CN110578556B - Moving blade with long and short wings and rotor - Google Patents

Moving blade with long and short wings and rotor Download PDF

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Publication number
CN110578556B
CN110578556B CN201910910707.9A CN201910910707A CN110578556B CN 110578556 B CN110578556 B CN 110578556B CN 201910910707 A CN201910910707 A CN 201910910707A CN 110578556 B CN110578556 B CN 110578556B
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China
Prior art keywords
blade
long
rotor
wing
short
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CN201910910707.9A
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Chinese (zh)
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CN110578556A (en
Inventor
张小龙
周根标
张利民
李翠芳
周亚锋
袁志才
杨星
申振
张武帅
安凯
刘妮
杜国栋
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Xian Shaangu Power Co Ltd
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Xian Shaangu Power Co Ltd
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Priority to CN201910910707.9A priority Critical patent/CN110578556B/en
Publication of CN110578556A publication Critical patent/CN110578556A/en
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Classifications

    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers

Abstract

The invention provides a moving blade with long and short wings and a rotor, which comprise a blade profile and a blade root, wherein the contact surface between the blade root and the blade profile is a hub cambered surface, the first side surface of the blade root at the pressure surface side of the blade profile is provided with the long wing, and the contact surface between the long wing and the blade profile is a hub cambered surface; a short wing is arranged on the second side surface of the blade root on the suction surface side of the blade profile, and the contact surface between the short wing and the blade profile is a hub cambered surface; the moving blade mass eccentricity e of the moving blade with the long and short wings is less than or equal to 2.0mm. The moving blade has the advantages of lower static stress level, smaller dynamic stress, uniform stress distribution, high first-order bending vibration frequency and good fatigue resistance. The middle body part with the long and short wings completely wraps the section of the blade profile bottom, and the pneumatic design requirement is completely realized in structure; the centrifugal bending stress can offset part of airflow bending stress by adjusting the gravity center position, so that the alternating stress amplitude is reduced, and the fatigue life of the moving blade is prolonged.

