CN103628929A - Steam turbine, and steam turbine stationary blade - Google Patents
Steam turbine, and steam turbine stationary blade Download PDFInfo
- Publication number
- CN103628929A CN103628929A CN201310321345.2A CN201310321345A CN103628929A CN 103628929 A CN103628929 A CN 103628929A CN 201310321345 A CN201310321345 A CN 201310321345A CN 103628929 A CN103628929 A CN 103628929A
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- wing
- mentioned
- sheet metal
- quiet
- veutro
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- 239000002184 metal Substances 0.000 claims abstract description 83
- 239000012530 fluid Substances 0.000 claims abstract description 8
- NOQGZXFMHARMLW-UHFFFAOYSA-N Daminozide Chemical class CN(C)NC(=O)CCC(O)=O NOQGZXFMHARMLW-UHFFFAOYSA-N 0.000 claims 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
- 230000000694 effects Effects 0.000 description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 12
- 238000005260 corrosion Methods 0.000 description 11
- 230000007797 corrosion Effects 0.000 description 11
- 238000000034 method Methods 0.000 description 9
- 230000003628 erosive effect Effects 0.000 description 6
- 238000003466 welding Methods 0.000 description 6
- 238000005520 cutting process Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 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
- 230000008485 antagonism Effects 0.000 description 2
- 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
- 238000007789 sealing Methods 0.000 description 2
- 229910001347 Stellite Inorganic materials 0.000 description 1
- AHICWQREWHDHHF-UHFFFAOYSA-N chromium;cobalt;iron;manganese;methane;molybdenum;nickel;silicon;tungsten Chemical compound C.[Si].[Cr].[Mn].[Fe].[Co].[Ni].[Mo].[W] AHICWQREWHDHHF-UHFFFAOYSA-N 0.000 description 1
- 230000002153 concerted effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004021 metal welding Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
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- 238000010008 shearing Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
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 is a steam turbine comprising a turbine stage having a stationary blade (1) and a moving blade (2) provided on the downstream side of the stationary blade in a working fluid flow direction, wherein the stationary blade (1) is formed in a hollow blade shape by deformation processing a metal plate, and wherein a slit (24) to guide liquid droplets deposited on a blade wall surface to the inside of the blade is formed in the blade wall by overlaying an airfoil suction-side metal plate (20) and an airfoil pressure-side metal plate (21) with a gap therebetween in a blade tail part (8) of the stationary blade (1).
Description
Technical field
The present invention relates to steam turbine, particularly relate in order to reduce the moving wing that the collision of the water droplet being generated by moist steam causes and corroding, will be created on the quiet wing structure that the liquid film of quiet aerofoil is removed.
Background technique
Conventionally, very low at final level group and its 1～2 grade of group level group place pressure above of low-pressure turbine, so as the steam of working fluid, become the moist steam condition of the small water droplet (water droplet core) that contains liquefaction.The water droplet core that condenses and be attached to aerofoil is integrated and on aerofoil, forms liquid film.In addition, this liquid film is destroyed by the steam of working fluid main flow, and from the wing, acies disperses in vapor stream again.These water droplets are sprayed downstream as the thick water droplet of the water droplet core much larger than initial generation.Although realize a little miniaturization 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 moving 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 forms the reason of loss.
For above-mentioned situation, for a long time, for the erosion that prevents from being caused by corrosion phenomenon, the front end of moving nose of wing is covered by the guard member of being made by the higher material of the hardness such as stellite.Or, there is the method as described in patent documentation 1: by the front edge surface to the wing, carry out various concavo-convex processing and form roughened surface, the impact force while relaxing droplet collision.But, from the problem of its processability, not one guard member is set surely, in addition, in general only protect aerofoil comprehensive not enough as corrosion countermeasure, therefore, conventionally also adopt in the lump other corrosion game method.
