CN103958949A - Sealing structure and rotating machine equipped with same - Google Patents
Sealing structure and rotating machine equipped with same Download PDFInfo
- Publication number
- CN103958949A CN103958949A CN201380003866.1A CN201380003866A CN103958949A CN 103958949 A CN103958949 A CN 103958949A CN 201380003866 A CN201380003866 A CN 201380003866A CN 103958949 A CN103958949 A CN 103958949A
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- CN
- China
- Prior art keywords
- recess
- guard shield
- sealing configuration
- epithelium
- side guard
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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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
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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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
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Abstract
The sealing structure (7) is provided with fins (40) that protrude from the outer circumferential surface of a rotor (5) along the circumferential direction (R), and stationary blades (30) on which an abradable film (60) is formed on the inner circumferential surface (50a) of the inner shroud (50) so as to face the fins (40), and depressions and protrusions are formed on the inner circumferential surface (50a) of the inner shroud (50) and the abradable film (60) is formed conforming to the depressions and protrusions.
Description
Technical field
The present invention relates to sealing configuration and possess the rotating machinery of sealing structure.
No. 2012-023071, the Japanese Patent Application of the application based on filing an application to Japan on February 6th, 2012 and advocate preference, and its content is incorporated herein.
Background technique
Conventionally, rotor in the rotating machineries such as steam turbine or gas turbine around, by making the gap between the Stationary side parts such as this rotor and stator blade minimum, and do one's utmost to reduce the leakage rate of fluid, the viewpoint that this performance from rotating machinery improves is most important.
Therefore, adopted a kind of sealing configuration, possessed: from the outer circumferential face of rotor along circumferential outstanding fin; To the high sealed member (with reference to following patent documentation 1) can wear material forming of the position spraying plating machinability relative with this fin of Stationary side parts.In such sealing configuration, even in the situation that during the rotation of rotor this rotor occurred to contact with Stationary side parts, by can wear material cutting also reducing the heating of contact position, thereby maintain the performance of rotating machinery.
At this, sealed member is the ring-shaped member along circumferential extension, and on side face, being formed with spraying plating within it can wear material and the worn away epithelium that forms.
[formerly technical paper]
[patent documentation]
No. 2009-174655, [patent documentation 1] TOHKEMY
Summary of the invention
[summary of invention]
[problem that invention will solve]
Yet, in the sealing configuration of recording at above-mentioned patent documentation 1, because needs arrange sealed member, therefore exist and manufacture more bothersome and processing charges rising and the surging such problem points of cost.
On the other hand, can consider sealed member to omit and technology from wear material to the direct spraying plating of Stationary side parts that can.
At this, when the rotation of rotor, at the inner side of adjacent stator blade guard shield, produce vertically each other shearing force, therefore can must bear this shearing force by wear material.Yet, can wear material because machinability is high, therefore exist be only to the direct spraying plating of stator blade can wear material because of this shearing force damaged, and then the possibility coming off from stator blade, the words of therefore merely carrying out spraying plating cannot be suitable for.
The present invention considers such situation and makes, even if the sealing configuration coming off that also can prevent in a kind of situation that can wear material produces damage that this can wear material is provided.
[solution]
According to first method of the present invention, sealing configuration is characterised in that to possess: fin, from the outer circumferential face of rotor along circumferentially outstanding; And stator blade, at the inner peripheral surface of inner side guard shield, in the mode relative with described fin, be formed with and can wear away epithelium, at the inner peripheral surface of described inner side guard shield, be formed with concaveconvex shape, the described epithelium that wears away forms along described concaveconvex shape.
In such sealing configuration, can wear away epithelium and form along concaveconvex shape, can enter this concaveconvex shape part and sclerosis deposited by wear material, so bonding area increase, can engage securely.Thus, even in the situation that can wearing away epithelium generation damage, engage securely because this can wear away epithelium, therefore can prevent that this from can wear away coming off of epithelium.
In the sealing configuration of first method of the present invention, can be that described concaveconvex shape consists of towards its inner recess forming the side the inner peripheral surface from described inner side guard shield and the described outer circumferential face that wears away epithelium.
In such sealing configuration, concaveconvex shape for example forms towards its inner recess forming by the inner peripheral surface from inner side guard shield.Thus, the inside that epithelium enters into recess can be worn away, therefore engaging force can be improved reliably.Thus, even in the situation that can wearing away epithelium generation damage, also can prevent that this from can wear away coming off of epithelium.
In the sealing configuration of first method of the present invention, can be that described recess forms in the mode along described circumferential extension.
In such sealing configuration, can upwards improve the engaging force that can wear away epithelium in week.Thus, even in the situation that can wearing away epithelium generation damage, also can prevent that this from can wear away coming off of epithelium.
