CN103628929B - The quiet wing of steam turbine and steam turbine - Google Patents
The quiet wing of steam turbine and steam turbine Download PDFInfo
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- CN103628929B CN103628929B CN201310321345.2A CN201310321345A CN103628929B CN 103628929 B CN103628929 B CN 103628929B CN 201310321345 A CN201310321345 A CN 201310321345A CN 103628929 B CN103628929 B CN 103628929B
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- veutro
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- 239000002184 metal Substances 0.000 claims abstract description 116
- NOQGZXFMHARMLW-UHFFFAOYSA-N Daminozide Chemical class CN(C)NC(=O)CCC(O)=O NOQGZXFMHARMLW-UHFFFAOYSA-N 0.000 claims abstract description 10
- 239000012530 fluid Substances 0.000 claims abstract description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 230000002708 enhancing effect Effects 0.000 claims 8
- 239000007788 liquid Substances 0.000 abstract description 46
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 13
- 238000005260 corrosion Methods 0.000 abstract description 8
- 230000007797 corrosion Effects 0.000 abstract description 8
- 230000000694 effects Effects 0.000 description 15
- 238000000034 method Methods 0.000 description 10
- 238000003466 welding Methods 0.000 description 7
- 230000003628 erosive effect Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 238000005520 cutting process Methods 0.000 description 3
- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical compound C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005530 etching Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000008485 antagonism Effects 0.000 description 1
- 230000002153 concerted effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000002040 relaxant effect Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 239000007787 solid Substances 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to the quiet wing of steam turbine and steam turbine, the dynamic wing corrosion providing the collision in order to reduce the water droplet generated by humid steam to cause, removing the quiet wing structure of the liquid film generated on quiet aerofoil.To achieve these goals, in the present invention, steam turbine possesses turbine stage group, this turbine stage group comprises the quiet wing (1) and is arranged on the dynamic wing (2) in downstream side, working-fluid flow direction of this quiet wing, the quiet wing (1) is formed as hollow wing by carrying out plastic working to sheet metal, at wing afterbody (8) place of the quiet wing (1), the sheet metal of wing dorsal part and the sheet metal of wing veutro are separated overlapping with gap, thus form the slit (24) of the drop guide vane inside by being attached to this alar wall face at alar wall face place.
Description
Technical field
The present invention relates to steam turbine, the dynamic wing corrosion that the collision particularly related to reduce the water droplet generated by humid steam causes, the quiet wing structure removed by the liquid film being created on quiet aerofoil.
Background technique
Usually, very low with its 1 ~ 2 grade group level group place pressure above in the final level group of low-pressure turbine, the steam therefore as working fluid becomes the humid steam state containing the small water droplet (water droplet core) liquefied.To condense and the water droplet core being attached to aerofoil is integrated and forms liquid film on aerofoil.In addition, this liquid film is destroyed by the steam of working fluid main flow, again disperses to vapor stream from acies after the wing.These water droplets are sprayed to downstream as the thick water droplet much larger than the initial water droplet core produced.Although realize miniaturization a little after this thick water droplet under the effect of main flow steam, but keep size to a certain degree and to dirty.Then, thick water droplet can not turn to sharp along stream due to its inertial force as steam, collides at high speed with the dynamic wing in downstream, becomes the reason of the corrosion of corroding wing surface, and the power of the rotation of the effect antagonism turbine wing, therefore form the reason of loss.
For above-mentioned situation, for a long time, in order to prevent the erosion caused by corrosion phenomenon, the front end of dynamic nose of wing is covered by the guard member that the material higher by hardness such as stellites is made.Or, there is method as described in patent document 1, which: form roughened surface by carrying out various concavo-convex processing to the front edge surface of the wing, relaxing impact force during droplet collision.But from the problem of its processability, and not necessarily can arrange guard member, in addition, in general only protect aerofoil comprehensive not enough as corrosion countermeasure, therefore, usually also adopt other corrosion game method in the lump.
Generally, in order to reduce the impact of corrosion, it is the most effective for removing drop self.Use method such shown in patent documentation 2 and patent documentation 3: in order to remove drop, slit being set between the quiet wing of hollow and its wing surface, attracting liquid film to reducing pressure in the quiet wing of hollow.In most cases, these slits are machined directly on the wing surface of the quiet wing structure with hollow structure.In addition, as described in patent documentation 4, also exist and slit portion carried out processing as independent component and is installed on the method for the quiet wing.
At first technical paper
Patent documentation
Patent documentation 1: Japanese Unexamined Patent Publication 61-142102 publication
Patent documentation 2: Japanese Unexamined Patent Publication 1-110812 publication
Patent documentation 3: Japanese Unexamined Patent Publication 11-336503 publication
Patent documentation 4: Japanese Unexamined Patent Publication 2007-23895 publication
The problem that invention will solve
The wing afterbody comprising the wing of wing trailing edge becomes the less sharp shape of wall thickness.Therefore, no matter by making a slice plate benging and being combined by wing afterbody and form the hollow structure of the quiet wing or hollow out the inside of solid member and under forming any situation in hollow portion, the position processing of after to a certain degree away from the wing acies of all having to can arrive slit to wing hollow region from wing surface.
