CN110410157A - Turbine rotor - Google Patents
Turbine rotor Download PDFInfo
- Publication number
- CN110410157A CN110410157A CN201910795463.4A CN201910795463A CN110410157A CN 110410157 A CN110410157 A CN 110410157A CN 201910795463 A CN201910795463 A CN 201910795463A CN 110410157 A CN110410157 A CN 110410157A
- Authority
- CN
- China
- Prior art keywords
- blade
- blades
- kinds
- turbine rotor
- wheel disc
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
-
- 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
- F01D5/16—Form or construction for counteracting blade vibration
-
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to turbine component fields, it is intended to which the resonance bring that turbine rotor is alleviated or avoided influences, and provides a kind of turbine rotor comprising wheel disc and the multiple blades for being connected to the wheel disc circumferential direction；The blade includes blade root, blade and integral shroud；There are two types of blades, the blade of two kinds of blades it is of different size；Two kinds of blades are respectively arranged on wheel disc.The beneficial effects of the invention are as follows the resonance influences that can be avoided total.
Description
Technical field
The present invention relates to turbine component fields, in particular to turbine rotor.
Background technique
Steam turbine is a kind of energy conversion, converts heat energy into mechanical energy.Turbine rotor is steam turbine energy
The design superiority and inferiority of core component in conversion process, especially movable vane piece is most important for the safety of steam turbine.
In fact the damage overwhelming majority of movable vane piece is all due to the excessive generation of dynamic stress.To ensure steam turbine blade
Safe operation, it is necessary to control dynamic stress when movable vane piece work, it is general require to avoid the intrinsic frequency of blade it is presumable
Excitation force frequency range tunes to open resonance.Even if as damping vane, the dynamic stress for avoiding resonance when also can be reduced its work,
To improve the safety margin of movable vane piece.But for short frequency-modulating blade (typically refer to steam passage height in 200mm or less),
Since blade is shorter, the influence of the factors to the blade natural frequency of vibration such as root connection rigidity, shear force and rotary inertia is very big, so right
It, which is vibrated, is difficult to calculate accurately, and vibration characteristics is difficult to hold.
Summary of the invention
The present invention is intended to provide a kind of turbine rotor, is influenced so that the resonance bring of turbine rotor is alleviated or avoided.
The embodiment of the present invention is achieved in that
A kind of turbine rotor comprising wheel disc and the multiple blades for being connected to the wheel disc circumferential direction；The blade includes
Blade root, blade and integral shroud；There are two types of blades, the blade of two kinds of blades it is of different size；Two kinds of blades respectively cloth on wheel disc
It sets.
In one embodiment, the leaf and root structure shape of two kinds of blades is identical, the crown structure shape phase of two kinds of blades
Together；For the blade of two kinds of blades in addition to width dimensions are different, other sizes are all the same.
In one embodiment, the integral shroud of multiple blades is combined sequentially into Guan Quan；The side of the integral shroud of the blade
Face is equipped with damping structure, connects so as to be damped between the integral shroud of adjacent blades by damping structure.
In summary describe, in the turbine rotor in the present embodiment, the intrinsic frequency of even one of blade with
Excitation force frequency resonates, since the intrinsic frequency of different size for leading to two kinds of blades of the blade of two kinds of blades is different, with
Another blade is set always not resonate.
And from the point of view of blades arrangement, resonance each is not in its adjacent blade of the blade of resonance state
State, thus exciting force to resonance blade input energy a part will not resonated blade absorb.And for being damped in setting
In the further scheme of structure, the energy for being left a part is dissipated due to damping.Although being not at the blade vibration of resonance state
Width can increased, but for whole system, blade dynamic stress is substantially reduced.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below will be to needed in the embodiment attached
Figure is briefly described, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not construed as pair
The restriction of range for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 is the structural schematic diagram of the turbine rotor in the embodiment of the present invention (part is shown)；
Fig. 2 is the structural schematic diagram of the first blade of the embodiment of the present invention；
Fig. 3 is cross-sectional view of the Fig. 2 along E2-E2 line；
Fig. 4 is the structural schematic diagram of the second blade of the embodiment of the present invention；
Fig. 5 is cross-sectional view of the Fig. 4 along E1-E1 line；
Fig. 6 is enlarged drawing at the M of Fig. 1.
