CN106884682B - A kind of large high-temperature high pressure turbine pump blade design method - Google Patents

A kind of large high-temperature high pressure turbine pump blade design method Download PDF

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Publication number
CN106884682B
CN106884682B CN201710107375.1A CN201710107375A CN106884682B CN 106884682 B CN106884682 B CN 106884682B CN 201710107375 A CN201710107375 A CN 201710107375A CN 106884682 B CN106884682 B CN 106884682B
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blade
unit
coefficient
millimeter
degree
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CN106884682A (en
Inventor
司翔宇
王秀礼
朱荣生
卢永刚
钟伟源
李扬
张国玉
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Jiangsu University
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Jiangsu University
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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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The present invention provides a kind of large high-temperature high pressure turbine pump blade design methods to be determined the main geometric parameters of blade using several relational expressions based on roturbo impeller outer diameter, be included mainly：Blade fluid flow angle β '1, vane inlet angle beta1, blade exit angle beta2, bucket flat segment thickness s1, blade bending portion thickness s2, blade working face thickness b1, vacuum side of blade thickness b2, blade section length L1、L2、L3, flank radius R1, back radius of curvature R2.The present invention provides a kind of method quickly designing novel turbine pump blade, saves manpower, improves lift and efficiency, widened the range of high efficient district, and improve the operational reliability of roturbo.

