CN103573298A - Sealing device, axial turbine and power plant - Google Patents
Sealing device, axial turbine and power plant Download PDFInfo
- Publication number
- CN103573298A CN103573298A CN201310246488.1A CN201310246488A CN103573298A CN 103573298 A CN103573298 A CN 103573298A CN 201310246488 A CN201310246488 A CN 201310246488A CN 103573298 A CN103573298 A CN 103573298A
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- Prior art keywords
- peripheral surface
- inner peripheral
- rotation
- meront
- seal arrangement
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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
- F01D11/02—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
- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
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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
- F05D2250/30—Arrangement of components
- F05D2250/38—Arrangement of components angled, e.g. sweep angle
-
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a sealing device, an axial turbine and a power plant. In one embodiment, a sealing device includes seal fins (4) provided on an inner circumferential surface of a stationary body (1) or an outer circumferential surface of a rotating body so as to be adjacent to each other in an axial direction of the rotating body in a gap between the outer circumferential surface of the rotating body and the inner circumferential surface of the stationary body. The device further includes at least one opening member provided on the inner circumferential surface of the stationary body, the opening member (11) being provided at a position between seal fins adjacent to each other in the axial direction, and having holes (11a) opened on a side of the inner circumferential surface of the stationary body. Corresponding axial turbine and power plant are also provided.
Description
Technical field
Embodiments of the present invention relate to seal arrangement, axial-flow blower machine (Japanese: タ mono-PVC Application) and generating complete sets of equipment (Japanese: プ ラ Application ト).
Background technique
Axial-flow blower machine, being used for having impeller (Japanese: ロ mono-タ) in the box of airtight working fluid, has respectively the moving wing and the quiet wing (Japanese: the quiet wing) in the outer circumferential face side of impeller and the inner peripheral surface side of box.And, in the gap between the gap between the outer circumferential face of impeller and the inner peripheral surface of the quiet wing, the inner peripheral surface of box and the outer circumferential face of the moving wing, be provided with the seal arrangement for working fluid is sealed.Turbomachinery at generating complete sets of equipment for large-scale etc., is generally used labyrinth-type excluder as seal arrangement.As such technology, there is Japanese publication communique, Japanese kokai publication hei 11-13404 communique (following, to be called patent documentation 1).
Summary of the invention
In seal arrangement, when sewing flow velocity while having under the state of circumferential composition that impeller is towards radial displacement at Sealing, circumferential pressure in Sealing distributes imbalance can occur, and produces the fluid force (hereinafter referred to as " non-stationary flow muscle power ") that makes impeller destabilization.Non-stationary flow muscle power, in the worst case, can cause the unstable vibration of impeller.Especially, in the large occasion of the differential pressure of the occasion of impeller High Rotation Speed, the entrance of seal arrangement and outlet, non-stationary flow muscle power becomes larger.
Knownly adopt in the situation that the inner peripheral surface side of box, the quiet wing has the honeycomb seal device of honeycomb parts replacing labyrinth-type excluder, compare with labyrinth-type excluder, unstable hydrokinetic attenuating is large, so, can make the unstable vibration stabilization of impeller.But, in honeycomb seal device, due to axial large pressure drop, may make the honeycomb of honeycomb parts sustain damage.Especially, at axial-flow blower machine, be steamturbine, the CO by the working fluid driving of high pressure
2the occasion of turbine, honeycomb more easily damages.
So problem of the present invention is, provides and can reduce non-stationary flow muscle power by thering is the opening features in a plurality of holes, and can suppress seal arrangement, axial-flow blower machine and the generating complete sets of equipment of damage in the hole of opening features.
Seal arrangement based on a mode of execution, possesses in the gap between the outer circumferential face of solid of rotation and the inner peripheral surface of meront to be located at a plurality of sealing fins of the inner peripheral surface of above-mentioned meront or the outer circumferential face of above-mentioned solid of rotation along the axial adjacent mode of above-mentioned solid of rotation.And then said apparatus possesses the opening features of being located at the inner peripheral surface place of above-mentioned meront along above-mentioned axial adjacent above-mentioned sealing fin position to each other, this opening features has towards a plurality of holes of the inner peripheral surface side opening of above-mentioned meront.
Accompanying drawing explanation
Fig. 1 mean the 1st mode of execution seal arrangement structure sectional view and to view.
Fig. 2 mean the 2nd mode of execution seal arrangement structure sectional view and to view.
Fig. 3 mean the 3rd mode of execution seal arrangement structure sectional view and to view.
Fig. 4 mean the 4th mode of execution seal arrangement structure sectional view and to view.
Fig. 5 means the sectional view of structure of the seal arrangement of the 5th mode of execution.
Fig. 6 means the sectional view of structure of the seal arrangement of the 6th mode of execution.
Fig. 7 means the sectional view of structure of the seal arrangement of the 7th mode of execution.
