CN102108881B - Secondary final stage blade for half-RPM (Revolution per Minute) nuclear turbine - Google Patents
Secondary final stage blade for half-RPM (Revolution per Minute) nuclear turbine Download PDFInfo
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- CN102108881B CN102108881B CN2011100688376A CN201110068837A CN102108881B CN 102108881 B CN102108881 B CN 102108881B CN 2011100688376 A CN2011100688376 A CN 2011100688376A CN 201110068837 A CN201110068837 A CN 201110068837A CN 102108881 B CN102108881 B CN 102108881B
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Abstract
The invention discloses a secondary final stage blade for a half-RPM (Revolution per Minute) nuclear turbine, comprising a blade root and a blade body, wherein a shroud band is arranged at the top of the blade body; and the blade root, the blade body and the shroud band are of an integral structure. The blade body is of an irregular body formed by laminating a plurality of feature sections based on a specific rule; the blade body has an effective height H, a root diameter Dr, a feature parameter installation angle c1, a chord length b1, a maximum width w1, an axial width Xa and a sectional area A; the section laminating rule is that the sections are laminated along the direction of the blade height from the root end to the top end, each section transits continuously and smoothly, the relative value of the blade height H can be monotonically increased to 1.0 from 0.0, the installation angle c1 is monotonically reduced to 27.41 degrees from 78.02 degrees, the sectional area A is more than or equal to 1.0 and less than or equal to 9.267, the axial width Xa is more than or equal to 1.0 and less than or equal to 2.496, the chord length b1 is more than or equal to 1.0 and less than or equal to 1.186; and the maximum width w1 is more than or equal to 1.0 and less than or equal to 7.147. The secondary final stage blade has the advantages of higher economical efficiency and reliability, and can be applied to nuclear turbines with the back pressure of 3-6 kPa, the power of 1,000 MW to 1,700 MW and the rotating speed of 1,500 rpm.
Description
Technical field
The present invention relates to turbine blade, specifically the second last stage blade used of a kind of half speed nuclear steam turbine.It is complementary with " exhaust stage blade that the half speed nuclear steam turbine is used ", and being suitable for back pressure is that 3～6kPa, power are that 1000～1700MW, rotating speed are the nuclear steam turbine of 1500rpm.
Background technique
Nuclear power, with its clean, economic, safe overall characteristic, is regarded as one of main flow direction of future source of energy industry development.By the end of the year 2009, China's nuclear power projects building scale reaches 2,192 ten thousand kilowatts of totally 20 units, and China has become in the world and building the country that nuclear power is largest.Planning according to Chinese government's formulation, to the year two thousand twenty, the nuclear power electric motor power that China comes into operation will be brought up to 7,500 ten thousand kilowatts from 1,000 ten thousand kilowatts of current still less thaies, the nuclear power proportion that accounts for national electric power electric motor power will be brought up to 5% left and right from current 2% when the time comes, this will actively push forward China's Construction of Nuclear Electricity cause, meet the demand of the continuous growth of China's economy and social development to the energy, ensure energy supply and safety, protection of the environment, and realize China's greenhouse-gas control target, reach electricity industry structure optimization and sustainable development, promote China's synthesized economic strength, industrial technology level and international status.
Flourish along with China's Nuclear Electricity, the single-machine capacity of nuclear power generating sets is also progressively increasing, in from 1000MW to 1700MW, all having corresponding unit to be in operation or building.Unit capacity is larger, and the quantity of low pressure (LP) cylinder and steam turbine total length also can be larger, and this will greatly affect the steam turbine whole efficiency, yet the quantity of low pressure (LP) cylinder and steam turbine total length can adopt longer exhaust stage blade to effectively reduce.Therefore, develop the most important thing that the nuclear power low-pressure last stage blade of big-length has more become current each large turbine making enterprise.
