CN109977537B - Turbine blade and method for producing a turbine blade - Google Patents
Turbine blade and method for producing a turbine blade Download PDFInfo
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- CN109977537B CN109977537B CN201910228780.8A CN201910228780A CN109977537B CN 109977537 B CN109977537 B CN 109977537B CN 201910228780 A CN201910228780 A CN 201910228780A CN 109977537 B CN109977537 B CN 109977537B
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
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Abstract
The invention relates to the technical field of engines, and provides a turbine blade and a preparation method thereof. The blade is divided into a first part of blade and a second part of blade by the shedding section, the center of mass of the first part of blade and the centroid of the shedding section have a distance in the radial direction of the blade, and the preparation method comprises the steps of determining the breaking rotational speed of a wheel disc assembled with the turbine blade and the design rotational speed of the turbine blade; determining the blade shedding rotating speed according to the design margin of the breaking rotating speed and the turbine blade shedding rotating speed; calculating an initial stress group of a blade shedding section according to the material limit of the turbine blade, the turbine blade shedding rotating speed and the turbine blade design rotating speed; establishing a finite element model of the turbine blade and simulating the normal working state of the turbine blade to obtain a design stress group; and adjusting the distance until a preset condition is met between the design stress group and the initial stress group. The area of the shedding section can be increased when the shedding rotational speed is equal, and the rigidity value of the blade is increased, so that the turbine blade can be normally shed when the shedding rotational speed is reached.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a preparation method of a turbine blade and a design device of the turbine blade.
Background
The mechanical over-rotation protection function of preventing the wheel disc from being broken due to the falling of the blades in the aeroengine or other gas turbine engines is realized, namely, a falling section is designed on the turbine blades, once the load of the engine is lost, the turbine rotor is over-rotated to a certain rotating speed, the blades fall off at the falling section, so that the wheel disc loses the power for continuously rising the rotating speed, and the damage to the engine caused by the over-rotation and the breakage of the wheel disc is avoided. The turbine blade prepared by the preparation method in the prior art has lower precision, and often cannot fall off when the falling rotational speed of the blade is reached, so that the wheel disc is damaged.
Therefore, there is a need to design a new method of manufacturing a turbine blade and a turbine blade.
The above information disclosed in the background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not form the prior art that is already known to a person of ordinary skill in the art.
Disclosure of Invention
The invention aims to overcome the defect that the turbine disc is damaged because the blades in the prior art are not always fallen off when the falling rotational speed of the blades is reached, and provides a preparation method of the turbine blade and a design device of the turbine blade, wherein the designed turbine blade falls off when the falling rotational speed of the blades is reached and the turbine disc is not damaged.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
According to one aspect of the invention, a method of manufacturing a turbine blade divided by a cut-off section into a first part blade and a second part blade, the centroid of the first part blade having a pitch from the centroid of the cut-off section in the radial direction of the turbine blade; the preparation method of the turbine blade comprises the following steps:
determining a burst speed of a disk on which the turbine blade is mounted and a design speed of the turbine blade;
determining the blade shedding rotating speed according to the design margin of the breaking rotating speed and the turbine blade shedding rotating speed;
calculating an initial stress group of a blade shedding section according to the material limit of the turbine blade, the turbine blade shedding rotating speed and the turbine blade design rotating speed;
establishing a finite element model of the turbine blade, and simulating the normal working state of the turbine blade to obtain a design stress group;
and adjusting the distance until a preset condition is met between the design stress group and the initial stress group.
In one exemplary embodiment of the present disclosure, the set of design stresses includes a design equivalent stress, a design tensile stress, and a design stretch-bend resultant stress.
In one exemplary embodiment of the present disclosure, adjusting the spacing includes:
the mass on one side of the first partial blade center axis in the finite element model of the turbine blade is adjusted such that the centroid is offset from the first partial blade center axis.