Generally, in order to reduce the impact of corrosion, it is the most effective removing drop self.Use such method shown in patent documentation 2 and patent documentation 3: in order to remove drop, between the quiet wing of hollow and its wing surface, slit is set, to reducing pressure in the quiet wing of hollow, attracts liquid film.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 there is the method for processing and be installed on the quiet wing using slit portion as independent component.
Technical paper formerly
Patent documentation
Patent documentation 1: Japan opens clear 61-142102 communique in fact
Patent documentation 2: Japanese kokai publication hei 1-110812 communique
Patent documentation 3: Japanese kokai publication hei 11-336503 communique
Patent documentation 4: TOHKEMY 2007-23895 communique
The problem that invention will solve
The wing afterbody of the wing that comprises wing trailing edge becomes the sharp shape that wall thickness is less.Therefore, no matter by making a slice plate crooked and formed in any situation in hollow portion in conjunction with the inside that forms the hollow structure of the quiet wing or hollow out solid member by wing afterbody, the position processing of acies after to a certain degree away from the wing of all having to can arrive to the slit of wing hollow region from wing surface.
In addition, as described in patent documentation 4, even for process and be installed on the method for the quiet wing using slit portion as independent component, in order to obtain sharp-pointed wing tail shape and to guarantee, drop is imported to the route of hollow portion from slit, must make slit construction location and above-mentioned example in the same manner to a certain degree away from acies after the wing.
On the other hand, in order effectively to remove liquid film, slit location is important factor.In the downstream side of quiet wing steam flow rate speedup, therefore the moisture being collected on aerofoil increases, therefore, in the situation that slit location is if slit processing is in the past like that by the position of wing structural specifications, likely not at enough downstream areas but form liquid film at slit downstream part moisture with regard to being attached to the wing once again.
Therefore in addition, in being provided with the region of slit, steam flow rate speedup, also exists liquid film to be destroyed by vapor stream and the situation of dispersing from aerofoil.In this case, the attraction of reducing pressure even if slit is set, can not will depart from the moisture removal of aerofoil.
Summary of the invention
Therefore, the object of the invention is to, in steam turbine, reduce the erosion of the moving wing being caused by corrosion, and improve reliability.
For solving the means of problem
To achieve these goals, in the present invention, steam turbine possesses turbine stage group, the moving wing that this turbine stage group comprises the quiet wing and is arranged on the working fluid flow direction downstream side of this quiet wing, the quiet wing forms hollow wing by sheet metal is carried out to plastic working, at the wing afterbody place of the quiet wing, make to separate between the sheet metal of wing dorsal part and the sheet metal of wing veutro overlapping with gap, thereby at alar wall face place, form the slit of the inner guiding of drop guide vane that will be attached to this alar wall face.
Invention effect
According to the present invention, the slit of removing the liquid film generating on the alar wall face of the quiet wing can be arranged near quiet wing trailing edge, can remove fully liquid film, therefore can reduce the erosion of the moving wing being caused by corrosion, improve reliability.
Accompanying drawing explanation
Fig. 1 means the schematic diagram of level group with the appearance of mobile liquid film on quiet aerofoil of steam turbine in the past.
Fig. 2 is the interplane stream sectional view that schematically shows the appearance that the drop liquid film that acies place expands from the quiet aerofoil at steam turbine in the past after the wing disperses.
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 being represented by double dot dash line of Fig. 3.
Fig. 5 is the enlarged view that the wing afterbody of Fig. 4 has been amplified.
Fig. 6 means the figure of the relation of the liquid film thickness that generates on aerofoil and liquid film flow.
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 that the wing afterbody of Fig. 8 has been amplified.
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 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 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 moving 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
28 rear acies
29 wedges are used hole
30 wedges are used hole
31 lip parts
Acies before 32 aerofoil profiles
34 protuberances
36 flanks
37 vents
40 flanks
Embodiment
First, the appearance of coming liquid film on simple declaration turbine airfoil and drop to produce with Fig. 1 and Fig. 2.