Description

Moving blade with long and short wings and rotor
Technical Field
The invention belongs to the field of blast furnace gas residual pressure turbines, relates to a moving blade, and in particular relates to a moving blade with long and short wings and a rotor.
Background
The moving blade is the most core element of the axial flow blast furnace gas residual pressure turbine expander for converting residual pressure and waste heat into mechanical energy, and the stress level and stress distribution are directly concerned with the reliability of the moving blade. The moving blades not only receive the centrifugal load, but also receive the alternating airflow load, so that the problem of vibration fatigue of the moving blades is remarkable, and the structural design of the moving blades is more demanding.
The moving blades of axial-flow type blast furnace gas residual pressure turbine expander are characterized by that the number of moving blades is relatively small, and the moving blades are usually made into the blade form with large chord length or large turning angle. The blade profile has larger pitch of adjacent blades, and can not adopt damping structures like a lacing structure, a shroud structure and the like which are commonly used for turbine moving blades, and the blade body (blade profile) of the moving blade can only be a free blade, so that higher requirements are put on the design of blade roots.
Most of the moving blades of the axial-flow blast furnace gas residual pressure turbine expander are circumferentially arranged in blade root grooves of a hub type main shaft, conventional moving blades are circumferentially distributed, adjacent moving blades are separated by spacer blocks, the adjacent moving blades are mutually squeezed in the circumferential direction during assembly, the last moving blade is arranged in a space of the spacer blocks, then the last moving blade is arranged in the spacer blocks, and the space is locked at the spacer blocks. For the blades with large chord length or large turning angle, the blade body bottom section is completely wrapped, the space of the spacer block is insufficient for placing the last moving blade, and only the design scheme of removing the spacer block can be selected.
The axial flow type blast furnace gas residual pressure turbine expander is usually used for directly driving a generator to generate power, the domestic power grid frequency is 50Hz, the corresponding generator rotating speed is 3000r/min, on a small-sized unit, the stress level of moving blades is low, the moving blade roots are designed well, on a medium-sized unit and a large-sized unit, the stress level of the moving blades is high, and the moving blade roots are difficult to design. Therefore, developing a circumferentially-installed rotor blade suitable for large chord lengths or large turning angles is a requirement for development of the blast furnace gas residual pressure turbine expander industry.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a moving blade with long and short wings and a rotor, which solve the technical problem that the fatigue life of the moving blade is short because the blade root of the moving blade in the prior art is difficult to bear large stress.
In order to solve the technical problems, the invention adopts the following technical scheme:
the moving blade with the long and short wings comprises a blade profile and a blade root, wherein the contact surface between the blade root and the blade profile is a hub cambered surface, the long wing is arranged on the first side surface of the blade root at the pressure surface side of the blade profile, and the contact surface between the long wing and the blade profile is a hub cambered surface; a short wing is arranged on the second side surface of the blade root on the suction surface side of the blade profile, and the contact surface between the short wing and the blade profile is a hub cambered surface;
the moving blade mass eccentricity e of the moving blade with the long and short wings is less than or equal to 2.0mm;
wherein ρ is the density;
V 1 is the volume of the leaf shape;
V 2 is the volume of the blade root;
V 3 is the volume of the long wing;
V 4 is the volume of the short wing;
e 1 the eccentricity of the blade profile relative to the centrifugal force direction central line of the blade;
e 2 the eccentricity of the blade root relative to the centrifugal force direction central line of the blade;
e 3 the eccentricity of the long wing relative to the centrifugal force direction central line of the blade;
e 4 is the eccentricity of the short wing relative to the centrifugal force direction central line of the blade.
The invention also has the following technical characteristics:
the moving blade with the long and short wings has the moving blade mass eccentricity e less than or equal to 0.2mm.
And the long wing, the short wing and the blade root are in smooth transition by adopting round angles.
The first side surface and the second side surface are a pair of parallel planes; the first side surface is parallel to the centrifugal force direction central line of the blade.
The blade root adopts a double inverted T-shaped blade root.
The non-bearing area at the bottom of the blade root is provided with a weight removing hole.
The invention also protects a moving blade with long and short wings, which comprises a blade profile and a blade root, wherein the contact surface between the blade root and the blade profile is a hub cambered surface, the first side surface of the blade root at the pressure surface side of the blade profile is provided with the long wing, and the contact surface between the long wing and the blade profile is a hub cambered surface; a short wing is arranged on the second side surface of the blade root on the suction surface side of the blade profile, and the contact surface between the short wing and the blade profile is a hub cambered surface;