In one exemplary embodiment of the present disclosure, the initial stress group includes at least an initial equivalent stress, an initial tensile stress, and an initial stretch-bending stress; calculating an initial stress group of a blade-shedding section according to the material limit of the turbine blade, the turbine blade-shedding rotating speed and the turbine blade design rotating speed, wherein the initial stress group comprises the following components:
determining initial equivalent stress of a shedding section according to the material limit of the turbine blade, the shedding rotating speed of the turbine blade and the design rotating speed of the turbine blade;
and determining the initial tensile stress and the initial stretch-bending stress of the shedding section according to the initial equivalent stress of the shedding section.
In one exemplary embodiment of the present disclosure, adjusting the spacing until a preset condition is satisfied between the set of design stresses and the set of initial stresses includes:
and adjusting the spacing to be equal to the initial stretch-bending stress in a threshold range.
In one exemplary embodiment of the present disclosure, adjusting the spacing includes:
and forming a groove on the finite element model of the turbine blade, wherein the falling section passes through the groove, and the depth and the area of the groove are adjusted so that the centroid of the falling section deviates from the central axis of the turbine blade.
In one exemplary embodiment of the present disclosure, the initial stress group includes at least an initial equivalent stress, an initial tensile stress, and an initial stretch-bending stress; calculating an initial stress group of a blade-shedding section according to the material limit of the turbine blade, the turbine blade-shedding rotating speed and the turbine blade design rotating speed, wherein the initial stress group comprises the following components:
determining initial equivalent stress of a blade shedding section according to the material limit of the turbine blade, the turbine blade shedding rotating speed and the turbine blade design rotating speed;
calculating initial tensile stress of the shedding section according to the initial equivalent stress;
calculating a centrifugal bending moment from the center of mass of the blade at the upper part of the shedding section to the center of the section;
and calculating the initial bending stress under the working conditions of centrifugal force and centrifugal bending moment.
In one exemplary embodiment of the present disclosure, adjusting the spacing until a preset condition is satisfied between the set of design stresses and the set of initial stresses includes:
adjusting the distance until the design equivalent stress is equal to the initial equivalent stress, wherein the design equivalent stress, the design tensile stress and the design stretch bending stress satisfy the following relation:
σ 0 ＝Kσ bending stress +(1-K)σ Tensile stress
Wherein sigma 0 To design the equivalent stress, sigma Bending stress To design the stretch-bending stress, sigma Tensile stress The design tensile stress is shown, and K is the structural constant.
According to one aspect of the invention, the turbine blade is divided by a cut-off section into a first part blade and a second part blade, the centroid of the first part blade having a spacing from the centroid of the cut-off section in the radial direction of the turbine blade.
In one exemplary embodiment of the present disclosure, the turbine blade is divided into a first partial blade and a second partial blade by a shedding section, a centroid of the first partial blade having a pitch from a centroid of the shedding section in a radial direction of the turbine blade, comprising:
the mass of both sides of the first part blade central axis of the turbine blade is different; or one side of the central axis of the first part of blades is provided with a groove, and the falling section passes through the groove.
According to the technical scheme, the invention has at least one of the following advantages and positive effects:
according to the preparation method of the turbine blade, the turbine blade is divided into the first part blade and the second part blade by the shedding section, the center of mass of the first part blade and the centroid of the shedding section have a distance in the radial direction of the turbine blade, the normal working state of the turbine blade is simulated by establishing the finite element model of the turbine blade to obtain the design stress group, and the design of the turbine blade is completed by adjusting the distance until the design stress group meets the preset condition. Compared with the prior art, on one hand, the center of mass of the first part of blades and the centroid of the shedding section have a distance in the radial direction of the turbine blades, bending stress is generated, the magnitude of the bending stress is controlled by adjusting the distance, the first part of blades can shed when the turbine blades which are simulated and designed reach the blade shedding speed, the design precision is higher, and the problem that in the prior art, when the turbine blades reach the blade shedding speed, the first part of blades are not shed, so that the wheel disc is damaged is solved; on the other hand, under the condition of the same falling-off rotating speed, the area of the falling-off section can be properly increased in design, the first part of blades of the turbine blade fall off when the falling-off rotating speed is reached by adjusting the distance, and the rigidity value of the turbine blade prepared by the method is improved due to the increase of the falling-off section, so that the service life of the turbine blade is prolonged.