Description

A kind of large high-temperature high pressure turbine pump blade design method
Technical field
The invention belongs to pump design and manufacturing field, it is related to a kind of design of roturbo blade, is particularly suitable for high temperature Hyperbaric environment.
Background technology
Roturbo is a kind of Reversible Hydraulic Machinery, is used by wide hair in industries such as power generations, however existing roturbo is used Blade service efficiency under high temperature and high pressure environment is not high, and a kind of blade of novel inner hollow can be in high temperature and high pressure environment Lower stable operation；However for the design of roturbo blade, existing method is mainly set using unitary, binary and Three Yuan theory Blade is counted, the flowing in impeller is made a series of it is assumed that with the flowing with different rules, instead of the complexity stream in impeller Dynamic, this design method is more complicated, and the blade for this novel inner hollow and is not suitable for.
Number of patent application 201610059473.8 discloses a kind of blade design method, cavitation inception can be made to be pushed away Late, cavitation inception performance, but the effect unobvious under high temperature and high pressure condition are improved.Number of patent application is 201610259479.X public A kind of hollow blade wall thickness control method has been opened, but has not provided the control method of blade other parameters, and has not been suitable for high temperature Hyperbaric environment.
Invention content
In order to overcome problem above, the present invention to be improved traditional roturbo with blade design method, provide a kind of new Roturbo Blade Optimization Design method.The geometric parameter of blade can be adjusted in the present invention, reach setting for roturbo The effect that meter performance curve is overlapped with the performance curve of requirement, the occasion especially suitable for high temperature and pressure.The present invention is with roturbo Based on impeller outer diameter, it is L that the section of blade, which includes length from the wing tail to wing tip,1、L2、L3Section, the working face of the blade It is equipped with cavity between the back side, the main geometric parameters of blade are determined using following relational expression, include mainly：Blade liquid Stream angle beta '1, vane inlet angle beta1, blade exit angle beta2, bucket flat segment thickness s1, blade bending portion thickness s2, blade work Make face thickness b1, vacuum side of blade thickness b2, blade section length L1、L2、L3, flank radius R1, back radius of curvature R2。
The technical scheme is that：
A kind of large high-temperature high pressure turbine pump blade design method, the design method meet：
β1=Δ β+β1′(4)
b1=b2=k1s1 (10)
L1=k2L2=k3L3 (13)
In formula：β'1a--- blade front shroud edge fluid flow angle, unit：Degree；
β'1b--- fluid flow angle at blade central axes, unit：Degree；
β'1c--- blade back shroud edge fluid flow angle, unit：Degree
K --- correction factor；
v0--- impeller inlet axis plane velocity, unit：Meter per second；
u1--- calculate the peripheral speed of point liquid, unit：Meter per second；
β1--- inlet blade angle, unit：Degree；
Δ β --- high incidence, unit：Degree；
β1' --- blade fluid flow angle, unit：Degree；
β2--- outlet blade angle, unit：Degree；
vm2--- impeller outlet axis plane velocity, unit：Meter per second；
ω2--- blade exit liquid relative velocity, unit：Meter per second；
H --- single-stage lift, unit：Rice；
N --- rotating speed, unit：Rev/min；
ns--- specific speed；
Q --- flow, unit：Cube meter per second；
A1--- coefficient；
A2--- coefficient；
D2--- impeller outlet diameter, unit：Rice；
Z --- the number of blade；
s1--- bucket flat segment thickness, unit：Millimeter；
s2--- blade bending portion thickness, unit：Millimeter；
b1--- blade working face thickness, unit：Millimeter；
b2--- vacuum side of blade thickness, unit：Millimeter；
k1--- coefficient；
kL--- coefficient, it is related with revolution；
L1--- bucket front cross-sectional length, unit：Millimeter；
L2--- middle part of blade cross-sectional length, unit：Millimeter；
L3--- bucket rear cross-sectional length, unit：Millimeter；
k2--- coefficient；
k3--- coefficient；
R1--- flank radius, unit：Rice；
R2--- back radius of curvature, unit：Rice.
Further, the adjusted coefficient K takes 0.9~1.1.
Further, the high incidence Δ β takes 5 °~20 °.
Further, the coefficient k2Take 0.3~0.7.
Further, the coefficient k3Take 0.4~0.7.
Formula (1), (2), (3) are blade fluid flow angle β '1The method that difference calculates point, by a calculating point liquid peripheral speed u1 It influences, COEFFICIENT K is modified.
The beneficial effects of the invention are as follows：
A kind of method quickly designing novel turbine pump blade is provided, manpower is saved, improves lift and efficiency, widen The range of high efficient district, and improve the operational reliability of roturbo.
Description of the drawings
Fig. 1 is the plane figure of the turbine of one embodiment of the invention.
Fig. 2 is the sectional view of the roturbo blade of one embodiment of the invention.
In figure：1. wing tail, is connected with back shroud；2. wing tip is connected with front shroud；3. working face；4. the back side.
Specific implementation mode
The invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 is the plane figure of the turbine of one embodiment of the invention.Fig. 2 is the roturbo of one embodiment of the invention With the sectional view of blade, the wing tail 1 is connected with turbine back shroud, and the wing tip 2 is connected with turbine front shroud, working face 3 It is set between wing tail 1 and wing tip 2 with the back side 4.
The present invention determines the main geometric parameters of blade using following relational expression based on roturbo impeller outer diameter It counts, includes mainly：Blade fluid flow angle β '1, vane inlet angle beta1, blade exit angle beta2, bucket flat segment thickness s1, blade is curved Bent portions thickness s2, blade working face thickness b1, vacuum side of blade thickness b2, blade section length L1、L2、L3, work face curvature half Diameter R1, back radius of curvature R2。
A kind of large high-temperature high pressure turbine pump blade design method, the design method meet：
β1=Δ β+β '1 (4)
b1=b2=k1s1 (10)
L1=k2L2=k3L3 (13)
In formula：β'1a--- blade front shroud edge fluid flow angle, unit：Degree；
β'1b--- fluid flow angle at blade central axes, unit：Degree；
β'1c--- blade back shroud edge fluid flow angle, unit：Degree
K --- correction factor；
v0--- impeller inlet axis plane velocity, unit：Meter per second；
u1--- calculate the peripheral speed of point liquid, unit：Meter per second；
β1--- inlet blade angle, unit：Degree；
Δ β --- high incidence, unit：Degree；
β′1--- blade fluid flow angle, unit：Degree；
β2--- outlet blade angle, unit：Degree；
vm2--- impeller outlet axis plane velocity, unit：Meter per second；
ω2--- blade exit liquid relative velocity, unit：Meter per second；
H --- single-stage lift, unit：Rice；
N --- rotating speed, unit：Rev/min；
ns--- specific speed；
Q --- flow, unit：Cube meter per second；
A1--- coefficient；
A2--- coefficient；
D2--- impeller outlet diameter, unit：Rice；
Z --- the number of blade；
s1--- bucket flat segment thickness, unit：Millimeter；
s2--- blade bending portion thickness, unit：Millimeter；
b1--- blade working face thickness, unit：Millimeter；
b2--- vacuum side of blade thickness, unit：Millimeter；
k1--- coefficient；
kL--- coefficient, it is related with revolution；
L1--- bucket front cross-sectional length, unit：Millimeter；
L2--- middle part of blade cross-sectional length, unit：Millimeter；
L3--- bucket rear cross-sectional length, unit：Millimeter；
k2--- coefficient；
k3--- coefficient；
R1--- flank radius, unit：Rice；
R2--- back radius of curvature, unit：Rice.
The adjusted coefficient K takes 0.9~1.1.
The high incidence Δ β takes 5 °~20 °.
The coefficient k2Take 0.3~0.7.
The coefficient k3Take 0.4~0.7.
Formula (1), (2), (3) are blade fluid flow angle β '1The method that difference calculates point, by a calculating point liquid peripheral speed u1 It influences, COEFFICIENT K is modified.
It is illustrated above with reference to what several embodiments were made for patent of the present invention, but patent of the present invention is not limited to Also include the other embodiments or variation within the scope of inventional idea of the present invention in above-described embodiment.