Steam turbine is as one of the main force of nuclear power plant equipment, and the design of steam turbine directly affects the nuclear power generating sets working efficiency.The capacity of steam turbine is larger, and generating density is higher, requires its initial conditions higher, and exhaust annulus area is larger, and the final stage needed and second last stage blade are just longer, just higher to the blade material requirement of strength, and the pneumatic and VIBRATION DESIGN of blade is also just more difficult.In the design of steam turbine, the structural design of linear leaf, because of wide, the with high content of technology core key technology that becomes steam turbine of its technology related to.For a long time, the relevant major company of Abroad Turbine manufacture is externally highly confidential by nuclear power exhaust stage blade technology and the second last stage blade technology that is complementary with it, make China's nuclear power enterprise have to rely on them, the cost fancy price is to its imported product, even if like this, SUPPLY CHAIN also quite is critical, and this has seriously restricted the pace of progress of China's Nuclear Electricity; In addition, Nuclear Electricity concerns national comprehensive development lifeblood, unsuitable under one's control.For this reason, China turbine making enterprise has strengthened the R&D intensity of nuclear power blade, has also successfully broken the blockade on new techniques of external relevant major company, independent research " exhaust stage blade that the half speed nuclear steam turbine is used ".For lasting, the sound development of China's Nuclear Electricity, now be badly in need of the second last stage blade that independent development and " exhaust stage blade that the half speed nuclear steam turbine is used " are complementary.
Summary of the invention
The object of the invention is to: for " exhaust stage blade that the half speed nuclear steam turbine is used " of China's independent research, the second last stage blade that provides the half speed nuclear steam turbine be complementary with it of independent research to use, it has characteristics rational in infrastructure, that dynamic stress is low, and being applicable to back pressure is that 3～6kPa, power are that 1000～1700MW, rotating speed are the nuclear steam turbine of 1500rpm.
The present invention is for realizing its technical purpose, and the technological scheme of employing is:
The second last stage blade that a kind of half speed nuclear steam turbine is used, have blade root and blade, and described blade top is provided with shroud, and blade root, blade and shroud are overall structures; Described blade is the obform body that is coincided and form by a specific rule by some characteristic cross-sections; The profile molded line of described characteristic cross-section is the closed curve surrounded by inner arc curve and back of the body arc curve, has characteristic parameter established angle c1, chord length b1, maximum ga(u)ge W1, axial width Xa, sectional area A; The rule that coincides in cross section be along the high direction of leaf from butt to top the continuous smooth transition in each cross section; The effective height of described blade is that H, root footpath are Dr; The relative value of the high H of leaf is by 0.0 monotone increasing to 1.0; Corresponding with it, the absolute value of established angle c1 is reduced to 27.41 ° by 78.02 ° of dullnesses; The relative value Changing Pattern of sectional area A from the root cross section to top section is: 9.267 >=A >=1.0; The relative value Changing Pattern of axial width Xa from the root cross section to top section is: 2.496 >=Xa >=1.0; The relative value Changing Pattern of chord length b1 from the root cross section to top section is: 1.186 >=b1 >=1.0, the relative value Changing Pattern of the maximum ga(u)ge W1 from the root cross section to top section is: 7.147 >=W1 >=1.0.
Described shroud has back of the body arc working surface S1 and inner arc working surface P1, S1 and P1 are the planes be parallel to each other, when 1 rev/min of rotational speed N, shroud back of the body arc working surface S1 contacts with adjacent blades shroud inner arc working surface P1, produce pressure stress F 1, A1 is the distance between working surface S1, P1, and T1 is the distance between working surface S1, P1 geometrical center; B2 is meridian inclination angle, shroud top;
Described shroud thickness H1 meets relation:
10＜H1＜20mm；
Described shroud top meridian angle of inclination B 2 meets relation:
10
0≤B2≤30
0
The included angle B 1 of described back of the body arc working surface S1 and turbine rotor medial axis X-axis meets relation:
A1=T1*COSB1，30
0≤B1≤50
0；
The shroud contact rotational speed N 1 of described adjacent blades meets relation:
0≤N1≤1000 rev/min;
The pressure stress F 1 of described working surface meets relation:
0.005 the ultimate strength of<F1≤0.03 times material.
Described blade root is fir-tree root.
