CN114526124B - Turbine blade with shroud, determining method and assembling method - Google Patents
Turbine blade with shroud, determining method and assembling method Download PDFInfo
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- CN114526124B CN114526124B CN202210156080.4A CN202210156080A CN114526124B CN 114526124 B CN114526124 B CN 114526124B CN 202210156080 A CN202210156080 A CN 202210156080A CN 114526124 B CN114526124 B CN 114526124B
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- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000005259 measurement Methods 0.000 claims description 22
- 238000004519 manufacturing process Methods 0.000 claims description 6
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000012163 sequencing technique Methods 0.000 claims description 3
- 238000005303 weighing Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000006872 improvement Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 125000006850 spacer group Chemical group 0.000 description 4
- 230000009467 reduction Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- VGGSQFUCUMXWEO-UHFFFAOYSA-N Ethene Chemical compound C=C VGGSQFUCUMXWEO-UHFFFAOYSA-N 0.000 description 1
- 239000005977 Ethylene Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
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
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/02—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for connecting objects by press fit or for detaching same
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention relates to the technical field of steam turbines, and discloses a steam turbine blade with a shroud, a determining method and an assembling method.
Description
Technical Field
The invention relates to the technical field of turbines, in particular to a turbine blade with a shroud, a determining method and an assembling method.
Background
In the industrial driving field, especially in the key fields of large ethylene, large air separation and the like, the requirements of variable rotation speed, large flow and high efficiency industrial steam turbines are continuously increased, and the high-efficiency and safe design of the variable rotation speed and large flow and high efficiency industrial steam turbines gradually highlights importance. Some of the blades are circumferentially arranged, so that the vibration reduction and damping effects of the blades are improved for reducing the steam leakage loss, and the Z-shaped shroud ring structure is adopted to ensure that the blades can be squeezed into groups. The method relies on design, measurement and grinding of the shroud ring to ensure proper interference of contact surfaces of two adjacent blade shroud rings, so that the blade top shroud ring is mutually squeezed during assembly, and the blade profile is twisted.
Disclosure of Invention
In view of the shortcomings of the prior art, it is an object of the present invention to provide a turbine blade with shroud, a method of determining and a method of assembling the same, which overcomes the above-mentioned drawbacks of the prior art.
In order to achieve the above purpose, the present invention provides the following technical solutions: the turbine blade with the shroud, the determining method and the assembling method comprise a blade body, wherein the blade body comprises the shroud, a blade body and a blade root which are integrally formed from top to bottom, the blade root comprises a first contact surface and a second contact surface, the first contact surface and the second contact surface are oppositely arranged, and the first contact surface is used for abutting against the second contact surface of the adjacent blade body;
the utility model discloses a blade, including blade main part, the shroud both sides all continue twice to buckle and set up, so that the both sides of shroud all are "Z" style of calligraphy, one side of shroud includes third contact surface, fifth contact surface and sixth contact surface, the opposite side of shroud includes fourth contact surface, seventh contact surface and eighth contact surface, the third contact surface is used for with adjacent blade main part's fourth contact surface butt and interference fit, fifth contact surface with adjacent blade main part's seventh contact surface clearance fit, sixth contact surface is used for with adjacent blade main part's eighth contact surface clearance fit.
