the invention
The present invention is designed to and mixes the turbine system that final stage LP blade is used in combination and expanded the hybrid blade notion by providing a kind of. especially, the invention provides a kind of system, its can be during low VAN air blast situation the cooled blade top area, can realize using the favourable design and the efficiencies of hybrid blade thus.
Therefore, the present invention can be implemented as a kind of xial flow steam turbine, comprising: rotor; Final stage, comprise have interior ring, outer shroud and its ask extension a plurality of nozzles dividing plate and be fixed to described rotor in described dividing plate downstream with row's blade with respect to described L O section rotation; With at least one ejection assemblies, be used for spraying cooling medium to the near zone of described final stage.
The present invention can also be embodied as a kind of method of cooling off its final stage in xial flow steam turbine, this xial flow steam turbine comprises rotor and this final stage, this final stage comprise have interior ring, outer shroud and ask the dividing plate of a plurality of nozzles of extension at it, with be fixed to described transferring to row's blade with respect to the rotation of described L O section in described dividing plate downstream, described method comprises: the near zone to described final stage sprays cooling medium.
Description of drawings
The schematic representation of low-pressure turbine when Fig. 1 illustrates double fluid;
Fig. 2 illustrates the schematic representation of the hybrid blade of partly finishing;
Fig. 3 illustrates the side view of turbine wheel, and this impeller has a plurality of hybrid blades that are mounted thereon;
Fig. 4 illustrates the sectional view of hybrid blade;
Fig. 5 comprises that in illustrated embodiments of the invention steam or water spray and/or the schematic representation of the hybrid blade system that water sprays;
Fig. 6 is the schematic representation that carries out steam jet according to illustrated embodiments of the invention by the nozzle of preceding outer side wall;
Fig. 7 is shown in the steam in the illustrated embodiments of the invention or the diagrammatic side view on aqueous jet moving-wire road; With
Fig. 8 is the schematic representation that steam or water injection/steam extract assembly.
Embodiment
Fig. 1 is the schematic representation of double-current method low-pressure turbine 10, and it comprises turbine cylinder 12, rotor 14 and a plurality of impellers that are positioned in two turbine section 16,18.With dashed lines is irised out directly outermost regions upwards of zone 20,22 expression exhaust stage blades, and this zone experience maximum air blast and heats under partial load condition.Therefore, in illustrated embodiments of the invention, steam or water injection, steam extraction and/or water spray nozzle and/or the blade that is used to cooling (a plurality of) final stage, make it possible to achieve the advantage of the hybrid blade that is used for such (a plurality of) level.
Fig. 2 schematically shows the exemplary configurations of mixed steam turbine blade 24.This turbine blade comprises petiole portion 26 and aerofoil portion 28.This aerofoil portion has operating temperature range, design speed, and with the root of blade that petiole portion links to each other, vane tip and extend outwardly into the longitudinal axis that vane tip extends inward into root of blade.Shank typically comprises and is used for blade is connected to the dovetail joint of rotor disk (Fig. 3) and the bucket platform that vapor stream is radially held in help.Aerofoil portion has leading edge and trailing edge, and wherein the direction of vapor stream is generally from leading edge and flows to trailing edge.This aerofoil also has on the pressure side and negative pressure (projection) side.
In the example that illustrates, the inside and outside groove 30,32 that makes progress in the footpath of formation on the pressure side of aerofoil portion 28, they are separated with the middle baffle plate 36 of crossing over by wide relatively web or rib.In this kind Blade Design, can adopt more () grooves or still less.Fig. 3 schematically shows row's hybrid blade 24, and it is installed on the turbine rotor disc 42.
Described aerofoil comprises main body or the major component 34 that mainly is made of metal.At this, term " metal " comprises " alloy " but can not be considered to be meant " metal foam " for the purpose of describing this invention.In exemplary embodiment described herein, main body 34 is metal part of monolithic, although the present invention is unnecessary this is limited.This metal part has first density of mass and extends to vane tip from root of blade diametrically basically.In aerofoil, save or get rid of the metal place and limit groove or recessed 30,32.For this, blade body or metal part can be by forgings, and punching press or casting form, and surface groove can pass through for example chemical milling, electrochemistry processing, and processing methods such as electro discharge machining or High-speed machining form.
