CN101839148A - Steam turbine rotor blade and corresponding steam turbine - Google Patents
Steam turbine rotor blade and corresponding steam turbine Download PDFInfo
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- CN101839148A CN101839148A CN201010115612A CN201010115612A CN101839148A CN 101839148 A CN101839148 A CN 101839148A CN 201010115612 A CN201010115612 A CN 201010115612A CN 201010115612 A CN201010115612 A CN 201010115612A CN 101839148 A CN101839148 A CN 101839148A
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- Prior art keywords
- movable vane
- outer circumferential
- shroud
- mentioned
- turbo machine
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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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
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- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/232—Three-dimensional prismatic conical
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
An object of the present invention to provide a steam turbine moving blade that can suppress a decrease in turbine efficiency and can reduce the length of a turbine shaft. In a steam turbine including a turbine rotor 7; a moving blade 1 secured to the turbine rotor 7; a shroud 3 provided on an outer circumferential side distal end of the moving blade 1; and an outer circumferential side stationary wall 4 internally embracing the turbine rotor 7 and forming an outer circumferential side passage wall of a steam path, the shroud 3 has an inner circumferential surface 14 so formed that a moving blade outlet flare angle [alpha]3 is greater than a moving blade inlet flare angle [alpha]2; an angle [alpha]1 formed between the outer circumferential side stationary wall 4 and the turbine central axis 50 is generally equal to the moving blade inlet flare angle [alpha]2; and an angle [alpha]4 formed between the outer circumferential side stationary wall and an turbine central axis 50 is generally equal to the moving blade outlet flare angle [alpha]3.
Description
Technical field
The present invention relates to be applicable to the turbo machine movable vane of steam turbine.
Background technique
In general, steam turbine is in the multistage level that is made of movable vane and stator blade of axially having of turbine rotor, and the peripheral part that exports in final level is provided with the diversion division that steam is directed to exhaust chamber.In such steam turbine, its structure is, steam is by quickening to increase kinetic energy with the stator blade that becomes the throttling runner, and kinetic energy is converted to energy of rotation and produces power with movable vane, by bleed runner and exhaust chamber it is transformed into rotor radial again and flows out.(with reference to patent documentation 1-TOHKEMY 2003-27901 communique etc.).
In such steam turbine, because that the shortening of the length of turbine shaft can reduce the axial heat of turbine rotor is flexible poor, thereby the certainty equivalence that can expect to reduce the loss that is caused by leakage current and improve the turbine shaft vibration really.
The axial length of low-pressure turbine depends on that the diversion division of downstream of the outer, stationary wall that is arranged at final level is to radially the position that turns to end.Therefore, if strengthen the curvature of diversion division, then diversion division can shorten the length of turbine shaft to turning to and can more finish by upstream side (below, be called for short upstream side) in the flow of steam direction radially.Yet exhaust chamber becomes the diffusion runner, forms adverse pressure gradient.Therefore,, strengthen the extended corner (angle that refers to the formation of steam flow channel periphery wall and turbo machine central shaft) of diversion division, vapor stream then takes place easily, might produce windage loss from the peeling off of diversion division if strengthen the curvature of diversion division.
In addition because the shortening of the length of turbine shaft, just need make vapor stream in shorter axle span to radially turning to.Therefore, in the level of bleeding of the upstream side that is arranged at low-pressure turbine, the extended corner of inner peripheral surface of shroud that constitutes the movable vane of the level of bleeding increases with deviation in abutting connection with the extended corner of the outer circumferential side stationary wall inner peripheral surface that is arranged on the movable vane downstream side.And movable vane outlet and the distance of bleeding between the runner shorten, and vapor stream is in the movable vane outlet and bleed between the runner inlet with shorter distance to radially turning to.Therefore, might produce windage loss at the runner entrance part of bleeding with regard to being easy to generate separation vortex.
Summary of the invention
So, the purpose of this invention is to provide a kind of can the inhibition because of the peeling off and the generation of the loss that secondary gas flow causes of air-flow, the efficient that can suppress turbo machine reduces, and can shorten the steam turbine movable vane of the length of turbine shaft.