the long wings and the short wings are used for adjusting the circumferential gravity center position of the moving blade, so that the centrifugal bending stress of the moving blade counteracts part of the airflow bending stress.
The invention also protects a rotor, which comprises a rotor main shaft, wherein the rotor main shaft is provided with a hub, the hub is provided with a plurality of moving blades, and the moving blades adopt moving blades with long and short wings.
The long wing of one moving blade is in contact with the short wing of the adjacent other moving blade.
The centrifugal force direction center line of the blade is in the same plane with the rotor axis, and the first side surface is parallel to the plane where the centrifugal force direction center line of the blade is located with the rotor axis.
Compared with the prior art, the invention has the following technical effects:
the moving blade has the advantages of low static stress level, small dynamic stress, uniform stress distribution, high first-order bending vibration frequency and good fatigue resistance.
(II) the middle body part with the long and short wings completely wraps the section of the blade profile bottom, and the pneumatic design requirement is completely realized in structure;
and (III) adjusting the gravity center position can realize that centrifugal bending stress counteracts part of airflow bending stress, reduce alternating stress amplitude and improve the fatigue life of the moving blade.
And (IV) the bottom section is provided with a weight removing hole, so that the stress distribution can be adjusted, and the problem of stress concentration of the moving blade is avoided.
And (V) no spacing block is needed to be arranged between the adjacent moving blades, and the long wings and the short wings are alternately and tightly arranged between the moving blades.
Drawings
Fig. 1 is a schematic structural view of a rotor blade with a double inverted T blade root having long and short wings.
Fig. 2 is a three-view and an equal side view structural schematic diagram of a moving blade with a double inverted-T blade root with long and short wings.
FIG. 3 is a schematic cross-sectional view of section A-A of FIG. 2.
Fig. 4 is a schematic sectional view of the section B-B of fig. 2.
Fig. 5 is a schematic view of an assembled structure of the rotor of the present invention.
Fig. 6 is a three-dimensional solid model built using UG.
FIG. 7 is a circularly symmetric model of a spindle, bucket and spacer block assembly built using UG.
FIG. 8 is a circularly symmetric model of a second stage bucket structure.
Fig. 9 is a VonMises stress cloud of the second stage full circle bucket.
Fig. 10 is a VonMises stress cloud of a second stage single bucket.
FIG. 11 is a second stage bucket vibration frequency result.
In fig. 6 to 11, the left side is: the diamond blade root movable blade is provided with a blade spacing block structure; the right sides are: double inverted T-shaped blade root movable vane structure with long and short wings.
The meaning of each reference numeral in the figures is: 1-blade profile, 2-blade root, 3-long wing, 4-short wing, 5-hub cambered surface, 6-first side, 7-second side, 8-de-duplication hole, 9-rotor main shaft, 10-hub and 11-moving blade;
o is the center point of the rotor axis, OZ is the centrifugal force direction center line of the blade, and R is the hub radius.
The following examples illustrate the invention in further detail.
Detailed Description
According to the invention, the circumferential gravity center position is changed by adjusting the long and short wings of the blade intermediate, and the gravity center position of the whole blade is changed by adjusting the size and the position of the weight removing hole, so that the centrifugal bending stress of the moving blade counteracts part of the airflow bending stress, the stress level of the blade is lower, and the stress of the working face of the air inlet and outlet tooth shape is relatively uniform.
In the invention, the duplicate removal holes are round holes, square holes, triangular holes or hexagonal holes.
In the present invention, the number of duplicate removal holes is 1 to 10.
In the invention, the tooth-shaped air inlet and outlet sides of the blade root are symmetrically distributed.
In the invention, the blade profile, the blade root, the long wing and the short wing are integrally formed into a whole structure.
In the invention, the blade profile is a blade profile with a large chord length or a blade profile with a large turning angle. The large chord length refers to the distance between the front edge point and the rear edge point of the section surface of the blade profile bottom, and is generally larger than 125mm in chord length of the axial-flow type blast furnace gas residual pressure turbine expansion movable blade, and the chord length of the movable blade is 165mm; the large turning angle refers to the corner between the inlet angle direction and the outlet angle direction of the blade profile bottom section, and the turning angle of the axial flow type blast furnace gas residual pressure turbine expansion movable blade is generally [90 degrees, 150 degrees ].
In the invention, the specific size and form of the long wings, the short wings and the weight removing holes depend on the blade stress analysis in the specific blade design.
The following specific embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following specific embodiments, and all equivalent changes made on the basis of the technical solutions of the present application fall within the protection scope of the present invention.
Example 1:
according to the above technical solution, as shown in fig. 1 to 4, the present embodiment provides a rotor blade with long and short wings, which includes a blade profile 1 and a blade root 2, wherein a contact surface between the blade root 2 and the blade profile 1 is a hub cambered surface 5, a long wing 3 is disposed on a first side 6 of the blade root 2 on a pressure surface side of the blade profile 1, and a contact surface between the long wing 3 and the blade profile 1 is the hub cambered surface 5; the second side 7 of the blade root 2 on the suction side of the blade profile 1 is provided with a short wing 4, and the contact surface between the short wing 4 and the blade profile 1 is a hub cambered surface 5;