Fig. 1 means the schematic diagram of level group with the mobile appearance of the liquid film expanding on the wall of its quiet wing of steam turbine in the past.The moving wing 2 that the turbine stage group of steam turbine has the quiet wing 1 that is fixed between outer circumferential side dividing plate 4 and inner circumferential side dividing plate 6 and is 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 that moves the front end of the wing 2, be provided with the shell 7 that forms stream wall.Utilize said structure, as the steam main flow of working fluid when by the quiet wing 1 by speedup, move the wing 2 energy and make rotor shaft 3 rotations.
In low-pressure turbine etc., in the situation that become moist steam condition as the steam main flow of working fluid, the drop being included in steam main flow is attached to the quiet wing 1, and this drop is assembled and formed liquid film on aerofoil.This liquid film flows to the direction of the determined power of making a concerted effort of the pressure in the interface with gas vapor and shearing force, moves near the rear acies of the quiet wing.What in Fig. 1, represent mobile liquid film flows 11.Near the liquid film of rear acies that moves to the wing becomes drop 13, disperses in the lump with steam main flow towards the moving wing 2.
Fig. 2 is the interplane stream sectional view that schematically shows the appearance that liquid film that drop expands from the aerofoil at the quiet wing 1 disperses.At air-flow steam 10, by quiet when interplane, 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 expanding on the aerofoil of the quiet wing 1 moves to the wing, from the wing, acies becomes drop 13 and disperses.The drop 13 dispersing and the moving wing 2 collisions that are arranged at downstream, become the reason of the corrosion of corroding moving wing surface, the power of effect and the rotation antagonism of the moving wing and become the reason of loss.
Based on above-mentioned, referring to suitable accompanying drawing, embodiments of the invention are elaborated.In addition, in comprising each figure of 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 means the explanatory drawing of structure of situation that the present invention is applied to the quiet wing 1 place of Fig. 1.Fig. 3 is the approximate three-dimensional map of the quiet wing 1 of the present embodiment, Fig. 4 is the sectional view in the position shown in the double dot dash line of Fig. 3, and Fig. 5 is the figure that the wing afterbody of Fig. 4 has been amplified.
As shown in Figure 3, the quiet wing 1 of the present embodiment is configured to main part 5 is engaged by welding line 9 with the wing afterbody 8 forming independently with respect to main part 5.As shown in Figure 4, main part 5 makes sheet metal generation plastic deformation by crooked grade of sheet material, becomes the structure of the hollow wing in inner side with hollow portion 26.On the other hand, wing afterbody 8 consists of with the side web 21 as forming the sheet metal of wing veutro wall the dorsal plate 20 as forming the sheet metal of wing dorsal part wall, becomes the structure that clips locating wedge 22 described later at dorsal plate 20 places and side web 21 is installed.
As shown in figure 10, locating wedge 22 forms by realizing the discoid lip part 31 of effect of separator and the protuberance cylindraceous 34 of being located at the two ends of lip part 31.As described later, by the protuberance of both sides 34 is inserted into the wedge forming in pairs respectively on dorsal plate 20 and side web 21, use in hole, can easily assigned position be fixed on in dorsal plate 20 and the mutual alignment of side web 21.In addition, discoid lip part 31 is clipped by dorsal plate 20 and side web 21, thereby between dorsal plate 20 and side web 21, forms the gap of the thickness degree of lip part 31.By regulating the thickness of lip part 31, can easily between dorsal plate 20 and side web 21, form the gap of regulation.In addition,, as long as realize the effect of the fixing and separator of position, 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, a side's of dorsal plate 20 end is weldingly 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, from the position of acies to a certain degree away from the wing to main part 5 sides cutting parts, is provided with to stepped part 27.
On the other hand, side web 21 separates the stepped part 27 that overlaps onto with gap dorsal plate 20.The sheet metal welding of the wing veutro of one end of side web 21 and main part 5 is fixed, the other end and stepped part 27 between there is gap.Between the stepped part 27 of dorsal plate 20 and the end of side web 21, gap is set, thereby can forms slit 24.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.For example, in the example shown in Fig. 3, slit 24 is arranged on whole wing short transverse total length, still, is not to be arranged on whole wing short transverse total length, also can be arranged on a part for wing short transverse outer circumferential side.
