CN101146980A - A diaphragm and blades for turbomachinery - Google Patents
A diaphragm and blades for turbomachinery Download PDFInfo
- Publication number
- CN101146980A CN101146980A CN200680009446.4A CN200680009446A CN101146980A CN 101146980 A CN101146980 A CN 101146980A CN 200680009446 A CN200680009446 A CN 200680009446A CN 101146980 A CN101146980 A CN 101146980A
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- China
- Prior art keywords
- blade
- step portion
- cover ring
- inner cover
- diversion disk
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
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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
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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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
-
- 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
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Abstract
A diaphragm for an axial flow turbomachine, in which outer shrouds (710) of adjacent fixed blades in a row of blades contact each other circumferentially to form a circumferentially continuous load path, but in which inner shrouds (730) of the blades only contact each other on contact faces (735, 735<SUP>1</SUP>, 743, 744) oriented to transmit loads in the radial and/or axial directions of the turbomachine.
Description
FIELD OF THE INVENTION
The present invention relates to the turbine field, and be particularly related to the blade that uses therein.Especially, but not uniquely, the layout that the present invention relates to turbine blade to be forming the turbine diaphragm of stator blade, the reduction that working fluid leaks in the turbine that causes simultaneously in the turbine being caused by the distortion because of the variation blade row of operating temperature of at high temperature working of this diversion disk.The present invention can be applied to steamturbine especially.
The background of invention
In fact, steamturbine at first is transformed into mechanical energy with the energy in the steam, and the form of energy of rotation is transformed into electric energy then.The many rows that are called the turbine blade of level are used to the rotary turbine axle.Each steam turbine stage respectively comprises member static and rotation: this static component is the turbine blade row (being referred to as " fixing blade " herein) who is installed in the turbine case; And the member of rotation is to be installed to blade row on the turbine rotor (be referred to as " motion blade) herein.
Pressurised steam axially enters turbine and at first impacts on the blade surface of row of fixed blades.This blade deflection steam to one raftings on the moving blade, and this motion blade transfers also steam deflection to be got back to axially, makes them certainly in the direction motion opposite to the steam of deflection.This just causes turbine rotor rotation steam slight expansion simultaneously.The next stage of the blade of fixing and moving repeats this process.This process continuously by turbine up to the steam complete expansion.
Each continuous level of optimizing blade is to handle the pressure and the volume of the steam of expecting in the position of blade in the turbine, because it will become decompression continuously when steam moves by continuous the raftinging of turbine blade.
As illustrated in fig. 1 and 2, Gu Ding turbine blade 103,203 both can directly be installed in the turbine case 100,200 and also can be installed in the discrete diversion disk 202.The blade that interconnection constitutes turbine stage to be providing damping, thereby avoids damaging the possible vibration of turbine.
With reference to Fig. 1, between stator blade 103 and motion blade 105, there is little axial clearance in case the uppermost leaf sheet contacts with each other.Between stationary housing 100 and rotating member 105,108; And also there is little radial clearance between rotor 101 and the static component 103,109.These gaps must be made as far as possible for a short time to avoid steam leakage, so it can not produce any power by blade owing to the vapor stream through the gap.Sealing fin 104 is set to reduce steam flow by them in radial clearance.Sealing fin 104 both can be fixed to the end that rotor 101, housing 100 also can be fixed to blade 103,105.
In stator blade 103 as shown in Figure 1 was installed to situation in the housing 100, housing 100 did not reconstruct accurate annular because any distortion of thermal effect will influence the end and the radial clearance between the rotor 101 of blade 109 because of blade row.This may cause some terminal contact seal fin 104 of turbine blade 109, and when rotor 101 rotations, its result damages sealing fin 104.In case the distortion of housing 100 disappears, cause steam leakage to increase to this damage that seals fin 104, because the sealing fin 104 less steam that may prevent pass through the end of turbine blade 109 and the leakage of the radial clearance between the rotor 101.