As a further development of the invention, the shroud spacing t is determined S By calculating to ensure the root spacing t H When the maximum deviation occurs, the shroud bands of two adjacent blade main bodies are also in interference, and the specific steps are as follows:
s11: the distance between the central lines of the blade roots of two adjacent blade bodies and the tolerance thereof are determined as follows:
t' H ＝x H +y H ＝y H (t Hl -x Hh ,t Hh -x Hl )+x H (x Hl ,x Hh )＝t H (t Hl -x Hh +x Hl ,t Hh -x Hl +x Hh )
wherein t' H Is the distance between the central lines of two adjacent blade roots, t H Is the distance between blade roots and the tolerance zone is t Hl ,t Hh ，x H For a first positioning dimension of the blade body at the blade root, the tolerance zone is x Hl ,x Hh ，y H A second positioning dimension of the blade body at the blade root;
s12: the distance between the central lines of two adjacent blade shroud bands and the tolerance thereof are as follows:
t' S ＝x S +y S ＝y S (t Sl -x Sh ,t Sh -x Sl )+x S (x Sl ,x Sh )＝t S (t Sl -x Sh +x Sl ,t Sh -x Sl +x Sh )
wherein t' S Is the center line spacing of two adjacent shroud bands, t S Is the interval of the shroud and the tolerance zone is t Sl ,t Sh ，x S For a first positioning dimension of the blade body at the shroud, the tolerance band is x Sl ,x Sh ，y S A second positioning dimension of the blade body at the shroud;
s13: determination of t 'by calculation' H The tolerance projection is carried out on the shroud, and when the projection value of the tolerance upper limit of the center line spacing between adjacent blade roots is smaller than the tolerance lower limit of the center line spacing between adjacent shrouds, the values are mutually matchedTwo adjacent blade roots are abutted, and the third contact surface is abutted with the fourth contact surface of the adjacent blade body and in interference fit:
(t Hh -x Hl +x Hh )*sin(A)/sin(B)≤(t Sl -x Sh +x Sl )
wherein A is the acute angle of the blade root, B is the angle between the third contact surface and the circumference of the impeller, and x is the blade root part Hl ,x Hh ,t Hl ,t Hh As is known, the shroud portion x Sl ,x Sh And the blade root part x Hl ,x Hh The values are the same;
s14: from S12 and S13, t is determined Sl The shroud spacing tolerance zone is consistent with the blade root spacing tolerance zone, then t Sh ＝t Sl +t Hh -t Hl 。
As a further improvement of the invention, a method for assembling a turbine blade with shroud, comprising the steps of:
s21: providing an impeller with a root groove in the circumferential direction;
s22: numbering, weighing and sequencing each blade main body;
s23: manufacturing a tooling blade, wherein the blade root projection distance of the tooling blade is larger than the shroud interval;
s24: sequentially placing a blade main body with the number I, a tooling blade and a blade main body with the number II into the impeller along a root groove;
s25: extruding the blade bodies with the measurement number of one and the blade bodies with the measurement number of two along the circumferential direction of the impeller so as to tightly extrude the blade roots of the two blade bodies and the blade roots of the tooling blades, and calculating the relative interference of the shroud between the blade body with the measurement number of one and the blade body with the measurement number of two by measuring the shroud clearance delta X between the blade body with the measurement number of one and the blade of the tooling blades and the shroud clearance delta Y between the blade body with the measurement number of two and the blade body with the measurement number of two;
s26: when the relative interference magnitude of the shroud is larger than 0 and smaller than 0.1mm, the third contact surface or the fourth contact surface does not need to be polished, and when the relative interference magnitude of the shroud is larger than 0.1mm, the third contact surface or the fourth contact surface needs to be polished;
s27: and repeatedly installing the rest blade main bodies through the tooling blades in sequence.
As a further improvement of the invention, the manufacturing substeps of the tooling blade are as follows:
s231: the lower limit projection value of the tolerance of the center line spacing between the tool blade and the blade root of the main body of the adjacent blade is larger than or equal to the upper limit value of the tolerance of the center line of the shroud of the tool blade and the main body of the adjacent blade plus a reserved minimum clearance, and the tolerance relation between the main body of the blade and the tool blade is converted into a number I, and the tolerance relation between the main body of the blade and the tool blade is converted into a number II:
(t hl tool -x Hh tool +x Hl )*sin(A)/sin(B)≥(t Sh tool -x Sl tool +x Sh )+Δt
(t Hl -x Hh +x Hl tool )*sin(A)/sin(B)≥(t Sh -x Sl +x Sh tool )+Δt
Wherein Deltat is the reserved minimum gap, t H tool Is the distance between blade roots and the tolerance zone is t Hl tool ,t Hh tool ，x H tool For the first positioning dimension of the blade body of the tooling blade at the blade root, the tolerance zone is x Hl tool ,x Hh tool The shroud spacing is the shroud spacing of the tooling blade and the tolerance zone is t Sl tool ,t Sh tool ，x S tool For a first positioning dimension of the blade body at the shroud, the tolerance band is x Sl tool ,x Sh tool ；
S232: supplementary tolerance t S tool With equation x Sh tool -x Sl tool ＝x Sh -x Sl Find tool x Sh tool ，t Sh tool Is a value of (2).