Drawings
The above and other features and advantages of the present invention will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.
FIG. 1 is a schematic view of a structure of a turbine blade in the related art
FIG. 2 is a flow chart of a method of making a turbine blade of the present invention;
FIG. 3 is a schematic view of a turbine blade in a first embodiment of a turbine blade designed for use in the method of manufacturing a turbine blade according to the present invention;
fig. 4 is a schematic view of a turbine blade according to a second embodiment of the present invention.
The reference numerals are explained as follows:
1. a centroid; 2. a centroid; 3. and (5) a falling-off section.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. However, the exemplary embodiments can be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus detailed descriptions thereof will be omitted.
Referring to fig. 1, in the conventional blade-shedding rotational speed calculation method, the blade-shedding rotational speed of a blade with a shedding section in a pure tensile stress state is predicted, the centroid of the part above the shedding section coincides with the centroid of the section, and the shedding section only bears centrifugal force.
The present invention firstly provides a method for preparing a turbine blade, wherein the turbine blade is divided into a first part blade and a second part blade by a shedding section 3, the centroid 1 of the first part blade and the centroid 2 of the shedding section 3 have a distance DeltaX in the radial direction of the turbine blade, and referring to fig. 2, the method for preparing the turbine blade can comprise the following steps
Step S110, determining the burst speed of the wheel disc assembled with the turbine blade and the design speed of the turbine blade.
And step S120, determining the blade shedding rotating speed according to the design margin of the wheel disc breaking rotating speed and the turbine blade shedding rotating speed.
And step S130, calculating an initial stress group of the blade shedding section according to the material limit of the turbine blade, the turbine blade shedding rotating speed and the turbine blade design rotating speed.
And step S140, establishing a finite element model of the turbine blade, and simulating the normal working state of the turbine blade to obtain a design stress group.
And step S150, adjusting the interval until the design stress group meets a preset condition.
Compared with the prior art, the center of mass 1 of the first part of blades and the centroid 2 of the shedding section 3 have a distance delta X in the radial direction of the turbine blade, bending stress is generated, the magnitude of the bending stress is controlled through the distance delta X, the first part of blades can shed when the turbine blade which is simulated and designed reaches the blade shedding speed, the design precision is higher, and the problem that the wheel disc is damaged because the first part of blades are not shed when the turbine blade in the prior art sometimes reaches the blade shedding speed is solved; on the other hand, under the condition of the same shedding rotational speed, the area of the shedding section 3 can be properly increased in design, the first part of blades of the turbine blade are shed when the shedding rotational speed is reached by adjusting the distance delta X, and the rigidity value of the turbine blade prepared by the method is improved due to the increase of the shedding section 3, so that the service life of the turbine blade is prolonged.
The following describes in detail each step of the method for designing a turbine blade according to an embodiment of the present disclosure:
in step S110, a disk break rotational speed at which the turbine blade is assembled and a design rotational speed of the turbine blade are determined.
Determining a disk breaking speed V at which a turbine blade is mounted disk Blade design rotational speed V 0 The method comprises the steps of carrying out a first treatment on the surface of the The breaking rotational speed of the wheel disc is such that the wheel disc is damaged when the rotational speed exceeds the speed, so that the wheel disc cannot work normally.
In step S120, the blade-shedding rotational speed is determined according to the design margin of the wheel disc fracture rotational speed and the turbine blade-shedding rotational speed.