Fig. 4 is the schematic cross-section of hybrid blade structure, and wherein filler portion 40 is arranged in the groove 30 of metal part and main metal-containing not, and it has second density of mass that is different from first density of mass.The filling material 40,38 of groove 30,32 can comprise the polymer based on carbamate of different-stiffness, based on the polymer of silicone, based on the composite of rubber or have the polymeric blends of suitable hardening agent and/or such as the other materials of carbon fiber, glass fibre or pottery, with regulating frequency, damping, corrosion resistance etc.For example, U. S. Patent 6287080 and 5931641 discloses some appropriate filler composites, and these patents are incorporated herein by reference to be quoted.Filling material is comprised with the selection that the metal covering of aerofoil portion is connected, and be not limited only to, bonding, viscose glue is bonding (adhesive film or gluing) and adhere between the metal covering of autoadhesion, filling material and aerofoil portion 28.
If think necessary or expectation, arrange that the filler portion 38 that is used for filling groove 32 can have the attribute different with the filler portion 40 that is used for filling groove 30, for example temperature resistant capability.Adopt different filler portions, or more particularly, adopt different fillers to allow under the situation that cost reduces, to improve the temperature resistant capability of hybrid blade.Use every kind of material and special position on the blade to be disposed for arbitrarily the needs of the temperature resistant capability of the blade of defining the level according to the temperature characteristic of filler.The blade that has extreme position to adopt more expensive exotic material that the design of hybrid blade is in for those under high air blast environment especially at blade has feasibility more.
Blade can manufacturedly make one or more grooves be filled by filling material, and filling material is selected to realize the expectation natural frequency of individual blade and whole row's blade.
In the first relevant method of example embodiment therewith, the groove 30,32 of the blade 24 in the such blade of a row is used as the natural frequency function and the filling material selected is filled.Therefore, fluted (from one to four or more) similar polymer filling material of can be designed as the expectation natural frequency that realizes individual blade and whole row's blade fill.In another example, each blade can comprise at least two kinds of for example different filling materials of different-stiffness, to realize the natural frequency of expectation.
In the second relevant method of example embodiment therewith, on the pressure side having two groups of recessed groove or organizing blade more and can form and in the groove of every group of blade, have different filling materials along aerofoil.By example, one group of blade can use the material of high strength more or " more rigidity " as the groove filler, and another group blade can use the material of low rigidity.Perhaps, a plurality of grooves of blade can use the multiple polymers filler to fill respectively in group, and a plurality of grooves of another group use different multiple polymers fillers to fill respectively.Therefore, for example with reference to the blade of Fig. 2, for first group of blade, groove 30 can use polymer " a " to fill, and groove 32 can use polymer " b " to fill.For second group of blade, groove 30 can be used for that polymer " c " is filled and groove 32 can use polymer " d " filling.Equally, these materials are selected to realize two groups of different natural frequencies in the blade.
Can adopt above-described Blade Design to come on accompanying drawing 3 shown turbine rotor wheels, to form row's blade.Especially, group A and group B can be with predetermined mapping configurations, and for example Mode A BAB is assembled on the turbine wheel, and the blade of organizing A like this is always adjacent with the blade of organizing B.In this manner, two groups of (or more groups) blades can on purpose be processed and reasonably assemble utilizing the inherent different of their resonant frequencies to be used as reducing the method for system for the response of synchronous and asynchronous vibration, and can't influence the aerodynamics attribute of Blade Design unfriendly.At this further, there is a kind of like this possibility, promptly design one group of blade, its natural frequency is arranged in (for example 4 revolutions and 5 revolutions are divided) between two " revolution " standards equably, and design another group blade, thereby it has different filler portions and makes it about other one group " revolution " excitation (for example 3 revolutions and 4 revolutions are divided) equivalent arrangements.
Also might be by changing the frequency characteristic that the vane group distribution pattern obtains expection equally.For example, also can application model AABBAA or AABAAB....
In another example embodiment, blade is fabricated to one or more grooves and fills carbamates or silicon polymer filling material, selects this filling material as the function of the damping characteristic of filling material.
Same this can be realized in one of two kinds of methods.First method is to use one or more fillers, filler to be selected to change the damping response of damping constant and whole row's blade of each blade in a plurality of grooves (perhaps blade groove) at each blade.According to the needed position of certain material characteristics, some grooves can be filled with high damping material or the material that can satisfy some other particular requirement (not necessarily relevant with damping).In some zone of blade, for example, corrosion may be institute's concerned issue; But etch-proof ideal material may be undesirable to vibration damping.In other zones, corrosion may not be any problem, and vibration damping may be a subject matter.In any case, by changing damping characteristic to bigger or littler degree, the system vibration amplitude in this row's blade can be reduced to acceptable level.