As a further improvement of the invention, the relative magnitude of interference of the shroud bands of two adjacent blade bodies of the tooling blade is determined as the substeps:
s251, measuring the difference value between the actual spacing and the theoretical spacing of the blade root and the shroud of the tool blade to be t He tool ，t Se tool The tool blade and the blade main body with the number of one or two, and the error between the blade root spacing of the tool blade and the theoretical value spacing is t He tool ＝t H tool -t H The error between the clearance of the tool blade shroud and the theoretical value clearance is t Se tool ＝t S tool -t S 。t He ＝t' H12 -t H ，t′ H12 The blade root center line spacing, t, when the blade bodies numbered one and two are adjacent Se ＝t' S12 -t S ，t′ H12 The center line spacing of the shroud when the blade bodies numbered one and two are adjacent;
s252, calculating the relative interference magnitude value of the shroud bands of two adjacent blade bodies of the tool blade, wherein the specific calculation formula is as follows:
(t He +t he tool )*sin(A)/sin(B)＝(t Se +t Se tool +ΔX+ΔY)
t He *sin(A)/sin(B)-t Se ＝(t Se tool +ΔX+ΔY)-t He tool * sin (A)/sin (B) wherein t He *sin(A)/sin(B)-t Se -the relative interference of the shroud between the blade body (9) numbered one and the blade body numbered two.
As a further improvement of the invention, Δx and Δy are measured by a feeler gauge.
The invention has the beneficial effects that: according to the invention, the two sides of the shroud ring are continuously bent twice, so that the two sides of the shroud ring are Z-shaped, certain blades arranged in the circumferential direction are Z-shaped, the Z-shaped shroud ring structure is adopted, the steam leakage loss during the operation of the steam turbine can be reduced, the top blade profile shape of the blades arranged in the circumferential direction is met, the extrusion of the shroud ring is tighter under the action of centrifugal force, and the grouping vibration reduction effect of the blades is improved.
The invention provides a method for determining the size of a blade, which can ensure that a third contact surface and a fourth contact surface in adjacent shroud bands still ensure interference fit even when the maximum deviation of the blade root spacing occurs when two adjacent blade main bodies are mutually close to and abut against each other, and simultaneously solve the problem that the shroud band spacing tolerance zone is difficult to calculate due to different angles of the shroud bands and the blade roots.
The invention provides an assembling method of a turbine blade with shroud bands, which utilizes a tooling blade to assemble, can adjust the size of each shroud band in real time, and can ensure that the shroud bands cannot be oversized and undersized under the condition of maximum deviation of blade root size by matching with the determining method of the shroud band blade in the invention, so that the blade bodies can be reasonably installed.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic installation view of the present invention;
FIG. 3 is a top view of FIG. 2 in accordance with the present invention;
FIG. 4 is a top plan view of the blade and blade root of the present invention;
FIG. 5 is a bottom view of the mounting of the blade airfoil and shroud of the present invention;
FIG. 6 is a schematic front view of the use of the tooling blade of the present invention;
FIG. 7 is a schematic top view of the use of the tooling blade of the present invention.
Reference numerals: 1. blade root; 2. a leaf body; 3. a shroud; 4. root groove; 5. a spacer strip; 6. an impeller; 8. tool blades; 9. a blade body; 11. a first contact surface; 12. a second contact surface; 13. a third contact surface; 14. a fourth contact surface; 15. a fifth contact surface; 16. a sixth contact surface; 17. a seventh contact surface; 18. and an eighth contact surface.
Detailed Description
The invention will now be described in further detail with reference to the drawings and examples. Wherein like parts are designated by like reference numerals. It should be noted that the words "front", "back", "left", "right", "upper" and "lower" used in the following description refer to directions in the drawings, and the words "bottom" and "top", "inner" and "outer" refer to directions toward or away from, respectively, the geometric center of a particular component.
Referring to fig. 1, a turbine blade with shroud according to this embodiment includes a blade body 9, where the blade body 9 includes a shroud 3, a blade body 2 and a blade root 1 integrally formed from top to bottom, the blade root 1 includes a first contact surface 11 and a second contact surface 12, the first contact surface 11 and the second contact surface 12 are disposed opposite to each other, according to fig. 1, the first contact surface 11 and the second contact surface 12 are two end surfaces of the blade root 1 toward the circumference of the impeller 6, the first contact surface 11 is used to abut against the second contact surface 12 of an adjacent blade body 9, and the second contact surface 12 is used to abut against the first contact surface 11 of the adjacent blade body 9, where the abutment is an interference fit;
the two sides of the shroud ring 3 are continuously bent twice, so that the two sides of the shroud ring 3 are Z-shaped, blades which are circumferentially installed are of a Z-shaped shroud ring 3 structure, the installation of the blades which are circumferentially installed is more convenient, the steam leakage loss during the operation of a steam turbine can be reduced, the vibration reduction damping effect of the blades is increased, the blades can be ensured to be tightly pressed into groups, one side of the shroud ring 3 comprises a third contact surface 13, a fifth contact surface 15 and a sixth contact surface 16, the other side of the shroud ring 3 comprises a fourth contact surface 14, a seventh contact surface 17 and an eighth contact surface 18, the third contact surface 13 is used for being abutted with the fourth contact surface 14 of an adjacent blade body 9 and in interference fit, the fifth contact surface 15 is in clearance fit with the seventh contact surface 17 of the adjacent blade body 9, and the sixth contact surface 16 is used for being in clearance fit with the eighth contact surface 18 of the adjacent blade body 9.