To achieve these goals, the movable vane of the steam turbine of the present invention's first scheme, have in the movable vane of steam turbine of shroud at the outer circumferential side front end, it is characterized in that, the inner peripheral surface of above-mentioned shroud forms, movable vane outlet extended corner is bigger than movable vane inlet extended corner, above-mentioned movable vane inlet extended corner with in abutting connection with the movable vane upstream side extended corner of the outer circumferential side stationary wall of the upstream side that is arranged on above-mentioned shroud about equally, and above-mentioned movable vane outlet extended corner with in abutting connection with the movable vane downstream side extended corner of the above-mentioned outer circumferential side stationary wall in the downstream side that is arranged on above-mentioned shroud about equally.
The movable vane of the steam turbine of alternative plan of the present invention, on the basis of first scheme, it is characterized in that, the outer circumferential face of above-mentioned shroud has and comprises the downstream side front end and the face turbo machine central axes, and the distance between outer circumferential face upstream side front end and the turbo machine central shaft is littler than the distance between outer circumferential face downstream side front end and the turbo machine central shaft.
The movable vane of the steam turbine of third party's case of the present invention on the basis of first scheme, is characterized in that, the outer circumferential face of above-mentioned shroud is made of the face with turbo machine central shaft almost parallel, and above-mentioned shroud is hollow.
The movable vane of the steam turbine of the cubic case of the present invention on the basis of alternative plan, is characterized in that, above-mentioned movable vane constitutes the final level of low-pressure turbine.
The movable vane of the steam turbine of the present invention's the 5th scheme on the basis of third party's case, is characterized in that, above-mentioned movable vane formation adjacency is arranged on from the level of bleeding of the upstream side of the runner of bleeding of steam flow channel extraction steam.
The steam turbine of the present invention's the 6th scheme has: turbine rotor; Be fixed on the movable vane on this turbine rotor; Be arranged on the shroud of this movable vane outer circumferential side front end; And above-mentioned turbine rotor wrapped in inside, form the outer circumferential side stationary wall of the outer circumferential side flow path wall of steam flow channel, it is characterized in that, the inner peripheral surface of above-mentioned shroud forms, movable vane outlet extended corner is bigger than movable vane inlet extended corner, above-mentioned movable vane inlet extended corner with in abutting connection with the movable vane upstream side extended corner of the above-mentioned outer circumferential side stationary wall of the upstream side that is arranged on above-mentioned movable vane about equally, and, above-mentioned movable vane outlet extended corner with in abutting connection with the movable vane downstream side extended corner of the above-mentioned outer circumferential side stationary wall in the downstream side that is arranged on above-mentioned movable vane about equally.
The steam turbine of the present invention's the 7th scheme, on the basis of the 6th scheme, it is characterized in that, the outer circumferential face of above-mentioned shroud has and comprises the downstream side front end and the face turbo machine central axes, and the distance between outer circumferential face upstream side front end and the turbo machine central shaft is littler than the distance between outer circumferential face downstream side front end and the turbo machine central shaft.
The steam turbine of the present invention all directions case on the basis of the 6th scheme, is characterized in that the outer circumferential face of above-mentioned shroud is made of the face with turbo machine central shaft almost parallel, and above-mentioned shroud is hollow.
Effect of the present invention is as follows.
According to the present invention, can suppress because of the peeling off and the generation of the loss that secondary gas flow causes of air-flow, the efficient that can suppress turbo machine reduces, and can shorten the length of turbine shaft.
Description of drawings
Fig. 1 is the sectional view of major component of final level of the steam turbine of first embodiment of the invention.
Fig. 2 is the sectional view of major component of final level of the steam turbine of second embodiment of the invention.
Fig. 3 is the sectional view of major component of the level of bleeding of the steam turbine of third embodiment of the invention.
Fig. 4 is the sectional view of major component of the level of bleeding of existing steam turbine.
Fig. 5 is the sectional view of major component of the level of bleeding of the steam turbine of four embodiment of the invention.
Fig. 6 is the sectional view of major component of the level of bleeding of the steam turbine of fifth embodiment of the invention.
Among the figure:
1,31-movable vane, 2,26-stator blade, 3,32,41, the 43-shroud, 4,27,28-outer circumferential side stationary wall, the 11-diversion division, the 12-exhaust chamber, 13,34, the inner peripheral surface of 35-outer circumferential side stationary wall, 14, the inner peripheral surface of 33-shroud, the inner peripheral surface of 15-diversion division, 16,22, the 24-plane of inclination, 17, the 21-parallel surface, the 19-steam flow channel, 20-steam, 23,37-upstream side parallel surface, 25,38-downstream side parallel surface, the 30-runner that draws gas, 36, the outer circumferential face of 47-shroud, the 40-stream that draws gas, 42-separation vortex, 50-turbo machine central shaft.