Icon: turbine rotor 100, wheel disc 10, blade 20, blade root 1, blade 2, integral shroud 3, the second blade A, the first blade
B, damping structure 4, central axes L1, hat circle 5.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.The present invention being usually described and illustrated herein in the accompanying drawings is implemented
The component of example can be arranged and be designed with a variety of different configurations.
Therefore, the detailed description of the embodiment of the present invention provided in the accompanying drawings is not intended to limit below claimed
The scope of the present invention, but it is merely representative of selected embodiment of the invention.Based on the embodiments of the present invention, the common skill in this field
Art personnel every other embodiment obtained without making creative work belongs to the model that the present invention protects
It encloses.
It should also be noted that similar label and letter indicate similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined in a attached drawing, does not then need that it is further defined and explained in subsequent attached drawing.
In the description of the present invention, it should be noted that if occur term " center ", "upper", "lower", "left", "right",
The orientation or positional relationship of the instructions such as "vertical", "horizontal", "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings,
Either the invention product using when the orientation or positional relationship usually put, be merely for convenience of the description present invention and simplification retouched
It states, rather than the device or element of indication or suggestion meaning must have a particular orientation, be constructed and operated in a specific orientation,
Therefore it is not considered as limiting the invention.If only being used in addition, occurring term " first ", " second " etc. in description of the invention
It is described in distinguishing, is not understood to indicate or imply relative importance.
If being not offered as requiring component absolute in addition, occurring the terms such as term "horizontal", "vertical" in description of the invention
Horizontal or pendency, but can be slightly tilted.If "horizontal" only refers to that its direction is more horizontal with respect to for "vertical", not
It is to indicate that the structure is had to fully horizontally, but can be slightly tilted.
In the description of the present invention, it is also necessary to which explanation is unless specifically defined or limited otherwise, if there is term
" setting ", " installation ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, be also possible to detachably connect
It connects, or is integrally connected；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, intermediate matchmaker can also be passed through
Jie is indirectly connected, and can be the connection inside two elements.It for the ordinary skill in the art, can be with concrete condition
Understand the concrete meaning of above-mentioned term in the present invention.
Embodiment
Referring to Fig. 1, the present embodiment provides a kind of turbine rotors 100 comprising wheel disc 10 and to be connected to wheel disc 10 circumferential
Multiple blades 20.Blade 20 includes blade root 1, blade 2 and integral shroud 3.There are two types of blades 20, the width of the blade 2 of two kinds of blades 20
Degree is different.Two kinds of blades 20 are respectively arranged on wheel disc 10.It is in the present embodiment, 2 width of blade is biggish for convenience of description
Blade 20 is defined as the first blade B.The lesser blade 20 of 2 width of blade is defined as the second blade A.The structure of first blade B is asked
Referring to figs. 2 and 3, the structure of the second blade A refers to Fig. 4 and Fig. 5.
After the structure, the steam flow channel of whole grade blade is only had any different into vapour section, and vapour Duan Ze is identical out, because
This throat opening be it is the same, flow area be also it is the same, do not influence the through-flow effect of steam turbine.But due to adjacent blades leaf
Body axial width is different, so both movable vane piece intrinsic frequencies are always different.
In the case of optional, the width Bd1 of the second blade A is the 59.9%-90.1% of the first blade B width Bd2.It is comprehensive
It closes the mechanical property for considering structure and obtains the sufficiently large intrinsic frequency of difference, the width of the second blade A is selected from the first blade B wide
Between the 70%-85% of degree.In the section, the intrinsic frequency of the second blade A and the first blade B have enough difference, energy
It is enough to avoid resonating simultaneously well, and the second blade A is also able to maintain enough structural strengths in the section, avoids shadow
Ring the overall mechanical properties of turbine rotor 100.
Cooperation is referring to Fig. 1 and Fig. 6, and in one embodiment, the integral shroud 3 of multiple blades 20 is combined sequentially into hat circle 5.Leaf
The integral shroud 3 of piece 20 is equipped with damping structure 4, so as to pass through the damping cooperation of damping structure 4 between the integral shroud 3 of adjacent blades 20.