In addition, as as described in patent documentation 4, even if for slit portion being carried out processing as independent component and being installed on the method for the quiet wing, in order to obtain sharp-pointed wing tail shape and guarantee, by the route of drop from slit importing hollow portion, slit construction location must be made identically with above-mentioned example to a certain degree away from acies after the wing.
On the other hand, in order to effectively remove liquid film, slit location is important factor.In the downstream side steam flow rate speedup of the quiet wing, therefore the moisture be collected on aerofoil increases, therefore, when slit location is as the position of slit processing in the past like that by wing structural specifications, likely form liquid film at slit downstream part moisture with regard to being attached to the wing once again not at enough downstream areas.
In addition, in the region being provided with slit, therefore also there is liquid film and destroyed by vapor stream and the situation of dispersing from aerofoil in steam flow rate speedup.In this case, even if arrange slit and carry out decompression attraction, the moisture removal of aerofoil can not be departed from.
Summary of the invention
Therefore, the object of the invention is to, in steam turbine, reduce by the erosion of corroding the dynamic wing caused, and improve reliability.
For solving the means of problem
To achieve these goals, in the present invention, steam turbine possesses turbine stage group, this turbine stage group comprises the quiet wing and is arranged on the dynamic wing in downstream side, working-fluid flow direction of this quiet wing, the quiet wing is formed as hollow wing by carrying out plastic working to sheet metal, make the spaced apart overlapping with gap of the sheet metal of the sheet metal of wing dorsal part and wing veutro at the wing afterbody place of the quiet wing, thus form the slit of the drop guide vane inside guiding that will be attached to this alar wall face at alar wall face place.
Invention effect
According to the present invention, the slit removing the liquid film generated on the alar wall face of the quiet wing can be arranged on quiet wing trailing edges, liquid film can be removed fully, therefore, it is possible to reduce by the erosion of corroding the dynamic wing caused, improve reliability.
Accompanying drawing explanation
Fig. 1 is the level group of the steam turbine represented in the past and the schematic diagram of the appearance of the liquid film flowed on quiet aerofoil.
Fig. 2 is the interplane stream sectional view schematically showing drop appearance dispersed from the liquid film expanded at the quiet aerofoil of steam turbine in the past in acies place after the wing.
Fig. 3 is the approximate three-dimensional map of the quiet wing of the first embodiment of the present invention.
Fig. 4 is the sectional view of the position represented by double dot dash line of Fig. 3.
Fig. 5 is the enlarged view be exaggerated by the wing afterbody of Fig. 4.
Fig. 6 is the figure of the relation representing liquid film thickness and the liquid film flow generated on aerofoil.
Fig. 7 is the approximate three-dimensional map of the quiet wing of the second embodiment of the present invention.
Fig. 8 is the wing sectional view of the quiet wing of the third embodiment of the present invention.
Fig. 9 is the enlarged view be exaggerated by the wing afterbody of Fig. 8.
Figure 10 is the stereogram of locating wedge.
Figure 11 is the approximate three-dimensional map of the quiet wing of the fourth embodiment of the present invention.
Figure 12 is the sectional view of the arbitrary section of the slit forming portion of the quiet wing shown in Figure 11.
Figure 13 is the approximate three-dimensional map of the quiet wing of the fifth embodiment of the present invention.
Figure 14 is the sectional view of the arbitrary section of the slit forming portion of the quiet wing shown in Figure 13.
Description of reference numerals
The 1 quiet wing
The 2 dynamic wings
5 main parts
8 wing afterbodys
20 dorsal plate
21 side webs
22 locating wedges
23 second slits
24 slits
25 clearance portion
26 hollow portions
27 stepped part
Acies after 28
29 wedge holes
30 wedge holes
31 lip parts
Acies before 32 aerofoil profiles
34 protuberances
36 flanks
37 vents
40 flanks
Embodiment
First, the appearance using Fig. 1 and Fig. 2 to come liquid film on simple declaration turbine airfoil and drop to produce.
Fig. 1 is the level group of the steam turbine represented in the past and the schematic diagram of the flowing appearance of the liquid film expanded on the wall of its quiet wing.The turbine stage group of steam turbine has the quiet wing 1 be fixed between outer circumferential side dividing plate 4 and inner circumferential side dividing plate 6 and the dynamic wing 2 being fixed on rotor shaft 3 in the flow direction downstream side of the working fluid of the quiet wing 1.At the outer circumferential side of the front end of the dynamic wing 2, be provided with the shell 7 forming flow path wall surface.Utilize said structure, as working fluid steam main flow by during the quiet wing 1 by speedup, give the dynamic wing 2 energy and rotor shaft 3 rotated.