At dorsal plate 20 and side web 21, have for a pair of wedge of above-mentioned locating wedge 22 is set and use hole 30 with hole 29 and wedge.As shown in Figure 5, at this wedge, with hole 29 and wedge, with 30 places, hole, embed locating wedges 22, and clamped by dorsal plate 20 and side web 21, thereby can between dorsal plate 20 and side web 21, form the clearance portion 25 of thickness degree of the lip part 31 of locating wedge 22.Owing to side web 21 being separated to the stepped part 27 that overlaps onto with gap dorsal plate 20, so clearance portion 25 is connected with slit 24, forms the stream of the drop guiding hollow portion 26 flowing 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, along wing short transverse, a plurality of the second slits 23 are set.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.Thereby the drop flowing into from the second slit 23 also can be by clearance portion 25 hollow portion 26 that leads.
After dorsal plate 20, side web 21 and locating wedge 22 are installed, by sealing wedges such as welding or solderings with hole 29 and wedge with hole 30, thereby dorsal plate 20 and side web 21 be fixed on to assigned position and make wing afterbody 8 structure that forms as one.Tegmentum 33 sealings as shown in Figure 3 of the upper and lower end of wing afterbody 8, or be directly welded in outer circumferential side dividing plate 4 and inner circumferential side dividing plate 6, prevent that drop is from the second slit 23, slit 24 and clearance portion 25 leakages.
In addition, wedge also can arrange in a plurality of positions along wing short transverse at certain intervals as shown in Figure 3 with hole between slit 24 and the second slit 23.At wing outer circumferential side, two places are set, from wing central authorities to inner circumferential side, because chord shortens, a place are set, throughout chimeric locating wedge can be stably fixedly dorsal plate 20 and side web 21.But, as long as can be stably fixedly dorsal plate 20 and side web 21, be not limited to the example shown in Fig. 3.Utilization, at dorsal plate 20 and hole 29,30 and locating wedge 22 for wedge that side web 21 places arrange in pairs, can easily be fixed on dorsal plate 20 and the mutual alignment of side web 21 position of the regulation that forms slit 24, clearance portion 25.
Next, the setting position of slit 24 and the second slit 23 is described.
The liquid film generating on aerofoil becomes unstable when steam flow rate speedup, and 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 being 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 be that more than 0.78 position arranges slit at this relative Weber number, a part for liquid film also can be dispersed in stream and can not effectively be removed moisture.Thereby slit 24, the second slit of processing and be formed on wing afterbody 8 places is all arranged on the part that the relative Weber number of liquid film stream is 0.78.
Fig. 6 means that the liquid film thickness generating on wall is the figure of the liquid film thickness (limit of dispersing liquid film thickness) of 0.78 o'clock with relative Weber number.Transverse axis is that the distance l that the arbitrary position from the acies 32 of the aerofoil profile shown in Fig. 4 to aerofoil is measured along aerofoil carries out by the distance L of measuring along aerofoil from the acies 32 of aerofoil profile to rear acies 28 distance that nondimensionalization forms.In the limit water film thickness position thinner than the water film thickness generating on aerofoil of dispersing, liquid film is not attached on aerofoil, even if slit is set, can not remove fully moisture.Slit location shown in Fig. 3 is that the second slit 23 of upstream side is arranged in the scope of l/L=0.65～0.75.Larger by the increase of the steam flow rate at downstream domain place than the scope of l/L=0.65～0.75, even remove liquid film at the second slit 23 places 100%, in its downstream side, also can again generate a large amount of liquid films.Because the relative Weber number of this liquid film surmounts the limit liquid film thickness that again disperses, slit 24 is arranged on to the position of the scope of l/L=0.75～0.9.Downstream domain at slit 24 also generates liquid film, but utilizes two above-mentioned slits can more than 80% removing the liquid film generating on quiet aerofoil.