Fig. 8 means the sectional view of structure of the seal arrangement of the 8th mode of execution.
Fig. 9 mean the 9th mode of execution seal arrangement structure sectional view and to view.
Figure 10 means the sectional view of structure of the seal arrangement of the 10th mode of execution.
Figure 11 means the sectional view of structure of the seal arrangement of the 11st mode of execution.
Figure 12 means the CO of the 12nd mode of execution
2the sectional view of the structure of turbine.
Figure 13 means the schematic diagram of formation of the thermal power generation system of the 13rd mode of execution.
Embodiment
Below, with reference to the accompanying drawings of embodiments of the present invention.
(the 1st mode of execution)
Fig. 1 mean the 1st mode of execution seal arrangement structure sectional view and to view.
In Fig. 1, as an example, represent to be arranged on the seal arrangement in axial-flow blower machine.As the example of this axial-flow blower machine, can enumerate steamturbine, CO
2turbine.Fig. 1 (a) means the meridian sectional view of the structure of seal arrangement.And, Fig. 1 (b) be from the A direction of Fig. 1 (a) see seal arrangement to view.And Fig. 1 (c) is the sectional view along the B-B line of Fig. 1 (a).
In Fig. 1, as the constituting component of seal arrangement, impeller 1, the quiet wing 2, quiet wing inner ring 3, a plurality of sealing fin 4, a plurality of honeycomb parts 5 have been represented.
The quiet wing 2 is arranged on the inner peripheral surface side of not shown box.In the inner peripheral surface side of the quiet wing 2, be provided with and be integrally formed with the quiet wing 2 or quiet wing inner ring 3 that split forms.The example of the meront that the quiet wing 2 and quiet wing inner ring 3 show for the present invention opens.
The seal arrangement of Fig. 1 is arranged in the gap between the outer circumferential face of impeller 1 and the inner peripheral surface of quiet wing inner ring 3.In addition, will be described being arranged on the seal arrangement of locating in gap between the inner peripheral surface of box and the outer circumferential face of the cover cap of the moving wing etc. hereinafter.
Sealing fin 4 is the parts that are used for working fluid to seal, and is located at the inner peripheral surface of quiet wing inner ring 3 in the gap between impeller 1 and quiet wing inner ring 3.The circumferential extension of sealing fin 4 along the outer circumferential face of impeller 1 towards impeller 1, is configured in the mode being axially adjacent to each other along impeller 1.And each length radially that seals fin 4 is configured to, make between impeller 1, to there is small gap.By such sealing fin 4, reduce the upstream side leakage of the working fluid of side towards downstream from seal arrangement.Sealing fin 4 is integrally formed with quiet wing inner ring 3 or split forms.
Honeycomb parts 5 are arranged on the inner peripheral surface of quiet wing inner ring 3, have towards a plurality of honeycomb 5a of the inner peripheral surface side opening of quiet wing inner ring 3.Honeycomb 5a is the hole to the end always with the shape of hexagonal prism structure.The parts that form the bottom surface of honeycomb 5a can be also quiet wing inner ring 3 for honeycomb parts 5.The honeycomb parts 5 of present embodiment, a plurality of honeycomb 5a that have standard and configure, specifically, have multiple row along the row of honeycomb 5a circumferentially arranged in columns.Honeycomb parts 5 and honeycomb 5a are respectively the present invention and open the opening features that shows and the example in a plurality of holes.
The seal arrangement of present embodiment not only possesses many sealing fins 4, but also possesses a plurality of honeycomb parts 5.And each honeycomb parts 5 are configured in axially adjacent sealing fin 4 position to each other at the inner peripheral surface place of quiet wing inner ring 3.And the inner peripheral surface of honeycomb parts 5 is configured to than the distance of the sealing top of fin 4 and the outer circumferential face of impeller 1 with the distance of the outer circumferential face of impeller 1.
Below, the effect of the 1st mode of execution is described.
Generally, in seal arrangement, in the micro-gap of fluid between sealing fin 4 and its forward surface by time produce pressure drop, in upstream side and the downstream side generation pressure difference of sealing fin 4.For this reason, if honeycomb parts 5 are set on this forward surface, the pressure sealing in the honeycomb 5a in downstream side of fin 4 becomes lower than the pressure in the honeycomb 5a of the upstream side of sealing fin 4, and honeycomb 5a can be stressed vertically.Its result, honeycomb 5a may sustain damage.Especially, be arranged on the seal arrangement in the turbine paragraph that the pressure difference of working fluid is large, its sealing upstream side of fin 4 and the pressure difference in downstream side also become greatly, and the risk that honeycomb 5a sustains damage uprises.