Determining the blade shedding rotating speed V according to the design margin n of the breaking rotating speed of the wheel disc and the blade shedding rotating speed blade The method comprises the steps of carrying out a first treatment on the surface of the The relation between the falling-off rotating speed of the sheet and the breaking rotating speed of the wheel disc and the design margin is as follows:
V blade ＝V disk /n
in step S130, an initial stress group of the blade-out section 3 is calculated from the material limit of the turbine blade, the turbine blade-out rotational speed, and the turbine blade design rotational speed.
In step S140, a finite element model of the turbine blade is built and a set of design stresses is obtained by simulating a normal operating state of the turbine blade.
In step S150, the pitch is adjusted until the set of design stresses meets a preset condition.
In the present exemplary embodiment, as shown with reference to fig. 3, the manner of changing the pitch Δx may be to change the mass on the first partial blade center axis side so that the centroid 1 of the first partial blade is offset from the first partial blade center axis. And the centroid 1 of the first part of the blade is offset from the centroid 2 of the falling section 3, and the mode of changing the mass of one side of the central axis of the first part of the blade can be to add a part of raw materials on one side of the mass to be changed in manufacturing, so that the mass of the left side and the right side of the central axis of the first part of the blade is different, the centroid 1 of the first part of the blade is offset from the central axis, and the centroid 1 of the first part of the blade and the centroid 2 of the falling section 3 generate a distance DeltaX in the radial direction of the turbine blade. The first part of the blades and the second part of the blades can be arranged in an offset way, so that the purpose that the centroid 1 of the first part of the blades and the centroid 2 of the falling section 3 are offset is achieved.
According to the blade material limit sigma b Blade-shedding rotational speed V blade Blade design rotational speed V 0 The equivalent stress sigma of the blade shedding section 3 is determined by the following shedding rotational speed calculation formula 0 The drop rotation speed calculation formula is:
V blade ＝V 0 (σ b /σ 0 ) 0.5
according to the equivalent stress sigma of the drop section 3 0 According to sigma Tensile stress ＝F/S＝m rw 2 S, it can be seen that the pull-off section 3 has a tensile stress sigma Tensile stress =350 MPa, determining the tensile stress σ of the shedding section 3 according to the equivalent stress decomposition formula Tensile stress And tensile and flexural stress sigma Bending stress The method comprises the steps of carrying out a first treatment on the surface of the The equivalent stress decomposition formula is:
σ 0 ＝Kσ bending stress +(1-K)σ Tensile stress
Where K is a structural constant and S is the area of the drop section 3.
And then establishing a finite element model of the turbine blade, and simulating the normal working state of the turbine blade to obtain a design stress group, wherein the design stress group can comprise design equivalent stress, design tensile stress and design bending stress.
When the distance DeltaX is adjusted, the design bending stress changes along with the change of the distance DeltaX, and the design equivalent stress and the design tensile stress do not change. Namely, the design equivalent stress is equal to the initial equivalent stress to be a certain value, and the design tensile stress is equal to the initial tensile stress to be a certain value.
The spacing Δx is adjusted such that the design bending stress up to the drop section 3 is equal to the initial bending stress within a threshold range. Thereby determining the spacing Δx and thus the final design of the finite element model.
For example, when a design rotational speed of a certain engine power turbine disk at which the disk breaking rotational speed is 180% is designed, a design margin n of the disk breaking rotational speed and the blade breaking rotational speed is 1.2, and a design rotational speed at which the blade breaking rotational speed is 150% can be obtained, and a material strength limit sigma is obtained b 1000MPa, sigma is known according to a falling-off rotating speed calculation formula 0 =445 MPa, the shedding rotational speed calculation formula is:
V blade ＝V 0 (σ b /σ 0 ) 0.5
when the blade is at the designed rotation speed, the tensile stress sigma of the falling section 3 can be known according to a tensile stress calculation formula Tensile stress =350 MPa, the tensile stress calculation formula is:
σ tensile stress ＝F/S＝m rw 2 /S
According to an equivalent stress decomposition formula, calculating the value of the tensile bending combined stress, wherein the equivalent stress decomposition formula is as follows:
σ 0 ＝Kσ bending stress +(1-K)σ Tensile stress
Sigma when K is 0.3 Bending stress The blade is subjected to 670MPa, the distance delta X between the center of mass 1 of the blade above the shedding section 3 and the center of the centroid 2 of the shedding section 3 is adjusted until the design bending stress of the shedding section 3 is equal to 670MPa, and the obtained blade automatically drops from the shedding section 3 at 150% of the design rotation speed without causing the rupture of a wheel disc (180% of the design rotation speed).
