CN110578556A - Moving blade with long and short wings and rotor - Google Patents
Moving blade with long and short wings and rotor Download PDFInfo
- Publication number
- CN110578556A CN110578556A CN201910910707.9A CN201910910707A CN110578556A CN 110578556 A CN110578556 A CN 110578556A CN 201910910707 A CN201910910707 A CN 201910910707A CN 110578556 A CN110578556 A CN 110578556A
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- blade
- long
- short
- rotor
- wing
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- 238000005452 bending Methods 0.000 claims abstract description 19
- 230000005484 gravity Effects 0.000 claims abstract description 7
- 230000007704 transition Effects 0.000 claims description 2
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 230000003068 static effect Effects 0.000 abstract description 2
- 125000006850 spacer group Chemical group 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000002955 isolation Methods 0.000 description 4
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- QNRATNLHPGXHMA-XZHTYLCXSA-N (r)-(6-ethoxyquinolin-4-yl)-[(2s,4s,5r)-5-ethyl-1-azabicyclo[2.2.2]octan-2-yl]methanol;hydrochloride Chemical compound Cl.C([C@H]([C@H](C1)CC)C2)CN1[C@@H]2[C@H](O)C1=CC=NC2=CC=C(OCC)C=C21 QNRATNLHPGXHMA-XZHTYLCXSA-N 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a moving blade with long and short wings and a rotor, which comprise blade profiles and blade roots, wherein the contact surface between the blade roots and the blade profiles 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 blades is less than or equal to 2.0 mm. The moving blade has the advantages of low static stress level, low dynamic stress, uniform stress distribution, high first-order bending vibration frequency and good fatigue resistance. The intermediate part with the long and short wings completely wraps the section of the blade profile bottom, and the pneumatic design requirement is completely realized on the structure; the centrifugal bending stress can be adjusted to offset part of the airflow bending stress by adjusting the position of the center of gravity, so that the amplitude of the alternating stress is reduced, and the fatigue life of the moving blade is prolonged.
Description
Technical Field
The invention belongs to the field of blast furnace gas residual pressure turbines, relates to a moving blade, and particularly relates to a moving blade with long and short blades and a rotor.
Background
The moving blade is the most central element of the axial flow type blast furnace gas residual pressure turbo-expander for converting residual pressure and residual heat into mechanical energy, and the stress level and the stress distribution directly concern the self reliability of the moving blade. The moving blade not only receives centrifugal load's effect, still receives the effect of air current alternating load, and the vibration fatigue problem of moving blade is obvious, has higher demand to the structural design of moving blade.
The moving blade of axial-flow blast furnace gas residual pressure turbo-expander features that the number of moving blades in a whole circle is relatively small, and the moving blade usually adopts a blade profile with large chord length or large turning angle. The blade profile makes the pitch of adjacent blades larger, the damping structures similar to the common lacing wire structure and the shroud structure of a turbine moving blade cannot be adopted, and the blade body (blade profile) of the moving blade can only be a free blade, so that higher requirements are provided for the design of the blade root.
the moving blades of axial-flow blast furnace gas residual pressure turbo-expander are mostly installed in the blade root groove of hub type main shaft along the circumferential direction, the conventional moving blades are distributed along the circumferential direction, the adjacent moving blades are separated by using a blade isolation block, and are mutually compacted along the circumferential direction during assembly, the space of the blade isolation block is used for installing the last moving blade, then the blade isolation block is placed in the last moving blade, and the last moving blade is locked at the position of the blade isolation block. For the blades with large chord length or large turning angle, the bottom section of the blade body needs to be completely wrapped, the space of the blade separation block is not enough for placing the last moving blade, and only the design scheme of removing the blade separation block is selected.
The axial flow type blast furnace gas residual pressure turbo-expander is usually used for directly driving a generator to generate electricity, the domestic power grid frequency is 50Hz, the corresponding rotating speed of the generator is 3000r/min, the stress level of a moving blade is lower on a small-sized unit, the blade root of the moving blade is designed, the stress level of the moving blade is higher on a medium-sized unit, and the design of the blade root of the moving blade is difficult. Therefore, it is a need in the development of the blast furnace gas pressure turbine expander industry to develop a circumferentially inserted moving blade suitable for large chord lengths or large turning angles.
disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a moving blade with a long and short blade and a rotor, and solve the technical problem that the fatigue life of the moving blade is short due to the fact that 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:
a moving blade with 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 first side surface of the blade root on the pressure surface side of the blade profile is provided with a long wing, and the contact surface between the long wing and the blade profile is the 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 movable blade mass eccentricity e of the movable blade with the long and short blades is less than or equal to 2.0 mm;
Wherein ρ is density;
V1Volume of the leaf profile;
V2the volume of the blade root;
V3Is the volume of the long wing;
V4Is the volume of the short wing;
e1The eccentricity of the blade profile relative to the central line of the centrifugal force direction of the blade;
e2The eccentricity of the blade root relative to the central line of the centrifugal force direction of the blade;
e3the eccentricity of the long wing relative to the central line of the centrifugal force direction of the blade;
e4the eccentricity of the short wing relative to the center line of the centrifugal force direction of the blade.
the invention also has the following technical characteristics:
The movable blade mass eccentricity e of the movable blade with the long and short blades is less than or equal to 0.2 mm.
the long wing, the short wing and the blade root are all in round-angle smooth transition.
The first side surface and the second side surface are a pair of parallel planes; the first side surface is parallel to the central line of the centrifugal force direction of the blade.
the blade root adopts a double-inverted-T-shaped blade root.
And 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; 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 wing and the short wing are used for adjusting the circumferential gravity center position of the moving blade, so that the centrifugal bending stress of the moving blade counteracts partial airflow bending stress.
The invention also protects a rotor, which comprises a rotor main shaft, wherein a hub is arranged on the rotor main shaft, a plurality of moving blades are arranged on the hub, and the moving blades with long and short blades are adopted as the moving blades in any claim.
The long wing of one moving blade is in contact with the short wing of another moving blade which is adjacent.
the central line of the centrifugal force direction of the blade is in the same plane with the axis of the rotor, and the first side surface is parallel to the plane where the central line of the centrifugal force direction of the blade is located with the axis of the rotor.
compared with the prior art, the invention has the following technical effects:
The moving blade of the invention has the advantages of low static stress level, low dynamic stress, uniform stress distribution, high first-order bending vibration frequency and good fatigue resistance.
(II) the intermediate part with the long and short wings completely wraps the section of the blade profile bottom, and the pneumatic design requirement is completely realized on the structure;
and (III) the centrifugal bending stress can be adjusted to offset part of the airflow bending stress by adjusting the position of the gravity center, so that the amplitude of the alternating stress is reduced, and the fatigue life of the moving blade is prolonged.
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.
(V) the adjacent moving blades of the invention do not need to be provided with spacing blocks, and the long and short blades between the moving blades are alternately and tightly arranged.
Drawings
FIG. 1 is a schematic structural view of a moving blade with a double-inverted-T root having long and short blades.
FIG. 2 is a schematic three-dimensional view and an isometric view of a double inverted T blade root rotor blade with long and short blades.
fig. 3 is a schematic sectional view of the section a-a in fig. 2.
fig. 4 is a schematic sectional structure view of the section B-B in fig. 2.
Fig. 5 is a schematic view of an assembly 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 main shaft, movable blades and spacer assembly built using UG.
FIG. 8 is a circularly symmetric model of a second stage bucket structure.
FIG. 9 is a VonMises stress cloud plot for a second stage full ring bucket.
FIG. 10 is a VonMises stress cloud plot for 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 movable blade with the rhombic blade root is provided with a blade spacer structure; the right side is: the double-inverted-T-shaped blade root movable blade structure with the long and short blades.
the meaning of the individual reference symbols in the figures is: 1-blade profile, 2-blade root, 3-long blade, 4-short blade, 5-hub cambered surface, 6-first side surface, 7-second side surface, 8-weight removal hole, 9-rotor spindle, 10-hub and 11-moving blade;
O is the center point of the rotor axis, OZ is the center line of the centrifugal force direction of the blade, and R is the radius of the hub.
The present invention will be explained in further detail with reference to examples.
Detailed Description
The invention changes the circumferential gravity center position by adjusting the long and short wings of the blade intermediate body, and changes the gravity center position of the whole blade by adjusting the size and the position of the weight-removing hole, so that the centrifugal bending stress of the moving blade counteracts partial airflow bending stress, the lower stress level of the blade is realized, and the stress of the working surface of the air inlet and exhaust tooth shape is relatively uniform.
in the invention, the weight-removing holes are circular holes, square holes, triangular holes or hexagonal holes.
In the present invention, the number of the deduplication holes is 1 to 10.
In the invention, the tooth shapes of the blade root are symmetrically distributed on the air inlet and outlet sides.