Embodiment
Below, with reference to suitable accompanying drawing to being described in detail for implementing mode of the present invention.In addition, shown in each accompanying drawing, identical constituting component is put on identical label.
At first, first mode of execution of the present invention is described.Fig. 1 (a) is a structure of representing the major component of the final level of observed low-pressure turbine from the side and exhaust chamber.Stator blade 2 and movable vane 1 constitute the final level of turbo machine in couples.The outer circumference end of stator blade 2 utilizes outer circumferential side stationary wall 4 to support, and all side stationary wall 5 support in the interior week end utilization.And stator blade 2 circumferentially is being provided with multi-disc.On the other hand, turbine rotor 7 circumferentially be fixed with multi-disc movable vane 1, be provided with the shroud 3 that is connected between the set multi-disc movable vane of periphery of rotor at the outer circumferential side front end of movable vane 1.This shroud 3 has the multi-disc of compiling movable vane, and with the fixing type of parts, perhaps in the cover between the configuration blade pitgh on each blade, the type that is circumferentially compressing by the reversing of blade that causes by rotation.The employed shroud 3 of present embodiment can be this two types any.
What the arrow 51 of Fig. 1 (a) was represented is the flow direction of the steam in the steam flow channel 19 that forms between outer circumferential side stationary wall 4 and interior all side stationary wall 5.Below, abbreviate the flow direction downstream side of steam as downstream side, and abbreviate the flow direction upstream side of steam as upstream side.
Be provided with the shell 9 that covers outer circumferential side stationary wall 4 at the turbo machine radial direction outer circumferential side of outer circumferential side stationary wall 4 (below, abbreviate outer circumferential side as), between outer circumferential side stationary wall 4 and shell 9, form exhaust chamber 12.In addition, the end of downstream side formation in outer circumferential side stationary wall 4 will be directed to the diversion division 11 of exhaust chamber 12 through the steam that movable vane 1 comes out.All sides in the turbo machine radial direction of diversion division 11 (below, all sides in abbreviating as) be provided with tapered roller bearing outer ring (ベ ア リ Application グ コ one Application) 10, between tapered roller bearing outer ring 10 and diversion division 11, form the diffusion runner 18 of ring-type.
Below, the structure of shroud 3 is described.At this, below, so-called " extended corner " is meant the periphery wall (for example, referring to the inner peripheral surface 13 of outer circumferential side stationary wall 4, the inner peripheral surface 14 of shroud 3, the inner peripheral surface 15 of diversion division 11) of steam flow channel 19 and the angle of turbo machine central shaft 50 formation.
Shown in Fig. 1 (b), the inner peripheral surface 14 of shroud 3 with extended corner from upstream side downstream the mode that increases gradually of side form agley to slyness radially.At this, the tangent line A (being represented by dotted lines) of the upstream side front end of inner peripheral surface 14 is called movable vane inlet spread angle alpha 2 to the angle of turbo machine central shaft 50.And the angle that the tangent line B (being represented by dotted lines) of the downstream side front end of inner peripheral surface 14 is formed turbo machine central shaft 50 is called movable vane outlet spread angle alpha 3.The inner peripheral surface 14 of the shroud 3 of present embodiment forms than movable vane inlet spread angle alpha 2 bigger modes with movable vane outlet spread angle alpha 3.
On the other hand, the inner peripheral surface 13 that constitutes the outer circumferential side stationary wall 4 of final level is called movable vane upstream side spread angle alpha 1 with turbo machine central shaft 50 angulations.In addition, though the mode that diversion division 11 increases from the upstream downstream gradually with extended corner forms agley to slyness radially, the tangent line D (being represented by dotted lines) that the inner peripheral surface 15 of diversion division 11 is bent away initial point C is called movable vane downstream side spread angle alpha 4 with the angle that turbo machine central shaft 50 forms.In the present embodiment, the inner peripheral surface 14 of shroud 3 forms as follows: movable vane inlet spread angle alpha 2 with in abutting connection with the movable vane upstream side spread angle alpha 1 of the outer circumferential side stationary wall 4 that is arranged on the movable vane downstream side about equally, and, movable vane outlet spread angle alpha 3 with in abutting connection with the movable vane downstream side spread angle alpha 4 of the diversion division 11 of the outer circumferential side stationary wall that is arranged on the movable vane upstream side about equally.