In low-pressure turbine etc., when the steam main flow as working fluid becomes humid steam state, the drop be included in steam main flow is attached to the quiet wing 1, and this drop is assembled and forms liquid film on aerofoil.This liquid film flows to the direction of the determined power of making a concerted effort with the pressure in the interface of gas vapor and shearing force, near the rear acies moving to the quiet wing.Represent the flowing 11 of the liquid film of movement in FIG.Liquid film near the rear acies moving to the wing becomes drop 13, disperses in the lump with steam main flow towards the dynamic wing 2.
Fig. 2 is the interplane stream sectional view schematically showing the appearance that drop disperses from the liquid film that the aerofoil at the quiet wing 1 expands.Air-flow steam 10 by quiet interplane time, drop is attached to the quiet wing 1, and drop gathers on quiet aerofoil and expands towards liquid film 12.Acies after the liquid film 12 that the aerofoil of the quiet wing 1 expands moves to the wing, after the wing, acies becomes drop 13 and disperses.The drop 13 dispersed collides with the dynamic wing 2 being arranged at downstream, becomes the reason of the corrosion of corroding dynamic wing surface, the power that effect and the rotation of the dynamic wing resist and become the reason of loss.
Based on above-mentioned, referring to suitable accompanying drawing, embodiments of the invention are described in detail.In addition, in each figure comprising Fig. 1, Fig. 2, to same structure element annotation same reference numerals.
(embodiment 1)
The first embodiment of the present invention is described.
Fig. 3 ~ Fig. 5 is the explanatory drawing of the structure of the situation representing the quiet wing 1 place the present invention being applied to Fig. 1.Fig. 3 is the approximate three-dimensional map of the quiet wing 1 of the present embodiment, and Fig. 4 is the sectional view of the position shown in the double dot dash line of Fig. 3, and Fig. 5 is the figure be exaggerated by the wing afterbody of Fig. 4.
As shown in Figure 3, the quiet wing 1 of the present embodiment is configured to main part 5 to be engaged by welding line 9 with the wing afterbody 8 formed independently relative to main part 5.As shown in Figure 4, main part 5 to be bent etc. by sheet material and makes sheet metal generation plastic deformation and make, and becomes the structure of the hollow wing in inner side with hollow portion 26.On the other hand, wing afterbody 8 is made up of with the side web 21 as the sheet metal forming wing veutro wall the dorsal plate 20 as the sheet metal forming wing dorsal part wall, becomes and clips locating wedge 22 described later at dorsal plate 20 place and be provided with the structure of side web 21.
As shown in Figure 10, locating wedge 22 is made up of the discoid lip part 31 of effect and the protuberance 34 of cylindrical shape at the two ends of being located at lip part 31 realizing separator.As described later, in dorsal plate 20 with side web 21, in the paired wedge hole formed, easily dorsal plate 20 and the mutual alignment of side web 21 can be fixed on assigned position respectively by being inserted into by the protuberance 34 of both sides.In addition, discoid lip part 31 is clipped by dorsal plate 20 and side web 21, thus between dorsal plate 20 and side web 21, form the gap of the thickness degree of lip part 31.By regulating the thickness of lip part 31, the gap of regulation easily can be formed between dorsal plate 20 and side web 21.In addition, as long as realize the effect of the fixing of position and separator, the lip part of locating wedge 22 and the shape of protuberance are not limited to discoid, cylindric.
Get back to the explanation of wing afterbody 8.As shown in Figure 5, the welding edges of a side of dorsal plate 20 is fixed on the sheet metal of the wing dorsal part of main part 5, acies after the wing of the other end formation sharp shape.In addition, the face of the wing inner surface side of dorsal plate 20 is cut a part from the position of acies after to a certain degree away from the wing to main part 5 side, is provided with stepped part 27.
On the other hand, side web 21 separates the stepped part 27 overlapping onto dorsal plate 20 with gap.One end of side web 21 is welded with the sheet metal of the wing veutro of main part 5 and is fixed, and the other end has gap between stepped part 27.Gap is set between the stepped part 27 and the end of side web 21 of dorsal plate 20, thus slit 24 can be formed.The wall of the nose of wing side of this slit 24 is formed by the end of side web 21, and the wall of wing rear edge side is formed by dorsal plate 20, at whole wing short transverse opening.Such as, in the example shown in Fig. 3, slit 24 is arranged on whole wing short transverse total length, but, not to be arranged on whole wing short transverse total length, can be arranged on a part for wing short transverse outer circumferential side yet.
A pair wedge hole 29 for arranging above-mentioned locating wedge 22 and wedge hole 30 is had at dorsal plate 20 and side web 21.As shown in Figure 5, embed locating wedge 22 in this wedge hole 29 with wedge hole 30 place, and clamped by dorsal plate 20 and side web 21, thus the clearance portion 25 of the thickness degree of the lip part 31 of locating wedge 22 can be formed between dorsal plate 20 and side web 21.Owing to side web 21 to be separated the stepped part 27 overlapping onto dorsal plate 20 with gap, therefore clearance portion 25 is connected with slit 24, is formed the stream of the drop guiding hollow portion 26 flowed into from slit 24.