In order to protect stator blade (and therefore sealing fin 104) not to be subjected to the influence of above-mentioned housing distortion not increasing the radial clearance between blade end and the rotor, this stator blade can be installed in the diversion disk shown in Figure 2.This diversion disk 202,203,204 is generally welded structure, install to allow it to center on turbine shaft into two, with outer shroud 202 or interior ring 204 have enough quality with guarantee radial deformation and be minimized and therefore blade 203 keep becoming accurate annular.The outer shroud of diversion disk 202 is installed in the groove 201 of this internal surface of 200 of turbine case, and the interior ring of diversion disk 204 is assembled in the groove 205 of rotor 207 simultaneously.The interior ring of this diversion disk 204 does not contact rotor 207, produces a gap betwixt, and the sealing that still is provided with tab in the groove 205 in rotor 207 is to reduce the vapor stream by the gap.The blade 209 of motion axially is positioned at and is adjacent to the stator blade that is arranged in the diversion disk 202,203,204 203 and is fixed to rotor by the root 208 of motion blade simultaneously.Cover loop section 210 what the end of motion blade 209 was provided with the motion blade, cover at the motion blade and produce a gap between loop section 210 and the turbine shroud 200.This gap is provided with another sealing that tab is arranged equally to reduce the vapor stream by this gap.
But nearest diversion disk design is more compact, shown in Fig. 3,4 and 5.In device shown in Figure 3, fixing blade 303 is installed in the small-sized diversion disk 302,303,309 with outer shroud 302 and interior ring 309.Sealing 306B is set to reduce by the interior ring of diversion disk 309 and the vapor stream in the gap between the rotor 301.This motion blade 304 has the root of blade 305 that is installed in the rotor 301.Sealing 306A is arranged in the gap between the internal surface of axial projection 310 of outer shroud of the outer cover ring 307 of motion blade 304 and diversion disk 302.The axial projection 310 of the outer shroud of diversion disk 302 radially is between the outer shroud of turbine shroud 300 and diversion disk 302.
This design of diversion disk allows favourable rotor structure, such as allowing to use drum rotor and T type root fixings.But, this means that the outer shroud 401,402 of the diversion disk 400,500 shown in the Figure 4 and 5 is different with the thermal inertia of interior ring 405,406.This result be under the speed that differs from one another outside 401,402 and 405,406 heating and cooling of interior ring.
As shown in Figure 4, the outer shroud of diversion disk 400 and interior ring must crack into two in 403,407 punishment, thus cross over its diameter division diversion disk, so that it can be positioned around rotor.The different thermal expansion that is caused by temperature difference can cause the distortion of two halves of diversion disk as striding among Fig. 5 shown in the form, so they form " 8 " or oval together.This means that stationary part moves more close motion parts in some zone of circumference,, cause nonvolatil leakage as mentioned above so this can cause damage when the sealing fin contacts blade or rotor in closed gap between them.
Therefore, an object of the present invention is to reduce or eliminate and comprise that a row is subjected to the problem of small-sized diversion disk of the turbine blade of thermal distortion, this thermal distortion causes the steam leakage that increases and the damage of turbine.
The general introduction of invention
Briefly, the invention provides the turbine diaphragm of axial flow turbine, wherein the outer cover ring of the blade of adjacent fixed contacts the load path that connects circumferentially to form each other circumferentially, but wherein the inner cover ring of blade only radially and/or on the surface of contact of axial load contacts with each other being oriented to transmitting.This arrangement has been cancelled through the load path of the circumference of inner cover ring and thereby has been improved the problem of described thermal distortion.
For realizing this result consistently, just need have pinch fit between the adjacent inner cover ring on its surface of contact, this pinch fit simultaneously must act on enough torsion and cover ring to this upward to guarantee that surface of contact keeps contacting with each other in the whole operating temperature range of turbo machine.