Specifically, the overlooking shape of the blade root 1 and the overlooking shape of the shroud 3 are diamond-shaped, and the angles of the two diamond-shaped shapes and the deflection angle between the two diamond-shaped shapes are different, so that the blade root 1 and the shroud 3 are clamped conveniently, and the helical blade body 2 is mounted conveniently.
In one embodiment, the present invention provides a method of validating a shrouded turbine blade:
determining shroud spacing t S By calculating to ensure the root spacing t H At maximum deviation, i.e. leafThe shroud 3 of two adjacent blade main bodies 9 also has interference while the root 1 is squeezed, and the specific steps are as follows:
s11: the distance between the root center lines of two adjacent blade bodies 9 and the tolerance thereof are determined as follows:
t' H ＝x H +y H ＝y H (t Hl -x Hh ,t Hh -x Hl )+x H (x Hl ,x Hh )＝t H (t Hl -x Hh +x Hl ,t Hh -x Hl +x Hh )
wherein t' H Is the distance between the central lines of two adjacent blade roots, t H Is the distance between blade roots and the tolerance zone is t Hl ,t Hh ，x H For a first positioning dimension of the blade body 2 at the blade root 1, the tolerance band is x Hl ,x Hh ，y H For the second positioning dimension of the blade airfoil 2 at the blade root 1, it is to be noted here that t Hl ,t Hh All are known preset data, the second positioning size is determined by determining the first positioning size, and the main function of the first positioning size is to determine the position of the blade body 2 at the blade root 1, wherein the numerical value determination and design are not in the discussion range in the invention;
s12: the distance between the central lines of two adjacent blade shroud bands and the tolerance thereof are as follows:
t' S ＝x S +y S ＝y S (t Sl -x Sh ,t Sh -x Sl )+x S (x Sl ,x Sh )＝t S (t Sl -x Sh +x Sl ,t Sh -x Sl +x Sh )
wherein t' S Is the center line spacing of two adjacent shroud bands, t S Is the interval of the shroud and the tolerance zone is t Sl ,t Sh ，x S For a first positioning dimension of the blade body 2 at the shroud 3, the tolerance band is x Sl ,x Sh ，y S For the second positioning dimension of the blade body 2 at the shroud 3, the second positioning dimension is also determined by the determination of the first positioning dimension, and the main function of the first positioning dimension is thatDetermining the position of the blade body 2 in pairs at the shroud 3, the numerical determination and design of which are not within the scope of the present invention;
s13: determination of t 'by calculation' H And the tolerance projection is carried out on the shroud (3), when the upper tolerance projection value of the center line spacing of adjacent blade roots is smaller than the lower tolerance value of the center line spacing of the adjacent shroud, the adjacent two blade roots (1) are abutted, and the third contact surface (13) is abutted with the fourth contact surface (14) of the adjacent blade body (9) and in interference fit:
(t Hh -x Hl +x Hh )*sin(A)/sin(B)≤(t Sl -x Sh +x Sl )
wherein A is an acute angle of the blade root, B is an angle between the third contact surface (13) and the circumference of the impeller (6), and x is the blade root part Hl ,x Hh ,t Hl ,t Hh As is known, the shroud portion x Sl ,x Sh And the blade root part x Hl ,x Hh The values are the same;
s14: from S12 and S13, t is determined Sl The shroud spacing tolerance zone is consistent with the blade root spacing tolerance zone, then t Sh ＝t Sl +t Hh -t Hl 。
The invention provides a method for confirming a turbine blade with a shroud, which can ensure that when two adjacent blade bodies 9 are mutually close to each other and are abutted, the third contact surface 13 and the fourth contact surface 14 in the adjacent shroud 3 still ensure interference fit even when the maximum deviation of the spacing of blade roots 1 occurs, and simultaneously solve the problem that the tolerance zone of the spacing between the shroud 3 is difficult to calculate due to different angles of the shroud 3 and the blade roots 1.