the moving blade mass eccentricity e of the moving blade with the long and short wings is less than or equal to 2.0mm;
wherein ρ is the density;
V 1 is the volume of the leaf shape;
V 2 is the volume of the blade root;
V 3 is the volume of the long wing;
V 4 is the volume of the short wing;
e 1 the eccentricity of the blade profile relative to the centrifugal force direction central line of the blade;
e 2 the eccentricity of the blade root relative to the centrifugal force direction central line of the blade;
e 3 the eccentricity of the long wing relative to the centrifugal force direction central line of the blade;
e 4 is the eccentricity of the short wing relative to the centrifugal force direction central line of the blade.
In the present embodiment, the long wings 3 and the short wings 4 are used to adjust the circumferential center of gravity position of the moving blade so that the centrifugal bending stress of the moving blade counteracts part of the airflow bending stress.
As a preferable scheme of the embodiment, the moving blade with long and short wings has the moving blade mass eccentricity e less than or equal to 0.2mm. When the mass eccentricity e of the movable vane is less than or equal to 0.2mm, the centrifugal bending stress of the vane is smaller.
As a preferred version of this embodiment, the first side 6 and the second side 7 are a pair of parallel planes. The first side 6 is parallel to the centrifugal force direction centre line of the blade.
As a preferred embodiment of the present embodiment, the blade root 2 is a double inverted T-shaped blade root. The double inverted T-shaped blade root is combined with the blade profile, the long wing and the short wing, so that the adjustability of the mass eccentricity of the moving blade is better when the moving blade is designed.
As a preferred solution of this embodiment, the bottom non-bearing area of the blade root 2 is provided with a de-duplication hole 8.
Example 2:
according to the above technical solution, as shown in fig. 5, the present embodiment provides a rotor, including a rotor main shaft 9, a hub 10 is disposed on the rotor main shaft 9, a plurality of rotor blades 11 are mounted on the hub 10, and the rotor blades 11 are rotor blades with long and short wings as described in embodiment 1;
the long wing 3 of one moving blade 11 is in contact with the short wing 4 of the adjacent other moving blade 11.
The centrifugal force direction center line of the blade is in the same plane with the rotor axis, and the first side surface 6 is parallel to the plane of the centrifugal force direction center line of the blade and the rotor axis.
In the present embodiment, the specific number of the rotor blades 11 is determined according to actual needs.
Effect contrast analysis:
fig. 6 to 11 are embodiment cases, left and right structural comparisons: the blade profile of the moving blade is identical, the height of the runner of the moving blade is identical, the main shaft and the blade root groove are identical, and the blade root structural forms are different. The left diagram is a structure that a traditional diamond blade root moving blade and a spacer block are arranged in a main shaft blade root groove, and the right diagram is a structure that a double inverted T-shaped blade root moving blade with long and short wings is arranged in the main shaft blade root groove, namely a rotor provided in the embodiment 2 of the invention.
Fig. 6 is a three-dimensional solid model built by using UG, fig. 7 is a circular symmetry model of a main shaft, a movable blade and a spacer block assembly built by using UG, fig. 8 is a circular symmetry model of a second-stage movable blade structure, a stress cloud image of the two structures and a vibration frequency analysis result of the movable blade are obtained through finite element simulation analysis distribution, fig. 9 is a volmacs stress cloud image of a second-stage whole-circle movable blade, fig. 10 is a volmacs stress cloud image of a second-stage single movable blade, and fig. 11 is a second-stage movable blade vibration frequency result.
The VonIses stress cloud diagrams of fig. 9 and 10 show that the maximum stress of the traditional diamond blade root moving blade and spacer block structure is 575.15MPa, and the maximum stress of the double inverted T blade root moving blade structure with long and short wings is 532.53MPa. Compared with the traditional diamond blade root movable blade and spacer block structure, the maximum stress of the double inverted T-shaped movable blade structure with the long and short wings can be reduced by 7.4%, and the blade root stress is more uniform.
The analysis result of the vibration frequency of the moving blade in fig. 11 shows that: the first-order bending vibration frequency of the second-stage moving blade with the traditional diamond blade root is 397.64Hz, and the first-order bending vibration frequency of the second-stage moving blade with the double inverted T blade root structure with the long and short wings is 420.5Hz. The comparison shows that the first-order bending vibration frequency of the second-stage moving blade with the double inverted T-shaped blade root structure with the long short wings is increased by 5.7% compared with that of the second-stage moving blade with the traditional diamond blade root.
The comparison analysis of the traditional structure and the novel structure shows that the double inverted T-shaped blade root moving blade with the long and short wings can effectively reduce the structural stress level of the moving blade, and can effectively improve the first-order bending vibration frequency of the moving blade. The excitation difficulty of the moving blade is increased, and the fatigue life of the moving blade is further prolonged.