In a preferred embodiment of the invention, when diversion disk is in the whole all working state of the state of cooling of assembling and turbine, contact with each other at the surface of contact of transfer charge radially, but the surface of contact of only loading in transfers when diversion disk reaches operating temperature contacts with each other.
In the present invention, the respective side edge of the adjacent inner cover ring of the opposed side edge contact adjacent blades of inner cover ring each opposed side edge simultaneously comprises protruding step portion, recessed step portion and one are with the step portion of cutting sth. askew of protruding step portion in conjunction with recessed step portion, this protruding step portion is in the relative tail end of its each side margin is configured to depression step portion with the common running of the contiguous inner cover ring that extend into blades adjacent simultaneously, and this chamfered step comprises that partly the surface of contact running is with axially at transfer charge between the adjacent inner cover ring part and prevent the transmission of the circumference of load between the adjacent inner cover ring part.
Preferably, each opposed side edge of inner cover ring part comprises planar section, and protruding step portion comprises the part of side margin, and it is outstanding with respect to planar section, and recessed step portion comprises lateral edge portions simultaneously, and it is with respect to the planar section undercut.In order between adjacent inner cover ring part, to transmit radial force, be provided with like this, promptly the surface of contact of planar section, protruding step portion and recessed step portion is abutting one another.
On the other hand, the invention provides the blade that in axial flow turbine, in fixing blade row, uses, comprising:
(a) outer cover ring part radially,
(b) vane airfoil profile part, and
(c) inner cover ring part radially, it has opposed side edge contacting the respective side edge of the adjacent inner cover ring part of adjacent blades in this blade row,
Wherein each opposed side edge comprises protruding step portion, recessed step portion and protruding step portion is attached to the chamfered step part of recessed step portion, this protruding terraced portion is in the terminal relatively of its each side margin and is configured in the recessed step portion of the adjacent inner cover ring common operation partly that extend into adjacent blades, and this chamfered step partly is arranged in the circumference transmission that the circumferencial direction in blade row laterally transmits power and prevents to load between the adjacent inner cover ring part between the adjacent inner cover ring part.
Utilize benefit of the present invention, provide on the edge within it the turbine blade with the adjacent vanes interconnection, but this turbine blade is not delivered to these adjacent vanes with the stretching of circumference and the power of extruding.This is that logical such layout realizes, guarantees that promptly each blade keeps the free contact that keeps simultaneously to expand at circumferencial direction between the blade.For example have the little circumferential clearance less than 0.5 millimeter, adjacent vanes no longer is delivered in stretching and the extruding force that heating or cooling cause the diversion disk distortion down.By the outer shroud that is fixed to diversion disk blade is remained on the appropriate location.
Will be apparent from the reading of following description and claim other aspects of the present invention.
The accompanying drawing summary
Describe example embodiment of the present invention now with reference to accompanying drawing, wherein identical label is represented identical or like parts.
Fig. 1 be with radial plane that the turbine spin axis overlaps in the phantom got, expression is installed in the stator blade in the housing and is installed in the layout of the motion blade in the rotor;
Fig. 2 be with radial plane that the turbine spin axis overlaps in the phantom got, expression is installed in the stator blade and the layout that is installed in the motion blade in the rotor in the big diversion disk;
Fig. 3 be with radial plane that the turbine spin axis overlaps in the phantom got, expression is installed in the stator blade and the layout that is installed in the motion blade in the rotor in the small-sized diversion disk;
Fig. 4 is the end elevation along the spin axis of turbine, expression is installed in a row of the stator blade in the small-sized diversion disk, isolates from other turbine structure and sees;
Fig. 5 is the view that is similar to Fig. 4, still, with the form of exaggeration, the row of fixed blades that expression is out of shape, this distortion is caused by the interior and outer shroud of diversion disk, and this diversion disk is owing to interior and different thermodynamic outer shroud are in different temperatures;
Fig. 6 is the perspective view of three adjacent turbine blades according to a preferred embodiment of the invention;
Fig. 7 a to 7c is a perspective view of preferably executing the turbine blade of example according to the present invention, and each view is on the not ipsilateral of blade;
Fig. 8 a is the perspective view of three adjacent turbine blades on the outer shroud that is installed in diversion disk of Fig. 6;
Fig. 8 b is the phantom of getting on the B-B line of Fig. 8 a, is illustrated in an outer cover ring part of the turbine blade of the outer ring inner surface that contacts diversion disk before occurring welding;
Fig. 9 a and 9b are the amplification views of the step edges joint on the inner cover ring of the adjacent turbine blades of Fig. 6 part, and (Fig. 9 is the joint of (Fig. 9 b) a) and after being heated before expression was heated;
Figure 10 is the view of similar Fig. 9 b, and expression acts on the power on the joint when complete group of turbine blade is inserted in the turbine diaphragm; And
Figure 11 is the perspective view of turbine blade according to another embodiment of the present invention.