In the sealing configuration of first method of the present invention, can be that the mode that described recess extends with the axial direction along described rotor forms.
In such sealing configuration, can improve in the axial direction the engaging force that can wear away epithelium.Thus, even in the situation that can wearing away epithelium generation damage, also can prevent that this from can wear away coming off of epithelium.
In the sealing configuration of first method of the present invention, can be that described recess is formed on along on described circumferential adjacent described inner side guard shield separatrix each other.
In such sealing configuration, on the separatrix of adjacent inner side guard shield, form recess, can make to wear away epithelium and enter this recess.Thus, when the shearing force producing between the inner side guard shield adjacent along this separatrix, can alleviate the shearing force of the amount entering that can wear away epithelium, therefore can prevent the distortion that the torsion of stator blade causes.
In the sealing configuration of first method of the present invention, can be, a side in the inner peripheral surface of described inner side guard shield and the described outer circumferential face that wears away epithelium, the described recess that forms with opposite side in inner peripheral surface at described inner side guard shield and the described outer circumferential face that wears away epithelium is relative and be formed with the second recess, and described sealing configuration possesses to the pin parts that insert between described recess and described the second recess.
In such sealing configuration, for example, when inner side shroud forms recess, by this recess with the chimeric of pin parts and engage the axial displacement that can reduce this inner side guard shield.And, by the second recess, can improve the engaging force that can wear away epithelium with engaging of pin parts.
In the sealing configuration of first method of the present invention, can be, described recess on the cross section of the bearing of trend quadrature with this recess, with the inner peripheral surface along with from described inner side guard shield or the described outer circumferential face that wears away epithelium towards the bottom of this recess and the mode that width broadens gradually form.
In such sealing configuration, can increase the bonding area that can wear away epithelium.And, power to the directive effect coming off in the time can wearing away epithelium, on the plane of inclination of the worn away epithelium that the face that forms in bottom with towards recess is corresponding, effect has resistance, therefore can engage more firmly.Thus, even in the situation that can wearing away epithelium generation damage, engage securely because this can wear away epithelium, therefore also can prevent that this from can wear away coming off of epithelium.
In the sealing configuration of first method of the present invention, can be that described recess, on the cross section of the bearing of trend quadrature with this recess, forms bloat from the inner peripheral surface of described inner side guard shield or the described outer circumferential face that wears away epithelium circular-arc.
In such sealing configuration, can increase the bonding area that can wear away epithelium, therefore can improve engaging force.
According to second method of the present invention, rotating machinery is characterised in that, possesses the sealing configuration that any one in above-mentioned is recorded.
According to this, form, due to the sealing configuration that any one possessing in above-mentioned is recorded, therefore can bring into play desired sealing function, even and in the situation that can wearing away epithelium damage occurs, also can prevent that this from can wear away coming off of epithelium.
[invention effect]
According to above-mentioned sealing configuration and possess the rotating machinery of sealing structure, can wear away epithelium enter concaveconvex shape part and harden, deposited, can engage securely thus.Therefore, even also can prevent that this from can wear away coming off of epithelium in the situation that can wearing away epithelium generation damage.
Accompanying drawing explanation
Fig. 1 is the sketch of the gas turbine (rotating machinery) of embodiments of the present invention.
Fig. 2 is the stereogram of the sealing configuration of embodiments of the present invention.
Fig. 3 means that the component parts of the sealing configuration of the first mode of execution of the present invention is the X-X sectional view of Fig. 1 of stator blade.
Fig. 4 means that the component parts of the sealing configuration of the second mode of execution of the present invention is the X-X sectional view of Fig. 1 of stator blade.
Fig. 5 means that the component parts of the sealing configuration of the 3rd mode of execution of the present invention is the X-X sectional view of Fig. 1 of stator blade.
Fig. 6 means that the component parts of the sealing configuration of the 4th mode of execution of the present invention is the X-X sectional view of Fig. 1 of stator blade.
Fig. 7 means that the component parts of the sealing configuration of the 5th mode of execution of the present invention is the X-X sectional view of Fig. 1 of stator blade.
Fig. 8 means that the component parts of the sealing configuration of the 6th mode of execution of the present invention is the Y-Y sectional view of Fig. 1 of stator blade.
Fig. 9 means that the component parts of the sealing configuration of the 7th mode of execution of the present invention is the Y-Y sectional view of Fig. 1 of stator blade.
Figure 10 means that the component parts of the sealing configuration of the 8th mode of execution of the present invention is the Y-Y sectional view of Fig. 1 of stator blade.
Figure 11 means that the component parts of the sealing configuration of the 8th mode of execution of the present invention is the sectional view of stator blade.