On the other hand, the outer circumferential face of shroud 3 forms, upstream side has plane of inclination 16, the downstream side has the parallel surface 17 parallel with turbo machine central shaft 50, and the distance of the upstream side front end of 3 outer circumferential face be shroud upstream side external diameter than the distance of the downstream side front end of 3 the outer circumferential face from turbo machine central shaft 50 to shroud is that shroud downstream side external diameter is littler from turbo machine central shaft 50 to shroud.In addition, the angle of inclination of plane of inclination 16 is set at, and the thickness of shroud 3 is roughly certain from the upstream side to the downstream side.
On the outer circumferential side stationary wall 4 relative, be provided with sealing fin 6, make the gap between outer circumferential side stationary wall 4 and the shroud 3 narrower, to be controlled at the leakage of the vapor stream that makes a circulation in the movable vane 1 with the parallel surface 17 of the outer circumferential face of shroud 3.In addition, in the final level of turbo machine,, thereby sealing fin 6 only can be arranged on the movable vane outlet side owing to the leakage Flow area that is formed by sealing fin 6 and shroud is less with respect to the Flow area of movable vane.
Below, the action effect of present embodiment is described.Because the inner peripheral surface 14 of shroud 3 is formed, make movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 about equally, and make movable vane outlet spread angle alpha 3 and movable vane downstream side spread angle alpha 4 about equally, thereby steam flows to shroud 3 and inner peripheral surface abreast from outer circumferential side stationary wall 4, flow abreast to diversion division 11 and inner peripheral surface from shroud 3, the smooth geocentric vertical of air-flow is turned to, can suppress by the peeling off and the generation of the loss that secondary gas flow causes of air-flow, and can suppress the reduction of turbine efficiency.
At this, in the present invention, preferably movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 and movable vane outlet spread angle alpha 3 equates respectively with movable vane downstream side spread angle alpha 4, but so long as the deviation of extended corner about equally, promptly in 5 °, still can expect effect of the present invention.
In addition, the inner peripheral surface 14 of shroud 3 is formed, make movable vane outlet spread angle alpha 3 bigger, make steam to turning to and to be shared by movable vane 1 radially than movable vane inlet spread angle alpha 2.The steam of the moving blade ' s shroud band side of the final level of low-pressure turbine, its speed is fast, kinetic energy is also big.All the time, mainly be that this high velocity vapor is realized to radially turning at the diffusion runner 18 and the exhaust chamber 12 of adverse pressure gradient.Among the present invention, compare with the movable vane outlet that vapor (steam) velocity is slow, the less movable vane inside of kinetic energy owing to make to share to turning to radially, thereby, can make the steam flow steering volume radially of exhaust chamber 12 littler compared with the existing.Its result with existing identical, promptly the peeling off under the situation that occurrence tendency is a same degree of flow channel shape, can shorten the length up to the axle before radially turning in the radius of curvature of the inner peripheral surface 15 of diversion division 11.
In addition, be accompanied by the increase of the extended corner that the shortening of the length of turbine shaft causes, the bending of shroud 3 strengthens, promptly, even the difference of α 3 and α 2 strengthens, increase by the weight that adopts following structure also can suppress shroud self, that is: the upstream side at the outer circumferential face of shroud 3 forms plane of inclination 16, form the parallel surface 17 with central axes in the downstream side, will be from turbo machine central shaft 50 to shroud the distance of upstream side front end of 3 outer circumferential face be that to do than the distance of the downstream side front end of 3 the outer circumferential face from turbo machine central shaft 50 to shroud be that the downstream side external diameter is littler to the upstream side external diameter.Its result can prevent the reduction of the strength reliability of turbine bucket.
Below, second mode of execution of the present invention is described.Fig. 2 (a) is the figure of structure that represents the major component of the final level of observed low-pressure turbine from the side and exhaust chamber.In addition, omit its explanation for the label identical with the first mode of execution identical construction element annotation.