On side web 21, as shown in Figure 3, at the flow direction upstream side of the steam main flow of slit 24, multiple second slit 23 is set along wing short transverse.This second slit 23 runs through side web 21 as shown in Figure 5, and when side web 21 is installed to dorsal plate 20, this second slit 23 is connected with the clearance portion 25 between dorsal plate 20 and side web 21.Thus, from second slit 23 flow into drop also can by clearance portion 25 hollow portion 26 that leads.
After installation dorsal plate 20, side web 21 and locating wedge 22, by closed wedge hole 29 and wedge holes 30 such as welding or solderings, thus dorsal plate 20 and side web 21 are fixed on assigned position and wing afterbody 8 is formed as an integral structure.Tegmentum 33 is closed as shown in Figure 3 for the upper and lower end of wing afterbody 8, or is directly welded in outer circumferential side dividing plate 4 and inner circumferential side dividing plate 6, prevents drop from revealing from the second slit 23, slit 24 and clearance portion 25.
In addition, wedge hole also can be arranged along wing short transverse in multiple position at certain intervals as shown in Figure 3 between slit 24 and the second slit 23.Arrange two places at wing outer circumferential side, from wing central authorities to inner circumferential side, arrange a place because chord shortens, chimeric locating wedge stably can fix dorsal plate 20 and side web 21 throughout.But, as long as dorsal plate 20 and side web 21 stably can be fixed, be then not limited to the example shown in Fig. 3.Utilize the wedge hole 29,30 and locating wedge 22 that arrange in pairs at dorsal plate 20 and side web 21 place, easily the mutual alignment of dorsal plate 20 and side web 21 can be fixed on the position of regulation forming slit 24, clearance portion 25.
Next, the setting position of slit 24 and the second slit 23 is described.
The liquid film that aerofoil generates becomes unstable when steam flow rate speedup, a part is dispersed from aerofoil.The wild effect of this liquid film produces in following situation: the relative Weber number Wr=0.5 × ρ h(U-W represented by the surface tension σ of vapor density ρ, liquid film thickness h, steam flow rate U, liquid film flow velocity W and liquid film) × (U-W)/σ is more than 0.78.Even if the position being more than 0.78 at this relative Weber number arranges slit, the part of liquid film also can be dispersed and effectively can not remove moisture in stream.Thus, to process and relative Weber number that slit 24, second slit that is formed in wing afterbody 8 place is all arranged on liquid film stream is the part of 0.78.
Fig. 6 is the figure of the liquid film thickness (limit of dispersing liquid film thickness) when representing that the liquid film thickness generated on wall is 0.78 with relative Weber number.Transverse axis is the distance of the distance l measured to the arbitrary position of aerofoil along aerofoil from the front acies of the aerofoil profile shown in Fig. 4 32 being carried out nondimensionalization by the distance L along aerofoil measurement from the front acies of aerofoil profile 32 to rear acies 28.In the position that the limit water film thickness that disperses is thinner than the water film thickness generated on aerofoil, liquid film is not attached on aerofoil, even if arrange slit can not remove moisture fully.Slit location shown in Fig. 3 is arranged in the scope of l/L=0.65 ~ 0.75 by the second slit 23 of upstream side.Comparatively large in the increase of the steam flow rate at territory place downstream of the scope than l/L=0.65 ~ 0.75, even if remove liquid film at the second slit 23 place 100%, also can again generate a large amount of liquid films in its downstream side.Because the relative Weber number of this liquid film surmounts the limit liquid film thickness that again disperses, slit 24 is arranged on the position of the scope of l/L=0.75 ~ 0.9.Also generate liquid film in the downstream domain of slit 24, but utilize two above-mentioned slits more than 80% of the liquid film generated on quiet aerofoil can be removed.
In the present embodiment, the conjugant of the quiet wing main part 5 becoming hollow structure and both wing afterbodys 8.In addition, wing afterbody 8 is formed by making the sheet metal of wing dorsal part be combined with the sheet metal of wing veutro.Wing afterbody 8 does not make the sheet metal of wing dorsal part directly engage with the sheet metal of wing veutro, clips separator, carry out overlap, thus after the wing, can arrange slit near acies in the mode forming gap between the sheet metal and the sheet metal of wing veutro of wing dorsal part.
Wing afterbody assembles side web and dorsal plate as follows: be assembled into the sharp-pointed portion being formed with rear acies and the dorsal plate being formed with step on the surface of a side by carrying out the manufactured side web of slit in the height direction, be clipped in the middle to make locating wedge, the space of the thickness degree of locating wedge is formed in the inner surface side of dorsal plate and side web, and then gap is set between the sheet side end face and notopleural stepped part of side web, form Article 2 slit.By notopleural stepped part being arranged on the position near rear acies, slit location can be made to be positioned near rear acies.
According to the structure of the present embodiment, the position of the slit being attached to the drop guide vane inside in alar wall face can be set in the region becoming the limit liquid film thickness that disperses, therefore, it is possible to remove more than 80% of the liquid film generated on the quiet wing, have and can reduce by the erosion of corroding the dynamic wing caused and improve the such effect of reliability.