Embodiment
(the first mode of execution)
Below, with reference to accompanying drawing, the rotating machinery of the first mode of execution of the present invention is described.
About the first mode of execution of the present invention, with reference to Fig. 1, describe.Gas turbine (rotating machinery) 1 possesses: generate compressed-air actuated compressor 2; To the pressurized air fuel combination being generated by compressor 2 and make its burning and generate the burner 3 of combustion gas M; The combustion gas M being generated by burner 3 is rotated to the turbine 4 of driving as working fluid.
Rotor 5 is inserted through to compressor 2 and turbine 4.Compressor 2 has: for rotor 5, insert logical compressor housing 2a; The compressor moving vane 2b that can rotate together with rotor 5; Be fixed on the compressor stator blade 2c on compressor housing 2a.Compressor moving vane 2b and compressor stator blade 2c along circumferential R be arrange respectively radially a plurality of.Compressor moving vane 2b and compressor stator blade 2c vertically (axial direction) P are arranged alternately, and form respectively 1 grade, and arrange respectively multistage by a plurality of blades along circumferentially R arranges.And the air of suction circulates between compressor stator blade 2c, the rotation of the compressor moving vane 2b by downstream side and compressed, thereby by repeatedly carrying out above-mentioned action compressed generation pressurized air.
In addition, turbine 4 has: for rotor 5, insert logical turbine shroud 10; The turbine moving blade 20 that can rotate together with rotor 5; Be fixed on the turbine stator vane (stator blade) 30 on turbine shroud 10.Turbine moving blade 20 and turbine stator vane 30 radially Q extend, and along circumferential R be arrange respectively radially a plurality of.And turbine moving blade 20 and turbine stator vane 30 vertically P are arranged alternately, by a plurality of blades along circumferentially R arranges, form respectively 1 grade, and arrange respectively multistage.And, the combustion gas M as working fluid flowing into from burner 3 circulates between turbine stator vane 30, make turbine moving blade 20 rotations in downstream side, by repeatedly carrying out above-mentioned action, to the rotor 5 that is fixed with turbine moving blade 20, apply torque and make its rotation.
In addition, in order to prevent that combustion gas M from spilling and sealing configuration 7 being arranged a plurality of along axial P from high side to low side, below describes sealing structure 7 in detail.
As shown in Figure 2, sealing configuration 7 possesses: from the outstanding a plurality of fins 40 of the outer circumferential face of rotor 5; Turbine stator vane 30.
A plurality of fins 40 are from the outer circumferential face of rotor 5 along circumferentially R is outstanding, and devices spaced apart configuration on axial P.And fin 40 is using the outer circumferential face of this rotor 5 as base end part 40a, and with along with from this base end part 40a towards turbine stator vane 30 sides and the mode of its width of constriction forms front end 40b.So, a plurality of fin 40,40 ... towards axial P, alternately dispose base end part 40a, the front end 40b of a fin 40, base end part 40a, the front end 40b of adjacent fin 40 ...
Turbine stator vane 30 has: the inner side guard shield 50 that is arranged on rotor 5 sides; Be formed at the worn away epithelium 60 of this inner side guard shield 50; The blade body 70 radially extending from this inner side guard shield 50; The outboard shroud 80 arranging in the end of this blade body 70.
Inner side guard shield 50 is called as Z-type guard shield, Z-shaped from the shape that radially Q inner side is observed.And, inner side guard shield 50 for suppress from and adjacent inner side guard shield 50 between high-temperature gas leakage and suppress the torsion of blade body 70 and Z-shaped.
In addition, inner side guard shield 50 P configuration vertically, and configure with the edge mutual butt of inner side guard shield 50 that circumferentially R is adjacent.
In addition, as shown in Figure 3, at the inner peripheral surface 50a of inner side guard shield 50, be formed with concaveconvex shape.In the present embodiment, recess 51 with the inner peripheral surface 50a from inner side guard shield 50 towards the inside of inner peripheral surface 50a, in other words form along the mode that circumferentially R extends towards the outside of Q radially.
Recess 51 has: shroud base portion 51a; The pair of shields side wall portion 51b generally perpendicularly arranging from inner peripheral surface 50a; The shroud bottom 51c that this pair of shields side wall portion 51b is linked and generally perpendicularly arrange with guard shield side wall portion 51b.
In addition, in the present embodiment, can wear away epithelium 60 in the mode relative with fin 40 (with reference to Fig. 2), the inner peripheral surface 50a spraying plating of guard shield 50 to the inside can wear material and is formed.And, can wear away epithelium 60 and form along concaveconvex shape, in the present embodiment, can wear away epithelium 60 from the shroud base portion 51a spraying plating of recess 51 until shroud bottom 51c forms protuberance 61.