Second method that example is relevant relates to equally blade is divided into two groups therewith, and each group comprises that different materials regulates the damping constant of each group intra vane.For example, all blades of a group will comprise one or more fillers in each groove, and all blades of second group will comprise one or more fillers of different choice.Can also assemble blade by disposing, i.e. ABAB... or AABBAA... to above-mentioned similar mapping.Different blade damping response strengthens blade row or group damping in every group of blade by utilizing in the mapping configuration, thereby reaches the purpose of vane group being mixed adjusting.Thereby frequency even the better utilization that can also change each blade are like this mixed the adjusting notion.
Each of said method can cause eliminating the typical machine damping at the middle span place of particular vane design.Span connection is the flow interfering that causes turbine efficiency to reduce in the middle of this.In other words, have the suitable filling material that improves damping characteristic, can remove current middle span baffle plate 36 fully by use.
As mentioned above, typical hybrid blade 24 comprises metal blade part 34, and it has recessed groove that holds composite interstitial substance filler 40,38 or the wall window that penetrates 30,32.Fig. 4 shows the cross section of typical hybrid aerofoil design, shows shallow grooves 30, and it is filled by compound or polymer material 40.
This hybrid blade design allows a plurality of favourable outcomes.Its generation allows the lighter blade of longer or wideer chord length blade.Also allow wideer chord length blade or have the aerodynamic blade of improvement than linear leaf, stage efficiency is provided thus.
The hybrid blade design also provides the ability of " mix and regulate " continuous leaf-level that engages with the overal frequgncy response of this level of damping.In addition, hybrid blade has the chance that reduces cost.Titanium on the current linear leaf that is used for being produced is very expensive, can reach 3 times of costs of Steel Alloy.Hybrid blade has the chance with the steel design instead of titanium design of band hybrid blade.Also have by increasing the hybrid blade material and reduce thus that stress level prolongs the leaf-level chance in working life in blade and the rotor.In addition, can arrange the level that has mix design more than, this will improve air efficient or increase length of blade to produce more power.Further, lighter hybrid blade allows to have bigger flexibility aspect the IRD of adjusting vane (interior hub or root diameter (RD)).For identical blade with IRD make the bigger annular region of bigger permission, if thermokinetics/performance design requirement.In typical turbo machine, move outside blade and increase epitrochanterian pulling load greatly, owing to increase the exponential factor of blade pulling load.In addition, can make blade longer when keeping or reducing IRD, the both can produce bigger annular region.New IGCC turbine design notion needs bigger annular region, because this application-specific has more high flow rate.Bigger hybrid blade annular region makes this become possibility, partly comes by flowing and need not to produce more LP.Because length (stress) restriction, this can't obtain physically to utilize current metal blade.
The objective of the invention is to produce the turbine system design that final stage LP blade is used in combination that mixes with the above-mentioned type.But, have several problems in the attainable process making hybrid system design.A problem is the high temperature that produces in low VAN operation.As mentioned above, the serious problems when using hybrid blade design (being the compound or polymer material in the metal blade) are in (the hanging down VAN) temperature regime of operation period that flows during when the rotor full load operation.In low discharge operation period, the vane tip zone is in the air blast situation that stream is heated to the temperature that seriously is higher than steady state operation.Therefore, the hybrid blade system design must be able to overcome the temperature increase.
Make that the feasible a kind of approach of hybrid blade design is the high-temperature composite material that exploitation is used in the high-temperature steam environment.Please refer to the common co-pending application of submitting on July 28th, 2,004 10/900222 in this respect, its content is contained in this by reference.Following second approach that is described in more detail is an active cooled blade top area during low VAN air blast situation.
In an exemplary embodiment shown in Figure 5, the water that system is included in the discharge areas sprays 44, and selectivity is connected water sprinkling 44 when VAN air blast situation is hanged down in existence.Such sprinkling can be by test or CFD analysis optimization.Sprinkling is positioned on outer discharge stream taper 46 or the inner conical 48, and perhaps both are as shown in Figure 5.The direction of stream and amount are optimized desiredly, make to exist enough current with cooled blade 24, but are not enough to blade front end or rear end are produced excessive corrosion.