The structure of present embodiment is that the end and the low-pressure turbine central shaft 50 in the inner peripheral surface downstream side of the outer circumferential side stationary wall 4 of the stator blade 2 of the final level of support form abreast, are roughly 0 degree in outer circumferential side stationary wall 4 outlet port movable vane upstream side spread angle alpha 1.On the other hand, the inner peripheral surface of shroud 3 is made of the parallel surface 21 parallel with the turbo machine central shaft 50 of upstream side and the plane of inclination 22 in downstream side.And the inner peripheral surface upstream-side-end is included in the parallel surface 21, and end of downstream side is included in the plane of inclination 22.The upstream-side-end of inner peripheral surface is included in the occasion in the plane, to comprise the plane of upstream-side-end and the angle of central shaft formation and be called movable vane inlet extended corner, the end of downstream side of inner peripheral surface is included in the occasion in the plane, will comprise the plane of end of downstream side and the angle of central shaft formation and be called movable vane outlet extended corner.Therefore, the angle that present embodiment forms parallel surface 21 and turbo machine central shaft 50 is as movable vane inlet spread angle alpha 2, and the angle that plane of inclination 22 and turbo machine central shaft 50 are formed is as movable vane outlet spread angle alpha 3.
In the present embodiment, the inner peripheral surface of shroud 3 forms, movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 are about equally, the movable vane downstream side spread angle alpha 4 of movable vane outlet spread angle alpha 3 and diversion division 11 about equally, and movable vane outlet spread angle alpha 3 is bigger than movable vane inlet spread angle alpha 2.In addition, as shown in Figure 2, inner peripheral surface 15 with diversion division 11 from upstream side downstream side radially not crooked, and the shape that tilts at a certain angle of central shaft relatively, in this case with the angle of inclination of the inner peripheral surface 15 of diversion division 11 as movable vane downstream side spread angle alpha 4.
The outer circumferential face of shroud 3 forms, it has: the upstream side parallel surface that comprise upstream side 23 parallel with turbo machine central shaft 50 and comprise the downstream side parallel surface 25 of downstream side, and relatively turbo machine central shaft 50 tilts and connects the plane of inclination 24 of upstream side parallel surface and downstream side parallel surface, and the distance of 3 outer circumferential face upstream side front end be shroud upstream side external diameter than the distance of 3 the outer circumferential face downstream side front end from central shaft 50 to shroud is that shroud downstream side external diameter is littler from central shaft 50 to shroud.In addition, the thickness of shroud 3 constitutes, and is roughly certain from the upstream side to the downstream side.
Present embodiment is owing to the inner peripheral surface 14 with shroud 3 forms, movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 are about equally, movable vane outlet spread angle alpha 3 and movable vane downstream side spread angle alpha 4 are about equally, and, movable vane outlet spread angle alpha 3 is bigger than movable vane inlet spread angle alpha 2, therefore, steam 20 flows substantially parallel with inner peripheral surface between the inner peripheral surface 15 of the inner peripheral surface 13 of the inner peripheral surface 14 of shroud 3 and outer circumferential side stationary wall 4 and diversion division 11.Thus, can suppress vapor stream because of the peeling off and the generation of the loss that secondary gas flow causes of air-flow, and can suppress the reduction of turbine efficiency.
In addition, in the present embodiment, preferably movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 and movable vane outlet spread angle alpha 3 equates respectively with movable vane downstream side spread angle alpha 4, but so long as the deviation of extended corner about equally, promptly in 5 °, still can expect effect of the present invention.
In addition, between the outlet, can make flow of steam, in comprising the exhaust chamber 12 of peeling off the high diversion division of trend with adverse pressure gradient, can make steam flow steering volume radially littler than existing to radially turning at the inlet of movable vane 2.Its result with existing identical, promptly the peeling off under the situation that occurrence tendency is a same degree of flow channel shape, can shorten the length up to the axle before radially turning in the radius of curvature of the inner peripheral surface 15 of diversion division 11.
By will be from turbo machine central shaft 50 to shroud the distance of upstream side front end of 3 outer circumferential face be that the distance that the upstream side external diameter is made than the downstream side front end of 3 the outer circumferential face from turbo machine central shaft 50 to shroud is the littler structure of downstream side external diameter, even thereby the angle of inclination of increasing plane of inclination 22, the weight that also can suppress shroud self increases.Its result can prevent the reduction of the strength reliability of turbine bucket.
Below, the 3rd mode of execution of the present invention is described.Fig. 3 is the figure that represents the bleed level and the structure of the major component of the runner of bleeding of observed from the side low-pressure turbine upstream side.In addition, omit its explanation for the label identical with the first mode of execution identical construction element annotation.