Described blade root is four tooth lineal shape fir-tree roots, and blade root platform has angle of inclination B 3;
Described blade root platform angle of inclination B 3 meets relation:
0
0≤B3≤5
0。
The invention has the beneficial effects as follows: the second last stage blade of said structure adopts advanced structural type-damped type to carry shroud, has excellent dynamic, pneumatic property, dynamic stress, damping and amortization, Security, rigidity and intensity; Blade root is adopted the lineal shape fir-tree root design of large carrying, and blade is combined with rotor firmly, is stablized, and is convenient to assembling, easy and simple to handle, quick; It has filled up China in the blank of nuclear steam turbine with time final blades technical elements, the needs of market to large capacity nuclear steam turbine have been met, the technical merit of China's blade is reached world-class levels, have higher Economy and reliability, improved the competitive ability of China's nuclear steam turbine in international market.
Summary of the invention
The present invention is further illustrated below in conjunction with accompanying drawing.
Fig. 1 is a kind of structural representation of the present invention.
Fig. 2 is the shroud structure schematic diagram.
Fig. 3 is the blade schematic cross-section.
Summary of the invention
Referring to Fig. 1, the present invention is comprised of blade root 3 and blade 2, and blade 2 tops are provided with shroud 1, and blade root 3, blade 2 and shroud 1 are overall structures, and they adopt suitable high strength alloy steel blade and rotor material integrally to manufacture.Blade pass is crossed blade root 3 and is arranged in the impeller groove on the rotating shaft cylindrical, and every circle race is installed 82 blades, after in the impeller groove in a week on impeller, all loading onto blade, has just formed the inferior final stage of steam turbine.
The carrier of now take is example as the half speed nuclear steam turbine of six steam discharge 1400MW grades, describe the present invention in detail, the optimum design back-pressure of this machine is 3.5kPa, in this design back-pressure scope, the effective height H of the second last stage blade blade that final scheme is determined is 997mm, root footpath Dr is 3110 mm, and its annulus area equals 12.86m
2.Take this root footpath and blade has completed the through-flow of low-voltage module as reference design.General design principle is that through-flow coupling design is carried out as a building block in three grades, low pressure end, for different types, by before design low pressure what, can realize the low pressure flow passage module of different capacity.
Fig. 1, Fig. 2 and Fig. 3, correlated variables of the present invention is defined as follows
:
H is the effective height of blade, i.e. distance between blade top section and blade root cross section.
Dr is the root footpath, namely blades installation after rotor, place, blade root cross section diameter of a circle (not marking in figure).
C1 is established angle, i.e. chord length b1 and the circumferentially angle of (Y-direction).
B1 is chord length, i.e. the distance on blade cross section inlet, outlet limit.
W1 is maximum ga(u)ge, i.e. blade cross section tangential width.
A is sectional area, i.e. the area of blade cross section (not marking in figure).
Xa is blade root cross section axial width.
H1 is shroud thickness.
S1 is shroud back of the body arc working surface.
P1 is shroud inner arc working surface.
A1 is the distance between shroud working surface S1, P1.
T1 is the distance between shroud working surface S1, P1 geometrical center.
B1 is the horizontal sextant angle of shroud back of the body arc working surface S1 and turbine rotor medial axis X-axis.
B2 is meridian inclination angle, shroud top.
B3 is the blade root platform inclination angle.
T is pitch, and namely adjacent two blade sustained height cross sections are at circumferential mounting distance.
O1 is blade root cross section outlet throat opening degree, i.e. the minimum range of Exit-edge and adjacent blade cross section back of the body arc.
1 ° of α is how much angles of outlet, sin
-1(O1/T).
W is the blade root axial width.