The detailed description of preferred embodiment
Describe turbine blade according to a preferred embodiment of the invention and comprise the diversion disk that this turbine blade is arranged now with reference to Fig. 6 to 10.
Fig. 7 a and 7b represent the single turbine blade 700 according to preferred example of the present invention.This blade 700 constitutes single solid section, forges and be machined into three parts from slug: outer cover ring part 710, blade-section 720 and inner cover ring part 730.
The plate that this outer cover ring part 710 constitutes substantial rectangular or parallelogram has four edge surfaces 711,712,714,716.Circumferencial direction in turbine diaphragm is bent so when all blades are assembled in the diversion disk, form a center of encircling its curvature in abutting connection with outer cover ring part 710 and overlap with the spin axis of turbine.
The inner radial surface 713 of outer cover ring part 710 forms the flow surface of turbine passage.In the manufacture process of turbine diaphragm, the radially-outer surface 715 of outer cover ring part 710 is fixed by welding to an outstanding inwards flange 805 of the outer shroud 800 of diversion disk, describes shown in Fig. 8 a and 8b and afterwards.
The right edge of the circumferential surface of outer cover ring part 710 712,714 is extending axially and be flat surface basically at turbine usually.When blade 700 is assembled in the diversion disk, adjacent shrouds cover the contact that there is circumference between the edge 712,714 in ring forming the continuous load path of circumference, but as explained below between inner cover ring part 730, do not have a circumferential contact.Edge 711,716 axially facing of outer cover ring part 710, that extend circumferentially also is that the distance between them is identical with the axial width of outer shroud 800 simultaneously on flat surface basically.
This blade-section 720 comprises an aerofoil profile 721 that outer cover ring part 710 is connected to inner cover ring part 730.This inner cover ring part 730 form substantial rectangular or parallelogram turbine diaphragm the plate of circumferencial direction bending therefore when all blades are assembled in the diversion disk, adjacent inner cover ring part 730 forms a ring, and the centre of curvature of this ring overlaps with the spin axis of turbine.In the turbine diaphragm of assembling, the radially-outer surface 740 of outer cover ring part 710 forms flow surface 738 pairs of rotor seals of inner radial surface simultaneously of turbine channel, for example, by means of, the blade 306 among similar Fig. 3, be installed in epitrochanterian sealing fin.