Protuberance 61 is outstanding towards the inside of inner side guard shield 50 from the outer circumferential face 60a that can wear away epithelium 60, have can wear away the 61a of side group portion, from outer circumferential face 60a, generally perpendicularly arrange a pair ofly wear away side wall portion 61b, this pair ofly worn away to the worn away side roof part 61c that side wall portion 61b links.
In addition, the shroud base portion 51a of recess 51 engages with the 61a of worn away side group portion of protuberance 61, the guard shield side wall portion 51b of recess 51 engages with the worn away side wall portion 61b of protuberance 61, and the shroud bottom 51c of recess 51 engages respectively with the worn away side roof part 61c of protuberance 61.
It should be noted that, as can wear material, can adopt for example nickel-base alloy.
As shown in Figure 2, blade body 70 is formed with the dorsal surface 72 that forms dorsal part by the facies ventralis 71 that forms veutro.
Facies ventralis 71 is crooked in the mode bloating towards dorsal surface 72 sides, and the mode that dorsal surface 72 bloats with the side towards identical with facies ventralis 71 is crooked.
Outboard shroud 80 and P vertically and the mutual butt of outboard shroud 80 that circumferentially R is adjacent and configure.
In the gas turbine 1 of sealing configuration 7 that possesses formation like this, can wear material as protuberance 61, enter in the recess 51 that is formed at inner side guard shield 50 and sclerosis deposited, therefore inner side guard shield 50 increases with the bonding area that can wear away epithelium 60.Thus, be accompanied by the increase of this bonding area and inner side guard shield 50 with can wear away epithelium 60 and engage securely.In addition, recess 51 forms in the mode along circumferentially R extends, and therefore can circumferentially on R, improve inner side guard shield 50 and the engaging force that can wear away epithelium 60.Therefore, though when making gas turbine 1 running in the situation that can wearing away epithelium 60 damage occur, also can prevent from wearing away epithelium 60 and peel off and situation about coming off from inner side guard shield 50.
In addition, in the present embodiment, can will be able to directly be located at inner side guard shield 50 by wear material.Thus, compare with structure in the past from wear material to the sealed member spraying plating of being located at inner side guard shield 50 that can, do not need sealed member, correspondingly can make rotor 5 and the distance of turbine stator vane 30 approach.Thus, as turbine 4 gas turbine 1 integral body even, can realize the miniaturization of equipment.
(the second mode of execution)
Below, about the gas turbine 201 of the second mode of execution of the present invention, use Fig. 4 to describe.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the sealing configuration 7 of the first mode of execution, the pair of shields side wall portion 51b of the recess 51 forming on inner side guard shield 50 is formed generally perpendicularly with respect to shroud base portion 51a.On the other hand, in the sealing configuration 207 of present embodiment, guard shield side wall portion 251b is formed generally perpendicularly with respect to shroud base portion 251a, but guard shield side wall portion 251d is acute angle with respect to shroud base portion 251a, forms.
That is, the recess 251 of inner side guard shield 250 on the cross section of the bearing of trend with recess 251 (circumferentially R) quadrature, with the inner peripheral surface 250a along with from inner side guard shield 250 towards the shroud bottom 251c of recess 251 and the mode that width broadens forms.In the present embodiment, guard shield side wall portion 251b is formed generally perpendicularly with respect to shroud base portion 251a, but guard shield side wall portion 251d is to form from the mode of relative guard shield side wall portion 251b separation along with 251c bottom shroud.Like this, on recess 251 and cross section bearing of trend (circumferentially R) quadrature, the width 261f of shroud bottom 251c broadens than the width 261e of the shroud base portion 251a of recess 251.
In addition, the protuberance 261 that can wear away epithelium 260 is shapes corresponding with recess 251, can wear away side wall portion 261d with along with forming from wearing away the mode of side wall portion 261b separation towards wearing away side roof part 261c.
In the gas turbine 201 of sealing configuration 207 that possesses formation like this, guard shield side wall portion 251d, can wear away side wall portion 261d and be obliquely installed, therefore can further increase inner side guard shield 250 and the bonding area that can wear away epithelium 260.And, power to the direction coming off radially Q inner side act on can wear away epithelium 260 time, have resistance can wear away on side wall portion 261d in order to prevent from coming off towards Q outside effect radially.Therefore thus, inner side guard shield 250 can be engaged more firmly with wearing away epithelium 260, even in the situation that can wearing away epithelium 260 damage occurs, also can prevent from wearing away epithelium 260 and peel off and situation about coming off from inner side guard shield 250.