In another exemplary embodiment, referring to fig. 4, the pitch Δx is changed by providing grooves in the radial direction of the drop section 3, and adjusting the depth h and area of the grooves such that the centroid 2 of the drop section 3 is offset from the central axis of the turbine blade. The shape of the groove is not particularly limited herein, as long as the position of the centroid 2 of the drop section 3 can be changed.
According to the blade material limit sigma b Blade-shedding rotational speed V blade Blade design rotational speed V 0 Determining the initial equivalent stress sigma of the blade shedding section 3 through a shedding rotational speed calculation formula 0 The method comprises the steps of carrying out a first treatment on the surface of the The calculation formula of the falling-off rotating speed is as follows:
V blade ＝V 0 (σ b /σ 0 ) 0.5
determining the initial tensile stress sigma of the preset shedding section 3 according to a tensile stress calculation formula 0 Tensile stress The tensile stress calculation formula is:
σ tensile stress ＝F/S＝m rw 2 /S
Then, respectively calculating the centrifugal bending moment M from the position of the center of mass 1 of the upper blade of the falling section 3 to the center of the section 2 0 x And M 0 y Building a beam unit model with a shedding section of 3 areas through finite elements, and calculating initial bending stress sigma under centrifugal force and centrifugal bending moment working conditions 0 Bending stress ；
And then establishing a finite element model of the turbine blade, and simulating the normal working state of the turbine blade for the model to obtain a design stress group, wherein the design stress group can comprise design equivalent stress, design tensile stress and design bending stress.
Since the area of the break-off section 3 is changed in this example embodiment, the design tensile stress and the design bending stress are changed with the change of the pitch Δx while the design equivalent stress is not changed when the pitch Δx is adjusted.
Adjusting the above-mentioned spacing DeltaX to design the equivalent stress sigma 0 Design tensile stress sigma Tensile stress And design stretch-bend stress sigma 0 Bending stress The following formula is satisfied:
σ 0 ＝Kσ bending stress +(1-K)σ Tensile stress
Wherein K is a structural constant.
The spacing Δx is adjusted such that the design bending stress up to the drop section 3 is equal to the initial bending stress within a threshold range. Thereby determining the spacing Δx and thus the final design of the finite element model.
The invention further provides a turbine blade which is divided into a first part blade and a second part blade by a shedding section, wherein the centroid of the first part blade and the centroid of the shedding section have a distance in the radial direction of the turbine blade.
The mass may be made different on both sides of the first part blade center axis of the turbine blade; the density of one side of the central axis of the turbine blade is higher than that of the other side, and the volume of one side of the central axis of the turbine blade is higher than that of the other side; it is also possible that the density and volume of one side of the centre axis of the turbine blade is greater than that of the other side.
The first part of the blade may have a groove formed in one side of the central axis of the first part of the blade, and the center of the falling cross section is changed by the groove after the groove is formed, so that a space is generated between the center of mass of the first part and the center of the falling cross section in the radial direction of the turbine blade.
