CN105909316A - Blade body structure of super-long last-stage rotor blade of large-scale steam turbine - Google Patents
Blade body structure of super-long last-stage rotor blade of large-scale steam turbine Download PDFInfo
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- CN105909316A CN105909316A CN201610221672.4A CN201610221672A CN105909316A CN 105909316 A CN105909316 A CN 105909316A CN 201610221672 A CN201610221672 A CN 201610221672A CN 105909316 A CN105909316 A CN 105909316A
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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
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- Engineering & Computer Science (AREA)
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- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention discloses a blade body structure of a super-long last-stage rotor blade of a large-scale steam turbine. The blade body molded line of the blade is a variable cross section twisting molded line formed by superposition of a plurality of characteristic cross sections according to a specific rule. The profile molded lines of the characteristic cross sections are closed curves enclosed by inner arc curves and back arc curves, and have characteristic parameters of installing angle c1, chord length b1, maximum thickness w1, axial width Xa and sectional area A. The superposition rule of the cross sections is that the cross sections are continuously and smoothly transited from root to top in a blade height direction. The relative value of the blade height H is monotonically increased from 0.0 to 1.0. Accordingly, the absolute value c1 of the installing angle is monotonically decreased from 81.692 to 5.875. The relative value change rule of the chord length b1 from the root cross section to the top cross section is that 1.67>=b1>=1.0. The relative value change rule of the maximum thickness w1 from the root cross section to the top cross section is that 5.56>=w1>=1.0. The relative value change rule of the axial width Xa from the root cross section to the top cross section is that 12.146>=Xa>=1.0. The relative value change rule of the area A from the root cross section to the top cross section is that 13.538>=A>=1.0.
Description
Technical field
The invention belongs to steam turbine flow technology field, relate to wet cooling gas turbine final stage moving blade molded line,
Specifically a kind of wet cooling gas turbine overlength final stage moving blade, develops for 1300MW wet cooling gas turbine, with
Time to be applicable to power grade be 4F-1200～1400MW wet cooling gas turbine.
Background technology
Along with national economy grows continuously and fast, the nationwide demand to electricity consumption the most quickly increases, medium
The generating set of capacity does not the most adapt to the requirement of electricity needs and environmental protection and energy saving.Therefore develop high parameter,
Large Copacity, efficiently, Environmental-protection coal-fired power station be that power industry faces and subject matter anxious to be resolved, limit
One of unit high capacity principal element processed is exactly the length of exhaust stage blade.Grasp high initial conditions and Large Copacity
The countries in the world turbine making business of coal fired power plant technology is few in number, owing to being come into leaves by steam turbine last stage
The restriction of sheet, generally use different exhaust casing numbers and modularized design can design from 600MW～
The various steam turbine of 1300MW.
The final stage moving blade of large-size steam turbine is the longest, is also one of topmost difficult point of Design of Steam Turbine.Mesh
Before, all there is the blade series of oneself in Ge great turbine making factory in the world.As: GE company has
In 3600rpm blade series, the longest blade is 40 inches (Ti), in 3000rpm blade series,
The longest blade is 48 inches of steel blades.Hitachi and Toshiba are on the blade series basis of GE company
On, have developed 48 inches of steel blades of 3000rpm respectively.The longest 3000rpm of Alstom
Blade be 46 inches of steel blades.4F-1200～1400MW wet cooling gas turbine
Being the type of China's independent development, its a length of 55 inches of grades of final stage moving blade, are the most in the world
The longest, do not have any precedent to use for reference, it is necessary to base oneself upon independent development.
Summary of the invention
The purpose of the present invention, be to provide one being applicable to power grade is the clammy vapour of 4F-1200～1400MW
The blade structure of the final stage moving blade of turbine, its a length of 55 inches of grades, through meticulously calculating, repeatedly trying
Test, constantly revise, be finally defined below technical scheme:
The blade structure of a kind of large-size steam turbine overlength final stage moving blade, this blade has integrally-built leaf
Body, blade root, shroud, lacing wire boss, the molded line of described blade is by specific rule by some characteristic cross-sections
The variable cross-section distortion molded line that rule coincides, the profile molded line of described characteristic cross-section is by inner arc curve and the back of the body
The closed curve that curved line surrounds, has a characteristic parameter: established angle c1, chord length b1, maximum gauge
W1, axial width Xa, sectional area A；It is characterized in that, the rule that coincides in cross section is, along leaf height direction
From butt to top, the continuous and derivable transition of each cross section；The relative value of leaf height H is monotonicallyd increase up to by 0.0
1.0；Corresponding, the absolute value c1 of established angle is reduced to 5.875 by 81.692 dullnesses；From root cross section
Relative value's Changing Pattern of chord length b1 to top section is: 1.67 >=b1 >=1.0；From root cross section to top section
Relative value's Changing Pattern of maximum gauge w1 be: 5.56 >=w1 >=1.0；From root cross section to top section
Relative value's Changing Pattern of axial width Xa is: 12.146 >=Xa >=1.0；Face from root cross section to top section
Relative value's Changing Pattern of long-pending A is: 13.538 >=A >=1.0；
Correlated variables defines:
The length of the blade portion of the effective depth of H blade, i.e. blade: blade top section is cut with blade root
Distance between face；
B1 chord length: blade cross section is into and out of the distance on vapour limit；
C1 blade angle: chord length b1 and the angle of Y-direction；
Xa axial width: blade root cross section axial width；
W1 maximum gauge: blade cross section tangential width.