As outer cover ring part 710, the edge 741,742 that inner cover ring part 730 has the axially facing on plane basically, extends circumferentially.But, unlike outer cover ring part 710, common axially extended edge that each is faced circumferentially, inner cover ring part 730 has protruding step portion 732,734, complementary recessed step portion 736,737, protruding step portion is attached to the chamfered step part 743,744 of recessed step portion and planar section 731,733.This planar section 731,733 occupies its half of height of covering the ring edge, extends the whole axial range of inner cover ring 730 and is positioned at the radially outward of recessed and protruding step portion.This protrusion step portion 732,734 comprises the part of covering ring edge outstanding with respect to the planar section 731,733 that covers the ring edge, and recessed step portion 736,737 comprises and covers the ring edge with respect to planar section 731,733 undercuts.Occupied half of axial range of inner cover ring by protruding step portion 732,734, this protruding step portion occupies the axial relative position on the relative edge of facing circumferentially of inner cover ring.Similarly, recessed step portion extend beyond the inner cover ring axial range residue half and occupy it and cover the relative axial position of ring on the edge separately.Therefore, when blade was assembled in the turbine diaphragm, the protruding step portion 732,734 of each inner cover ring and 736,737 pairings of the recessed step portion of adjacent inner cover ring were to form the differential expansion joint of the slip between the inner cover ring, as explained in more detail below.
Slip differential expansion joint between the adjacent inner cover ring 730 has contact surface, and it comprises the surface 735 that the radially outward of protruding step portion 732,734 is faced, the surface of radially inwardly facing 735 of recessed step portion 736,737
1(its feature also may be the surface that overhangs of horizontal edge part 731,733), and the step portion 743,744 of cutting sth. askew, this part form angled surface between recessed and protruding step portion.Therefore, when turbine diaphragm was in the state of assembling fully, the contact surface 735 on any given inner cover ring 730 was radially near the contact surface on the adjacent inner cover ring 735
1So that between on the inner cover ring, transmit radial load.In addition, when the operating temperature of turbine, the step portion of cutting sth. askew 743,744 on any given inner cover ring 730 also abutting one another in case circumferencial direction laterally transmit load between the inner cover ring, promptly common axially.But, the surface 733,734,736 that the circumferential surface of inner cover ring part 730 is right; 731,732,737 do not contact each other, but kept separately to prevent in circumference or tangent direction transmission stretching or extruding force by about 0.1 millimeter to 0.5 millimeter little gap.As previously mentioned, will cause diversion disk to be pulled out around rotor, have the result who mentions in the relevant prior art by axisymmetric in the transmission of these power of circumferencial direction.Therefore, keep above-mentioned little circumferential clearance between the adjacent inner cover ring part 730 to allow thermal expansion.
Should be appreciated that in this embodiment of the present invention, design is such, as the whole row of blade 700, or level, when being assembled into diversion disk, blade be inserted in the process of diversion disk airfoil section 721 by the distortion of blade produce in torsion.Be provided with like this, in the state of cooling of assembling, interior torsion causes immediate contact surface 735,735
1Be pressed together, because each immediate mask has the interior torsion of the identical size that is applied to it, therefore last power is zero when all adjacent inner cover rings are in the pairing contact.
In order to renovate, the inner cover ring part 730 of blade 700 suitably do not have with the interlocking of adjacent inner cover ring part inner cover ring portion circumference/tangent direction enters and contacts, promptly between inner cover ring perpendicular to the not significantly load transmission of direction on the plane of turbine dead in line.
Be used for being attached to turbine in order to construct the turbine diaphragm that comprises fixing blade 700 rows or level, this blade 700 is inserted in the T type outer shroud 800.The footpath of outer cover ring 710 715 nestles up radially the inwardly inner radial surface 808 of outstanding flange 805 to the outside, and this flange constitutes T type outer shroud 800 posts.The major component that abuts against outer shroud 800 of outer cover ring part 710 and flange 805 and blade 700 have generation two nominal cylindrical channels 804 between the interconnection outer cover ring part 710.For at outer shroud 800 internal fixation blades 700, as is known, soldered splice is inserted in the passage 804 simultaneously in the welding process of an automation the outer cover ring scarfweld in flange 805.