In the invention, the blade profile, the blade root, the long wing and the short wing are of an integrally formed integral structure.
In the invention, the blade profile is a blade profile with 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 bottom section of the blade profile, the chord length of the movable blade of the axial flow type blast furnace gas residual pressure turbine expansion is usually larger than 125mm, and the chord length of the movable blade is 165 mm; the large turning angle refers to the turning angle between the inlet angle direction and the outlet angle direction of the blade profile bottom section, usually the turning angle of the axial flow type blast furnace gas residual pressure turbine expansion moving blade is [90 degrees ], 150 degrees ], and the turning angle of the moving blade is 95 degrees.
In the invention, the specific size and form of the long wing, the short wing and the weight-reducing hole are determined according to the stress analysis of the blade during the specific blade design.
The following embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following embodiments, and all equivalent changes based on the technical solutions of the present invention are within the protection scope of the present invention.
Example 1:
following the above technical solution, as shown in fig. 1 to 4, the present embodiment provides a moving blade with long and short blades, which includes a blade profile 1 and a blade root 2, a contact surface between the blade root 2 and the blade profile 1 is a hub arc surface 5, a first side surface 6 of the blade root 2 on a pressure surface side of the blade profile 1 is provided with a long blade 3, and a contact surface between the long blade 3 and the blade profile 1 is the hub arc 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 a 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 blades is less than or equal to 2.0 mm;
Wherein ρ is density;
V1volume of the leaf profile;
V2the volume of the blade root;
V3Is the volume of the long wing;
V4is the volume of the short wing;
e1The eccentricity of the blade profile relative to the central line of the centrifugal force direction of the blade;
e2the eccentricity of the blade root relative to the central line of the centrifugal force direction of the blade;
e3The eccentricity of the long wing relative to the central line of the centrifugal force direction of the blade;
e4the eccentricity of the short wing relative to the center line of the centrifugal force direction of the blade.
In the present embodiment, the long blade 3 and the short blade 4 are used to adjust the circumferential center of gravity of the rotor blade so that the centrifugal bending stress of the rotor blade cancels a part of the flow bending stress.
As a preferable mode of the embodiment, the moving blade mass eccentricity e of the moving blade with the long and short blades is less than or equal to 0.2 mm. When the mass eccentricity e of the movable blade is less than or equal to 0.2mm, the centrifugal bending stress of the blade is smaller.
as a preferable mode of this embodiment, the first side surface 6 and the second side surface 7 are a pair of parallel planes. The first side 6 is parallel to the centre line of the centrifugal force direction of the blade.
as a preferable solution of this embodiment, the blade root 2 is a double inverted T-shaped blade root. By adopting the double-inverted-T-shaped blade root combined with the blade profile, the long blade and the short blade, 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 weight-reducing hole 8.
Example 2:
Following 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 moving blades 11 are mounted on the hub 10, and the moving blades 11 adopt the moving blades with long and short blades described in embodiment 1;
The long blade 3 of one rotor blade 11 is in contact with the short blade 4 of another adjacent rotor blade 11.
the central line of the centrifugal force direction of the blade and the axis of the rotor are in the same plane, and the first side surface 6 is parallel to the plane where the central line of the centrifugal force direction of the blade and the axis of the rotor are located.
In the present embodiment, the specific number of the rotor blades 11 is determined according to actual needs.
and (3) effect comparison analysis:
Fig. 6 to 11 are the case of the embodiment, comparing the left and right structures: the blade profiles of the moving blades are completely the same, the heights of the moving blade flow channels are completely the same, and the main shaft and the blade root groove are also completely the same, but the blade root structural forms are different. The left drawing shows a structure in which a conventional diamond-shaped blade root moving blade plus a spacer is mounted in a main shaft blade root groove, and the right drawing shows a structure in which a double inverted T-shaped blade root moving blade with a long wing and a short wing according to the present invention is mounted in a main shaft blade root groove, that is, a rotor according to embodiment 2 of the present invention.
Fig. 6 is a three-dimensional solid model established by UG, fig. 7 is a cyclic symmetry model of a main shaft, movable blades and spacer block assembly body established by UG, fig. 8 is a cyclic symmetry model of a second-stage movable blade structure, stress cloud maps of two structures and vibration frequency analysis results of the movable blades are obtained by finite element simulation analysis distribution, fig. 9 is a von mises stress cloud map of the second-stage whole-circle movable blade, fig. 10 is a von mises stress cloud map of the second-stage single movable blade, and fig. 11 is a second-stage movable blade vibration frequency result.