According to other features of the present invention (it can spray 44 with water and combine or substitute to be provided with) is as shown in Figure 6 from the outer side wall 50 of L O section 52, perhaps as the tight front uperize or the water at 24 tops of blade that example is shown among Fig. 7.And another replacement scheme is used and is configured near the vane tip among Fig. 8 and the little extraction groove 54 in the nozzle outer side wall 50 in blade 24 tight the place aheads extracts stream, reduces air blast thus and heats situation.
More specifically with reference to Fig. 5, as shown therein, two final stages of steam turbine are shown as including hybrid blade.In this example embodiment, go up and/following water sprays 44 and is shown in the low pressure discharging guard shield diffuser region and cools off.Extraly or alternatively, steam or water spray 56 and are arranged on nozzle blade 52 upstreams (Fig. 6), and perhaps steam/water sprays and/or steam jet is arranged on the downstream side of nozzle blade 52.
Spray selection in particular with reference to steam or water, Fig. 6 exemplarily shows steam (or water) spray chamber 58 that limits in outer shroud 50, comprise being used to guide steam (or water) jetburner of steam 56 towards the upstream extremity of final stage nozzle 60, described steam is directed into spray chamber by the vapor injection port in the low pressure housing 62.Fig. 6 also schematically shows the water that is used in that the low pressure discharging guard shield/diffuser region in last stage hybrid bucket 24 downstreams is cooled off and sprays 44.
As mentioned above, injection of steam or water and/or steam extraction also can be arranged on the downstream side of nozzle blade 52, the upstream side of hybrid blade 24.Therefore, as shown in Figure 7, main steam 64 can be conducted through steam jet chamber 66, passage 68 and groove 70, with the downstream that is directed cooling jet 60 and the top of adjacent hybrid blade 24.Temperature in the zone that this jet flow helps to reduce to suffer air blast to heat situation.In replacement scheme, steam jet groove 170 can be configured to recessed spoon 54, specifically illustrate as Fig. 8, as the replacement scheme of steam jet, steam extracts (a plurality of) drawing hole or (a plurality of) passage 168 that can extract recessed spoon 54 by steam, enter in the steam extracting cavity 166 and also finally for example finishes to condenser thus.The little extraction groove of the tight front of use blade extracts stream and has reduced air blast heating situation.
As shown in Figure 5, the hybrid blade system can relate to more than a level, particularly when developing the higher temperature composite material.This can allow to have in (a plurality of) final stage the aerofoil that increases area or increase efficient.In addition, because the pulling load that blade reduces, this allows littler and shorter rotor disk.Shorter rotor allows littler embedded space.Shorter rotor also helps rotor dynamics, because more crucial fundamental frequency can move on the running speed.In addition, by the equal length blade being moved to the outside, the hybrid blade system design also allows bigger annular.This can not use conventional rotors design to realize, because blade can not be handled increased load with the overweight rotor that makes.This allows to obtain bigger turbo machine output by identical rotor length.
Though the present invention has practicality most at present and preferred embodiment is described in conjunction with being considered to, should recognize and the invention is not restricted to disclosed mode of execution, on the contrary, the invention reside in covering and be included in the spirit of accompanying Claim and various modification and the equivalent arrangements in the category.
Claims (10)
1. xial flow steam turbine comprises:
Rotor;
Final stage, comprise have interior ring (52), the dividing plate of outer shroud (52) and a plurality of nozzles (60) of extending betwixt and be fixed to described rotor with row's blade (24) with respect to described L O section rotation in described dividing plate downstream; With
At least one ejection assemblies (44,56,58,66,68,70) is used for spraying cooling medium to the near zone of described final stage.
2. the water that xial flow steam turbine according to claim 1, wherein said ejection assemblies are included in the discharge areas in described exhaust stage blade downstream sprays (44).
3. xial flow steam turbine according to claim 1, wherein said ejection assemblies comprises the steam that is limited in the described outer shroud (50) or water spray chamber (58,66) and towards the described nozzle (60) of described dividing plate directed steam or water jet nozzle (56,54).
4. xial flow steam turbine according to claim 3, wherein said jetburner are arranged in the upstream of described nozzle with respect to the vapor flow path by final stage.
5. xial flow steam turbine according to claim 3, wherein said nozzle chambers (66) is with respect to the downstream of the vapor flow path of passing through final stage in described nozzle (60).