As shown in Figure 3, in the outer circumferential side stationary wall 27 that supports stator blade 26 with constitute and be provided with between the outer circumferential side stationary wall 28 of next stage at circumferential openings and the bleeding point 29 that is communicated with the runner 30 of bleeding.Bleed runner 30 the outer circumferential side of outer circumferential side stationary wall along extending circumferentially and be arranged to circular aspirating chamber (not shown) and be communicated with.The part of the steam 20 that flows in steam flow channel 19 is sucked into aspirating chamber from bleeding point 29 by the runner 30 of bleeding, and this pumping airflow 40 takes out outside turbo machine by the place that along the circumferential direction connects at aspirating chamber or the pipe arrangement of bleeding (not shown) of many places again.
Between stator blade 26 and bleeding point 29, constitute the movable vane 31 of the level of bleeding with stator blade 26 and be fixed on the turbine rotor 7 being circumferentially with multi-disc, be provided with shroud 32 in the outer circumference end of movable vane 31.The inner peripheral surface 33 of shroud 32 forms, the mode that increases gradually downstream from the upstream with extended corner is to radially crooked sleekly, the angle that the tangent line F (being represented by dotted lines) of the downstream side front end of shroud inner peripheral surface 33 forms turbo machine central shaft 50, the angle that to be movable vane outlet spread angle alpha 3 form turbo machine central shaft 50 than the tangent line E (being represented by dotted lines) of the upstream side front end of shroud inner peripheral surface 33, promptly movable vane inlet spread angle alpha 2 is bigger.
In addition, with the inner peripheral surface 34 of outer circumferential side stationary wall 27 and turbo machine central shaft 50 angulations as movable vane upstream side spread angle alpha 1, with the upstream side sidewall of bleeding point 29 and turbo machine central shaft 50 angulations as movable vane downstream side spread angle alpha 4.In the present embodiment, the inner peripheral surface 33 of shroud 32 forms, movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 about equally, movable vane outlet spread angle alpha 3 and movable vane downstream side spread angle alpha 4 are about equally.
In addition, the outer circumferential face of shroud 32 is by the upstream side parallel surface that comprise upstream side parallel with turbo machine central shaft 50 37 and comprise the downstream side parallel surface 38 of downstream side, and turbo machine central shaft 50 constitutes to curved surface 39 radially crooked and that connect upstream side parallel surface 37 and downstream side parallel surface 38 relatively.In the present embodiment, by shroud upstream side external diameter is made the lightweight that the structure littler than downstream side external diameter realized shroud.
At the low-pressure turbine upstream stage,, on the inner peripheral surface of the outer circumferential side stationary wall 27 relative, dispose the sealing fin 6 that is provided with along extending circumferentially with upstream side parallel surface 37 and downstream side parallel surface 38 because the influence that the performance that is caused by the leakage of steam reduces is very big.In addition, at the sealing fin of outer circumferential side stationary wall the position being set is provided with the distance that is used between sealing fin 6 and the parallel surface and keeps certain step.By configuration sealing fin on the parallel surface of shroud outer circumferential face, though sealing fin 6 produces axial displacement with the position relation of shroud 32 because of the on-stream thermal expansion difference that is caused by high temperature, even both gaps can not change yet and can keep sealability in this case.
As shown in Figure 3, the part of the outer circumferential side in the air-flow that movable vane 31 flows out has radially composition, and its importing is bled in the runner 30.
Fig. 4 is the schematic representation that the level of bleeding of the upstream side of existing low-pressure turbine is axially shortening.Because it is little that the upstream stage of low-pressure turbine and downstream stage are compared length of blade, and big with respect to the length of blade seal clearance, therefore, compares its leakage loss with downstream stage and relatively increase.Therefore, be necessary to improve sealing effect to outlet configuration multi-disc sealing fin 6 from the inlet of movable vane 31.Yet, because the axial thermal expansion difference in the low-pressure turbine is big, thereby, being necessary to dispose shroud 41 abreast in order to keep radial clearance with turbo machine central shaft 50, the movable vane inlet extended corner of shroud 41 and movable vane outlet extended corner all are 0 degree.Because it is little that the upstream stage of low-pressure turbine and downstream stage are compared length of blade, peripheral velocity is little, thereby little at the flow velocity of blade front end, has again, owing to be the speedup stream of positive pressure gradient, thereby be difficult to produce and peel off.Yet the level of bleeding is provided with the runner 30 of bleeding in the steam flow channel periphery wall adjacency in downstream side, is used to make the part of steam to extraction.The length of axle is being done short occasion, movable vane outlet spread angle alpha 3 becomes big with the deviation of movable vane downstream side spread angle alpha 4, and, shorten the distance of movable vane outlet and bleeding point 29 in order to shorten a span.Therefore, between movable vane outlet and bleeding point 29 since steam with short axle span to radially turning to, thereby be not near generation separation vortex 42 bleeding point 29 sometimes.