In case the structure diversion disk as described in detail above, is crossed over its diameter with it and is cut into two semi-circular parts at outer shroud 800 places.The outer cover ring 710 of blade 700 and fixing each other is so cut outer shroud 800 at the some place that two outer shrouds meet.This just allows to center on two parts that the rotor in the turbine is placed diversion disk when the assembling turbine.So two semi-circular parts of outer shroud 800 can be secured together again, for example, as is known, insert strong bolt by means of the bolt flange of the reservation of passing through outer shroud 800, in the outer cover ring that will repair, produce annular completely load path.
With reference to Fig. 7 and 10, will further describe now and when the assembling diversion disk, affact two power on the adjacent inner cover ring 730.As already mentioned, be assembled in the process of diversion disk at blade, aerofoil profile 721 is twisted out its intrinsic aligning with respect to the outer cover ring part slightly, because this result forces the inner cover ring part at surface of contact 735,735
1On enter contact each other.As seeing in Figure 10, the protruding step portion 734 of the inner cover ring 730 on the right extend in the recessed step portion 737 of common operation of inner cover ring on the left side, with the surface of contact of radially inwardly facing 735 that is formed by recessed step portion 737
1Nestle up the surface of contact 735 that the radially outward of protruding step portion 734 is faced.Similarly, the recessed step portion 736 (Fig. 7 b) of the common operation of the inner cover ring on the right of the protruding step portion 732 of the inner cover ring on the left side (Fig. 7 c) extend into is with the surface of contact of radially facing inwards 735 that is formed by recessed step portion 736
1Nestle up the surface of contact 735 that the radially outward that formed by protruding step portion 732 is faced.Equate and opposite power radially near surface of contact 735,735
1Place's effect, producing last power when assembling whole blade row is zero.In fact, in the time of in being assembled to turbine diaphragm, between adjacent shrouds at its surface of contact 735,735 radially
1On have interference fit.This adds enough moments of torsion to guarantee surface of contact 735,735 in the process of turbine work to covering circulating application
1Keep firmly contact each other.
Should be appreciated that in the state of assembling, do not work and blade 700 when being in ambient temperature when turbine, the step portion 743,744 of cutting sth. askew does not contact each other.This is because shown in Fig. 9 a, the gap between the planar section 731,733 at adjacent shrouds edge is than broad.But, during heating, cover that ring expands thereby protruding step portion 734,735 further extends in the recessed step portion 736,737 of common operation separately, enter contact each other up to the face of chamfered step part 743,744.This just prevents protruding exponent part 732,734 and all extend in the recessed step portion 736,737 and czermak space is covered shown in Fig. 9 b in the centre that keeps little, to guarantee not pass through the circumference load path of inner cover ring.The further thermal expansion of inner cover ring near the surface of contact 743,744 of cutting sth. askew on produce equate and opposite power that this power provides zero last power in the turbine diaphragm of the operation of assembling.The laterally effect of this power circumferential/tangential direction of partly locating in chamfered step.
In another not preferred embodiment of the present invention, as shown in figure 11, the expansion joint mechanism between the inner cover ring part 730a of adjacent blades 700a is different from the sort of shown in Fig. 6 to 10.In the described preferred embodiment of relevant Fig. 6 to 10, when assembling, the surface of contact 735,735 of inner cover ring
1With respect to radially the contacting with each other of turbine axis, but chamfered step part 743,744 only just contacts with each other when turbine reaches operating temperature.But, in another embodiment of Figure 11, omit the chamfered step part 743 that radially surface of contact while contact of the interference between the inner cover ring 730a in the state of cooling of the assembling of diversion disk appears at the inner cover ring edge
1With 744
1Face on, between the inner cover ring of adjacent blades, stay little round gap, just as the situation in the preferred embodiment.This eliminates between the inner cover ring 730a in the transmission power of circumferencial direction again because chamfered step part 743
1, 744
1At general axial resistance load.