The blade molded line of this blade is made up of 42 characteristic cross section overlappings, wherein has 3 crucial cross sections, i.e.
It is positioned at the section B-B at leaf high 4.12%, is positioned at the M-M cross section at leaf high 50.02%, be positioned at leaf high
Y-Y cross section at 95.71%, these crucial control point, cross section coordinates are as follows:
A length of 55 inches of this blade.
Proving through simulation test, the aeroperformance of above-mentioned blade fully meets design requirement.
Accompanying drawing explanation
Fig. 1 is blade molded line front view.
Fig. 2 is blade molded line top view.
Fig. 3 is blade section feature parameter schematic diagram.
Fig. 4 is blade profile overlapping figure.
Detailed description of the invention
The present invention provides a kind of turbine overlength moving vane, and it is crucial and difficult point is blade molded line, design
Molded line each cross section aeroperformance excellent, reasonable along molded line short transverse area change, molded line characteristic cross section
High-order fairing, subsonics, across sound, Supersonic Flow excellent, the 55 inches of final stages designed and developed with it
Blade blade stress is little, meets the strength specification structural requirement of current material.Its structural element is different from existing
Having product, the leading indicator of its technical performance meets or exceeds existing like product, and whole synthesis performance is excellent
In existing like product.
This technical problem to be solved of the present invention and the technical scheme used:
(1) blade profile characterisitic parameter design: based on boundary condition needed for engineering, determine the aerofluxus of this set blade profile
Velocity interval, in 200-250m/s scope, uses root footpath scope in 1800-2000mm, maximum leaving area
Up to 15m2, effective leaf height is less than or equal to 1400mm.Maximum use Mach number is less than 2.2.
Use streamline curvature method to complete the through-flow coupling of low-voltage module, determine the fundamental characteristics ginseng of this set blade profile
Number, geometry flow inlet angle is in the range of 73-176 °, and effective geometry angle is in the range of 36.5-7.3 °.
(2) blade design: this set blade profile uses blade profile special 3D sculpting software acquired character cross section 42
Individual, revise each area of section Changing Pattern according to requirement of strength design, be met the blade profile of requirement of strength
Area distributions.Use full ternary CFD to analyze software and leaf-level is carried out aerodynamic analysis, according to leaf-level
Flow feature, local directed complete set blade profile contour line, it is thus achieved that meet root subsonic flow, middle part mixed flow
Dynamic, each blade profile cross section of top Supersonic Flow.
(3) blade profile optimization: use high-order Bezier curve and three rank C SPLs to this set blade profile 42
Characteristic cross section has carried out fairing of line and blade local modification, uses full ternary to optimize software Design3D to movable vane
Each cross section molded line carries out aeroperformance optimization, it is thus achieved that geometrically high-order fairing each characteristic cross section, simultaneously
Aerodynamic characteristic is excellent.