In the present embodiment, the two conjugant of the quiet wing main part that becomes hollow structure 5 and wing afterbody 8.In addition, wing afterbody 8 is by making the sheet metal of wing dorsal part be combined and form 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, between the sheet metal of wing dorsal part and the sheet metal of wing veutro, clips separator, with form the mode in gap carry out overlapping, thereby slit can be set near acies after the wing.
Wing afterbody is assembled side web and dorsal plate as follows: by short transverse, carry out the manufactured side web of slit be assembled into be formed with after acies sharp-pointed portion and on a side surface, be formed with the dorsal plate of step, so that locating wedge is clipped in the middle, in the inner surface side of dorsal plate and side web, form the space of the thickness degree of locating wedge, and then between the sheet side end face of side web and notopleural stepped part, gap is set, form second slit.By notopleural stepped part being arranged on to the position near rear acies, can make slit location be positioned at rear acies near.
According to the structure of the present embodiment, can be by the set positions of slit of drop guide vane inside that is attached to alar wall face in the region that becomes the limit liquid film thickness that disperses, therefore can, by more than 80% removal of the liquid film generating on the quiet wing, have and can reduce the erosion of the moving wing being caused by corrosion and improve the such effect of reliability.
In addition, wing afterbody 8 can also from than dimensionless apart from l/L=0.5 downstream and from than the second slit 23, the position by upstream side starts as wing afterbody 8, and manufacture independently with main part 5.
(embodiment 2)
Next, use Fig. 7 to describe the second embodiment of the present invention.In the present embodiment, slit is not formed on the whole region of quiet wing short transverse, but is defined as the region with the fore-end face-off of the moving wing 2 shown in Fig. 1.
Though utilize slit 24, the second slit 23 to remove liquid film, also attract steam simultaneously with liquid film.This follows the increase of steam flow to reduce and cause direct impact the performance of steam turbine.In addition the etching extent that the drop dispersing from the quiet wing, produces is followed the increase of the peripheral speed that moves the wing and is increased.Therefore, the wing in more than 70% region of wing short transverse structure by the wing afterbody 8 shown in embodiment 1 and main part 5 engage form.
In the present embodiment, at the liquid film that can remove the region that etching extent is larger, can also obtain be in addition reduced in slit place follow the such effect of steam flow, in addition also there is following effect: by the region of disome structure be defined as wing short transverse 30%, be a part for the wing short transverse that especially easily produces of liquid film, thereby under the such long wing of the quiet wing of the final level group of low-pressure turbine, make the making of tectosome become easy.
In addition, the wing afterbody 8 shown in Fig. 3 and Fig. 5 is used locating wedge 22 and forms, but also can form wing afterbody 8 by precision casting.
(embodiment 3)
Next, for the third embodiment of the present invention, be illustrated in Fig. 8 and Fig. 9.Fig. 8 is the wing profile of the 3rd embodiment's the quiet wing, 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 does not fully independently form with main part 5, and the dorsal plate 20 of wing afterbody 8 directly extends use by the member that forms the aerofoil of main part 5.That is, wing dorsal part place, main part 5 is formed by piece of metal plate with wing afterbody 8.On the other hand, wing veutro and embodiment 1 form independently with the sheet metal that forms main part 5 and wing afterbody 8 in the same manner.Overlap onto in the stepped part 27 of the dorsal plate 20 being integrally formed with main part 5 to side web 21 devices spaced apart, one end is weldingly fixed on by welding line 9 on the sheet metal of wing veutro of main part 5.On the other hand, the opposing party's of side web 21 end has gap between main part 5 and the stepped part 27 of the dorsal plate 20 that forms as one.Identical with embodiment 1, between dorsal plate 20 and side web 21, separate overlapping with gap, thereby a side's of slit wall is formed by the end of side web 21, the opposing party's wall is formed by notopleural stepped part, forms slit 24.By gap is set, can between notopleural stepped part 27 and the end of side web 21, form slit 24.