Still further, the present invention provides a turbine blade designing apparatus which is divided into a first partial blade and a second partial blade by a drop section 3, the center of mass 1 of the first partial blade and the center of mass of the drop section 3 having a distance Δx in the radial direction of the turbine blade, characterized in that the turbine blade designing apparatus may comprise the following modules
A first determining module for determining a wheel disc fracture speed at which the turbine blade is assembled and a design speed of the turbine blade;
the second determining module is used for determining the blade falling rotating speed according to the design margin of the wheel disc breaking rotating speed and the turbine blade falling rotating speed;
the calculating module is used for calculating an initial stress group of the blade falling section 3 according to the material limit of the turbine blade, the turbine blade falling rotating speed and the turbine blade design rotating speed;
the simulation module is used for establishing a finite element model of the turbine blade and simulating the normal working state of the turbine blade to obtain a design stress group;
and the adjusting module is used for adjusting the distance DeltaX until the design stress group meets the preset condition.
The specific embodiments of the turbine blade designing device are described in detail in the above method for manufacturing a turbine blade, and therefore, will not be described herein.
The above described features, structures or characteristics may be combined in any suitable manner in one or more embodiments, such as the possible, interchangeable features as discussed in connection with the various embodiments. In the above description, numerous specific details are provided to give a thorough understanding of embodiments of the invention. One skilled in the relevant art will recognize, however, that the inventive aspects may be practiced without one or more of the specific details, or with other methods, components, materials, and so forth. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention.
Although relative terms such as "upper" and "lower" are used in this specification to describe the relative relationship of one component of an icon to another component, these terms are used in this specification for convenience only, such as in terms of the orientation of the examples described in the figures. It will be appreciated that if the device of the icon is flipped upside down, the recited "up" component will become the "down" component. Other relative terms.
In the present specification, the terms "a," "an," "the," "said" are used to indicate the presence of one or more elements/components/etc.; the terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements/components/etc., in addition to the listed elements/components/etc.
It should be understood that the invention is not limited in its application to the details of construction and the arrangement of components set forth in the specification. The invention is capable of other embodiments and of being practiced and carried out in various ways. The foregoing variations and modifications are intended to fall within the scope of the present invention. It should be understood that the invention disclosed and defined in this specification extends to all alternative combinations of two or more of the individual features mentioned or evident from the text and/or drawings. All of these different combinations constitute various alternative aspects of the present invention. The embodiments described in this specification illustrate the best mode known for carrying out the invention and will enable those skilled in the art to make and use the invention.
Claims (10)
1. A method of manufacturing a turbine blade, characterized in that the turbine blade is divided by a cut-off section into a first part of blades and a second part of blades, the centroid of the first part of blades and the centroid of the cut-off section having a pitch in the radial direction of the turbine blade; the preparation method of the turbine blade comprises the following steps:
determining a burst speed of a disk on which the turbine blade is mounted and a design speed of the turbine blade;
determining the blade shedding rotating speed according to the design margin of the breaking rotating speed and the turbine blade shedding rotating speed;
calculating an initial stress group of a blade shedding section according to the material limit of the turbine blade, the turbine blade shedding rotating speed and the turbine blade design rotating speed;
establishing a finite element model of the turbine blade, and simulating the normal working state of the turbine blade to obtain a design stress group;
and adjusting the distance until a preset condition is met between the design stress group and the initial stress group.
2. The method of manufacturing a turbine blade of claim 1, wherein the set of design stresses includes a design equivalent stress, a design tensile stress, and a design stretch-bend resultant stress.
3. The method of manufacturing a turbine blade according to claim 2, wherein adjusting the pitch comprises:
the mass on one side of the first partial blade center axis in the finite element model of the turbine blade is adjusted such that the centroid is offset from the first partial blade center axis.
4. A method of manufacturing a turbine blade according to claim 3, wherein the set of initial stresses comprises at least an initial equivalent stress, an initial tensile stress and an initial stretch-bending stress; calculating an initial stress group of a blade-shedding section according to the material limit of the turbine blade, the turbine blade-shedding rotating speed and the turbine blade design rotating speed, wherein the initial stress group comprises the following components:
determining initial equivalent stress of a shedding section according to the material limit of the turbine blade, the shedding rotating speed of the turbine blade and the design rotating speed of the turbine blade;
and determining the initial tensile stress and the initial stretch-bending stress of the shedding section according to the initial equivalent stress of the shedding section.