(4) blade profile feature: turbine overlength final stage moving blade molded line is that variable cross-section distorts molded line, molded line
Established angle, chord length, axial width and sectional area are seamlessly transitted to top by root, and described molded line is by some
Characteristic cross-section coincides by a specific rule and forms, the profile molded line of described characteristic cross-section be by inner arc curve and
Carrying on the back the closed curve that curved line surrounds, its appearance profile is shown in Fig. 1, Fig. 2, has characteristic parameter and (sees figure
3): established angle c1, chord length b1, maximum gauge w1, axial width Xa, sectional area A；Changing of cross section
Conjunction rule is, along leaf height direction from butt to top, and the continuous and derivable transition of each cross section；Leaf height H's is relative
Value is monotonicallyd increase up to 1.0 by 0.0；Corresponding, the absolute value c1 of established angle is reduced to by 81.692
5.875；Relative value's Changing Pattern of chord length b1 from root cross section to top section is: 1.67 >=b1 >=1.0；
Relative value's Changing Pattern of the maximum gauge w1 from root cross section to top section is: 5.56 >=w1 >=1.0；From
Root cross section to relative value's Changing Pattern of the axial width Xa of top section is: 12.146 >=Xa >=1.0；From root
Cross section to relative value's Changing Pattern of the area A of top section is: 13.538 >=A >=1.0；
Correlated variables defines:
The length of the blade portion of the effective depth of H blade, i.e. blade: blade top section is cut with blade root
Distance between face；
B1 chord length: blade cross section is into and out of the distance on vapour limit；
C1 blade angle: chord length b1 and the angle of Y-direction；
Xa axial width: blade root cross section axial width；
W1 maximum gauge: blade cross section tangential width.
(5) blade profile key cross section: this set molded line relates to 42 characteristic cross sections altogether, 3 keys therein are cut
Face relative altitude and point range coordinate are shown in Table 1, table 2.The profile of 3 characteristic cross-sections that the art of this patent relates to
Shape is key technology, is claimed.Theoretical contour discrete point coordinate (X, Y) of each characteristic cross-section
Describe.With the discrete point of the theoretical contour of each characteristic cross-section as the center of circle, radius is that 0.5mm makees envelope circle
Involved contour shape scope (referred to as tolerance range) is protected.On the basis of theoretical contour, pass through
Shape and corresponding tolerance range obtained by analogy basins or rotation or translation are all protected by this patent.
Table 1 molded line key cross section molded line relative altitude
| Cross section title | Leaf high altitude relatively |
| B-B | 4.12% |
| M-M | 50.02% |
| Y-Y | 95.71% |
Table 2 crucial control point, cross section coordinate
(6) blade profile characteristic cross section overlapping figure: 42 characteristic cross section overlapping figures of blade profile are shown in Fig. 4, this patent skill
The locus (shaping rule) of the contour shape of the characteristic cross-section that art relates to is key technology, and request is protected
Protect.With the Static-state Space theoretical contour of each characteristic cross-section as the center of circle, radius is that 0.5mm makees envelope circle institute
The spatial form entity scope that the face formed and shaping rule are constituted is protected.
The each cross section molded line original shape provided by the present invention or the TWO-DIMENSIONAL CASCADE making analogy basins or Rotation Design will
There is excellent aerodynamic characteristic.Overlap by this and can design air flue height based on molded line less than or equal to 1400
Turbine final stage moving blade series, designed final stage moving blade not only has the aerodynamic characteristic of advanced person, and
The requirement of strength vibration can be met.
Claims (3)
1. a blade structure for large-size steam turbine overlength final stage moving blade, this blade has integrally-built
Blade, blade root, shroud, lacing wire boss, the molded line of described blade is specific by one by some characteristic cross-sections
Variable cross-section that rule coincides distortion molded line, the profile molded line of described characteristic cross-section be by inner arc curve and
Carry on the back the closed curve that curved line surrounds, there is characteristic parameter: established angle c1, chord length b1, maximum gauge
W1, axial width Xa, sectional area A；It is characterized in that, the rule that coincides in cross section is, along leaf height direction
From butt to top, the continuous and derivable transition of each cross section；The relative value of leaf height H is monotonicallyd increase up to 1.0 by 0.0；
Corresponding, the absolute value c1 of established angle is reduced to 5.875 by 81.692 dullnesses；From root cross section to top
Relative value's Changing Pattern of chord length b1 in cross section is: 1.67 >=b1 >=1.0；From root cross section to top section
Relative value's Changing Pattern of big thickness w1 is: 5.56 >=w1 >=1.0；Axial from root cross section to top section
Relative value's Changing Pattern of width Xa is: 12.146 >=Xa >=1.0；Area A from root cross section to top section
Relative value's Changing Pattern be: 13.538 >=A >=1.0；
Correlated variables defines:
The length of the blade portion of the effective depth of H blade, i.e. blade: blade top section is cut with blade root
Distance between face；
B1 chord length: blade cross section is into and out of the distance on vapour limit；
C1 blade angle: chord length b1 and the angle of Y-direction；
Xa axial width: blade root cross section axial width；
W1 maximum gauge: blade cross section tangential width.
