CN103958949B - Sealing configuration and possess the rotating machinery of sealing structure - Google Patents
Sealing configuration and possess the rotating machinery of sealing structure Download PDFInfo
- Publication number
- CN103958949B CN103958949B CN201380003866.1A CN201380003866A CN103958949B CN 103958949 B CN103958949 B CN 103958949B CN 201380003866 A CN201380003866 A CN 201380003866A CN 103958949 B CN103958949 B CN 103958949B
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- China
- Prior art keywords
- recess
- epithelium
- guard shield
- side guard
- peripheral surface
- 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.)
- Expired - Fee Related
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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
-
- 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 feature of this sealing configuration (7) is to possess: fin (40), from the outer circumferential face of rotor (5) circumferentially (R) give prominence to; And stator blade (30), inner peripheral surface (50a) in inner side guard shield (50) is formed in the mode relative with described fin (40) can wear away epithelium (60), be formed with concaveconvex shape at the inner peripheral surface (50a) of described inner side guard shield (50), the described epithelium (60) that wears away is formed along described concaveconvex shape.
Description
Technical field
The present invention relates to sealing configuration and possess the rotating machinery of sealing structure.
Its content based on No. 2012-023071, the Japanese Patent Application of filing an application to Japan on February 6th, 2012 and CLAIM OF PRIORITY, and is incorporated herein by the application.
Background technique
Usually, around rotor in the rotating machinery such as steam turbine or gas turbine, by making the gap between these Stationary side such as rotor and stator blade parts minimum, and do one's utmost the leakage rate reducing fluid, the viewpoint that this performance from rotating machinery improves is most important.
Therefore, have employed a kind of sealing configuration, possess: the fin circumferentially given prominence to from the outer circumferential face of rotor; What the position spraying plating machinability relative with this fin to Stationary side parts was high can the sealed member (with reference to following patent documentation 1) of wear material.In such sealing configuration, even if this rotor and Stationary side parts there occurs when contacting when the rotation of rotor, by the heating that also can reduce contact position can be cut by wear material, thus maintain the performance of rotating machinery.
At this, sealed member is the ring-shaped member circumferentially extended, and side face being formed with spraying plating within it can wear material and the worn away epithelium formed.
[at first technical paper]
[patent documentation]
No. 2009-174655, [patent documentation 1] Japanese Unexamined Patent Publication
Summary of the invention
[summary of invention]
[inventing the problem that will solve]
But, in the sealing configuration that above-mentioned patent documentation 1 is recorded, 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, sealed member can be considered to omit and can the technology of wear material to the direct spraying plating of Stationary side parts.
At this, when the rotation of rotor, produce shearing force vertically each other at the inner side guard shield of adjacent stator blade, therefore can must bear this shearing force by wear material.But, can wear material high due to machinability, therefore exist be only to the direct spraying plating of stator blade can wear material damaged because of this shearing force, and then from the possibility that stator blade comes off, the words of therefore merely carrying out spraying plating cannot be suitable for.
The present invention considers such situation and makes, and can also can prevent when producing damage this can the sealing configuration come off of wear material by wear material even if provide a kind of.
[solution]
According to the 1st aspect of the present invention, the feature of sealing configuration is to possess: fin, circumferentially gives prominence to from the outer circumferential face of rotor; And stator blade, be formed at the inner peripheral surface of inner side guard shield can wear away epithelium in the mode relative with described fin, be formed with concaveconvex shape at the inner peripheral surface of described inner side guard shield, the described epithelium that wears away is formed along described concaveconvex shape.
In such sealing configuration, can wear away epithelium and be formed along concaveconvex shape, can enter this concaveconvex shape part and harden and deposition by wear material, therefore bonding area increases, and can engage securely.Thus, even if when epithelium can be worn away, and damage occurs, engage securely because this can wear away epithelium, therefore, it is possible to prevent this from can wear away coming off of epithelium.
In the sealing configuration of the 1st aspect of the present invention, Ke Yishi, described concaveconvex shape is consisted of the recess formed towards its inside from inner peripheral surface and the described side worn away in the outer circumferential face of epithelium of described inner side guard shield.