In addition, wing afterbody 8 can also from than dimensionless distance l/L=0.5 downstream and from than the second slit 23 by upstream side position as wing afterbody 8, and to manufacture independently with main part 5.
(embodiment 2)
Next, Fig. 7 is used to be described the second embodiment of the present invention.In the present embodiment, slit is not formed in the quiet whole region of wing short transverse, but is defined as the region stood facing each other with the fore-end of the dynamic wing 2 shown in Fig. 1.
Though utilize slit 24, second slit 23 to remove liquid film, also attract steam with liquid film simultaneously.This increase performance reduction on steam turbine with steam flow causes direct impact.In addition, the etching extent that the drop dispersed from the quiet wing produces increases with the increase of the peripheral speed of the dynamic wing.Therefore, the wing structure in the region of wing short transverse more than 70% is formed with the joint of main part 5 by the wing afterbody 8 shown in embodiment 1.
In the present embodiment, the liquid film in the larger region of etching extent can removed, the effect that the adjoint steam flow that is reduced in slit place is such can also be obtained in addition, in addition also there is following effect: the region that disome constructs is defined as 30% of wing short transverse, i.e. the part of wing short transverse that especially easily produces of liquid film, thus under the long wing that the quiet wing of low-pressure turbine final level group is such, make the making of tectosome become easy.
In addition, the wing afterbody 8 shown in Fig. 3 and Fig. 5 uses locating wedge 22 and is formed, but also can form wing afterbody 8 by precision casting.
(embodiment 3)
Next, for the third embodiment of the present invention, represent in Fig. 8 and Fig. 9.Fig. 8 is the wing profile of the quiet wing of the embodiment of the 3rd, and Fig. 9 is the enlarged view of the wing afterbody of the quiet wing shown in Fig. 8.
The wing afterbody 8 of the present embodiment is fully not independent with main part 5 to be formed, and the component of the aerofoil forming main part 5 is directly extended use by the dorsal plate 20 of wing afterbody 8.That is, wing dorsal part place, main part 5 and wing afterbody 8 are formed by piece of metal plate.On the other hand, wing veutro is formed with the sheet metal forming main part 5 and wing afterbody 8 identically with embodiment 1 independently.Side web 21 overlaps onto in the stepped part 27 of the dorsal plate 20 be integrally formed with main part 5 at spaced intervals, and one end is weldingly fixed on the sheet metal of wing veutro of main part 5 by welding line 9.On the other hand, the end of the opposing party of side web 21 has gap between main part 5 and the stepped part 27 of dorsal plate 20 formed as one.Identical with embodiment 1, spaced apart overlapping with gap at dorsal plate 20 and side web 21, thus the wall of a side of slit is formed by the end of side web 21, the wall of the opposing party is formed by notopleural stepped part, forms slit 24.By arranging gap, slit 24 can be formed between notopleural stepped part 27 and the end of side web 21.
Make side web 21 identical by the method shown in locating wedge 22 with the method that dorsal plate 20 engages and Fig. 3.According to the present embodiment, except the effect of embodiment 1, be piece of metal plate by the sheet metal of the dorsal plate and main part 5 that make wing afterbody 8, the machining period of cutting etc. of welding, component can be reduced, can be reduced by the erosion of corroding the dynamic wing caused by more low cost.
(embodiment 4)
Next, for the fourth embodiment of the present invention, represent in Figure 11 and Figure 12.Figure 11 is the approximate three-dimensional map of the quiet wing of the present embodiment.Figure 12 is the sectional view of the arbitrary section of the slit forming portion of Figure 11.The structure of the aerofoil profile of Figure 11 is the structure of the aerofoil profile shown in Fig. 8, the side web 21 of wing afterbody 8 do not utilize with main part independently component formed, but the component of the aerofoil forming main part is directly extended use.
In the present embodiment, aerofoil profile entirety is formed by mold pressing bending in advance by a sheet material.After mold pressing bending, cut off wing veutro portion in enough positions away from leading edge, take out side web 21.The slit forming portion of notopleural wing afterbody and veutro carries out cutting on the thickness direction of wing plate material, processes the gap flow path portion forming the outer shape of aerofoil profile, the dorsal part of wing inner face and veutro.At cutting portion 35 place of the side web 21 of leading edge, inside the wing, be fixed with the flank 36 strengthened by welding etc., on this flank, by being welded and fixed side web 21.The wing tail side of side web 21 by being arranged on the upstream side of the second slit 23, the locating wedge between slit 24 and the second slit 23 is fixed.In addition, flank 36 place strengthened, is provided with the vent 37 that the hollow portion 26 disconnected because of flank 36 can be made to be communicated with.By arranging vent 37, the pressure of wing hollow portion can be made to become even, can the load that produces in the pressure of flank 36 strengthened of abirritation.
In the present embodiment, except embodiment 1 and the effect of embodiment 3, owing to arranging the flank 36 strengthened inside the wing, also there is the effect that in increase, the structural strength of hollow wing is such.