(the 3rd mode of execution)
Below, about the gas turbine 301 of the 3rd mode of execution of the present invention, use Fig. 5 to describe.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the sealing configuration 207 of the second mode of execution, guard shield side wall portion 251b is formed generally perpendicularly with respect to shroud base portion 251a, and guard shield side wall portion 251d is acute angle with respect to shroud base portion 251a and forms.On the other hand, in the sealing configuration 307 of present embodiment, guard shield side wall portion 351b, 351d are all acute angle with respect to shroud base portion 351a and form.
That is, the recess 351 of inner side guard shield 350 on the cross section of the bearing of trend with recess 351 (circumferentially R) quadrature, with the inner peripheral surface 350a along with from inner side guard shield 350 towards the shroud bottom 351c of recess 351 and the mode that width broadens forms.In the present embodiment, guard shield side wall portion 351b, 351d form in the mode along with being separated from each other towards shroud bottom 351c.Like this, on recess 351 and cross section bearing of trend (circumferentially R) quadrature, the width 361f of shroud bottom 351c broadens than the width 361e of the shroud base portion 351a of recess 351.
In addition, the protuberance 361 that can wear away epithelium 360 is shapes corresponding with recess 351, can wear away side wall portion 361b, 361d and form in the mode along with being separated from each other towards wearing away side roof part 361c.
In the gas turbine 301 of sealing configuration 307 that possesses formation like this, guard shield side wall portion 351b, 351d, can wear away side wall portion 361b, 361d and be obliquely installed, therefore can further increase inner side guard shield 350 and the bonding area that can wear away epithelium 360.And, power to the direction coming off radially Q inner side act on can wear away epithelium 360 time, have resistance can wear away on side wall portion 361b, 361d all in order to prevent from coming off towards Q outside effect radially.Therefore thus, inner side guard shield 350 can be engaged more firmly with wearing away epithelium 360, even in the situation that can wearing away epithelium 360 damage occurs, also can prevent from wearing away epithelium 360 and peel off and situation about coming off from inner side guard shield 350.
(the 4th mode of execution)
Below, about the gas turbine 401 of the 4th mode of execution of the present invention, use Fig. 6 to describe.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the recess 51 of the inner side guard shield 50 of the sealing configuration 7 of the first mode of execution, shroud base portion 51a is substantially vertical with guard shield side wall portion 51b, and guard shield side wall portion 51b is also substantially vertical with shroud bottom 51c.On the other hand, the mode that the recess 451 of the sealing configuration 407 of present embodiment bloats with the inner peripheral surface 450a from inner side guard shield 450 in the cross section of the bearing of trend with recess 451 (circumferentially R) quadrature is circular-arcly and forms.
That is, the recess 451 of inner side guard shield 450 is the semi-circular shape bloating towards the inside of inner side guard shield 450 from inner peripheral surface 450a.
In addition, the protuberance 461 that can wear away epithelium 460 is shapes corresponding with recess 451, is the semi-circular shape bloating towards foreign side from outer circumferential face 460a.
In the gas turbine 401 of sealing configuration 407 that possesses formation like this, also can increase inner side guard shield 450 and the bonding area that can wear away epithelium 460, therefore can by inner side guard shield 450 with can wear away epithelium 460 and engage securely.
(the 5th mode of execution)
Below, about the gas turbine 501 of the 5th mode of execution of the present invention, use Fig. 7 to describe.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the sealing configuration 7 of the first mode of execution, recess 51 forms towards its inside from the inner peripheral surface 50a side of inner side guard shield 50.On the other hand, in the sealing configuration 507 of present embodiment, recess 561 forms towards its inside from wearing away the outer circumferential face 560a of epithelium 560.
That is, recess 561 has: can wear away the 561a of side group portion; The a pair of side wall portion 561b that wears away generally perpendicularly arranging from outer circumferential face 560a; By this pair of wear away that side wall portion 561b links and with the worn away side bottom 561c that can wear away side wall portion 561b and generally perpendicularly arrange.
In addition, protuberance 551 is shapes corresponding with recess 561, outstanding towards the inside that can wear away epithelium 560 from the inner peripheral surface 550a of inner side guard shield 550, there is inner side guard shield base portion 551a, the pair of shields side wall portion 551b generally perpendicularly arranging from inner peripheral surface 550a, this pair of shields side wall portion 551b to be linked shroud top 551c.
In the gas turbine 501 of sealing configuration 507 that possesses formation like this, also can increase inner side guard shield 550 and the bonding area that can wear away epithelium 560, therefore can by inner side guard shield 550 with can wear away epithelium 560 and engage securely.
In addition, as long as recess is optionally set at inner side guard shield 550 and the either party that can wear away in epithelium 560, and the opposing party, protuberance is set, the degrees of freedom therefore designing broadens.