On the other hand, return Fig. 3, in the present embodiment, owing to make following structure, that is: make the inner peripheral surface 33 of shroud 32 to radially crooked sleekly, thereby extended corner is increased downstream gradually from the upstream, make movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 and movable vane outlet spread angle alpha 3 and movable vane downstream side spread angle alpha 4 respectively about equally, therefore, between outlet, make flow of steam by inlet to radially turning at movable vane 2, can make flow of steam than bleeding point 29 more by upstream side to radially turning to, can suppress because in the reduction of peeling off the turbine efficiency that causes of the air-flow of the runner entrance part of bleeding and shorten the length of turbine shaft.
In addition, in the present embodiment, also preferably movable vane inlet spread angle alpha 2 and movable vane upstream side spread angle alpha 1 and movable vane outlet spread angle alpha 3 equates respectively with movable vane downstream side spread angle alpha 4, but as long as the deviation of extended corner about equally, promptly in 5 °, still can expect effect of the present invention.
In addition, with respect to Fig. 4 (b), shown in Fig. 4 (c) by from the outer circumferential face upstream extremity to downstream and the shroud that constitutes of the parallel surface of central axes, the shroud 32 of present embodiment is by making following structure, that is: outer circumferential face is by upstream side parallel surface and downstream side parallel surface, and constitute to curved surface radially crooked and that connect upstream side parallel surface and downstream side parallel surface, shroud downstream side external diameter is bigger than shroud upstream side external diameter, thereby, even strengthen the bending of shroud 32, the difference that is movable vane inlet spread angle alpha 2 and movable vane outlet spread angle alpha 3 strengthens, and also can suppress the increase of shroud own wt.Its result can prevent the reduction of the strength reliability of turbine bucket.
Below, the 4th mode of execution of the present invention is described.Fig. 5 is the figure that represents the bleed level and the structure of the major component of the runner of bleeding of observed from the side low-pressure turbine upstream side.In addition, omit its explanation for the label identical with the 3rd mode of execution identical construction element annotation.
Present embodiment and the 3rd mode of execution dissimilarity are the structure of shroud.The inner peripheral surface of the shroud 43 of present embodiment is made of upstream side inner peripheral surface 45 that comprises upstream extremity and the downstream side inner peripheral surface 46 that comprises downstream.In the present embodiment, the inner peripheral surface of shroud 43 also forms, upstream side inner peripheral surface 45 and turbo machine central shaft 50 angulations be movable vane inlet spread angle alpha 2 with the inner peripheral surface 33 of outer circumferential side stationary wall 27 and turbo machine central shaft 50 angulations be movable vane upstream side spread angle alpha 1 about equally, downstream side inner peripheral surface 46 and turbo machine central shaft 50 angulations be movable vane outlet spread angle alpha 3 with in abutting connection with the inner peripheral surface 36 of the outer circumferential side stationary wall 28 that is arranged on the downstream side and turbo machine central shaft 50 angulations be movable vane downstream side spread angle alpha 4 about equally, and movable vane outlet spread angle alpha 3 is bigger than movable vane inlet spread angle alpha 2.
On the other hand, the outer circumferential face 47 of shroud 43 is made of parallel surface parallel with turbo machine central shaft 50 from the upstream extremity to the downstream, is provided with sealing fin 6 on relative outer circumferential side stationary wall 27.
According to present embodiment, can obtain the effect identical with the 3rd mode of execution.In addition, the shroud 43 of present embodiment is hollow because of inside forms has realized lightweight.Thus, both can keep parallel between shroud outer circumferential face 47 and the outer circumferential side stationary wall, the weight that can suppress shroud self again increases.Its result can keep sealability and prevent the reduction of the strength reliability of turbine bucket.