Claims (5)

1. The moving blade with the long and short wings comprises a blade profile (1) and a blade root (2), wherein the contact surface between the blade root (2) and the blade profile (1) is a hub cambered surface (5), and the moving blade is characterized in that the long wing (3) is arranged on a first side surface (6) of the blade root (2) at the pressure surface side of the blade profile (1), and the contact surface between the long wing (3) and the blade profile (1) is the hub cambered surface (5); a short wing (4) is arranged on a second side surface (7) of the blade root (2) on the suction surface side of the blade profile (1), and the contact surface between the short wing (4) and the blade profile (1) is a hub cambered surface (5);
the long wings (3) and the short wings (4) are used for adjusting the circumferential gravity center position of the moving blade, so that the centrifugal bending stress of the moving blade counteracts part of the airflow bending stress;
the long wing (3), the short wing (4) and the blade root (2) are in smooth transition through round angles;
the first side surface (6) and the second side surface (7) are a pair of parallel planes; the first side surface (6) is parallel to the centrifugal force direction central line of the blade;
the blade root (2) adopts a double inverted T-shaped blade root;
the non-bearing area at the bottom of the blade root (2) is provided with a de-duplication hole (8);
the moving blade mass eccentricity e of the moving blade with the long and short wings is less than or equal to 2.0mm;
wherein,is the density;
V 1 is the volume of the leaf shape;
V 2 is the volume of the blade root;
V 3 is the volume of the long wing;
V 4 is the volume of the short wing;
e 1 the eccentricity of the blade profile relative to the centrifugal force direction central line of the blade;
e 2 the eccentricity of the blade root relative to the centrifugal force direction central line of the blade;
e 3 the eccentricity of the long wing relative to the centrifugal force direction central line of the blade;
e 4 is the eccentricity of the short wing relative to the centrifugal force direction central line of the blade.
2. The rotor blade with long and short wings according to claim 1, wherein the rotor blade with long and short wings has a rotor blade mass eccentricity e of 0.2mm or less.
3. Rotor comprising a rotor shaft (9), a hub (10) being arranged on the rotor shaft (9), a plurality of rotor blades (11) being arranged on the hub (10), characterized in that rotor blades (11) are rotor blades with long and short wings according to any one of claims 1 to 2.
4. A rotor as claimed in claim 3, characterized in that the long wing (3) of one rotor blade (11) is in contact with the short wing (4) of the adjacent other rotor blade (11).
5. A rotor according to claim 3, wherein the blade centrifugal force direction centre line is in the same plane as the rotor axis, and wherein the first side (6) is parallel to the plane in which the blade centrifugal force direction centre line is in the rotor axis.
CN201910910707.9A 2019-09-25 2019-09-25 Moving blade with long and short wings and rotor Active CN110578556B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Application Number Priority Date Filing Date Title
CN201910910707.9A CN110578556B (en) 2019-09-25 2019-09-25 Moving blade with long and short wings and rotor

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CN110578556B true CN110578556B (en) 2024-03-26

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Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002106302A (en) * 2000-09-28 2002-04-10 Toshiba Corp Turbine rotor
JP2002349201A (en) * 2001-05-29 2002-12-04 Mitsubishi Heavy Ind Ltd Turbin rotor blade
CN101131093A (en) * 2007-09-25 2008-02-27 西安交通大学 Blade root platform damping structure of blast furnace gas turbine blade
CN101666290A (en) * 2009-10-14 2010-03-10 黄争鸣 Wind turbine blade structure, processing and forming method and applications thereof
CN203374321U (en) * 2013-05-24 2014-01-01 华电国际电力股份有限公司山东分公司 Moving blade of low-pressure rotor
DE102015224151A1 (en) * 2015-12-03 2017-06-08 MTU Aero Engines AG Center point threading of blades
CN108131169A (en) * 2018-02-05 2018-06-08 中国科学院工程热物理研究所 Root architecture is stretched suitable for the adjustment of feather joint rotor blade position of centre of gravity
CN108204249A (en) * 2016-12-20 2018-06-26 上海汽轮机厂有限公司 Variable speed last-stage moving blade of air-cooled steam turbine
CN211008775U (en) * 2019-09-25 2020-07-14 西安陕鼓动力股份有限公司 Moving blade with long and short wings and rotor

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002106302A (en) * 2000-09-28 2002-04-10 Toshiba Corp Turbine rotor
JP2002349201A (en) * 2001-05-29 2002-12-04 Mitsubishi Heavy Ind Ltd Turbin rotor blade
CN101131093A (en) * 2007-09-25 2008-02-27 西安交通大学 Blade root platform damping structure of blast furnace gas turbine blade
CN101666290A (en) * 2009-10-14 2010-03-10 黄争鸣 Wind turbine blade structure, processing and forming method and applications thereof
CN203374321U (en) * 2013-05-24 2014-01-01 华电国际电力股份有限公司山东分公司 Moving blade of low-pressure rotor
DE102015224151A1 (en) * 2015-12-03 2017-06-08 MTU Aero Engines AG Center point threading of blades
CN108204249A (en) * 2016-12-20 2018-06-26 上海汽轮机厂有限公司 Variable speed last-stage moving blade of air-cooled steam turbine
CN108131169A (en) * 2018-02-05 2018-06-08 中国科学院工程热物理研究所 Root architecture is stretched suitable for the adjustment of feather joint rotor blade position of centre of gravity
CN211008775U (en) * 2019-09-25 2020-07-14 西安陕鼓动力股份有限公司 Moving blade with long and short wings and rotor

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