To this, in the present embodiment, honeycomb parts 5 are not arranged on the forward surface of sealing fin 4, but in the inner peripheral surface side with the identical quiet wing inner ring 3 of sealing fin 4, are arranged on axially adjacent sealing fin 4 position to each other.With respect to sealing the situation that the upstream side of fin 4 and the pressure difference in downstream side are large, in axially adjacent sealing fin 4 region each other, almost there is no pressure difference.Therefore, according to present embodiment, the possibility that honeycomb 5a is subject to excessive power vertically can be reduced, the risk that honeycomb 5a sustains damage can be reduced.
And, according to present embodiment, in the region surrounding by the sealing fin 4 by adjacent, honeycomb parts 5 are set, can relax the imbalance that circumferential pressure distributes by the damping effect being produced by honeycomb parts 5.Therefore,, according to present embodiment, can reduce the non-stationary flow muscle power that causes impeller 1 destabilization.
And, according to present embodiment, because honeycomb 5a to the end always plays the effect of resistance with respect to the circumferential flow velocity of fluid, can reduce (the Japanese: cycle) flow velocity that spirals in the cavity in the unbalanced generation source that the circumferential pressure as fluid distributes.Therefore,, according to present embodiment, can further reduce the non-stationary flow muscle power that causes impeller 1 destabilization.
As mentioned above, in the present embodiment, in the axial adjacent sealing fin 4 of impeller 1 position to each other, honeycomb parts 5 are set.Therefore,, according to present embodiment, can reduce non-stationary flow muscle power by honeycomb parts 5, and can suppress the damage of honeycomb 5a.
(the 2nd mode of execution)
Fig. 2 mean the 2nd mode of execution seal arrangement structure sectional view and to view.
Fig. 2 (a)～Fig. 2 (c) is respectively that the meridian sectional view corresponding with Fig. 1 (a)～Fig. 1 (c), A direction are to view, B-B line sectional view.
In the present embodiment, sealing fin 4 is not arranged on the inner peripheral surface of quiet wing inner ring 3, and is arranged on the outer circumferential face of impeller 1.Sealing fin 4 can form with impeller 1, also can with impeller 1 split form.
And in the present embodiment, the inner peripheral surface of quiet wing inner ring 3 has the 1st S as the inner peripheral surface of honeycomb parts 5
1, and at axial adjacent honeycomb parts 5, be positioned at each other the 2nd S in the upstream side of honeycomb parts 5 of upstream or the downstream side of the honeycomb parts 5 in downstream
2.The 1st S
1for thering is the hollow-core construction of a plurality of honeycomb 5a, to this, the 2nd S
2form the solid construction that does not have such hole.
And in the present embodiment, sealing fin 4 is arranged at the outer circumferential face place of impeller 1 and the 2nd S
2position in opposite directions.Its result, each honeycomb parts 5 are configured in vertically adjacent sealing fin 4 position to each other at the inner peripheral surface place of quiet wing inner ring 3.
Below, the effect of the 2nd mode of execution is described.
As mentioned above, in the present embodiment, with the 1st mode of execution similarly, in the position to each other of the axial adjacent sealing fin 4 along impeller 1, honeycomb parts 5 are set.Therefore, according to present embodiment, with the 1st mode of execution similarly, can reduce non-stationary flows muscle power by honeycomb parts 5, and can suppress the damage of honeycomb 5a.
And, in the present embodiment, by handle, seal fin 4 and be arranged on impeller 1 side, for example, can be at the 2nd S
2form and easily cut material (Japanese: cut soon material) layer (not shown).Thus, can reduce to seal the micro-gap between fin 4 and quiet wing inner ring 3, reduce packing leakage flow.
And, in the present embodiment, contingency sealing fin 4 and the 2nd S when impeller 1 rotation
2during contact, because the surface area of impeller 1 is large, so, from impeller 1, easily dispel the heat.Thus, can avoid impeller 1 to cause the risk of unstable vibration etc. because of thermal distortion.
In addition, in the present embodiment, for example, because of the heat expansion of turbine impeller 1 in service, cause sometimes the position changing of the relative positions vertically of impeller 1.For this reason, if the 2nd S
2axial narrow width, when the changing of the relative positions vertically of the position of impeller 1, the position of sealing fin 4 may from the 2nd S
2position court and the 1st S in opposite directions
1the position changing of the relative positions in opposite directions.So, in the present embodiment, the 2nd S
2axial width preferably set the width with surplus for, thereby, even if the position changing of the relative positions of impeller 1 sealing fin 4 also can continue and the 2nd S
2in opposite directions.
(the 3rd mode of execution)
Fig. 3 mean the 3rd mode of execution seal arrangement structure sectional view and to view.
Fig. 3 (a) and Fig. 3 (b) are respectively that the meridian sectional view corresponding with Fig. 1 (a) and Fig. 1 (b), A direction are to view.
In the present embodiment, with the 1st mode of execution similarly, sealing fin 4 is arranged on the inner peripheral surface of quiet wing inner ring 3, honeycomb parts 5 are configured in vertically adjacent sealing fin 4 position (Fig. 3 (a)) to each other at the inner peripheral surface place of quiet wing inner ring 3.But the honeycomb parts 5 of present embodiment as shown in Figure 3 (b), along a plurality of parts 5b of being circumferentially divided into of impeller 1,5c, have stiffening element 6 along circumferential adjacent parts 5b, 5c each other.