In such sealing configuration, concaveconvex shape is such as formed towards its inner recess formed by the inner peripheral surface from inner side guard shield.Thus, the inside that epithelium enters into recess can be worn away, therefore, it is possible to reliably improve engaging force.Thus, even if when epithelium can be worn away, and damage occurs, also can prevent this from can wear away coming off of epithelium.
In the sealing configuration of the 1st aspect of the present invention, Ke Yishi, described recess is formed in the mode extended along described circumference.
In such sealing configuration, the engaging force that can wear away epithelium can be improved in the circumferential.Thus, even if when epithelium can be worn away, and damage occurs, also can prevent this from can wear away coming off of epithelium.
In the sealing configuration of the 1st aspect of the present invention, Ke Yishi, described recess is formed in the mode extended along the axial direction of described rotor.
In such sealing configuration, the engaging force that can wear away epithelium can be improved in the axial direction.Thus, even if when epithelium can be worn away, and damage occurs, also can prevent this from can wear away coming off of epithelium.
In the sealing configuration of the 1st aspect of the present invention, Ke Yishi, described recess is formed in along on the adjacent described inner side guard shield of described circumference separatrix each other.
In such sealing configuration, the separatrix of adjacent inner side guard shield forms recess, can make to wear away epithelium and enter this recess.Thus, when producing the shearing force between the inner side guard shield adjacent along this separatrix, the shearing force of the amount entered that can wear away epithelium can be alleviated, therefore, it is possible to prevent the distortion that the torsion of stator blade causes.
In the sealing configuration of the 1st aspect of the present invention, can be, in inner peripheral surface and the described side worn away in the outer circumferential face of epithelium of described inner side guard shield, relative with the described recess that inner peripheral surface and the described opposite side worn away in the outer circumferential face of epithelium at described inner side guard shield is formed and be formed with the second recess, described sealing configuration possesses the pin parts to inserting between described recess and described second recess.
Such as, in such sealing configuration, when inner side shroud forms recess, by the Qian He of this recess and pin parts and engage the axial displacement that can reduce guard shield inside this.And, the engaging force that can wear away epithelium can be improved by the joint of the second recess and pin parts.
In the sealing configuration of the 1st aspect of the present invention, can be, described recess on the cross section orthogonal with the bearing of trend of this recess, with along with from the inner peripheral surface of described inner side guard shield or the described outer circumferential face wearing away epithelium towards the bottom of this recess and the mode that width broadens gradually formed.
In such sealing configuration, the bonding area that can wear away epithelium can be increased.And, power to act on to the direction come off can wear away epithelium time, the plane of inclination of the worn away epithelium corresponding with the face that the bottom towards recess is formed acts on resistance, therefore, it is possible to engage more firmly.Thus, even if when epithelium can be worn away, and damage occurs, engage securely because this can wear away epithelium, therefore also can prevent this from can wear away coming off of epithelium.
In the sealing configuration of the 1st aspect of the present invention, Ke Yishi, described recess, on the cross section orthogonal with the bearing of trend of this recess, is formed as the arc-shaped bloated from inner peripheral surface or the described outer circumferential face wearing away epithelium of described inner side guard shield.
In such sealing configuration, the bonding area that can wear away epithelium can be increased, therefore, it is possible to improve engaging force.
According to the 2nd aspect of the present invention, the feature of rotating machinery is, possess above-mentioned in any one record sealing configuration.
According to this formation, due to possess above-mentioned in any one record sealing configuration, therefore, it is possible to play desired by sealing function, even and if when can wear away epithelium occur damage, also can prevent this from can wear away coming off of epithelium.
[invention effect]
According to above-mentioned sealing configuration and the rotating machinery possessing sealing structure, can wear away epithelium enter concaveconvex shape part and harden, deposition, can engage securely thus.Therefore, even if also can prevent this from can wear away coming off of epithelium when epithelium can be worn away, and damage occurs.
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 represents the component parts of sealing configuration of the first mode of execution of the present invention and the X-X sectional view of Fig. 1 of stator blade.
Fig. 4 represents the component parts of sealing configuration of the second mode of execution of the present invention and the X-X sectional view of Fig. 1 of stator blade.