(embodiment 5)
Next, Figure 13 and Figure 14 is used to be described the 5th mode of execution of the present invention.Figure 13 is the approximate three-dimensional map of the quiet wing of the present embodiment, and Figure 14 is the sectional view of the arbitrary section of the slit forming portion of the quiet wing shown in Figure 13.In the embodiment shown in Fig. 5 or Fig. 9, in order to carry out the fixing of dorsal plate and side web and guarantee the size of clearance portion of dorsal part and veutro, the locating wedge of use shown in Figure 10.In the present embodiment, replace this locating wedge, be provided with the flank 40 be formed in inside dorsal plate.
In the wing inner lateral surfaces of dorsal plate 20, be formed with recess by engraving, this recess is formed and supplies the water film flow sucked from slit to carry out the clearance portion flowed.Plurality of positions in addition in the wing short transverse of recess, the flow direction along steam main flow is provided with flank 40.When combining dorsal plate 20 with side web 21, by engaging side web 21 at flank 40 place, between dorsal plate 20 and side web 21, form the gap stream of the width of the height dimension with flank 40.In addition, side web 21 is set to relative to flank 40 cover upper cover, and is fixed by welding etc.According to the present embodiment, the width of gap stream can regulate by regulating flank height.
In addition, in the embodiment of Figure 13, flank is arranged on notopleural internal surface, but also can be arranged on the inner surface side of side web 21.In addition, the quiet wing shown in Figure 13 is the example replaced locating wedge and use the flank 40 of the present embodiment in the quiet wing illustrated by embodiment 2, but in the quiet wing of embodiment 1, embodiment 3 or embodiment 4, also can replace locating wedge and use the flank 40 of the present embodiment.
In the present embodiment, identical with other embodiment, following effect can be realized, namely, slit can be made to be positioned near rear acies, can reduce by the erosion of corroding the dynamic wing caused, improve reliability, and there is following effect, in the formation of clearance portion stream and the joint of dorsal plate and side web, do not need the part be separated completely with dorsal plate and side web as locating wedge, therefore pass through the minimizing of the parts count of assembling and assemble the reduction in man-hour, the manufacture cost of the quiet wing of hollow can be reduced.
Claims (22)
1. a steam turbine, it is characterized in that, this steam turbine possesses turbine stage group, this turbine stage group comprises the quiet wing and the dynamic wing, the above-mentioned quiet wing has and will be attached to first slit of drop to the wing inside guiding reduced pressure in this alar wall face on alar wall face, the above-mentioned dynamic wing is arranged on the downstream side, working-fluid flow direction of the above-mentioned quiet wing
The above-mentioned quiet wing is the quiet wing of the hollow wing of carrying out plastic working to sheet metal and being formed,
Have above-mentioned first slit at the aerofoil of the wing afterbody of the above-mentioned quiet wing, above-mentioned first slit is communicated with the hollow portion of the quiet wing of above-mentioned hollow wing, arranges, and separate overlapping with gap by the sheet metal of wing dorsal part with the sheet metal of wing veutro and formed along wing short transverse.
2. steam turbine according to claim 1, is characterized in that,
There are at the main flow flow direction upstream side of above-mentioned first slit multiple second slits arranged along wing short transverse,
Above-mentioned second slit is connected with the gap arranged between the sheet metal and the sheet metal of above-mentioned wing veutro of above-mentioned wing dorsal part.
3. steam turbine according to claim 2, is characterized in that,
Above-mentioned first slit and above-mentioned second slit are arranged at wing veutro,
Before the aerofoil profile from the above-mentioned quiet wing acies to aerofoil arbitrary position along aerofoil distance l with from acies before above-mentioned aerofoil profile to the quiet wing after the ratio l/L position be in the scope of 0.65 ~ 0.75 of the distance L along aerofoil of acies above-mentioned second slit is set, in the above-mentioned position be in the scope of 0.75 ~ 0.9 than l/L, above-mentioned first slit is set.
4. steam turbine according to claim 1, is characterized in that,
This steam turbine has:
Wedge hole, the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro arrange a pair above-mentioned wedge hole;
Locating wedge, it has separator portion and protuberance, above-mentioned separator portion is formed gap by the clamping of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro, raised part is arranged at the two ends in this separator portion, is inserted into above-mentioned wedge hole and the mutual alignment of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro is fixed; And
Stepped part, it is arranged at the wing inner surface side of the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end of the sheet metal of above-mentioned wing veutro overlapping at spaced intervals, thus forms above-mentioned first slit.
5. steam turbine according to claim 2, is characterized in that,
This steam turbine has:
Wedge hole, the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro arrange a pair above-mentioned wedge hole;
Locating wedge, it has separator portion and protuberance, above-mentioned separator portion is formed gap by the clamping of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro, raised part is arranged at the two ends in this separator portion, is inserted into above-mentioned wedge hole and the mutual alignment of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro is fixed; And
Stepped part, it is arranged at the wing inner surface side of the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end of the sheet metal of above-mentioned wing veutro overlapping at spaced intervals, thus forms above-mentioned first slit.