In summary it describes, in the turbine rotor 100 in the present embodiment, the intrinsic frequency of even one of blade 20
Rate resonates with excitation force frequency, due to the intrinsic frequency of different size for leading to two kinds of blades 20 of the blade 2 of two kinds of blades 20
Rate is different, so that another blade 20 did not always resonate.
And from the point of view of the arrangement of blade 20, each it is not in its adjacent blade 20 of the blade 20 of resonance state
Resonance state, so exciting force absorbs a part blade 20 that will not resonated of resonance 20 input energy of blade.And for
In the further scheme of setting damping structure 4, the energy for being left a part is dissipated due to damping.Although being not at resonance
20 amplitude of blade of state can increased, but for whole system, 20 dynamic stress of blade is substantially reduced.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (3)
1. a kind of turbine rotor, it is characterised in that:
Including wheel disc and the multiple blades for being connected to the wheel disc circumferential direction；The blade includes blade root, blade and integral shroud；Blade has
Two kinds, the blade of two kinds of blades it is of different size；Two kinds of blades are respectively arranged on wheel disc.
2. turbine rotor according to claim 1, it is characterised in that:
The leaf and root structure shape of two kinds of blades is identical, and the crown structure shape of two kinds of blades is identical；The blade of two kinds of blades is except width
It is different outer to spend size, other sizes are all the same.
3. turbine rotor according to claim 1, it is characterised in that:
The integral shroud of multiple blades is combined sequentially into Guan Quan；The side of the integral shroud of the blade is equipped with damping structure, so that phase
It is damped and is connected by damping structure between the integral shroud of adjacent blade.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2019105843410 | 2019-07-01 | ||
| CN201910584341.0A CN110242356A (en) | 2019-07-01 | 2019-07-01 | Turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110410157A true CN110410157A (en) | 2019-11-05 |
Family
ID=67890385
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910584341.0A Pending CN110242356A (en) | 2019-07-01 | 2019-07-01 | Turbine rotor |
| CN201910795463.4A Pending CN110410157A (en) | 2019-07-01 | 2019-08-27 | Turbine rotor |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910584341.0A Pending CN110242356A (en) | 2019-07-01 | 2019-07-01 | Turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN110242356A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1877083A (en) * | 2006-07-06 | 2006-12-13 | 东方汽轮机厂 | Steam turbine moving vane shroud structure |
| US20070147992A1 (en) * | 2005-12-23 | 2007-06-28 | Delta Electronics, Inc. | Fan and fan housing thereof |
| US20110223012A1 (en) * | 2010-03-10 | 2011-09-15 | Kabushiki Kaisha Toshiba | Turbine rotor assembly and steam turbine |
| CN104822903A (en) * | 2012-06-14 | 2015-08-05 | Ge亚飞欧有限责任公司 | Aerofoil array for a gas turbine with anti fluttering means |
| EP2907970A1 (en) * | 2014-02-13 | 2015-08-19 | United Technologies Corporation | Mistuned concentric airfoil assembly and method of mistuning same |
-
2019
- 2019-07-01 CN CN201910584341.0A patent/CN110242356A/en active Pending
- 2019-08-27 CN CN201910795463.4A patent/CN110410157A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070147992A1 (en) * | 2005-12-23 | 2007-06-28 | Delta Electronics, Inc. | Fan and fan housing thereof |
| CN1877083A (en) * | 2006-07-06 | 2006-12-13 | 东方汽轮机厂 | Steam turbine moving vane shroud structure |
| US20110223012A1 (en) * | 2010-03-10 | 2011-09-15 | Kabushiki Kaisha Toshiba | Turbine rotor assembly and steam turbine |
| CN104822903A (en) * | 2012-06-14 | 2015-08-05 | Ge亚飞欧有限责任公司 | Aerofoil array for a gas turbine with anti fluttering means |
| EP2907970A1 (en) * | 2014-02-13 | 2015-08-19 | United Technologies Corporation | Mistuned concentric airfoil assembly and method of mistuning same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110242356A (en) | 2019-09-17 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191105 |
|
| RJ01 | Rejection of invention patent application after publication |