Claims (5)

1. a kind of large high-temperature high pressure turbine pump blade design method, which is characterized in that the section of the blade is from wing tail (1) To wing tip (2) include length be L1、L2、L3Section, between the working face (3) and the back side (4) of the blade be equipped with cavity, institute State design method satisfaction：
β1=Δ β+β '1 (4)
b1=b2=k1s1 (10)
L1=k2L2=k3L3 (13)
In formula：β'1a--- blade front shroud edge fluid flow angle, unit：Degree；
β'1b--- fluid flow angle at blade central axes, unit：Degree；
β'1c--- blade back shroud edge fluid flow angle, unit：Degree
K --- correction factor；
v0--- impeller inlet axis plane velocity, unit：Meter per second；
u1--- calculate the peripheral speed of point liquid, unit：Meter per second；
β1--- inlet blade angle, unit：Degree；
Δ β --- high incidence, unit：Degree；
β′1--- blade fluid flow angle, unit：Degree；
β2--- outlet blade angle, unit：Degree；
vm2--- impeller outlet axis plane velocity, unit：Meter per second；
ω2--- blade exit liquid relative velocity, unit：Meter per second；
H --- single-stage lift, unit：Rice；
N --- rotating speed, unit：Rev/min；
ns--- specific speed；
Q --- flow, unit：Cube meter per second；
A1--- coefficient；
A2--- coefficient；
D2--- impeller outlet diameter, unit：Rice；
Z --- the number of blade；
s1--- bucket flat segment thickness, unit：Millimeter；
s2--- blade bending portion thickness, unit：Millimeter；
b1--- blade working face thickness, unit：Millimeter；
b2--- vacuum side of blade thickness, unit：Millimeter；
k1--- coefficient；
kL--- coefficient, it is related with revolution；
L1--- bucket front cross-sectional length, unit：Millimeter；
L2--- middle part of blade cross-sectional length, unit：Millimeter；
L3--- bucket rear cross-sectional length, unit：Millimeter；
k2--- coefficient；
k3--- coefficient；
R1--- flank radius, unit：Rice；
R2--- back radius of curvature, unit：Rice.
2. a kind of large high-temperature high pressure turbine pump blade design method according to claim 1, which is characterized in that described Adjusted coefficient K takes 0.9~1.1.
3. a kind of large high-temperature high pressure turbine pump blade design method according to claim 1, which is characterized in that described High incidence Δ β takes 5 °~20 °.
4. a kind of large high-temperature high pressure turbine pump blade design method according to claim 1, which is characterized in that described Coefficient k2Take 0.3~0.7.
5. a kind of large high-temperature high pressure turbine pump blade design method according to claim 1, which is characterized in that described Coefficient k3Take 0.4~0.7.
CN201710107375.1A 2017-02-27 2017-02-27 A kind of large high-temperature high pressure turbine pump blade design method Active CN106884682B (en)

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Publication number Priority date Publication date Assignee Title
CN108457704B (en) * 2018-05-26 2023-10-27 吉林大学 Bionic blade

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Publication number Priority date Publication date Assignee Title
US3964841A (en) * 1974-09-18 1976-06-22 Sigma Lutin, Narodni Podnik Impeller blades
DE59704501D1 (en) * 1996-03-28 2001-10-11 Mtu Aero Engines Gmbh Airfoil blade
CN101629583A (en) * 2009-06-23 2010-01-20 江苏大学 Methods for calculating and thickening profile of impeller vane of axial flow pump
CN104763473B (en) * 2015-02-12 2017-01-04 溧阳市超强链条制造有限公司 Airfoil piece
CN204805151U (en) * 2015-07-02 2015-11-25 江苏德华泵业有限公司 Two -way axial -flow pump

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