6. steam turbine according to claim 3, is characterized in that,
This steam turbine has:
Wedge hole, the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro arrange a pair above-mentioned wedge hole;
Locating wedge, it has separator portion and protuberance, above-mentioned separator portion is formed gap by the clamping of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro, raised part is arranged at the two ends in this separator portion, is inserted into above-mentioned wedge hole and the mutual alignment of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro is fixed; And
Stepped part, it is arranged at the wing inner surface side of the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end of the sheet metal of above-mentioned wing veutro overlapping at spaced intervals, thus forms above-mentioned first slit.
7. steam turbine according to any one of claim 1 to 6, is characterized in that,
The sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro respectively by with formed the quiet wing main part sheet metal independently sheet metal form.
8. steam turbine according to claim 7, is characterized in that,
A part of region of the quiet wing short transverse outer circumferential side of the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro by with above-mentioned quiet wing main part independently sheet metal form.
9. steam turbine according to any one of claim 1 to 6, is characterized in that,
The sheet metal of above-mentioned wing dorsal part is made up of identical components with the sheet metal of the main part forming the quiet wing,
The sheet metal of above-mentioned wing veutro by with formed the above-mentioned quiet wing main part sheet metal independently sheet metal form.
10. steam turbine according to claim 9, is characterized in that,
The above-mentioned quiet wing has enhancing flank at wing hollow portion, and this enhancing flank strengthens the weld part forming the sheet metal of above-mentioned quiet wing main part and the sheet metal of above-mentioned wing veutro,
Above-mentioned enhancing flank has vent, and the wing hollow portion that this vent makes to be divided into two-part by this enhancing flank and disconnects is communicated with.
11. steam turbines according to Claims 2 or 3, is characterized in that,
This steam turbine has the flank in the wing inner lateral surfaces of the sheet metal of sheet metal or the above-mentioned wing veutro being formed in above-mentioned wing dorsal part,
The sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro engage via above-mentioned flank.
The quiet wing of 12. 1 kinds of steam turbines, is characterized in that,
The quiet wing of this steam turbine has and will be attached to first slit of drop to the wing inside guiding reduced pressure in this alar wall face on alar wall face,
Plastic working is carried out to sheet metal and makes it be formed as hollow wing,
Above-mentioned first slit is formed at the aerofoil of the wing afterbody of the above-mentioned quiet wing, above-mentioned first slit is communicated with the hollow portion of the quiet wing of above-mentioned hollow wing, arrange along wing short transverse, and separate overlapping with gap by the sheet metal of wing dorsal part with the sheet metal of wing veutro and formed.
The quiet wing of 13. steam turbines according to claim 12, is characterized in that,
There are at the main flow flow direction upstream side of above-mentioned first slit multiple second slits arranged along wing short transverse,
Above-mentioned second slit is connected with the gap be arranged between the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro.
The quiet wing of 14. steam turbines according to claim 13, is characterized in that,
Above-mentioned first slit and above-mentioned second slit are arranged on wing veutro,
Before the aerofoil profile from the above-mentioned quiet wing acies to aerofoil arbitrary position along aerofoil distance l with from acies before above-mentioned aerofoil profile to the quiet wing after the ratio l/L position be in the scope of 0.65 ~ 0.75 of the distance L along aerofoil of acies above-mentioned second slit is set, be provided with above-mentioned first slit in the position that above-mentioned l/L is in the scope of 0.75 ~ 0.9.
The quiet wing of 15. steam turbines according to claim 12, is characterized in that,
The quiet wing of this steam turbine has:
Wedge hole, the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro arrange a pair above-mentioned wedge hole;
Locating wedge, it has separator portion and protuberance, above-mentioned separator portion is formed gap by the clamping of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro, raised part is arranged at the two ends in this separator portion, is inserted into above-mentioned wedge hole and the mutual alignment of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro is fixed; And
Stepped part, it is arranged at the wing inner surface side of the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end of the sheet metal of above-mentioned wing veutro overlapping at spaced intervals, thus forms above-mentioned first slit.
The quiet wing of 16. steam turbines according to claim 13, is characterized in that,
The quiet wing of this steam turbine has:
Wedge hole, the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro arrange a pair above-mentioned wedge hole;
Locating wedge, it has separator portion and protuberance, above-mentioned separator portion is formed gap by the clamping of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro, raised part is arranged at the two ends in this separator portion, is inserted into above-mentioned wedge hole and the mutual alignment of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro is fixed; And
Stepped part, it is arranged at the wing inner surface side of the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end of the sheet metal of above-mentioned wing veutro overlapping at spaced intervals, thus forms above-mentioned first slit.
The quiet wing of 17. steam turbines according to claim 14, is characterized in that,
The quiet wing of this steam turbine has:
Wedge hole, the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro arrange a pair above-mentioned wedge hole;
Locating wedge, it has separator portion and protuberance, above-mentioned separator portion is formed gap by the clamping of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro, raised part is arranged at the two ends in this separator portion, is inserted into above-mentioned wedge hole and the mutual alignment of the sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro is fixed; And
Stepped part, it is arranged at the wing inner surface side of the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end of the sheet metal of above-mentioned wing veutro overlapping at spaced intervals, thus forms above-mentioned first slit.