The von mises stress cloud charts in fig. 9 and 10 show that the maximum stress of the conventional diamond-shaped root movable blade and spacer blade structure is 575.15MPa, and the maximum stress of the double-inverted-T root movable blade structure with the long and short blades is 532.53 MPa. Compared with the traditional structure of the diamond-shaped blade root movable blade and the spacer blade, the double-inverted-T movable blade structure with the long and short blades can reduce the maximum stress by 7.4 percent, and the stress of the blade root is more uniform.
FIG. 11 shows the results of the blade vibration frequency analysis: the first-order bending vibration frequency of the traditional second-stage moving blade with the diamond-shaped 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 420.5 Hz. The comparison shows that the first-order bending vibration frequency of the second-stage moving blade with the long and short blades in the double-inverted-T blade root structure is increased by 5.7 percent compared with that of the traditional diamond-shaped blade root second-stage moving blade.
Compared with the traditional structure and the novel structure, the double-inverted-T blade root moving blade with the long and short blades 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 (10)
1. A moving blade with long and short wings comprises 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), and is characterized in that a long wing (3) is arranged on a first side surface (6) of the blade root (2) on 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 a contact surface between the short wing (4) and the blade profile (1) is a hub cambered surface (5);
The movable blade mass eccentricity e of the movable blade with the long and short blades is less than or equal to 2.0 mm;
wherein ρ is density;
V1volume of the leaf profile;
V2The volume of the blade root;
V3Is the volume of the long wing;
V4Is the volume of the short wing;
e1The eccentricity of the blade profile relative to the central line of the centrifugal force direction of the blade;
e2the eccentricity of the blade root relative to the central line of the centrifugal force direction of the blade;
e3The eccentricity of the long wing relative to the central line of the centrifugal force direction of the blade;
e4The eccentricity of the short wing relative to the center line of the centrifugal force direction of the blade.
2. the rotor blade with long and short blades according to claim 1, wherein the rotor blade with long and short blades has a rotor blade mass eccentricity e of 0.2mm or less.
3. The rotor blade with long and short blades as claimed in claim 1, wherein the long blade (3), the short blade (4) and the blade root (2) are all in round smooth transition.
4. The rotor blade with long and short blades as claimed in claim 1, wherein said first side surface (6) and said second side surface (7) are a pair of parallel planes; the first side surface (6) is parallel to the central line of the centrifugal force direction of the blade.
5. The rotor blade with long and short blades as claimed in claim 1, characterized in that the blade root (2) is a double inverted T-shaped blade root.
6. The rotor blade with a long and short airfoil as claimed in claim 1, characterized in that the non-load-bearing area of the bottom of the blade root (2) is provided with a weight-reducing hole (8).
7. a moving blade with long and short wings comprises 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), and is characterized in that a long wing (3) is arranged on a first side surface (6) of the blade root (2) on 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 a contact surface between the short wing (4) and the blade profile (1) is a hub cambered surface (5);
the long wing (3) and the short wing (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.
8. A rotor comprising a rotor main shaft (9), a hub (10) is provided on the rotor main shaft (9), and a plurality of moving blades (11) are mounted on the hub (10), characterized in that the moving blades (11) with long and short blades according to any one of claims 1 to 6 are adopted as the moving blades (11).
9. The rotor as recited in claim 8, characterized in that the long limb (3) of one rotor blade (11) is in contact with the short limb (4) of another adjacent rotor blade (11).
10. a rotor according to claim 8, characterized in that the centre line of the centrifugal force direction of the blade is in the same plane as the rotor axis, and that the first side (6) is parallel to the plane in which the centre line of the centrifugal force direction of the blade is in connection with the rotor axis.
Priority Applications (1)
| 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 |
Applications Claiming Priority (1)
| 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 |
Publications (2)
| Publication Number | Publication Date |
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| CN110578556A true CN110578556A (en) | 2019-12-17 |
| CN110578556B CN110578556B (en) | 2024-03-26 |
Family
ID=68813607
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910910707.9A Active CN110578556B (en) | 2019-09-25 | 2019-09-25 | Moving blade with long and short wings and rotor |
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|---|---|---|---|---|
| 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 |
-
2019
- 2019-09-25 CN CN201910910707.9A patent/CN110578556B/en active Active
Patent Citations (9)
| 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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| Publication number | Publication date |
|---|---|
| CN110578556B (en) | 2024-03-26 |
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