(1) blade design, along the pneumatic design in high several feature blade cross sections of leaf
Adopt special-purpose through-flow designing program, top section of the present invention following blade part several typical section molded line key element and mounting points have been designed, blade profile between each typical section adopts profile to be smoothly connected, feature along high each the basic blade profile of leaf is: root is the subsonic speed blade profile, middle part is Transonic Blade Profile, top is the supersonic speed blade profile, supersonic speed blade profile cross section is the Focal point and difficult point of blade design, in order to coordinate intensity and pneumatic restriction to blade profile, by the optimization to blade profile parameters, improve, finally substantially realized along ultimate strength stress design such as Ye Gao, meet simultaneously the requirement of blade root intensity and blade aeroperformance.The cross-section area of basic blade profile reduces along dullness highly, is turriform and changes, and the relative value of the high H of the leaf ratio of the high value of total leaf (a certain depth of section of blade with) is by 0.0 monotone increasing to 1.0; Corresponding with it, the absolute value of established angle c1 is reduced to 27.41 ° by 78.02 ° of dullnesses; The relative value of sectional area A from the root cross section to top section (top section is 1.0) Changing Pattern is: 9.267 >=A >=1.0; The relative value of axial width Xa from the root cross section to top section (top section is 1.0) Changing Pattern is: 2.496 >=Xa >=1.0; The relative value of chord length b1 from the root cross section to top section (top section is 1.0) Changing Pattern is: 1.186 >=b1 >=1.0; The relative value of maximum ga(u)ge W1 from the root cross section to top section (top section is 1.0) Changing Pattern is: 7.147 >=W1 >=1.0.Basic blade profile is along highly dull twisting formation, and how much angle α 1o edges of the outlet of basic blade profile highly dullness controllably reduce.
(2) linkage structure of shroud structure-large deformation damping vane design
The shroud thickness had a style of one's own with blade is H1, and thickness H1 meets relation: 10mm<H1<20mm, and meridian angle of inclination B 2 is arranged at the shroud top, and shroud top meridian angle of inclination B 2 meets relation: 10
0≤ B2≤30
0Carry horizontal channelling and radial flow that shroud structure has stoped the leaf top aspect pneumatic, when 1 rev/min of about rotational speed N, shroud back of the body arc working surface S1 contacts with adjacent blades shroud inner arc working surface P1, produce larger pressure stress F 1, contact rotational speed N 1 meets relation: 0≤N1≤1000 rev/min, and working surface pressure stress F 1 meets relation: the ultimate strength of 0.005<F1≤0.03 times material; The included angle B 1 of shroud inner arc working surface P1 and turbine rotor medial axis X-axis meets relation: A1=T1*COSB1,30
0≤ B1≤50
0Shroud increases blade rigid when blade working, make the free vane under static state when rated speed, limit significantly the twist recovery on leaf top, forms whole circle restraining structure, decrease blade dynamic stress.
(3) blade root design
Blade root is four tooth lineal shape fir-tree roots, and blade root platform has angle of inclination B 3, and blade root platform angle of inclination B 3 meets relation: 0
0≤ B3≤5
0.This structure can make that blade is simple, fast to be assemblied on rotor, and the blade after assembling with rotor, be combined more firm, stablize.
Protection scope of the present invention is not limited to above-described embodiment, and above-described embodiment is in the numerous preferred embodiments of the present invention, and protection scope of the present invention should expand to the disclosed feature of claims or their combination.