Below, the effect of the 3rd mode of execution is described.
Due to the upstream side S at each sealing fin 4
3with downstream side S
4between there is pressure difference, so, each seal fin 4 at the height of the outer circumferential face from honeycomb parts 5 in the scope of the height of inner peripheral surface, be subject to from upstream side S
3towards downstream side S
4power.So in the present embodiment, at parts 5b, 5c along circumferentially adjacent each other, the mode of joining with the side with sealing fin 4 arranges the stiffening element 6 for sealing fin 4 is strengthened vertically.Therefore, in the present embodiment, from upstream side S
3towards downstream side S
4power be reinforced parts 6 and bear, thus, can suppress to seal distortion, the breakage of fin 4, improve the reliability of sealing fin 4.
And, in the present embodiment, each honeycomb parts 5, along the Segmentation Number of circumferentially cutting apart, can be any amount.For example, in the situation that each honeycomb parts 5 edges are circumferentially divided into 4 parts, at these parts, 4 stiffening elements 6 are set each other.And, being not limited to shown in Fig. 3 (b) towards, shape of stiffening element 6, for example, can make stiffening element 6 towards towards with the uneven direction of directions X, also can make the shape of stiffening element 6 become the shape beyond bar-shaped.And each stiffening element 6 can join with the sealing fin 4 of both sides, also can only join with one-sided sealing fin 4.
(the 4th mode of execution)
Fig. 4 mean the 4th mode of execution seal arrangement structure sectional view and to view.
Fig. 4 (a) and Fig. 4 (b) are respectively that the meridian sectional view corresponding with Fig. 2 (a) and Fig. 2 (b), A direction are to view.
In the present embodiment, with the 2nd mode of execution similarly, sealing fin 4 is arranged on the outer circumferential face of impeller 1, honeycomb parts 5, are configured in vertically adjacent sealing fin 4 position (Fig. 4 (a)) to each other at the outer circumferential face place of quiet wing inner ring 3.But the honeycomb parts 5 of present embodiment as shown in Figure 4 (b), along a plurality of parts 5b of being circumferentially divided into of impeller 1,5c, have stiffening element 6 along circumferential adjacent parts 5b, 5c each other.This is identical with the 3rd mode of execution.
Below, the effect of the 4th mode of execution is described.
Upstream side S at the wall of 5 of adjacent vertically honeycomb parts
5with downstream side S
6between there is pressure difference, therefore, each wall bears from upstream side S in the scope of the height of inner peripheral surface at the height of the outer circumferential face from honeycomb parts 5
5towards downstream side S
6power.So in the present embodiment, at parts 5b, 5c along circumferentially adjacent each other, the mode of joining with the side with above-mentioned wall is provided with the stiffening element 6 for above-mentioned wall is strengthened vertically.Therefore, in the present embodiment, from upstream side S
5towards downstream side S
6power be reinforced parts 6 and bear, thus, can suppress distortion, the breakage of above-mentioned wall, improve the reliability of honeycomb parts 5.
(the 5th mode of execution)
Fig. 5 means the sectional view of structure of the seal arrangement of the 5th mode of execution.
Fig. 5 (a) and Fig. 5 (b) are respectively meridian sectional view, the B-B line sectional views corresponding with Fig. 1 (a) and Fig. 1 (c).
The arrow C of Fig. 5 (b) represents the sense of rotation of impeller 1.And arrow D is illustrated in the inside Normal direction in inner peripheral surface place of quiet wing inner ring 3.And arrow E represents from the bottom of honeycomb 5a towards the direction of opening portion.
In the present embodiment, from the bottom of honeycomb 5a, towards the direction E of opening portion, with respect to the Normal direction D of same position, towards the opposite direction of the sense of rotation C of impeller 1, roll tiltedly.Thus, the direction E towards opening portion compares with the identical occasion of Normal direction D with bottom from honeycomb 5a, can make the resistance that the circumferential flow velocity of honeycomb 5a convection cell is given become large.Therefore, according to present embodiment, can reduce the flow velocity that spirals, further reduce non-stationary flow muscle power.
(the 6th mode of execution)
Fig. 6 means the sectional view of structure of the seal arrangement of the 6th mode of execution.
Fig. 6 (a) and Fig. 6 (b) are respectively meridian sectional view, the B-B line sectional views corresponding with Fig. 1 (a) and Fig. 1 (c).