Fig. 5 represents the component parts of sealing configuration of the 3rd mode of execution of the present invention and the X-X sectional view of Fig. 1 of stator blade.
Fig. 6 represents the component parts of sealing configuration of the 4th mode of execution of the present invention and the X-X sectional view of Fig. 1 of stator blade.
Fig. 7 represents the component parts of sealing configuration of the 5th mode of execution of the present invention and the X-X sectional view of Fig. 1 of stator blade.
Fig. 8 represents the component parts of sealing configuration of the 6th mode of execution of the present invention and the Y-Y sectional view of Fig. 1 of stator blade.
Fig. 9 represents the component parts of sealing configuration of the 7th mode of execution of the present invention and the Y-Y sectional view of Fig. 1 of stator blade.
Figure 10 represents the component parts of sealing configuration of the 8th mode of execution of the present invention and the Y-Y sectional view of Fig. 1 of stator blade.
Figure 11 is the component parts of sealing configuration and the sectional view of stator blade that represent the 8th mode of execution of the present invention.
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, be described with reference to Fig. 1.Gas turbine (rotating machinery) 1 possesses: generate compressed-air actuated compressor 2; Make it burn to the pressurized air fuel combination generated by compressor 2 and generate the burner 3 of combustion gas M; The combustion gas M generated by burner 3 is carried out the turbine 4 of rotary actuation as working fluid.
Rotor 5 is inserted through compressor 2 and turbine 4.Compressor 2 has: the compressor housing 2a inserted for rotor 5; 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 circumferentially R radially arranges multiple respectively.Compressor moving vane 2b and compressor stator blade 2c vertically (axial direction) P is arranged alternately, and forms 1 grade respectively, and arrange multistage respectively by multiple blades that circumferentially R is arranged.Further, the air of suction circulates between compressor stator blade 2c, is compressed, compressed by repeatedly carrying out above-mentioned action thus generate pressurized air by the rotation of the compressor moving vane 2b in downstream side.
In addition, turbine 4 has: the turbine shroud 10 inserted for rotor 5; 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 circumferentially R radially arranges multiple respectively.And turbine moving blade 20 and turbine stator vane 30 vertically P are arranged alternately, form 1 grade respectively by multiple blades that circumferentially R is arranged, and arrange multistage respectively.And, the combustion gas M as working fluid flowed into from burner 3 circulates between turbine stator vane 30, the turbine moving blade 20 in downstream side is rotated, applies torque to the rotor 5 being fixed with turbine moving blade 20 by repeatedly carrying out above-mentioned action and make it rotate.
In addition, in order to prevent combustion gas M from high side to low side spill and by sealing configuration 7 axially P arrange multiple, below describe sealing structure 7 in detail.
As shown in Figure 2, sealing configuration 7 possesses: from multiple fins 40 that the outer circumferential face of rotor 5 is outstanding; Turbine stator vane 30.
Multiple fin 40 from the outer circumferential face of rotor 5 circumferentially R give prominence to, and configuration spaced apart on axial P.And, fin 40 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 side, the mode of its width of constriction forms front end 40b.So, multiple fin 40,40 ... base end part 40a, front end 40b, the base end part 40a of adjacent fin 40, the front end 40b of a fin 40 is alternately configured with towards axial P ...
Turbine stator vane 30 has: the inner side guard shield 50 being arranged on rotor 5 side; Be formed at the worn away epithelium 60 of guard shield 50 inside this; The blade body 70 that guard shield 50 radially extends inside this; The outboard shroud 80 arranged in the end of this blade body 70.
Inner side guard shield 50 is called as Z-type guard shield, and the shape observed inside radial Q is Z-shaped.And inner side guard shield 50 is in order to suppress the leakage from the high-temperature gas between adjacent inner side guard shield 50 and suppress the torsion of blade body 70 and Z-shaped.
In addition, inner side guard shield 50 P configuration vertically, and the inner side guard shield 50 adjacent with circumferentially R mutually abuts and configures.