As can be seen, each of the edge 731a, the 733a that face circumferentially of inner cover ring part 730a is provided with half of axial length that protruding step portion 733a occupies each edge of facing circumferentially basically, and this protruding step portion is the axial opposing ends at its edge of facing circumferentially separately.Each step portion of cutting sth. askew 743
1, 744
1Form one between recessed step portion 731a and protruding step portion 733a angled.Angled face that when the assembling turbine diaphragm, contacts the chamfered step of adjacent inner cover ring of these of chamfered step part 743,744 with the immediate relation of substantial axial.
Though above description mentions outer cover ring 710 and be welded to outer shroud 801, connecting blade 700 is possible to other method of the outer shroud of diversion disk, such as fixing by T root type, or similarly.
In being still another embodiment of the present invention, in the turbine of other pattern,, can use expansion joint mechanism as air turbine.In addition, the present invention also can be applied to blade fixing in the compressor.
The present invention can use on the wide scope of the temperature and pressure that turbine stands, the pressure of 150 to 600 degree for example Celsius and 5 to 300 crust.Can use the suitable material of steel and/or nickel alloy or other herein in the manufacturing of the turbine components of Miao Shuing.
Above-mentionedly described the present invention, in the scope of the present invention of claim, can make amendment simultaneously in pure mode of giving an example.The present invention also is to describe or implicit or expression in the accompanying drawings or implicit any individual characteristics or any conclusion of any this category feature and any combination or any this category feature or combination herein, more than these all expand to its equivalence.Therefore, range of the present invention and scope should not be subjected to the restriction of any above-mentioned example embodiment, disclosed each feature can be replaced by other features identical, equivalent or similar purpose in specification (comprising claim and accompanying drawing), unless specially explanation in addition.
The discussion that runs through the prior art of specification is not a kind of approval, and this technology is by extensively known or constitute the part of general knowledge in this field.
Run through whole description and claim, unless this paper clearly needs, " comprising ", speech such as (" comprise ", " comprising ") was configured the notion that include opposite with exclusive or detailed notion; In other words, be the notion of " including, but are not limited to ".
Claims (15)
1. blade that uses in the fixing blade of a row of axial flow turbine comprises:
(a) outer cover ring part radially,
(b) vane airfoil profile part, and
(c) part is inwardly covered in the footpath, has the opposite side edge in order to contact the respective side edge of the adjacent inner cover ring part of adjacent blades in this blade row.
Wherein each opposed side edge comprises protruding step portion, recessed step portion and protruding step portion is attached to the chamfered step part of recessed step portion, this protruding step portion is in its side margin relative two terminal and be configured in the recessed step portion that extend into the adjacent inner cover ring part of the adjacent blades of common operation separately, and this chamfered step partly is set to laterally transmit the power between the adjacent inner cover ring part and prevent the circumference transmission of the load between the adjacent inner cover ring part with the circumferencial direction in blade row.
2. according to the blade of claim 1, wherein each opposed side edge of inner cover ring part also comprises a planar section, its convexity step portion comprises in the part of the outstanding side margin of planar section simultaneously, and recessed step portion comprises the part with respect to the side margin of planar section undercut.
3. according to the blade of claim 2, wherein the surface of contact of planar section, protruding step portion and recessed step portion is arranged to radially nestle up each other in blade row, thereby transmits radial force between adjacent inner cover ring part.
4. according to any aforementioned sharp blade that requires, this blade is the steamturbine blade.
5. according to the blade of arbitrary money of claim 1 to 3, this blade is air turbine blade or compressor blade.
6. the diversion disk of axial flow turbine, wherein the outer cover ring of adjacent fixed blade contacts each other circumferentially forming the continuous load path of circumference in the blade row, but wherein the inner cover ring of blade only radially and/or axially transmits on the surface of contact of passing load and contacts with each other being oriented in turbo machine.
7. according to the diversion disk of claim 6, have interference fit between the wherein adjacent inner cover ring on its surface of contact, this interference fit adds enough torsion and keeps contacting with each other with surface of contact in the whole work of guaranteeing turbo machine covering circulating application simultaneously.