Make side web 21 identical with the method shown in Fig. 3 with the method that dorsal plate 20 engages by locating wedge 22.According to the present embodiment, except embodiment 1 effect, by making the dorsal plate of wing afterbody 8 and the sheet metal of main part 5, be piece of metal plate, can reduce the machining period of the cutting etc. of welding, member, can be by the more low-cost erosion that reduces the moving wing being caused by corrosion.
(embodiment 4)
Next, for the fourth embodiment of the present invention, in Figure 11 and Figure 12, represent.Figure 11 is the approximate three-dimensional map of the quiet wing of the present embodiment.Figure 12 is the sectional view of 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 of wing afterbody 8 21 do not utilize with main part independently member form, but the member that forms the aerofoil of main part is directly extended to use.
In the present embodiment, aerofoil profile integral body is formed by mold pressing bending in advance by a sheet material.After mold pressing bending, enough, away from the position cut-out wing veutro portion of leading edge, take out side web 21.The slit forming portion of notopleural wing afterbody and veutro is carried out cutting on the thickness direction of wing plate material, and processing is to form the gap stream portion of the outer shape of aerofoil profile, the dorsal part of wing inner face and veutro.At cutting portion 35 places of the side web 21 of leading edge, by welding, wait in wing inner side and be fixed with the flank 36 that strengthens use, on this flank, by being welded and fixed side web 21.The wing tail side of side web 21 is fixed by the locating wedge being arranged between upstream side, slit 24 and second slit 23 of the second slit 23.In addition,, at flank 36 places that strengthen use, be provided with the vent 37 that can make because of hollow portion 26 connections of flank 36 disconnections.By vent 37 is set, can make the pressure of wing hollow portion become evenly, the load can abirritation producing in the pressure that strengthens the flank 36 of use.
In the present embodiment, except embodiment 1 and embodiment's 3 effect, owing in wing inner side, the flank 36 that strengthens use being set, also there is the such effect of the structural strength of hollow wing in increase.
(embodiment 5)
Next, use Figure 13 and Figure 14 to describe 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 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, for the size of carrying out the fixing of dorsal plate and side web and guaranteeing the clearance portion of dorsal part and veutro, use the locating wedge shown in Figure 10.In the present embodiment, replace this locating wedge, be provided with the flank 40 that is formed on dorsal plate inner side.
In the wing inner lateral surfaces of dorsal plate 20, by engraving, be formed with recess, this recess forms for the water film flow sucking from slit and carries out mobile clearance portion.Plurality of positions in the wing short transverse of recess is provided with flank 40 on the flow direction along steam main flow in addition.When combination dorsal plate 20 and side web 21, by engaging side webs 21 at flank 40 places, 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 respect to flank 40 cover upper cover, and fixing by welding etc.According to the present embodiment, the width of gap stream can be by regulating flank height to regulate.
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 in the illustrated quiet wing of embodiment 2, to replace locating wedge and the example that uses the flank 40 of the present embodiment, but in embodiment 1, embodiment 3 or embodiment's 4 the quiet wing, also can replace locating wedge and use the flank 40 of the present embodiment.
In the present embodiment, identical with other embodiment, can be achieved as follows effect,, can make slit be positioned near rear acies, can reduce the erosion of the moving wing being caused by corrosion, improve reliability, and there is following effect, in the engaging of the formation of clearance portion stream and dorsal plate and side web, do not need as locating wedge and dorsal plate and the completely separated part of side web, the therefore reduction in the minimizing of the part number by assembling and assembling man-hour, can reduce the manufacture cost of the quiet wing of hollow.