(the 6th mode of execution)
Below, about the gas turbine 601 of the 6th mode of execution of the present invention, use Fig. 8 to describe.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the sealing configuration 7 of the first mode of execution, recess 51 forms in the mode of extending along circumferential R.On the other hand, in the sealing configuration 607 of present embodiment, recess 651 forms in the mode of extending along axial P.
That is, recess 651 is along the circumferential adjacent inner side guard shield 650,650 of R ... the radially Q inner side of separatrix 654 each other, along axial P and have compartment of terrain form a plurality of on circumferential R.
In addition, can wear away epithelium 660 enters the inside of recess 651 as protuberance 661 and forms.
In the gas turbine 601 of sealing configuration 607 that possesses formation like this, recess 651 forms in the mode of extending along axial P, therefore axially on P, can improve inner side guard shield 650 and the engaging force that can wear away epithelium 660.
In addition, at adjacent inner side guard shield 650,650 ... on separatrix 654 each other, producing this inner side guard shield 650,650 ... between shearing force time, can reduce can wear away epithelium 660 and as protuberance 661, enter into the shearing force of the amount in recess 651.Thus, the distortion that the torsion of turbine stator vane 630 causes can be prevented, the stability of gas turbine 601 self can be improved.
(the 7th mode of execution)
Below, about the gas turbine 701 of the 7th mode of execution of the present invention, use Fig. 9 to describe.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the sealing configuration 607 of the 6th mode of execution, recess 651 is formed on along the circumferential adjacent inner side guard shield 650,650 of R ... the radially Q inner side of separatrix 654 each other.On the other hand, in the sealing configuration 707 of present embodiment, recess 751 is formed in the size of inner side guard shield 750 axial P separately.
That is, recess 751 is in the substantial middle of the axial P size of inner side guard shield 750, has interval and form a plurality of along axial P and on circumferential R.
In the gas turbine 701 of sealing configuration 707 that possesses formation like this, recess 751 also forms in the mode of extending along axial P, therefore can axially on P, improve inner side guard shield 750 and the engaging force that can wear away epithelium 760.
(the 8th mode of execution)
Below, about the gas turbine 801 of the 8th mode of execution of the present invention, use Figure 10, Figure 11 to describe.
At this, Figure 10 is the Y-Y sectional view of Fig. 1 of the sealing configuration 807 of present embodiment, and Figure 11 dissects resulting sectional view by inner side guard shield 850 parts of sealing configuration 807.
In this embodiment, for the common parts of the parts with aforesaid mode of execution use, mark same label, the description thereof will be omitted.
In the sealing configuration 607 of the 6th mode of execution, recess 651 is only towards its inner structure forming from the inner peripheral surface 650a of inner side guard shield 650.On the other hand, in the sealing configuration 807 of present embodiment, recess has from the inner peripheral surface 850a of inner side guard shield 850 towards its inner recess 851 forming and the second recess 862 relative with this recess 851 and that form towards its inside from wearing away the outer circumferential face 860a of epithelium 860.And, to inserting pin parts 890 between recess 851 and the second recess 862.
That is, as shown in figure 10, recess 851 is the circumferential adjacent inner side guard shield 850,850 of R on edge ... the radially Q inner side of separatrix 854 each other, has interval and towards its inside, forms a plurality of from the inner peripheral surface 850a of inner side guard shield 850 along circumferential R.And as shown in figure 11, recess 851 is for an inner side guard shield 850, P has interval and forms 2 positions vertically.
It should be noted that, above-mentioned numerical value is an example, can be also 3 positions, is not defined as this numerical value.
In addition, as shown in figure 10, the second recess 862 is the circumferential adjacent inner side guard shield 850,850 of R on edge ... the radially Q inner side of separatrix 854 each other, has interval and towards its inside, forms a plurality of from wearing away the outer circumferential face 860a of epithelium 860 along circumferential R.And as shown in figure 11, the second recess 862 is for an inner side guard shield 850, P has interval and forms 2 positions vertically.
In addition, pin parts 890 are bar-like member, and one end 890a is disposed at the shroud bottom 851c of recess 851, and the other end 890b is disposed at the worn away side bottom 861c of the second recess 862.
In addition, as the manufacture method of sealing configuration 807, the recess 851 of guard shield 850 inserts pin parts 890 to the inside, and spraying plating can wear material and make pin parts 890 be fixed on recess 851, and forms and can wear away epithelium 860.
In so possessing the gas turbine 801 of sealing configuration 807, pin parts 890 are by adjacent inner side guard shield 850,850 ... circumferentially R combination securely of edge each other, and can reduce the displacement to axial P.