In addition, as shown in Figure 3, concaveconvex shape is formed with at the inner peripheral surface 50a of inner side guard shield 50.In the present embodiment, recess 51 with from the inner peripheral surface 50a of inner side guard shield 50 towards the inside of inner peripheral surface 50a, mode that in other words circumferentially R extends outside radial Q formed.
Recess 51 has: shroud base portion 51a; From the pair of shields sidewall portion 51b that inner peripheral surface 50a is generally perpendicularly arranged; This pair of shields sidewall portion 51b is linked and 51c bottom the shroud generally perpendicularly arranged with shroud 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 can wear material and being formed to the inside.And, epithelium 60 can be worn away and formed along concaveconvex shape, in the present embodiment, epithelium 60 can be worn away from the shroud base portion 51a spraying plating of recess 51 until 51c bottom shroud, form protuberance 61.
Protuberance 61 is given prominence to from the outer circumferential face 60a that can wear away epithelium 60 towards the inside of inner side guard shield 50, has the worn away side roof part 61c that can wear away sidewall portion 61b for a pair, this pair can be worn away sidewall portion 61b link that can wear away side base portion 61a, generally perpendicularly arrange from outer circumferential face 60a.
In addition, the shroud base portion 51a of recess 51 engages with the worn away side base portion 61a of protuberance 61, the shroud wall portion 51b of recess 51 engages with the worn away sidewall portion 61b of protuberance 61, and bottom the shroud of recess 51,51c engages respectively with the worn away side roof part 61c of protuberance 61.
It should be noted that, as can wear material, such as nickel-base alloy can be adopted.
As shown in Figure 2, blade body 70 is formed with the dorsal surface 72 forming dorsal part by the facies ventralis 71 forming veutro.
Facies ventralis 71 bends in the mode bloated towards dorsal surface 72 side, and dorsal surface 72 bends in the mode bloated towards the side identical with facies ventralis 71.
The outboard shroud 80 that outboard shroud 80 is adjacent with P and circumferential R vertically mutually abuts and configures.
In the gas turbine 1 possessing the sealing configuration 7 so formed, can wear material enter into as protuberance 61 be formed at inner side guard shield 50 recess 51 in and harden and deposition, therefore inner side guard shield 50 and the bonding area that can wear away epithelium 60 increase.Thus, along with the increase of this bonding area inner side guard shield 50 with can wear away epithelium 60 and engage securely.In addition, recess 51 is formed in the mode that circumferentially R extends, therefore, it is possible to improve inner side guard shield 50 and the engaging force that can wear away epithelium 60 on circumferential R.Therefore, even if when making gas turbine 1 operate when epithelium 60 can be worn away, and damage occurs, also can prevent from wearing away epithelium 60 and peeling off from inner side guard shield 50 and situation about coming off.
In addition, in the present embodiment, inner side guard shield 50 can will can be directly located at by wear material.Thus, compared with the structure in the past of wear material, sealed member can not needed with to the sealed member spraying plating being located at inner side guard shield 50, rotor 5 correspondingly can be made close with the distance of turbine stator vane 30.Thus, as turbine 4, even gas turbine 1 is overall, 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, Fig. 4 is used to be described.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, mark same label, the description thereof will be omitted.
In the sealing configuration 7 of the first mode of execution, the pair of shields sidewall portion 51b of the recess 51 that inner side guard shield 50 is formed is formed generally perpendicularly relative to shroud base portion 51a.On the other hand, in the sealing configuration 207 of present embodiment, shroud wall portion 251b is formed generally perpendicularly relative to shroud base portion 251a, but shroud wall portion 251d relative to shroud base portion 251a be acute angle formed.
That is, the recess 251 of inner side guard shield 250 is on the cross section that the bearing of trend (circumferential R) with recess 251 is orthogonal, with along with from the inner peripheral surface 250a of inner side guard shield 250 bottom the shroud of recess 251 251c and the mode that width broadens formed.In the present embodiment, shroud wall portion 251b is formed generally perpendicularly relative to shroud base portion 251a, but shroud wall portion 251d with along with bottom shroud 251c and from relative shroud wall portion 251b be separated mode formed.Like this, on the cross section orthogonal with bearing of trend (circumferential R) of recess 251, bottom shroud, the width 261f of 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 sidewall portion 261d to be formed from the mode that can wear away sidewall portion 261b separation along with towards wearing away side roof part 261c.