2. the blade structure of large-size steam turbine overlength final stage moving blade as claimed in claim 1, its feature
Being, the blade molded line of this blade is made up of 42 characteristic cross section overlappings, wherein has 3 crucial cross sections,
I.e. it is positioned at the section B-B at leaf high 4.12%, is positioned at the M-M cross section at leaf high 50.02%, be positioned at leaf high
Y-Y cross section at 95.71%, these crucial control point, cross section coordinates are as follows:
3. the blade structure of large-size steam turbine overlength final stage moving blade as claimed in claim 1, its feature
It is, a length of 55 inches of this blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610221672.4A CN105909316A (en) | 2016-04-11 | 2016-04-11 | Blade body structure of super-long last-stage rotor blade of large-scale steam turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610221672.4A CN105909316A (en) | 2016-04-11 | 2016-04-11 | Blade body structure of super-long last-stage rotor blade of large-scale steam turbine |
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| Publication Number | Publication Date |
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| CN105909316A true CN105909316A (en) | 2016-08-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610221672.4A Pending CN105909316A (en) | 2016-04-11 | 2016-04-11 | Blade body structure of super-long last-stage rotor blade of large-scale steam turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109101722A (en) * | 2018-08-09 | 2018-12-28 | 东方电气集团东方汽轮机有限公司 | A kind of turbine blade composite molding design method |
| CN109117552A (en) * | 2018-08-09 | 2019-01-01 | 东方电气集团东方汽轮机有限公司 | A kind of turbine blade varying load Method for Flow Pattern Design |
| CN109707462A (en) * | 2018-12-28 | 2019-05-03 | 东方电气集团东方汽轮机有限公司 | A kind of full rotary speed steam turbine 1450mm titanium alloy final blades |
Citations (3)
| 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 |
| CN101117895A (en) * | 2007-09-06 | 2008-02-06 | 东方电气集团东方汽轮机有限公司 | Variable-speed turbine final stage moving vane |
| CN105401982A (en) * | 2015-12-14 | 2016-03-16 | 东方电气集团东方汽轮机有限公司 | Tail-stage movable blade body structure for half-rotating-speed nuclear turbine |
-
2016
- 2016-04-11 CN CN201610221672.4A patent/CN105909316A/en active Pending
Patent Citations (3)
| 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 |
| CN101117895A (en) * | 2007-09-06 | 2008-02-06 | 东方电气集团东方汽轮机有限公司 | Variable-speed turbine final stage moving vane |
| CN105401982A (en) * | 2015-12-14 | 2016-03-16 | 东方电气集团东方汽轮机有限公司 | Tail-stage movable blade body structure for half-rotating-speed nuclear turbine |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109101722A (en) * | 2018-08-09 | 2018-12-28 | 东方电气集团东方汽轮机有限公司 | A kind of turbine blade composite molding design method |
| CN109117552A (en) * | 2018-08-09 | 2019-01-01 | 东方电气集团东方汽轮机有限公司 | A kind of turbine blade varying load Method for Flow Pattern Design |
| CN109101722B (en) * | 2018-08-09 | 2022-03-22 | 东方电气集团东方汽轮机有限公司 | Composite forming design method for turbine blade |
| CN109117552B (en) * | 2018-08-09 | 2022-04-12 | 东方电气集团东方汽轮机有限公司 | Turbine blade variable load flow pattern design method |
| CN109707462A (en) * | 2018-12-28 | 2019-05-03 | 东方电气集团东方汽轮机有限公司 | A kind of full rotary speed steam turbine 1450mm titanium alloy final blades |
| CN109707462B (en) * | 2018-12-28 | 2022-03-18 | 东方电气集团东方汽轮机有限公司 | 1450mm titanium alloy final-stage blade of full-speed steam turbine |
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| CB02 | Change of applicant information |
Inventor after: Zhou Xianding Inventor after: Chen Tiening Inventor after: Pu Shouwu Inventor after: Gou Xiaoping Inventor after: Fang Yu Inventor after: Fan Xiaoping Inventor after: Zhong Gangyun Inventor after: Wu Qilin Inventor after: Fan Zhifei Inventor after: Yin Mingyan Inventor after: Wang Shunde Inventor after: Du Xiaoqin Inventor before: Zhou Xianding Inventor before: Chen Tiening Inventor before: Pu Shouwu Inventor before: Gou Xiaoping Inventor before: Fang Yu Inventor before: Fan Xiaoping Inventor before: Zhong Gangyun Inventor before: Wu Qilin Inventor before: Fan Zhifei Inventor before: Yin Mingyan Inventor before: Wang Shunde Inventor before: Du Xiaoqin |
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Application publication date: 20160831 |