In one embodiment, the present invention provides a method of assembling a shrouded turbine blade:
s21: providing an impeller 6 with a root groove 4 formed in the circumferential direction;
s22: numbering, weighing and sequencing each blade body 9;
s23: manufacturing a tooling blade 8, wherein the projection distance of the blade root 1 of the tooling blade 8 is larger than the distance of the shroud 3, and for the purposes of the specification, the projection distance of the blade root 1 of the tooling blade 8 is required to be larger than the distance of the shroud 3 as much as possible, so that accurate measurement can be ensured by a measuring means, and a minimum specification feeler gauge can be inserted at least in the following embodiments;
s24: sequentially placing the blade body 9 with the number I, the tooling blade 8 and the blade body 9 with the number II into the impeller 6 along the root groove 4, namely arranging the blade body 9 with the number I and the blade body 9 with the number II in the drawing, wherein the blade body 9 with the number I and the blade body 9 with the number II are respectively positioned at two sides of the tooling blade 8;
s25: the blade bodies 9 with the measurement number I and the blade bodies 9 with the measurement number II are extruded along the circumferential direction of the impeller 6 so as to tightly extrude the blade roots 1 of the two blade bodies 9 and the blade roots 1 of the tooling blades 8, and the relative interference of the shroud between the blade bodies 9 with the measurement number I and the blade bodies 9 with the measurement number II is calculated by measuring the shroud clearance delta X between the blade bodies 9 with the measurement number I and the tooling blades 8 and measuring the shroud clearance delta Y between the blade bodies 9 with the measurement number II and the tooling blades 8;
s26: when the relative interference value of the shroud is larger than 0 and smaller than 0.1mm, the third contact surface 13 or the fourth contact surface 14 does not need to be polished, and when the relative interference value of the shroud 3 is larger than 0.1mm, the third contact surface 13 or the fourth contact surface 14 needs to be polished, so that the situation that the blade roots 1 cannot be tightly attached to each other due to the fact that the interval between the shroud 3 between adjacent blade bodies 9 is too large is prevented, the problem that blade-shaped torsion force is too large due to assembly is solved, and final assembly is carried out;
s27: the above steps are repeated sequentially for the rest of the blade bodies 9 by the tooling blade 8 for installation.
The invention provides an assembling method of a turbine blade with a shroud, which utilizes a tooling blade 8 to assemble, can adjust the size of each shroud 3 in real time, and can ensure that the shroud 3 can not be oversized or undersized under the condition that the blade root 1 has the maximum deviation in size by matching with the determining method of the shroud 3 blade in the invention, and ensure that each blade main body 9 can be reasonably installed.
In one embodiment, the manufacturing sub-steps of the tooling blade are:
s231: the lower limit projection value of the tolerance of the center line spacing between the tool blade 8 and the blade root of the adjacent blade main body 9 is larger than or equal to the upper limit value of the tolerance of the center line of the shroud of the tool blade 8 and the adjacent blade main body 9 plus a reserved minimum clearance, and the tolerance relation between the blade main body 9 and the tool blade 8 is converted into a number I, and the tolerance relation between the blade main body 9 and the tool blade 8 is converted into a number II:
(t hl tool -x Hh tool +x Hl )*sin(A)/sin(B)≥(t Sh tool -x Sl tool +x Sh )+Δt
(t Hl -x Hh +x Hl tool )*sin(A)/sin(B)≥(t Sh -x Sl +x Sh tool )+Δt
Wherein Δt is the reserved minimum gap, which is the reserved minimum gap in S23, and the value thereof is determined according to the need, t H tool Is the distance between blade roots and the tolerance zone is t Hl tool ,t Hh tool ，x H tool For a first positioning dimension of the blade body of the tooling blade 8 at the blade root 1, the tolerance zone is x Hl tool ,x Hh tool ，t S tool Is the shroud spacing of the tooling blade 8 and the tolerance band is t Sl tool ,t Sh tool ，x S tool For a first positioning dimension of the blade body 2 at the shroud 3, the tolerance band is x Sl tool ,x Sh tool ；
S232: supplementary tolerance band equation x Sh tool -x Sl tool ＝x Sh -x Sl Find tool x Sh tool ，t Sh tool Is a value of (2).
Wherein x is the root portion Hl ,x Hh ,t Hl To know, the dimensional tolerance of the tool blade root is the same as that of two adjacent blade roots, and the shroud part t Sh ,x Sl ,x Sh x Sl ,x Sh ,t Sh It is also known that the above formula is only t Sh tool And x Sl tool ,x Sh tool Unknown, supplement equation x Sh tool -x Sl tool ＝x Sh -x Sl Then x can be found Sh tool ，t Sh tool Thereby making it possible to specifically produce the desired tooling blade 8.