In the gas turbine 201 possessing the sealing configuration 207 so formed, shroud wall portion 251d, sidewall portion 261d can be worn away be obliquely installed, therefore, it is possible to increase inner side guard shield 250 and the bonding area that can wear away epithelium 260 further.And, power act on inside the direction come off and radial Q can wear away epithelium 260 time, have resistance effect outside radial Q can be worn away on sidewall portion 261d to prevent from coming off.Thereby, it is possible to by inner side guard shield 250 with can wear away epithelium 260 and engage more firmly, even if therefore when epithelium 260 can be worn away, and damage occurs, also can prevent from wearing away epithelium 260 and peel off from inner side guard shield 250 and situation about coming off.
(the 3rd mode of execution)
Below, about the gas turbine 301 of the 3rd mode of execution of the present invention, Fig. 5 is used to be described.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, mark same label, the description thereof will be omitted.
In the sealing configuration 207 of the second mode of execution, shroud wall portion 251b is formed generally perpendicularly relative to shroud base portion 251a, shroud wall portion 251d relative to shroud base portion 251a be acute angle formed.On the other hand, in the sealing configuration 307 of present embodiment, shroud wall portion 351b, 351d all relative to shroud base portion 351a be acute angle formed.
That is, the recess 351 of inner side guard shield 350 is on the cross section that the bearing of trend (circumferential R) with recess 351 is orthogonal, with along with from the inner peripheral surface 350a of inner side guard shield 350 bottom the shroud of recess 351 351c and the mode that width broadens formed.In the present embodiment, shroud wall portion 351b, 351d with along with bottom shroud 351c and the mode be separated from each other formed.Like this, on the cross section orthogonal with bearing of trend (circumferential R) of recess 351, bottom shroud, the width 361f of 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 sidewall portion 361b, 361d to be formed along with the mode be separated from each other towards wearing away side roof part 361c.
In the gas turbine 301 possessing the sealing configuration 307 so formed, shroud wall portion 351b, 351d, sidewall portion 361b, 361d can be worn away be obliquely installed, therefore, it is possible to increase inner side guard shield 350 and the bonding area that can wear away epithelium 360 further.And, power act on inside the direction come off and radial Q can wear away epithelium 360 time, can to wear away on sidewall portion 361b, 361d all in order to prevent from coming off outside radial Q effect have resistance.Thereby, it is possible to by inner side guard shield 350 with can wear away epithelium 360 and engage more firmly, even if therefore when epithelium 360 can be worn away, and damage occurs, also can prevent from wearing away epithelium 360 and peel off from inner side guard shield 350 and situation about coming off.
(the 4th mode of execution)
Below, about the gas turbine 401 of the 4th mode of execution of the present invention, Fig. 6 is used to be described.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, 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, 51a is substantially vertical with shroud wall portion 51b for shroud base portion, and shroud wall portion 51b is also substantially vertical with 51c bottom shroud.On the other hand, the recess 451 of the sealing configuration 407 of present embodiment in the cross section that the bearing of trend (circumferential R) with recess 451 is orthogonal with the mode bloated from the inner peripheral surface 450a of inner side guard shield 450 be arc-shaped formed.
That is, the recess 451 of inner side guard shield 450 is in the semi-circular shape bloated 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, in the semi-circular shape bloated from outer circumferential face 460a towards foreign side.
In the gas turbine 401 possessing the sealing configuration 407 so formed, also can increase inner side guard shield 450 and the bonding area that can wear away epithelium 460, therefore, it is possible to 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, Fig. 7 is used to be described.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, mark same label, the description thereof will be omitted.
In the sealing configuration 7 of the first mode of execution, recess 51 is formed from the inner peripheral surface 50a side of inner side guard shield 50 towards its inside.On the other hand, in the sealing configuration 507 of present embodiment, recess 561 is from wearing away the outer circumferential face 560a of epithelium 560 towards its inner formation.