Claims (3)
1. the second last stage blade that the half speed nuclear steam turbine is used, have blade root and blade, and described blade top is provided with shroud, and blade root, blade and shroud are overall structures; Described blade is the obform body that is coincided and form by a specific rule by some characteristic cross-sections; The profile molded line of described characteristic cross-section is the closed curve surrounded by inner arc curve and back of the body arc curve, has characteristic parameter established angle c1, chord length b1, maximum ga(u)ge W1, axial width Xa, sectional area A; The rule that coincides in cross section be along the high direction of leaf from butt to top the continuous smooth transition in each cross section; It is characterized in that, the effective height of described blade is that H, root footpath are Dr; The relative value of the high H of leaf is by 0.0 monotone increasing to 1.0; Corresponding with it, the absolute value of established angle c1 is reduced to 27.41 ° by 78.02 ° of dullnesses; The relative value Changing Pattern of sectional area A from the root cross section to top section is: 9.267 >=A >=1.0; The relative value Changing Pattern of axial width Xa from the root cross section to top section is: 2.496 >=Xa >=1.0; The relative value Changing Pattern of chord length b1 from the root cross section to top section is: 1.186 >=b1 >=1.0, and the relative value Changing Pattern of the maximum ga(u)ge W1 from the root cross section to top section is: 7.147 >=W1 >=1.0;
Described shroud has back of the body arc working surface S1 and inner arc working surface P1, S1 and P1 are the planes be parallel to each other, when 1 rev/min of rotational speed N, shroud back of the body arc working surface S1 contacts with adjacent blades shroud inner arc working surface P1, produce pressure stress F 1, A1 is the distance between working surface S1, P1, and T1 is the distance between working surface S1, P1 geometrical center; B2 is meridian inclination angle, shroud top;
Described shroud thickness H1 meets relation:
10＜H1＜20mm；
Described shroud top meridian angle of inclination B 2 meets relation:
10
0≤B2≤30
0
The included angle B 1 of described back of the body arc working surface S1 and turbine rotor medial axis X-axis meets relation:
A1=T1*COSB1，30
0≤B1≤50
0；
The shroud contact rotational speed N 1 of described adjacent blades meets relation:
0≤N1≤1000 rev/min;
The pressure stress F 1 of described working surface meets relation:
0.005 the ultimate strength of<F1≤0.03 times material.
2. the second last stage blade used of half speed nuclear steam turbine according to claim 1, is characterized in that, described blade root is fir-tree root.
3. the second last stage blade used of half speed nuclear steam turbine according to claim 2, is characterized in that, described blade root is four tooth lineal shape fir-tree roots, and blade root platform has angle of inclination B 3;
Described blade root platform angle of inclination B 3 meets relation:
0
0≤B3≤5
0。
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100688376A CN102108881B (en) | 2011-03-22 | 2011-03-22 | Secondary final stage blade for half-RPM (Revolution per Minute) nuclear turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100688376A CN102108881B (en) | 2011-03-22 | 2011-03-22 | Secondary final stage blade for half-RPM (Revolution per Minute) nuclear turbine |
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|---|---|
| CN102108881A CN102108881A (en) | 2011-06-29 |
| CN102108881B true CN102108881B (en) | 2013-11-27 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240054B (en) * | 2014-07-07 | 2017-03-22 | 上海电气电站设备有限公司 | Penultimate-stage moving blade for half-speed high-capacity nuclear turbine |
| CN104775853B (en) * | 2015-04-16 | 2017-02-22 | 东方电气集团东方汽轮机有限公司 | Penultimate-stage moving blade for feed pump turbines |
| CN106844839B (en) * | 2016-12-14 | 2020-01-31 | 中国长江动力集团有限公司 | Method for optimizing the profile of a steam turbine blade |
| CN108194149B (en) * | 2018-02-11 | 2023-10-13 | 杭州汽轮机股份有限公司 | High-efficient rotary drum level moving blade of industrial steam turbine |
| 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 |
| CN111706400B (en) * | 2020-06-19 | 2023-03-31 | 杭州汽轮动力集团有限公司 | Penult-stage self-locking moving blade of gas turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200961492Y (en) * | 2006-08-25 | 2007-10-17 | 哈尔滨汽轮机厂有限责任公司 | Large scale full speed nuclear steam turbine second last stage blade |
| CN201581934U (en) * | 2009-12-21 | 2010-09-15 | 上海电气电站设备有限公司 | Half-speed high-capacity nuclear turbine last-stage movable blade |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7946821B2 (en) * | 2007-07-16 | 2011-05-24 | Nuovo Pignone Holdings, S.P.A. | Steam turbine rotating blade |
| JP2010216321A (en) * | 2009-03-16 | 2010-09-30 | Hitachi Ltd | Moving blade of steam turbine, and steam turbine using the same |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200961492Y (en) * | 2006-08-25 | 2007-10-17 | 哈尔滨汽轮机厂有限责任公司 | Large scale full speed nuclear steam turbine second last stage blade |
| CN201581934U (en) * | 2009-12-21 | 2010-09-15 | 上海电气电站设备有限公司 | Half-speed high-capacity nuclear turbine last-stage movable blade |
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