In one embodiment, the determining the shroud relative interference quantum step between the blade body 9 numbered one and the blade body 9 numbered two is:
s251, measuring the difference value between the actual spacing and the theoretical spacing of the blade root 1 and the shroud 3 of the tool blade 8 to be t He tool ，t Se tool The tool blade 8 and the blade body 9 with the number of one or two, and the error between the blade root spacing of the tool blade 9 and the theoretical value spacing is t He tool ＝t H tool -t H The error between the shroud spacing of the tooling blade 9 and the theoretical value spacing is t Se tool ＝t S tool -t S ，t He ＝t' H12 -t H ，t' H12 The blade root center line spacing, t, when the blade bodies numbered one and two are adjacent Se ＝t′ S12 -t S ，t′ H12 The center line spacing of the shroud when the blade bodies numbered one and two are adjacent;
s252, calculating the relative interference magnitude value of the shroud bands of two adjacent blade main bodies 9 of the tooling blade 8, wherein the specific calculation formula is as follows:
(t' He +t he tool )*sin(A)/sin(B)＝(t' Se +t Se tool +ΔX+ΔY)
t' He *sin(A)/sin(B)-t' Se ＝(t Se tool +ΔX+ΔY)-t He tool *sin(A)/sin(B)
Wherein t' He *sin(A)/sin(B)-t' S The shroud relative interference between the blade body 9 numbered one and the blade body 9 numbered two.
Further, for theoretical values, i.e., shroud spacing t' S ＝t S Blade root spacing t' H ＝t H That is, the positive and negative tolerances are both 0, which is the prior art in the art and is not described herein in detail. In one embodiment, ΔX and ΔY are measured by a feeler gauge.
In one embodiment, Δx and Δy are measured by a screw micrometer.
In one embodiment, the blade root and the root groove further comprise a spacer 5, as shown in fig. 2, wherein the spacer 5 is arranged between the bottom of the root groove 4 and the blade root 1, and functions to ensure the installation coordination between the root groove 4 and the blade root 1.
In one embodiment, in the actual installation process, the blade body 9 of the previous stage is already installed, the size of the blade body 9 of the next stage is already determined, the blade body 9 of the next stage is tightly pressed and fixed with the root groove 4 along the radial direction of the impeller 6 along the root groove 4 by the spacer 5, the blade root 1 of the blade body 9 of the next stage is continuously and circumferentially knocked so as to be further tightly attached to the blade root 1 of the previous stage, in the process, the third contact surface 13 and the fourth contact surface 14 of two adjacent blades are in interference, so that the blade bodies 2 are mutually pressed, the blade root 1 and the shroud 3 of the whole circle of blades are subjected to external torque, and therefore, the effect that the blade root 1 and the shroud 3 of the whole circle of blades are mutually tightly combined is ensured.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above examples, and all technical solutions belonging to the concept of the present invention belong to the protection scope of the present invention. It should be noted that modifications and adaptations to the present invention may occur to one skilled in the art without departing from the principles of the present invention and are intended to be within the scope of the present invention.
Claims (5)
1. Steam turbine blade with shroud, including blade main part (9), blade main part (9) are including from top to bottom integrated into one piece's shroud (3), blade body (2) and blade root (1), its characterized in that: the blade root (1) comprises a first contact surface (11) and a second contact surface (12), the first contact surface (11) and the second contact surface (12) are oppositely arranged, and the first contact surface (11) is used for abutting against the second contact surface (12) of the adjacent blade main body (9);
the two sides of the shroud ring (3) are continuously bent twice, so that the two sides of the shroud ring (3) are Z-shaped, one side of the shroud ring (3) comprises a third contact surface (13), a fifth contact surface (15) and a sixth contact surface (16), the other side of the shroud ring (3) comprises a fourth contact surface (14), a seventh contact surface (17) and an eighth contact surface (18), the third contact surface (13) is used for abutting and interference fit with the fourth contact surface (14) of an adjacent blade body (9), the fifth contact surface (15) is in clearance fit with the seventh contact surface (17) of the adjacent blade body (9), and the sixth contact surface (16) is used for clearance fit with the eighth contact surface (18) of the adjacent blade body (9).