8. according to the diversion disk of claim 6 or claim 7, wherein the surface of contact of this transmission radial load contacts with each other when this diversion disk is in the whole all working state of the assembling state of cooling and turbine, and the contact of still transmitting axial load only just contacts with each other when diversion disk reaches operating temperature.
9. according to the diversion disk of arbitrary money of claim 6 to 8, wherein the side margin contact of the opposed side edge of inner cover ring and the corresponding adjacent inner cover ring of adjacent blades simultaneously each opposed side edge comprise protruding step portion, recessed step portion and the chamfered step part that protruding step portion is attached to recessed step portion, this protruding step portion be in its separately side margin opposing ends and be configured in the recessed step portion of common operation of the adjacent inner cover ring that extend into adjacent blades, this chamfered step comprises that partly operation is with at the axial surface of contact of transfer charge between adjacent inner cover ring, to prevent the circumference transmission of load between the adjacent inner cover ring part.
10. according to the diversion disk of claim 9, wherein each opposed side edge of inner cover ring part also comprises planar section, its convexity step portion comprises the part of the side margin outstanding with respect to planar section simultaneously, and recessed step portion comprises the lateral edge portions with respect to the planar section undercut simultaneously.
11. according to the diversion disk of claim 10, wherein the surface of contact of planar section, protruding step portion and recessed step portion is configured to radially abutting one another, thereby ring transmits the radial force of covering in adjacent between the part.
12. steamturbine diversion disk according to arbitrary money of claim 6 to 11.
13. air turbine or compressor diversion disk according to arbitrary money of claim 6 to 11.
14. comprise turbine according to the diversion disk of arbitrary money of claim 6 to 11.
15. comprise compressor according to the diversion disk of arbitrary money of claim 6 to 11.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0505978.7 | 2005-03-24 | ||
| GBGB0505978.7A GB0505978D0 (en) | 2005-03-24 | 2005-03-24 | Interlocking turbine blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101146980A true CN101146980A (en) | 2008-03-19 |
Family
ID=34531746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200680009446.4A Pending CN101146980A (en) | 2005-03-24 | 2006-03-22 | A diaphragm and blades for turbomachinery |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20090191053A1 (en) |
| JP (1) | JP2008534837A (en) |
| CN (1) | CN101146980A (en) |
| DE (1) | DE112006000603T5 (en) |
| GB (1) | GB0505978D0 (en) |
| WO (1) | WO2006100256A1 (en) |
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| CN102767399A (en) * | 2011-05-05 | 2012-11-07 | 阿尔斯通技术有限公司 | Diaphragm for turbomachines and manufacturing method |
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| FR2552159B1 (en) * | 1983-09-21 | 1987-07-10 | Snecma | DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS |
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-
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- 2005-03-24 GB GBGB0505978.7A patent/GB0505978D0/en not_active Ceased
-
2006
- 2006-03-22 DE DE112006000603T patent/DE112006000603T5/en not_active Withdrawn
- 2006-03-22 JP JP2008502404A patent/JP2008534837A/en not_active Withdrawn
- 2006-03-22 CN CN200680009446.4A patent/CN101146980A/en active Pending
- 2006-03-22 WO PCT/EP2006/060937 patent/WO2006100256A1/en not_active Application Discontinuation
-
2007
- 2007-09-24 US US11/902,642 patent/US20090191053A1/en not_active Abandoned
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| CN102767399A (en) * | 2011-05-05 | 2012-11-07 | 阿尔斯通技术有限公司 | Diaphragm for turbomachines and manufacturing method |
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Also Published As
| Publication number | Publication date |
|---|---|
| GB0505978D0 (en) | 2005-04-27 |
| WO2006100256A1 (en) | 2006-09-28 |
| JP2008534837A (en) | 2008-08-28 |
| DE112006000603T5 (en) | 2008-02-07 |
| US20090191053A1 (en) | 2009-07-30 |
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Open date: 20080319 |