6. xial flow steam turbine according to claim 1, comprise that steam extracts assembly (166,168,170,54), be used for extracting steam from vapor flow path by final stage, with respect to described vapor flow path in the downstream of nozzle (60) and the upstream of blade (24), wherein said steam extracts assembly and comprises steam extracting cavity (166) that is limited in the described outer shroud and the extraction of the steam with opening (54) groove (170), and this steam extracts groove to have towards the directed recessed spoon of the described nozzle (60) of described dividing plate.
7. xial flow steam turbine according to claim 1, wherein at least one described blade comprises airfoil portion, this airfoil portion has: metalwork (34) that (1) mainly constitutes and have first density of mass by metal, and wherein said metalwork radially extends to roughly described vane tip from described root of blade roughly; (2) at least one fibre composites part (38,40) has second density of mass less than described first density of mass.
One kind in xial flow steam turbine the cooling its final stage method, this xial flow steam turbine comprises rotor and this final stage, this final stage comprise have interior ring (52), the dividing plate of outer shroud (52) and a plurality of nozzles (60) of extending betwixt, with be fixed to described rotor in described dividing plate downstream with row's blade (24) with respect to the rotation of described L O section, described method comprises:
Near zone to described final stage sprays cooling medium (44,56,58,66,68,70).
9. method according to claim 8, wherein said injection are included in water spray (44) in the discharge areas in described exhaust stage blade (20) downstream.
10. method according to claim 8, wherein said injection comprise that steam or the water spray chamber (58,66) from be limited to described outer shroud (50) passes through towards steam or water jet nozzle (56,54) uperize or the water of the described nozzle orientation of described dividing plate.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/452403 | 2006-06-14 | ||
| US11/452,403 US20070292265A1 (en) | 2006-06-14 | 2006-06-14 | System design and cooling method for LP steam turbines using last stage hybrid bucket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101089370A true CN101089370A (en) | 2007-12-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA200710110090XA Pending CN101089370A (en) | 2006-06-14 | 2007-06-14 | System design and cooling method for lp steam turbines using last stage hybrid bucket |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20070292265A1 (en) |
| JP (1) | JP2007332967A (en) |
| KR (1) | KR20070119535A (en) |
| CN (1) | CN101089370A (en) |
| DE (1) | DE102007027365A1 (en) |
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| JPH1054204A (en) * | 1996-05-20 | 1998-02-24 | General Electric Co <Ge> | Multi-component blade for gas turbine |
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| US7147437B2 (en) * | 2004-08-09 | 2006-12-12 | General Electric Company | Mixed tuned hybrid blade related method |
-
2006
- 2006-06-14 US US11/452,403 patent/US20070292265A1/en not_active Abandoned
-
2007
- 2007-06-11 DE DE102007027365A patent/DE102007027365A1/en not_active Withdrawn
- 2007-06-13 JP JP2007155865A patent/JP2007332967A/en not_active Withdrawn
- 2007-06-13 KR KR1020070057850A patent/KR20070119535A/en not_active Application Discontinuation
- 2007-06-14 CN CNA200710110090XA patent/CN101089370A/en active Pending
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| CN102128054A (en) * | 2010-01-12 | 2011-07-20 | 株式会社东芝 | Steam turbine |
| CN103452604A (en) * | 2012-05-31 | 2013-12-18 | 阿尔斯通技术有限公司 | Control system for axial flow turbine |
| CN103452604B (en) * | 2012-05-31 | 2015-08-12 | 阿尔斯通技术有限公司 | For the control system of axial flow turbine |
| CN103527258A (en) * | 2012-06-28 | 2014-01-22 | 阿尔斯通技术有限公司 | Cooling system and method for an axial flow turbine |
| CN103527258B (en) * | 2012-06-28 | 2016-12-28 | 通用电器技术有限公司 | Axial-flow turbine and the method for cooling shaft steam turbines blade |
| CN109339873A (en) * | 2018-09-30 | 2019-02-15 | 东方电气集团东方汽轮机有限公司 | Last stage vane of steam turbine protective device for high back pressure heat supply |
| CN110030039A (en) * | 2019-05-16 | 2019-07-19 | 哈尔滨汽轮机厂有限责任公司 | A kind of steam turbine dehumidifying grade hollow shelf |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20070119535A (en) | 2007-12-20 |
| DE102007027365A1 (en) | 2007-12-20 |
| JP2007332967A (en) | 2007-12-27 |
| US20070292265A1 (en) | 2007-12-20 |
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