The honeycomb parts 5 of present embodiment as shown in Figure 6 (b), along impeller 1 circumferentially, alternately include 1st region 5d and the 2nd region 5e different from the height of inner peripheral surface.Its result, the honeycomb parts 5 of present embodiment are circumferential along impeller 1, between the 1st region 5d and the 2nd region 5e, have step 7.According to present embodiment, the circumferential flow velocity of step 7 convection cells plays the effect of resistance, therefore, can reduce the flow velocity that spirals, and further reduces non-stationary flow muscle power.
In addition, step 7 for example also can be arranged on the fragment (Japanese: セ グ メ Application ト) boundary each other of quiet wing inner ring 3.In the case, each fragment has the one party in the 1st region 5d and the 2nd region 5e.And honeycomb parts 5 also can be more than or equal to 3 kinds of different regions of inner peripheral surface height and have step 7 by comprising.
(the 7th mode of execution)
Fig. 7 means the sectional view of structure of the seal arrangement of the 7th mode of execution.Fig. 7 is the meridian sectional view corresponding to Fig. 1 (a).
In the present embodiment, the inner peripheral surface at honeycomb parts 5 is provided with the circumferential slit 8 along impeller 1.According to present embodiment, the circumferential flow velocity of slit 8 convection cells plays drag effect, the flow velocity that spirals further can be reduced, and further reduces non-stationary flow muscle power.
In addition, slit 8 can be arranged at the inner peripheral surface of honeycomb parts 5 interval (i.e. the interval of 360 degree) of circumferential complete cycle, also can only be arranged on a circumferential part interval.And, although can not connecting honeycomb parts 5, slit 8 also can connect honeycomb parts 5, from strengthen the viewpoint that area is set of honeycomb parts 5 as far as possible, preferably do not connect honeycomb parts 5.
(the 8th mode of execution)
Fig. 8 means the sectional view of structure of the seal arrangement of the 8th mode of execution.Fig. 8 is the meridian sectional view corresponding to Fig. 1 (a).
The seal arrangement of Fig. 8, outside the constituting component shown in Fig. 1, also possesses upstream side honeycomb parts 9 and downstream side honeycomb parts 10.Upstream side honeycomb parts 9, are arranged on the position of upstream side of the sealing fin 4 of upstream at the inner peripheral surface place of quiet wing inner ring 3, have towards a plurality of honeycomb 9a of the inner peripheral surface side opening of quiet wing inner ring 3.And downstream side honeycomb parts 10, are arranged on the position in downstream side of the sealing fin 4 in downstream at the inner peripheral surface place of quiet wing inner ring 3, have towards a plurality of honeycomb 10a of the inner peripheral surface side opening of quiet wing inner ring 3.The example of the outer openings parts that upstream side honeycomb parts 9 and downstream side honeycomb parts 10 show for the present invention opens.
According to present embodiment, by the inner peripheral surface place at quiet wing inner ring 3, honeycomb parts 5 are not only set upstream side honeycomb parts 9 and downstream side honeycomb parts 10 are also set, thereby can further improve damping effect, can further reduce unstable hydrokinetic generation.In addition, the seal arrangement of present embodiment, also can only possess the either party in upstream side honeycomb parts 9 and downstream side honeycomb parts 10.
(the 9th mode of execution)
Fig. 9 mean the 9th mode of execution seal arrangement structure sectional view and to view.
Fig. 9 (a) and Fig. 9 (b) are respectively that the meridian sectional view corresponding with Fig. 1 (a) and Fig. 1 (b), A direction are to view.
In the present embodiment, honeycomb parts 5 have been replaced as opening features 11.Each opening features 11 is arranged on vertically adjacent sealing fin 4 position to each other at the inner peripheral surface place of quiet wing inner ring 3, have towards a plurality of hole 11a of the inner peripheral surface side opening of quiet wing inner ring 3.Hole 11a is the hole to the end always with columned shape.
According to present embodiment, by the position to each other of the sealing fin 4 adjacent vertically, opening features 11 is set, not only can similarly by opening features 11, reduce non-stationary flow muscle power with the 1st～8th mode of execution, and can suppress the damage of hole 11a.In addition, the shape of hole 11a can be also the shape (for example quadrangular shape) beyond cylindric.
(the 10th mode of execution)
Figure 10 means the sectional view of structure of the seal arrangement of the 10th mode of execution.Figure 10 is the meridian sectional view corresponding with Fig. 1 (a).Figure 10, as an example, represents to be arranged on the seal arrangement in axial-flow blower machine.
Figure 10, as the constituting component of seal arrangement, represents box 12, the moving wing 13, cover cap 14, a plurality of sealing fin 4, and a plurality of honeycomb parts 5.
The moving wing 13 is arranged on the outer circumferential face side of above-mentioned impeller 1.Outer circumferential face side at the moving wing 13 is provided with and moves the cover cap 14 that the wing 13 is integrally formed or split forms.The example of the solid of rotation that the moving wing 13 and cover cap 14 show for the present invention opens.
The seal arrangement of Figure 10 is arranged in the gap between the inner peripheral surface of box 12 and the outer circumferential face of cover cap 14.