Claims (18)
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 moving wing, the above-mentioned quiet wing has and will be attached to the slit of the inner guiding of drop guide vane of this alar wall face on alar wall face, the above-mentioned moving wing is arranged on the working fluid flow direction downstream side of the above-mentioned quiet wing
The above-mentioned quiet wing is that sheet metal is carried out to plastic working and the quiet wing of the hollow wing that forms,
Wing afterbody at the above-mentioned quiet wing has above-mentioned slit, and above-mentioned slit is separated overlapping and form with gap by the sheet metal of wing dorsal part and the sheet metal of wing veutro.
2. steam turbine according to claim 1, is characterized in that,
Main flow flow direction upstream side at above-mentioned slit has a plurality of the second slits that arrange along wing short transverse,
The gap arranging between the sheet metal of above-mentioned the second slit and sheet metal at above-mentioned wing dorsal part and above-mentioned wing veutro is connected.
3. steam turbine according to claim 2, is characterized in that,
Above-mentioned slit and above-mentioned the second slit are arranged at wing veutro,
The aerofoil profile from the above-mentioned quiet wing acies to the distance l along aerofoil of the arbitrary position of aerofoil and acies from above-mentioned aerofoil profile to the quiet wing after the position of ratio l/L in 0.65～0.75 scope of the distance L along aerofoil of acies above-mentioned the second slit is set, than l/L, the position in 0.75～0.9 scope arranges above-mentioned slit above-mentioned.
4. according to the steam turbine described in any one in claims 1 to 3, it is characterized in that,
This steam turbine has:
Wedge, with hole, arranges a pair of above-mentioned wedge and uses hole on the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro;
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 of this separator portion, is inserted into above-mentioned wedge and with hole, makes the mutual alignment of the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned veutro fix; And
Stepped part, the wing inner surface side that it is arranged at the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end devices spaced apart ground of sheet metal of above-mentioned wing veutro overlapping, thereby forms above-mentioned slit.
5. according to the steam turbine described in any one in claim 1 to 4, it is characterized in that,
The sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro respectively by with form the quiet wing main part sheet metal independently sheet metal form.
6. steam turbine according to claim 5, is characterized in that,
The sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro by a part of region of quiet wing short transverse outer circumferential side and above-mentioned quiet wing main part independently sheet metal form.
7. according to the steam turbine described in any one in claim 1 to 4, it is characterized in that,
The sheet metal of above-mentioned wing dorsal part consists of identical components with the sheet metal that forms the main part of the quiet wing,
The sheet metal of above-mentioned wing veutro by with form the above-mentioned quiet wing main part sheet metal independently sheet metal form.
8. steam turbine according to claim 7, is characterized in that,
The above-mentioned quiet wing has enhancing flank at wing hollow portion, and this enhancing flank strengthens forming the weld part of 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 this vent makes to be divided into two-part by this enhancing flank and the wing hollow portion that disconnects is communicated with.
9. a quiet wing for steam turbine, is characterized in that,
The quiet wing of this steam turbine has and will be attached to the slit of the inner guiding of drop guide vane of this alar wall face on alar wall face,
Sheet metal is carried out plastic working and makes it form hollow wing, at wing afterbody place, make the sheet metal of wing dorsal part and the sheet metal of wing veutro separate overlapping with gap, thereby form above-mentioned slit.
10. the quiet wing of steam turbine according to claim 9, is characterized in that,
Main flow flow direction upstream side at above-mentioned slit has a plurality of the second slits that arrange along wing short transverse,
Above-mentioned the second slit is connected with the gap being arranged between the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro.
The quiet wing of 11. steam turbines according to claim 10, is characterized in that,
Above-mentioned slit and above-mentioned the second slit are arranged on wing veutro,
The aerofoil profile from the above-mentioned quiet wing acies to the distance l along aerofoil of the arbitrary position of aerofoil and acies from above-mentioned aerofoil profile to the quiet wing after the position of ratio l/L in 0.65～0.75 scope of the distance L along aerofoil of acies above-mentioned the second slit is set, the position at above-mentioned l/L in 0.75～0.9 scope is provided with above-mentioned slit.