In addition, when spraying plating can wear material, the other end 890b of pin parts 890 is side-prominent, therefore can wear material deposited good, can form and can wear away epithelium 860.Thus, via pin parts 890 can by inner side guard shield 850 with can wear away epithelium 860 and engage securely.
It should be noted that, each shape of each component parts shown in the above-described embodiment or combination etc. are an example, without departing from the spirit and scope of the invention, based on designing requirement etc., can carry out various changes.
In addition, in the above-described embodiment, as an example of rotating machinery, enumerating gas turbine is that example is illustrated, but also goes for other the rotating machinery such as steam turbine.
[industrial applicibility]
According to above-mentioned sealing configuration and possess the rotating machinery of sealing structure, can wear away epithelium enter concaveconvex shape part and harden, deposited, can engage securely thus.Therefore, even also can prevent that this from can wear away coming off of epithelium in the situation that can wearing away epithelium generation damage.
[label declaration]
1,201,301,401,501,601,701,801 gas turbines (rotating machinery)
5 rotors
7,207,307,407,507,607,707,807 sealing configurations
30 turbine stator vanes (stator blade)
40 fins
50,250,350,450,550,650,750,850 inner side guard shields
50a, 250a, 350a, 550a, 650a, 850a inner peripheral surface
51,251,351,451,561,651,751,851 recesses
60,260,360,460,560,660,760,860 can wear away epithelium
60a, 260a, 360a, 560a, 860a outer circumferential face
654,854 separatrix
R is circumferential
Claims (9)
1. a sealing configuration, possesses:
Fin, from the outer circumferential face of rotor along circumferentially outstanding;
And stator blade, at the inner peripheral surface of inner side guard shield, in the mode relative with described fin, be formed with and can wear away epithelium,
Inner peripheral surface at described inner side guard shield is formed with concaveconvex shape, and the described epithelium that wears away forms along described concaveconvex shape.
2. sealing configuration according to claim 1, wherein,
Described concaveconvex shape consists of towards its inner recess forming the side the inner peripheral surface from described inner side guard shield and the described outer circumferential face that wears away epithelium.
3. sealing configuration according to claim 2, wherein,
Described recess forms in the mode along described circumferential extension.
4. sealing configuration according to claim 2, wherein,
The mode that described recess extends with the axial direction along described rotor forms.
5. sealing configuration according to claim 3, wherein,
Described recess is formed on along on described circumferential adjacent described inner side guard shield separatrix each other.
6. sealing configuration according to claim 4, wherein,
A side in the inner peripheral surface of described inner side guard shield and the described outer circumferential face that wears away epithelium, the described recess that forms with opposite side in inner peripheral surface at described inner side guard shield and the described outer circumferential face that wears away epithelium is relative and be formed with the second recess,
Described sealing configuration possesses to the pin parts that insert between described recess and described the second recess.
7. according to the sealing configuration described in any one in claim 3～5, wherein,
Described recess on the cross section of the bearing of trend quadrature with this recess, with the inner peripheral surface along with from described inner side guard shield or the described outer circumferential face that wears away epithelium towards the bottom of this recess and the mode that width broadens gradually form.
8. according to the sealing configuration described in any one in claim 2～5, wherein,
Described recess, on the cross section of the bearing of trend quadrature with this recess, forms bloat from the inner peripheral surface of described inner side guard shield or the described outer circumferential face that wears away epithelium circular-arc.