In the gap of sealing fin 4 between box 12 and cover cap 14, be arranged on the inner peripheral surface of box 12.Sealing fin 4 extends along circumferential along the outer circumferential face of cover cap 14, is configured to adjacent one another are vertically.Sealing fin 4 is integrally formed with box 12 or split forms.
According to present embodiment, by the position to each other of the sealing fin 4 adjacent vertically, honeycomb parts 5 are set, can similarly by honeycomb parts 5, reduce non-stationary flows muscle power with the 1st mode of execution etc., but also can suppress the damage of honeycomb 5a.
(the 11st mode of execution)
Figure 11 means the sectional view of structure of the seal arrangement of the 11st mode of execution.Figure 11 is the meridian sectional view corresponding with Fig. 1 (a).
In the present embodiment, sealing fin 4 is not arranged on the inner peripheral surface of box 12, and is arranged on the outer circumferential face of cover cap 14.Sealing fin 4 can form with cover cap 14, also can with cover cap 14 splits form.
And in the present embodiment, the inner peripheral surface of box 12 has: as the 1st S of the inner peripheral surface of honeycomb parts 5
1, and at adjacent vertically honeycomb parts 5, be positioned at each other the 2nd S in the upstream side of honeycomb parts 5 of upstream or the downstream side of the honeycomb parts 5 in downstream
2.The 1st S
1for thering is the hollow-core construction of a plurality of honeycomb 5a, and the 2nd S
2for not thering is the solid construction in such hole.
And in the present embodiment, sealing fin 4 is arranged at the outer circumferential face place of cover cap 14 and the 2nd S
2position in opposite directions.Its result, each honeycomb parts 5 are configured in vertically adjacent sealing fin 4 position to each other at the inner peripheral surface place of box 12.
According to present embodiment, by the position to each other of the sealing fin 4 adjacent vertically, honeycomb parts 5 are set, can similarly by honeycomb parts 5, reduce non-stationary flow muscle power with the 2nd mode of execution etc., but also can suppress the damage of honeycomb 5a.
In addition, the seal arrangement of the 1st～11st mode of execution, also can be arranged on the position outside the gap between gap, the inner peripheral surface of box 12 and the outer circumferential face of cover cap 14 between the outer circumferential face of impeller 1 and the inner peripheral surface of quiet wing inner ring 3.Seal arrangement, for example, also can be located at the gland packing of axial-flow blower machine.
(the 12nd mode of execution)
Figure 12 means the CO of the 12nd mode of execution
2the sectional view of the structure of turbine 101.The CO of Figure 12
2the example of the axial-flow blower machine that turbine 101 shows for the present invention opens.
From turbine wheel 103, towards radial outside, with fixed intervals, be equipped with the moving wing 105 in the form of a ring.These moving wings 105 also in accordance with regulations interval set vertically, between the moving wing 105 of adjacency vertically, be equipped with the quiet wing 106.The quiet wing 106 sets by fixed intervals in the form of a ring.The root of the moving wing 105 is embedded in the outer circumferential face of turbine wheel 103.
In Figure 12, represented for example the moving wing 105 and the quiet wing 106 respectively alternately to set vertically the example of 5 level structures of each 5 formation, but the moving wing 105 is not particularly limited with the progression of the quiet wing 106.
The CO of Figure 12
2 turbine 101, the CO of supercritical state
2(carbon dioxide) carrys out drives impeller machine impeller 103 as working fluid, and, make from CO
2the CO that turbine 101 is discharged
2circulate and inject CO
2in turbine 101, be used for each portion to carry out cooling.
CO
2at 31 ℃, 7.4MPa, there is transition point, the CO of Figure 12
2 turbine 101 is use CO in the situation that temperature and pressure is higher than this transition point
2as prerequisite.
CO at Figure 12
2the upstream side of turbine 101 is provided with sleeve pipe 107, and from then on sleeve pipe 107 is the CO of supercritical state
2gas injects in turbine as working fluid.The CO being injected into
2gas is vertically from upstream side side flow, never illustrated outlet pipe discharge towards downstream.
The in the situation that honeycomb parts 110 being set in this seal arrangement 108, preferably adopt the honeycomb parts 110(honeycomb parts 5 of the structure of the 1st～11st mode of execution).
(the 13rd mode of execution)
Figure 13 means the schematic diagram of formation of the thermal power generation system 120 of the 13rd mode of execution.The thermal power generation system of Figure 13 is the example that the present invention opens the generating complete sets of equipment showing.
As shown in figure 13, the CO of Figure 12
2 turbine 101 can be assembled into and can generate electricity and CO simultaneously
2the separated and thermal power generation system 120 that reclaims in.The thermal power generation system 120 of Figure 13 possesses the CO shown in oxygenerator 121, burner 122, Figure 12
2 turbine 101, generator 123, regenerative heat exchanger 124, cooler 125, water-separator 126 and CO
2pump 127.