5. The method of manufacturing a turbine blade according to claim 4, wherein adjusting the pitch until a preset condition is satisfied between the set of design stresses and the set of initial stresses comprises:
and adjusting the spacing to be equal to the initial stretch-bending stress in a threshold range.
6. The method of manufacturing a turbine blade according to claim 2, wherein adjusting the pitch comprises:
and forming a groove on the finite element model of the turbine blade, wherein the falling section passes through the groove, and the depth and the area of the groove are adjusted so that the centroid of the falling section deviates from the central axis of the turbine blade.
7. The method of manufacturing a turbine blade according to claim 6, wherein the set of initial stresses comprises at least an initial equivalent stress, an initial tensile stress, and an initial stretch-bending stress; calculating an initial stress group of a blade-shedding section according to the material limit of the turbine blade, the turbine blade-shedding rotating speed and the turbine blade design rotating speed, wherein the initial stress group comprises the following components:
determining initial equivalent stress of a blade shedding section according to the material limit of the turbine blade, the turbine blade shedding rotating speed and the turbine blade design rotating speed;
calculating initial tensile stress of the shedding section according to the initial equivalent stress;
calculating a centrifugal bending moment from the center of mass of the blade at the upper part of the shedding section to the center of the section;
and calculating the initial bending stress under the working conditions of centrifugal force and centrifugal bending moment.
8. The method of manufacturing a turbine blade according to claim 7, wherein adjusting the pitch until a preset condition is satisfied between the set of design stresses and the set of initial stresses comprises:
adjusting the distance until the design equivalent stress is equal to the initial equivalent stress, wherein the design equivalent stress, the design tensile stress and the design stretch bending stress satisfy the following relation:
σ 0 ＝Kσ bending stress +(1-K)σ Tensile stress
Wherein sigma 0 To design the equivalent stress, sigma Bending stress To design the stretch-bending stress, sigma Tensile stress The design tensile stress is shown, and K is the structural constant.
9. A turbine blade characterized in that the turbine blade is divided into a first part blade and a second part blade by a shedding section, and the centroid of the first part blade and the centroid of the shedding section have a distance in the radial direction of the turbine blade;
the size of the interval can enable the design stress group and the initial stress group of the turbine blade to meet preset conditions;
the initial stress group is obtained according to the material limit of the turbine blade, the turbine blade falling speed and the turbine blade design speed.
10. The turbine blade of claim 9, wherein the turbine blade is divided into a first partial blade and a second partial blade by a drop section, a centroid of the first partial blade having a spacing from a centroid of the drop section in a radial direction of the turbine blade, comprising:
the mass of both sides of the first part blade central axis of the turbine blade is different; or one side of the central axis of the first part of blades is provided with a groove, and the falling section passes through the groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910228780.8A CN109977537B (en) | 2019-03-25 | 2019-03-25 | Turbine blade and method for producing a turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910228780.8A CN109977537B (en) | 2019-03-25 | 2019-03-25 | Turbine blade and method for producing a turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109977537A CN109977537A (en) | 2019-07-05 |
| CN109977537B true CN109977537B (en) | 2023-05-30 |
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| CN111102015A (en) * | 2019-12-31 | 2020-05-05 | 中北大学 | Speed-limiting protection device for turbine generator blade |
| CN112324515B (en) * | 2020-10-29 | 2022-10-18 | 中国航发南方工业有限公司 | Turbine blade reliability improvement method |
| CN113390377A (en) * | 2021-07-21 | 2021-09-14 | 中国航发成都发动机有限公司 | Three-coordinate measuring machine detection data management system |
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