9. a rotating machinery, it possesses the sealing configuration described in any one in claim 1～7.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2012023071A JP5308548B2 (en) | 2012-02-06 | 2012-02-06 | Seal structure and rotary machine equipped with the same |
| JP2012-023071 | 2012-02-06 | ||
| PCT/JP2013/052564 WO2013118701A1 (en) | 2012-02-06 | 2013-02-05 | Sealing structure and rotating machine equipped with same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103958949A true CN103958949A (en) | 2014-07-30 |
| CN103958949B CN103958949B (en) | 2016-03-16 |
Family
ID=48947464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380003866.1A Expired - Fee Related CN103958949B (en) | 2012-02-06 | 2013-02-05 | Sealing configuration and possess the rotating machinery of sealing structure |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US20130216362A1 (en) |
| EP (1) | EP2813736B1 (en) |
| JP (1) | JP5308548B2 (en) |
| KR (1) | KR101600732B1 (en) |
| CN (1) | CN103958949B (en) |
| IN (1) | IN2014MN00911A (en) |
| WO (1) | WO2013118701A1 (en) |
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|---|---|---|---|---|
| JPH1018016A (en) * | 1996-07-08 | 1998-01-20 | Suzuki Motor Corp | Wear resistant member and treatment of surface thereof |
| US6457939B2 (en) * | 1999-12-20 | 2002-10-01 | Sulzer Metco Ag | Profiled surface used as an abradable in flow machines |
| JP2005214148A (en) * | 2004-01-30 | 2005-08-11 | Ishikawajima Harima Heavy Ind Co Ltd | Engine parts and coating method |
| JP2006132328A (en) * | 2004-11-02 | 2006-05-25 | Toshiba Corp | Shaft sealing mechanism and rotary machine |
| FR2895021A1 (en) * | 2005-12-16 | 2007-06-22 | Snecma Sa | Turbomachine e.g. low pressure turbine, for aircraft`s jet engine, has rotor composed of disks that are reunited by annular connecting part, and sealing unit arranged between blades of each disks and crown of diffuser blade |
| CN101765736A (en) * | 2008-01-25 | 2010-06-30 | 三菱重工业株式会社 | Seal structure |
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|---|---|---|---|---|
| US5439348A (en) * | 1994-03-30 | 1995-08-08 | United Technologies Corporation | Turbine shroud segment including a coating layer having varying thickness |
| JPH08135403A (en) * | 1994-11-14 | 1996-05-28 | Mitsubishi Heavy Ind Ltd | Gas turbine stationary blade |
| JP3477347B2 (en) * | 1997-07-30 | 2003-12-10 | 三菱重工業株式会社 | Gas turbine interstage seal device |
| DE10334698A1 (en) * | 2003-07-25 | 2005-02-10 | Rolls-Royce Deutschland Ltd & Co Kg | Shroud segment for a turbomachine |
| JP5411569B2 (en) * | 2009-05-01 | 2014-02-12 | 株式会社日立製作所 | Seal structure and control method |
| US8172519B2 (en) * | 2009-05-06 | 2012-05-08 | General Electric Company | Abradable seals |
| EP2336572B1 (en) * | 2009-12-14 | 2012-07-25 | Techspace Aero S.A. | Shroud or section of shroud in two parts for a vane diffuser of an axial compressor |
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2012
- 2012-02-06 JP JP2012023071A patent/JP5308548B2/en not_active Expired - Fee Related
-
2013
- 2013-02-04 US US13/758,158 patent/US20130216362A1/en not_active Abandoned
- 2013-02-05 IN IN911MUN2014 patent/IN2014MN00911A/en unknown
- 2013-02-05 WO PCT/JP2013/052564 patent/WO2013118701A1/en active Application Filing
- 2013-02-05 EP EP13746796.5A patent/EP2813736B1/en not_active Not-in-force
- 2013-02-05 KR KR1020147014047A patent/KR101600732B1/en active IP Right Grant
- 2013-02-05 CN CN201380003866.1A patent/CN103958949B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1018016A (en) * | 1996-07-08 | 1998-01-20 | Suzuki Motor Corp | Wear resistant member and treatment of surface thereof |
| US6457939B2 (en) * | 1999-12-20 | 2002-10-01 | Sulzer Metco Ag | Profiled surface used as an abradable in flow machines |
| JP2011185272A (en) * | 1999-12-20 | 2011-09-22 | Sulzer Metco Ag | Profiled surface used as abradable coating in fluid machine |
| JP2005214148A (en) * | 2004-01-30 | 2005-08-11 | Ishikawajima Harima Heavy Ind Co Ltd | Engine parts and coating method |
| JP2006132328A (en) * | 2004-11-02 | 2006-05-25 | Toshiba Corp | Shaft sealing mechanism and rotary machine |
| FR2895021A1 (en) * | 2005-12-16 | 2007-06-22 | Snecma Sa | Turbomachine e.g. low pressure turbine, for aircraft`s jet engine, has rotor composed of disks that are reunited by annular connecting part, and sealing unit arranged between blades of each disks and crown of diffuser blade |
| CN101765736A (en) * | 2008-01-25 | 2010-06-30 | 三菱重工业株式会社 | Seal structure |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2813736B1 (en) | 2016-11-30 |
| WO2013118701A1 (en) | 2013-08-15 |
| EP2813736A4 (en) | 2015-11-25 |
| CN103958949B (en) | 2016-03-16 |
| JP5308548B2 (en) | 2013-10-09 |
| IN2014MN00911A (en) | 2015-04-17 |
| JP2013160313A (en) | 2013-08-19 |
| US20130216362A1 (en) | 2013-08-22 |
| EP2813736A1 (en) | 2014-12-17 |
| KR20140083048A (en) | 2014-07-03 |
| KR101600732B1 (en) | 2016-03-07 |
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Address after: Kanagawa Prefecture, Japan Patentee after: Mitsubishi Power Co.,Ltd. Address before: Kanagawa Prefecture, Japan Patentee before: MITSUBISHI HEAVY INDUSTRIES, Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160316 Termination date: 20220205 |