12. according to the quiet wing of the steam turbine described in any one in claim 9 to 11, it is characterized in that,
The quiet wing of this steam turbine has:
Wedge, with hole, arranges a pair of above-mentioned wedge and uses hole on the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned wing veutro;
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 of this separator portion, is inserted into above-mentioned wedge and with hole, makes the mutual alignment of the sheet metal of above-mentioned wing dorsal part and the sheet metal of above-mentioned veutro fix; And
Stepped part, the wing inner surface side that it is arranged at the sheet metal of above-mentioned wing dorsal part, makes the rear edge side end devices spaced apart ground of sheet metal of above-mentioned wing veutro overlapping, thereby forms above-mentioned slit.
13. according to the quiet wing of the steam turbine described in any one in claim 9 to 12, it is characterized in that,
The sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro respectively by the sheet metal with forming quiet wing main part independently sheet metal form.
The quiet wing of 14. steam turbines according to claim 13, is characterized in that,
The sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro by a part of region of quiet wing short transverse outer circumferential side and above-mentioned quiet wing main part independently sheet metal form.
15. according to the quiet wing of the steam turbine described in any one in claim 9 to 12, it is characterized in that,
The sheet metal of above-mentioned wing dorsal part consists of identical components with the sheet metal that forms the main part of the above-mentioned quiet wing,
The sheet metal of above-mentioned wing veutro by with form the above-mentioned quiet wing main part sheet metal independently sheet metal form.
The quiet wing of 16. steam turbines according to claim 15, is characterized in that,
The above-mentioned quiet wing has enhancing flank at wing hollow portion, and this enhancing flank strengthens forming the weld part of 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 this vent makes to be divided into two-part by this enhancing flank and the wing hollow portion that disconnects is communicated with.
17. according to the steam turbine described in claim 2 or 3, it is characterized in that,
This steam turbine has the flank in the wing inner lateral surfaces that is formed on the sheet metal of above-mentioned wing dorsal part or the sheet metal of above-mentioned wing veutro,
The sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro engages via above-mentioned flank.
18. according to the quiet wing of the steam turbine described in claim 10 or 11, it is characterized in that,
This steam turbine has the flank in the wing inner lateral surfaces that is formed on the sheet metal of above-mentioned wing dorsal part or the sheet metal of above-mentioned wing veutro,
The sheet metal of the sheet metal of above-mentioned wing dorsal part and above-mentioned wing veutro engages 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 true CN103628929A (en) | 2014-03-12 |
| CN103628929B CN103628929B (en) | 2016-01-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310321345.2A Active CN103628929B (en) | 2012-07-30 | 2013-07-29 | The quiet wing of steam turbine and steam turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20140030065A1 (en) |
| EP (1) | EP2692990B1 (en) |
| JP (1) | JP5919123B2 (en) |
| CN (1) | CN103628929B (en) |
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| CN104653235A (en) * | 2013-11-21 | 2015-05-27 | 三菱日立电力***株式会社 | Steam turbine |
| CN105697071A (en) * | 2014-12-15 | 2016-06-22 | 三菱日立电力***株式会社 | Steam Turbine Stationary Blade |
| CN112211679A (en) * | 2019-07-10 | 2021-01-12 | 三菱重工业株式会社 | Steam turbine, stationary blade for steam turbine, and heating method for stationary blade for steam turbine |
| CN113508217A (en) * | 2019-02-27 | 2021-10-15 | 三菱动力株式会社 | Turbine stator blade and steam turbine |
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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 |
| 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 |
| JP7179652B2 (en) * | 2019-02-27 | 2022-11-29 | 三菱重工業株式会社 | Turbine stator blades and steam turbines |
| 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 |
| CN103628929B (en) | 2016-01-13 |
| EP2692990A3 (en) | 2015-04-22 |
| JP2014025443A (en) | 2014-02-06 |
| EP2692990B1 (en) | 2018-11-07 |
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