The high temperature that burner 122 generates and the CO of high pressure
2gas is injected into the CO shown in Figure 12
2 turbine 101, is used for drives impeller machine impeller 103 rotation.Generator 123 is connected with the running shaft of turbine wheel 103, and generator 123 utilizes the rotary driving force of turbine wheel 103 to generate electricity.
From CO
2the CO that turbine 101 is discharged
2be cooled by regenerative heat exchanger 124 with water vapor, then further by cooler 125, undertaken cooling.Then, by water-separator 126, water is removed, only extracted CO
2.This CO
2by CO
2pump 127 compresses and boosts.
By CO
2the CO of the high pressure that pump 127 has boosted
2a part by regenerative heat exchanger 124, be warmed up to 400 ℃ of left and right.The CO discharging from regenerative heat exchanger 124
2as cooling CO
2be used for carrying out the cooling of turbine 101, but also be fed into burner 122.
By CO
2the CO of the high pressure that pump 127 has boosted
2in, the CO except recycling in generating by regenerative heat exchanger 124
2remaining CO in addition
2, store, reclaim for other purposes (for example,, for increasing oil extraction).
As mentioned above, the power generation system 120 of present embodiment is only utilized the CO that burning generates
2generate electricity with water, CO
2major part carry out cycling and reutilization, do not worry discharging the NOx as harmful gas, and do not need to arrange separately and be used for separation and reclaim CO
2equipment.And then, remaining CO
2can directly with highly purified state, be recovered, can be easily for the various uses beyond generating electricity.
Above, the 1st～13rd mode of execution is illustrated, but these mode of executions are to disclose for example, are not used for scope of invention to limit.These mode of executions can be implemented with other various forms.And, for these mode of executions, in the scope of purport that does not depart from invention, by carrying out various omissions, displacement, change, can obtain various modified examples.These forms, modified example are contained in scope of invention, purport, these forms, modified example be included in the invention scope of asking for protection and the scope that is equal to therewith in.
Description of reference numerals
1: impeller, 2: the quiet wing, 3: quiet wing inner ring, 4: sealing fin, 5: honeycomb parts, 5a: honeycomb, 5b, 5c: parts, 5d: the 1st region, 5e: the 2nd region, 6: stiffening element, 7: step, 8: slit, 9: upstream side honeycomb parts, 9a: honeycomb, 10: downstream side honeycomb parts, 10a: honeycomb, 11: opening features, 11a: hole, 12: box, 13: the moving wing, 14: cover cap, 101:CO
2turbine, 102: inner side box, 103: turbine wheel, 105: the moving wing, 106: the quiet wing, 107: sleeve pipe, 108: seal arrangement, 109: sealing fin, 110: honeycomb parts, 111: gland packing, 120: thermal power generation system, 121: oxygenerator, 122: burner, 123: generator, 124: regenerative heat exchanger, 125: cooler, 126: water-separator, 127:CO
2pump
Claims (10)
1. a seal arrangement, is characterized in that, possesses opening features and a plurality of sealing fin,
Described a plurality of sealing fin, in the gap between the outer circumferential face of solid of rotation and the inner peripheral surface of meront, to be located at the inner peripheral surface of described meront or the outer circumferential face of described solid of rotation along the axial adjacent mode of described solid of rotation;
Described opening features, is arranged at the inner peripheral surface place of described meront along described axial adjacent described sealing fin position to each other, has towards a plurality of holes of the inner peripheral surface side opening of described meront.
2. seal arrangement as claimed in claim 1, is characterized in that, described sealing fin is located at the outer circumferential face of described solid of rotation,
The inner peripheral surface of described meront has the 1st as the inner peripheral surface of described opening features, with along described axially adjacent described opening features, be positioned at each other the upstream side of described opening features of upstream or the downstream side of the described opening features in downstream the 2nd
Described sealing fin is located at the outer circumferential face place of described solid of rotation and described the 2nd face position in opposite directions.
3. seal arrangement as claimed in claim 1 or 2, is characterized in that, described opening features is circumferentially divided into a plurality of parts along described solid of rotation, along described circumferentially adjacent described parts, has each other stiffening element.
4. seal arrangement as claimed in claim 1 or 2, it is characterized in that, from the bottom in the hole of described opening features, towards the direction of opening portion, the opposite direction with respect to the inside Normal direction of the inner peripheral surface of described meront towards the sense of rotation of described solid of rotation rolls tiltedly.
5. seal arrangement as claimed in claim 1 or 2, is characterized in that, the inner peripheral surface of described opening features circumferentially has a step along described solid of rotation.
6. seal arrangement as claimed in claim 1 or 2, is characterized in that, at the inner peripheral surface place of described opening features, is provided with along the slit of the circumferential extension of described solid of rotation.