Below, the 5th mode of execution of the present invention is described.Fig. 6 is the figure that represents the bleed level and the structure of the major component of the runner of bleeding in observed from the side low-pressure turbine downstream side.The portion of bleeding is identical with the 3rd mode of execution, is the shape of shroud, sealing fin is made and had and the first mode of execution identical construction with the 3rd mode of execution dissimilarity, and present embodiment also can obtain the effect identical with the 3rd mode of execution.
Claims (8)
1. the movable vane of a steam turbine possesses shroud at the outer circumferential side front end, it is characterized in that,
The inner peripheral surface of above-mentioned shroud forms,
Movable vane outlet extended corner is bigger than movable vane inlet extended corner,
Above-mentioned movable vane inlet extended corner with in abutting connection with the movable vane upstream side extended corner of the outer circumferential side stationary wall of the upstream side that is arranged on above-mentioned shroud about equally, and,
Above-mentioned movable vane outlet extended corner with in abutting connection with the movable vane downstream side extended corner of the above-mentioned outer circumferential side stationary wall in the downstream side that is arranged on above-mentioned shroud about equally.
2. the movable vane of steam turbine according to claim 1 is characterized in that,
The outer circumferential face of above-mentioned shroud has and comprises the downstream side front end and the face turbo machine central axes, and the distance between outer circumferential face upstream side front end and the turbo machine central shaft is littler than the distance between outer circumferential face downstream side front end and the turbo machine central shaft.
3. the movable vane of steam turbine according to claim 1 is characterized in that,
The outer circumferential face of above-mentioned shroud is made of the face with turbo machine central shaft almost parallel,
Above-mentioned shroud is hollow.
4. the movable vane of steam turbine according to claim 2 is characterized in that,
Above-mentioned movable vane constitutes the final level of low-pressure turbine.
5. the movable vane of steam turbine according to claim 3 is characterized in that,
Above-mentioned movable vane constitutes the level of bleeding that extracts the runner upstream side of bleeding of steam from steam flow channel in abutting connection with being arranged on.
6. a steam turbine has: turbine rotor; Be fixed on the movable vane on this turbine rotor; Be arranged on the shroud of this movable vane outer circumferential side front end; And above-mentioned turbine rotor wrapped in inside, and form the outer circumferential side stationary wall of the outer circumferential side flow path wall of steam flow channel, it is characterized in that,
The inner peripheral surface of above-mentioned shroud forms,
Movable vane outlet extended corner is bigger than movable vane inlet extended corner,
Above-mentioned movable vane inlet extended corner with in abutting connection with the movable vane upstream side extended corner of the above-mentioned outer circumferential side stationary wall of the upstream side that is arranged on above-mentioned movable vane about equally, and
Above-mentioned movable vane outlet extended corner with in abutting connection with the movable vane downstream side extended corner of the above-mentioned outer circumferential side stationary wall in the downstream side that is arranged on above-mentioned movable vane about equally.
7. steam turbine according to claim 6 is characterized in that,
The outer circumferential face of above-mentioned shroud has and comprises the downstream side front end and the face turbo machine central axes, and the distance between outer circumferential face upstream side front end and the turbo machine central shaft is littler than the distance between outer circumferential face downstream side front end and the turbo machine central shaft.
8. steam turbine according to claim 6 is characterized in that,
The outer circumferential face of above-mentioned shroud is made of the face with turbo machine central shaft almost parallel,
Above-mentioned shroud is hollow.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2009-062229 | 2009-03-16 | ||
| JP2009062229A JP2010216321A (en) | 2009-03-16 | 2009-03-16 | Moving blade of steam turbine, and steam turbine using the same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101839148A true CN101839148A (en) | 2010-09-22 |
Family
ID=41849497
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010115612A Pending CN101839148A (en) | 2009-03-16 | 2010-02-11 | Steam turbine rotor blade and corresponding steam turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20100232966A1 (en) |
| EP (1) | EP2236754A3 (en) |
| JP (1) | JP2010216321A (en) |
| CN (1) | CN101839148A (en) |
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| CN112352090B (en) * | 2018-07-13 | 2023-01-10 | 三菱重工业株式会社 | Guide plate, steam turbine, inner member, and method for manufacturing guide plate |
Also Published As
| Publication number | Publication date |
|---|---|
| US20100232966A1 (en) | 2010-09-16 |
| EP2236754A3 (en) | 2014-01-08 |
| JP2010216321A (en) | 2010-09-30 |
| EP2236754A2 (en) | 2010-10-06 |
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Application publication date: 20100922 |