A method of validating a turbine blade with shroud is provided,
determining shroud spacing t S By calculating to ensure the root spacing t H When the maximum deviation occurs, the shroud bands (3) of two adjacent blade main bodies (9) are also in interference, and the specific steps are as follows:
s11: the distance between the blade root central lines of two adjacent blade bodies (9) and the tolerance thereof are determined as follows:
t' H ＝x H +y H ＝y H (t Hl -x Hh ,t Hh -x Hl )+x H (x Hl ,x Hh )＝t H (t Hl -x Hh +x Hl ,t Hh -x Hl +x Hh )
wherein t' H Is the distance between the central lines of two adjacent blade roots, t H Is the distance between blade roots and the tolerance zone is t Hl ,t Hh ，x H For a first positioning dimension of the blade airfoil (2) at the blade root (1), the tolerance band thereof is x Hl ,x Hh ，y H -a second positioning dimension of the blade airfoil (2) at the blade root (1);
s12: the distance between the central lines of two adjacent blade shroud bands and the tolerance thereof are as follows:
t' S ＝x S +y S ＝y S (t Sl -x Sh ,t Sh -x Sl )+x S (x Sl ,x Sh )＝t S (t Sl -x Sh +x Sl ,t Sh -x Sl +x Sh )
wherein t' S Is the center line spacing of two adjacent shroud bands, t S Is the interval of the shroud and the tolerance zone is t Sl ,t Sh ，x S For a first positioning dimension of the blade body (2) at the shroud (3), the tolerance band thereof is x Sl ,x Sh ，y S -a second positioning dimension of the blade body (2) at the shroud (3);
s13: determination of t 'by calculation' H And the tolerance projection is carried out on the shroud (3), when the upper tolerance projection value of the center line spacing of adjacent blade roots is smaller than the lower tolerance value of the center line spacing of the adjacent shroud, the adjacent two blade roots (1) are abutted, and the third contact surface (13) is abutted with the fourth contact surface (14) of the adjacent blade body (9) and in interference fit:
(t Hh -x Hl +x Hh )*sin(A)/sin(B)≤(t Sl -x Sh +x Sl )
wherein A is an acute angle of the blade root, B is an angle between the third contact surface (13) and the circumference of the impeller (6), and x is the blade root part Hl ,x Hh ,t Hl ,t Hh As is known, the shroud portion x Sl ,x Sh And the blade root part x Hl ,x Hh The values are the same;
s14: from S12 and S13, t is determined Sl The shroud spacing tolerance zone is consistent with the blade root spacing tolerance zone, then t Sh ＝t Sl +t Hh -t Hl 。
2. A method of assembling a shrouded turbine blade, comprising: the method comprises the following specific steps:
s21: providing an impeller (6) with a root groove (4) formed in the circumferential direction;
s22: numbering, weighing and sequencing each of said blade bodies (9);
s23: manufacturing a tooling blade (8), wherein the projection distance of blade roots (1) of the tooling blade (8) is larger than the distance of the shroud (3);
s24: sequentially placing a blade main body (9) with the number I, a tool blade (8) and a blade main body (9) with the number II into the impeller (6) along the root groove (4);
s25: the blade bodies (9) with the measurement number of one and the blade bodies (9) with the measurement number of two are extruded along the circumferential direction of the impeller (6) so as to tightly press the blade roots (1) of the blade bodies (9) and the blade roots (1) of the tooling blades (8), and the relative interference of the shroud between the blade bodies (9) with the measurement number of one and the blade bodies (9) with the measurement number of two is calculated by measuring the shroud clearance delta X between the blade bodies (9) with the measurement number of one and the tooling blades (8) and the shroud clearance delta Y between the blade bodies (9) with the measurement number of two and the blade bodies (9) with the measurement number of two;
s26: when the relative interference value of the shroud is larger than 0 and smaller than 0.1mm, the third contact surface (13) or the fourth contact surface (14) does not need to be polished, and when the relative interference value of the shroud is larger than 0.1mm, the third contact surface (13) or the fourth contact surface (14) needs to be polished;
s27: and (3) sequentially repeating the steps for the rest blade main bodies (9) through the tool blades (8).