That is, recess 561 has: can wear away side base portion 561a; What generally perpendicularly arrange from outer circumferential face 560a can wear away sidewall portion 561b for a pair; This pair can be worn away sidewall portion 561b link and with the worn away side bottom 561c that can wear away sidewall portion 561b and generally perpendicularly arrange.
In addition, protuberance 551 is shapes corresponding with recess 561, the pair of shields sidewall portion 551b give prominence to 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, generally perpendicularly arranging from inner peripheral surface 550a, the shroud top 551c that this pair of shields sidewall portion 551b is linked.
In the gas turbine 501 possessing the sealing configuration 507 so formed, also can increase inner side guard shield 550 and the bonding area that can wear away epithelium 560, therefore, it is possible to by inner side guard shield 550 with can wear away epithelium 560 and engage securely.
In addition, as long as optionally arrange recess at inner side guard shield 550 and either party that can wear away in epithelium 560, and arrange protuberance the opposing party, the degrees of freedom therefore designed broadens.
(the 6th mode of execution)
Below, about the gas turbine 601 of the 6th mode of execution of the present invention, Fig. 8 is used to be described.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, mark same label, the description thereof will be omitted.
In the sealing configuration 7 of the first mode of execution, recess 51 is formed in the mode that circumferentially R extends.On the other hand, in the sealing configuration 607 of present embodiment, recess 651 is formed in the mode that axially P extends.
That is, recess 651 is at the adjacent inner side guard shield 650,650 of circumferentially R ... inside the radial Q of separatrix 654 each other, axially P and there is compartment of terrain on circumferential R formed multiple.
In addition, epithelium 660 can be worn away enter the inside of recess 651 as protuberance 661 and formed.
In the gas turbine 601 possessing the sealing configuration 607 so formed, recess 651 is formed in the mode that axially P extends, and therefore can improve inner side guard shield 650 and the engaging force that can wear away epithelium 660 on axial P.
In addition, at adjacent inner side guard shield 650,650 ... on separatrix 654 each other, producing guard shield 650,650 inside this ... between shearing force time, can reduce and can wear away epithelium 660 enters into the amount in recess 651 shearing force as protuberance 661.Thereby, it is possible to prevent the distortion that the torsion of turbine stator vane 630 causes, 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, Fig. 9 is used to be described.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, mark same label, the description thereof will be omitted.
In the sealing configuration 607 of the 6th mode of execution, recess 651 is formed in the adjacent inner side guard shield of circumferentially R 650,650 ... inside the radial Q 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 the respective axial P of inner side guard shield 750.
That is, recess 751 is in the substantial middle of the axial P size of inner side guard shield 750, axially P and have interval and formed multiple on circumferential R.
In the gas turbine 701 possessing the sealing configuration 707 so formed, recess 751 is also formed in the mode that axially P extends, therefore, it is possible to improve inner side guard shield 750 and the engaging force that can wear away epithelium 760 on axial P.
(the 8th mode of execution)
Below, about the gas turbine 801 of the 8th mode of execution of the present invention, Figure 10, Figure 11 is used to be described.
At this, Figure 10 is the Y-Y sectional view of Fig. 1 of the sealing configuration 807 of present embodiment, and Figure 11 is the sectional view obtained by inner side guard shield 850 partial sectional of sealing configuration 807.
In this embodiment, for the parts that the parts used with aforesaid mode of execution are common, mark same label, the description thereof will be omitted.
In the sealing configuration 607 of the 6th mode of execution, recess 651 is only the structure formed towards its inside 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 of being formed and and that from the outer circumferential face 860a that can wear away epithelium 860 towards its inside formed second recess 862 relative with this recess 851.And, sell parts 890 to inserting between recess 851 and the second recess 862.
That is, as shown in Figure 10, recess 851 is at the adjacent inner side guard shield 850,850 of circumferentially R ... inside the radial Q of separatrix 854 each other, circumferentially R has interval and is formed multiple from the inner peripheral surface 850a of inner side guard shield 850 towards its inside.And as shown in figure 11, recess 851 is for an inner side guard shield 850, and P has interval and forms 2 positions vertically.
It should be noted that, above-mentioned numerical value is an example, also can be 3 positions, not be defined as this numerical value.