7. seal arrangement as claimed in claim 1 or 2, it is characterized in that, inner peripheral surface place at described meront possesses outer openings parts, described outer openings parts are arranged on one or both in the position in downstream side of described sealing fin in Yu downstream, position of upstream side of described sealing fin of upstream, have towards a plurality of holes of the inner peripheral surface side opening of described meront.
8. an axial-flow blower machine, is characterized in that, possesses meront, solid of rotation and seal arrangement,
Described meront has the box for airtight working fluid, and is located at the quiet wing of the inner peripheral surface side of described box;
Described solid of rotation has the impeller being arranged in described box, and is located at the moving wing of the outer circumferential face side of described impeller;
Described seal arrangement is arranged in the gap between the outer circumferential face of described solid of rotation and the inner peripheral surface of described meront in the mode that described working fluid is sealed,
Described seal arrangement possesses opening features and a plurality of sealing fin,
Described a plurality of sealing fin, in the gap between the outer circumferential face of described solid of rotation and the inner peripheral surface of described meront, to be located at the inner peripheral surface of described meront or the outer circumferential face of described solid of rotation along the axial adjacent mode of described solid of rotation;
Described opening features, is arranged at the inner peripheral surface place of described meront along described axial adjacent described sealing fin position to each other, has towards a plurality of holes of the inner peripheral surface side opening of described meront.
9. axial-flow blower machine as claimed in claim 8, is characterized in that, described working fluid is supercritical carbon dioxide.
One kind generating complete sets of equipment, it is characterized in that, possess: be used for generating the burner of the carbon dioxide using as working fluid, the axial-flow blower machine as claimed in claim 9 that described carbon dioxide is moved as described working fluid, with the generator being connected with described axial-flow blower machine.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2012161746A JP2014020509A (en) | 2012-07-20 | 2012-07-20 | Seal device, axial flow turbine, and power-generating plant |
| JP2012-161746 | 2012-07-20 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103573298A true CN103573298A (en) | 2014-02-12 |
| CN103573298B CN103573298B (en) | 2016-03-16 |
Family
ID=48877022
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310246488.1A Expired - Fee Related CN103573298B (en) | 2012-07-20 | 2013-06-20 | Seal arrangement, axial turbine and power plant |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20140020403A1 (en) |
| EP (1) | EP2687683A2 (en) |
| JP (1) | JP2014020509A (en) |
| CN (1) | CN103573298B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114207252A (en) * | 2019-08-06 | 2022-03-18 | 赛峰飞机发动机公司 | Abradable component for a turbine wheel and comprising a wear surface provided with guide vanes |
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|---|---|---|---|---|
| JP5567077B2 (en) * | 2012-08-23 | 2014-08-06 | 三菱重工業株式会社 | Rotating machine |
| EP2899405B1 (en) | 2012-11-13 | 2017-07-12 | Mitsubishi Heavy Industries Compressor Corporation | Rotary machine |
| JP6131177B2 (en) * | 2013-12-03 | 2017-05-17 | 三菱重工業株式会社 | Seal structure and rotating machine |
| US10738892B2 (en) * | 2015-01-27 | 2020-08-11 | Mitsubishi Hitachi Power Systems, Ltd. | Rotary machine with seal device |
| EP3228826B1 (en) * | 2016-04-05 | 2021-03-17 | MTU Aero Engines GmbH | Seal segment arrangement having a connector, corresponding gas turbine engine and method of manufacturing |
| EP3228827B1 (en) | 2016-04-05 | 2021-03-03 | MTU Aero Engines GmbH | Seal carrier for a turbomachine, corresponding gas turbine engine and method of manufacturing |
| US9816388B1 (en) * | 2016-09-22 | 2017-11-14 | General Electric Company | Seal in a gas turbine engine having a shim base and a honeycomb structure with a number of cavities formed therein |
| EP3312388B1 (en) | 2016-10-24 | 2019-06-05 | MTU Aero Engines GmbH | Rotor part, corresponding compressor, turbine and manufacturing method |
| US10450963B2 (en) * | 2017-05-02 | 2019-10-22 | Rolls-Royce Corporation | Shaft seal crack obviation |
| JP7281991B2 (en) * | 2019-07-23 | 2023-05-26 | 三菱重工業株式会社 | sealing member and rotary machine |
| JP2023084574A (en) * | 2021-12-07 | 2023-06-19 | 三菱重工業株式会社 | Rotary machine |
| US20240410287A1 (en) * | 2023-03-21 | 2024-12-12 | Raytheon Technologies Corporation | Integral composite stator labyrinth seal |
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| CN114207252B (en) * | 2019-08-06 | 2024-05-24 | 赛峰飞机发动机公司 | Abradable component for a turbine wheel and comprising a wear surface provided with guide vanes |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2687683A2 (en) | 2014-01-22 |
| JP2014020509A (en) | 2014-02-03 |
| CN103573298B (en) | 2016-03-16 |
| US20140020403A1 (en) | 2014-01-23 |
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