3. A method of assembling a shrouded turbine blade in accordance with claim 2 wherein: the manufacturing substeps of the tool blade are as follows:
s231: the lower limit projection value of the tolerance of the center line spacing between the tool blade (8) and the blade root of the adjacent blade main body (9) is larger than or equal to the upper limit value of the tolerance of the center line of the shroud of the tool blade (8) and the adjacent blade main body (9) plus a reserved minimum clearance, the tolerance relation between the blade main body (9) and the tool blade (8) with the number of one is converted, and the tolerance relation between the blade main body (9) and the tool blade (8) with the number of two is converted:
(t hl tool -x Hh tool +x Hl )*sin(A)/sin(B)≥(t Sh tool -x Sl tool +x Sh )+Δt
(t Hl -x Hh +x Hl tool )*sin(A)/sin(B)≥(t Sh -x Sl +x Sh tool )+Δt
Wherein Deltat is the reserved minimum gap, t H tool Is the distance between blade roots and tolerance zoneAt t Hl tool ,t Hh tool ，x H tool For a first positioning dimension of the blade body (2) of the tooling blade (8) at the blade root (1), the tolerance zone is x Hl tool ,x Hh tool Is the shroud spacing of the tooling blade (8) and the tolerance band is t Sl tool ,t Sh tool ，x S tool For a first positioning dimension of the blade body (2) at the shroud (3), the tolerance band thereof is x Sl tool ,x Sh tool ；
S232: supplementary tolerance t S tool With equation x Sh tool -x Sl tool ＝x Sh -x Sl Find tool x Sh tool ，t Sh tool Is a value of (2).
4. A method of assembling a shrouded turbine blade in accordance with claim 2 wherein: the method comprises the following steps of determining the relative interference quantum of the shroud between the blade body (9) with the number I and the blade body (9) with the number II:
s251, measuring the difference value between the actual distance between the blade root (1) and the shroud (3) and the theoretical distance of the tool blade (8) to be t He tool ，t Se tool The tool blade (8) and the blade body (9) with the number of one or two, and the error between the blade root spacing of the tool blade (8) and the theoretical value spacing is t He tool ＝t H tool -t H The error between the shroud spacing of the tool blade (8) and the theoretical value spacing is t Se tool ＝t S tool -t S ，t He ＝t' H12 -t H ，t' H12 The blade root center line spacing, t, when the blade bodies numbered one and two are adjacent Se ＝t′ S12 -t S ，t′ H12 The center line spacing of the shroud when the blade bodies numbered one and two are adjacent;
s252, calculating the relative interference magnitude value of the shroud bands of two adjacent blade main bodies (9) of the tool blade (8), wherein the specific calculation formula is as follows:
(t He +t he tool )*sin(A)/sin(B)＝(t Se +t Se tool +ΔX+ΔY)
t He *sin(A)/sin(B)-t Se ＝(t Se tool +ΔX+ΔY)-t He tool *sin(A)/sin(B)，
Wherein t is He *sin(A)/sin(B)-t Se -the relative interference of the shroud between the blade body (9) numbered one and the blade body (9) numbered two.
5. A method of assembling a shrouded turbine blade in accordance with claim 2 wherein: Δx and Δy were measured by a feeler gauge.
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|---|---|---|---|---|
| CN1877083A (en) * | 2006-07-06 | 2006-12-13 | 东方汽轮机厂 | Steam turbine moving vane shroud structure |
| CN102086781A (en) * | 2009-12-07 | 2011-06-08 | 阿尔斯托姆科技有限公司 | Turbine assembly |
| CN102156035A (en) * | 2011-03-24 | 2011-08-17 | 西安交通大学 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
| CN204572072U (en) * | 2015-01-28 | 2015-08-19 | 上海电气电站设备有限公司 | A kind of mounting structure of moving vane group of turbomachinery |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1877083A (en) * | 2006-07-06 | 2006-12-13 | 东方汽轮机厂 | Steam turbine moving vane shroud structure |
| CN102086781A (en) * | 2009-12-07 | 2011-06-08 | 阿尔斯托姆科技有限公司 | Turbine assembly |
| CN102156035A (en) * | 2011-03-24 | 2011-08-17 | 西安交通大学 | Turbine blade vibration characteristic testing and measuring device with shroud damping block and blade root wedged damping block |
| CN204572072U (en) * | 2015-01-28 | 2015-08-19 | 上海电气电站设备有限公司 | A kind of mounting structure of moving vane group of turbomachinery |
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Address after: 310000 Building 1, No. 608, Kangxin Road, Linping District, Hangzhou, Zhejiang Applicant after: Hangzhou Turbine Power Group Co.,Ltd. Address before: 310000 Building 1, No. 608, Kangxin Road, economic and Technological Development Zone, Yuhang District, Hangzhou City, Zhejiang Province Applicant before: HANGZHOU STEAM TURBINE Co.,Ltd. |
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