In addition, as shown in Figure 10, the second recess 862 is at the adjacent inner side guard shield 850,850 of circumferentially R ... inside the radial Q of separatrix 854 each other, circumferentially R has interval and is formed multiple from the outer circumferential face 860a that can wear away epithelium 860 towards its inside.And as shown in figure 11, the second recess 862 is for an inner side guard shield 850, and P has interval and forms 2 positions vertically.
In addition, pin parts 890 are bar-like member, and bottom the shroud that one end 890a is configured at recess 851,851c, the other end 890b are configured 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 is formed and can wear away epithelium 860.
In the gas turbine 801 so possessing sealing configuration 807, pin parts 890 are by adjacent inner side guard shield 850,850 ... circumferentially R combines securely each other, and can reduce the displacement to axial P.
In addition, spraying plating can wear material time, the other end 890b side of pin parts 890 is given prominence to, therefore can the deposition of wear material good, can be formed 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 in the above-described embodiment or combination etc. are an example, without departing from the spirit and scope of the invention, can carry out various change based on designing requirement etc.
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 the rotating machinery possessing sealing structure, can wear away epithelium enter concaveconvex shape part and harden, deposition, can engage securely thus.Therefore, even if also can prevent this from can wear away coming off of epithelium when epithelium can be worn away, and damage occurs.
[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, guard shield inside 250,350,450,550,650,750,850
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 epithelium can be worn away
60a, 260a, 360a, 560a, 860a outer circumferential face
654,854 separatrix
R circumference
Claims (5)
1. a sealing configuration, possesses:
Fin, circumferentially gives prominence to from the outer circumferential face of rotor;
And stator blade, be formed at the inner peripheral surface of inner side guard shield can wear away epithelium in the mode relative with described fin,
Be formed with concaveconvex shape at the inner peripheral surface of described inner side guard shield, the described epithelium that wears away is formed along described concaveconvex shape,
Described concaveconvex shape is consisted of the recess formed towards its inside from inner peripheral surface and the described side worn away in the outer circumferential face of epithelium of described inner side guard shield,
Described recess is formed in the mode extended along described circumference,
Described recess is formed in along on the adjacent described inner side guard shield of described circumference separatrix each other.
2. a sealing configuration, possesses:
Fin, circumferentially gives prominence to from the outer circumferential face of rotor;
And stator blade, be formed at the inner peripheral surface of inner side guard shield can wear away epithelium in the mode relative with described fin,
Be formed with concaveconvex shape at the inner peripheral surface of described inner side guard shield, the described epithelium that wears away is formed along described concaveconvex shape,
Described concaveconvex shape is consisted of the recess formed towards its inside from inner peripheral surface and the described side worn away in the outer circumferential face of epithelium of described inner side guard shield,
Described recess is formed in the mode extended along the axial direction of described rotor,
Described recess is formed at the inner peripheral surface of described inner side guard shield and the described side worn away in the outer circumferential face of epithelium, the second recess is formed at the inner peripheral surface of described inner side guard shield and the described opposite side worn away in the outer circumferential face of epithelium, described recess is relative with described second recess
Described sealing configuration possesses the pin parts to inserting between described recess and described second recess.
3. sealing configuration according to claim 1, wherein,
Described recess on the cross section orthogonal with the bearing of trend of this recess, with along with from the inner peripheral surface of described inner side guard shield or the described outer circumferential face wearing away epithelium towards the bottom of this recess and the mode that width broadens gradually formed.
4. sealing configuration according to claim 1, wherein,
Described recess, on the cross section orthogonal with the bearing of trend of this recess, is formed as the arc-shaped bloated from inner peripheral surface or the described outer circumferential face wearing away epithelium of described inner side guard shield.
5. a rotating machinery, it possesses the sealing configuration according to any one of Claims 1 to 4.
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 CN103958949A (en) | 2014-07-30 |
| CN103958949B true 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) |
Citations (6)
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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 |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
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 |
| 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 |
| CN103958949A (en) | 2014-07-30 |
| KR20140083048A (en) | 2014-07-03 |
| KR101600732B1 (en) | 2016-03-07 |
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