18., according to claim 12 to the quiet wing of the steam turbine according to any one of 17, is characterized in that,
The sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro respectively by with the sheet metal forming quiet wing main part independently sheet metal form.
The quiet wing of 19. steam turbines according to claim 18, is characterized in that,
A part of region of the quiet wing short transverse outer circumferential side of the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro by with above-mentioned quiet wing main part independently sheet metal form.
20., according to claim 12 to the quiet wing of the steam turbine according to any one of 17, is characterized in that,
The sheet metal of above-mentioned wing dorsal part is made up of identical components with the sheet metal of the main part forming the above-mentioned quiet wing,
The sheet metal of above-mentioned wing veutro by with formed the above-mentioned quiet wing main part sheet metal independently sheet metal form.
The quiet wing of 21. steam turbines according to claim 20, is characterized in that,
The above-mentioned quiet wing has enhancing flank at wing hollow portion, and this enhancing flank strengthens the weld part forming the sheet metal of above-mentioned quiet wing main part and the sheet metal of above-mentioned wing veutro,
Above-mentioned enhancing flank has vent, and the wing hollow portion that this vent makes to be divided into two-part by this enhancing flank and disconnects is communicated with.
The quiet wing of 22. steam turbines according to claim 13 or 14, is characterized in that,
The quiet wing of this steam turbine has the flank in the wing inner lateral surfaces of the sheet metal of sheet metal or the above-mentioned wing veutro being formed in above-mentioned wing dorsal part,
The sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro engage via above-mentioned flank.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2012-167902 | 2012-07-30 | ||
| JP2012167902A JP5919123B2 (en) | 2012-07-30 | 2012-07-30 | Steam turbine and stationary blade of steam turbine |
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| Publication Number | Publication Date |
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| CN103628929A CN103628929A (en) | 2014-03-12 |
| CN103628929B true CN103628929B (en) | 2016-01-13 |
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| CN201310321345.2A Active CN103628929B (en) | 2012-07-30 | 2013-07-29 | The quiet wing of steam turbine and steam turbine |
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| US (1) | US20140030065A1 (en) |
| EP (1) | EP2692990B1 (en) |
| JP (1) | JP5919123B2 (en) |
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| WO2015015859A1 (en) * | 2013-07-30 | 2015-02-05 | 三菱重工業株式会社 | Moisture removal device for steam turbine and slit hole formation method |
| JP6230383B2 (en) | 2013-11-21 | 2017-11-15 | 三菱日立パワーシステムズ株式会社 | Steam turbine stationary blades and steam turbine |
| JP6393178B2 (en) * | 2014-12-15 | 2018-09-19 | 三菱日立パワーシステムズ株式会社 | Steam turbine stationary blade |
| KR102400690B1 (en) | 2017-09-05 | 2022-05-20 | 미츠비시 파워 가부시키가이샤 | Steam turbine blades, steam turbines, and methods of manufacturing steam turbine blades |
| EP3591175A1 (en) * | 2018-07-02 | 2020-01-08 | Siemens Aktiengesellschaft | Exhaust outlet of a steam turbine |
| JP7179651B2 (en) * | 2019-02-27 | 2022-11-29 | 三菱重工業株式会社 | Turbine stator blades and steam turbines |
| JP7179652B2 (en) * | 2019-02-27 | 2022-11-29 | 三菱重工業株式会社 | Turbine stator blades and steam turbines |
| JP7293011B2 (en) * | 2019-07-10 | 2023-06-19 | 三菱重工業株式会社 | Steam turbine stator vane, steam turbine, and method for heating steam turbine stator vane |
| KR20220062650A (en) * | 2019-12-11 | 2022-05-17 | 미츠비시 파워 가부시키가이샤 | Turbine stators, turbine stator assemblies, and steam turbines |
| JP7162641B2 (en) * | 2020-07-20 | 2022-10-28 | 三菱重工業株式会社 | steam turbine vane |
| CN115917119B (en) * | 2020-09-28 | 2024-06-07 | 三菱重工业株式会社 | Steam turbine |
| EP3978725B1 (en) * | 2020-09-30 | 2024-03-27 | Itp Next Generation Turbines, S.L. | Turbine guide vane |
| WO2024101217A1 (en) * | 2022-11-11 | 2024-05-16 | 三菱重工業株式会社 | Steam turbine blade, steam turbine, and method for manufacturing steam turbine blade |
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Also Published As
| Publication number | Publication date |
|---|---|
| EP2692990A2 (en) | 2014-02-05 |
| JP5919123B2 (en) | 2016-05-18 |
| US20140030065A1 (en) | 2014-01-30 |
| EP2692990A3 (en) | 2015-04-22 |
| JP2014025443A (en) | 2014-02-06 |
| EP2692990B1 (en) | 2018-11-07 |
| CN103628929A (en) | 2014-03-12 |
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