CN112197922B - Turbine blade vibration fatigue simulation piece and design method thereof - Google Patents
Turbine blade vibration fatigue simulation piece and design method thereof Download PDFInfo
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- CN112197922B CN112197922B CN202010860211.8A CN202010860211A CN112197922B CN 112197922 B CN112197922 B CN 112197922B CN 202010860211 A CN202010860211 A CN 202010860211A CN 112197922 B CN112197922 B CN 112197922B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
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- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
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Abstract
The invention discloses a turbine blade vibration fatigue simulation piece and a design method thereof, wherein the turbine blade vibration fatigue simulation piece comprises: a clamping section; the blade body section is fixed on the clamping section and has symmetrical cross section shape, the vibration stress ratio of a blade back root part and a leading edge root part in the root part of the blade body section is equal to the vibration stress ratio of a blade basin/back danger point of a designed turbine blade model in vibration mode analysis, and the length L of the blade body section enables the first-order bending natural frequency of a turbine blade vibration fatigue simulation piece to be the same as the first-order bending natural frequency of the designed turbine blade model; and simulating a blade root fillet, arranging at the joint of the blade body section root and the clamping section, wherein the radius of the blade root fillet is the same as the blade root radius of the designed turbine blade model. The turbine blade vibration fatigue simulation part designed by the invention has the advantages of simple structural form, no complex high-order curved surface, low manufacturing, processing and testing cost, capability of rapidly acquiring the vibration fatigue performance of the blade, short evaluation period and low cost.
Description
Technical Field
The invention relates to the technical field of turbine blade detection, in particular to a turbine blade vibration fatigue simulation piece and a design method thereof.
Background
The current research on the vibration fatigue performance of the turbine blade is realized by a full-size designed turbine blade vibration fatigue test. However, the long process is required for the turbine blade from the design drawing to the mold manufacturing to the blade casting, and the designed turbine blade is expensive, resulting in high test cost. In order to reduce the test cost, only a very limited number of tests can be carried out, and the vibration fatigue reliability evaluation of the turbine blade is limited.
The prior art needs to adopt a full-size designed turbine blade for testing, the full-size turbine blade needs a long process from design drawing to die manufacturing to blade casting, and the manufacturing, machining and testing costs of the designed turbine blade are high, so that the evaluation period of the vibration fatigue performance of the turbine blade is long and the cost is high.
Disclosure of Invention
The invention provides a turbine blade vibration fatigue simulation piece, which aims to solve the technical problems of long evaluation period and high cost caused by the adoption of a turbine blade with a full-size design in the conventional turbine blade vibration fatigue test.
The technical scheme adopted by the invention is as follows:
a turbine blade vibration fatigue simulator, comprising:
the clamping section is used for being fixed on the test bed during testing;
the blade body section is fixed on the clamping section and has symmetrical cross section shape, the vibration stress ratio of a blade back root part and a leading edge root part in the root part of the blade body section is equal to the vibration stress ratio of a blade basin/back danger point of a designed turbine blade model in vibration mode analysis, and the length L of the blade body section enables the first-order bending natural frequency of a turbine blade vibration fatigue simulation piece to be the same as the first-order bending natural frequency of the designed turbine blade model;
and the simulated blade root fillet is arranged at the joint of the blade body section root and the clamping section, and the radius R3 of the simulated blade root fillet is the same as the blade root rounding radius of the designed turbine blade model.
Further, the clamping section is cube shaped and sized to enclose the main blade section.
Further, the cross-sectional profile of the main blade section comprises:
the blade back simulation circular arc section has the radius R1 equal to the radius of a tangent circle at the maximum blade back mode vibration stress position in the blade root section of the designed turbine blade model;
the concave surfaces of the two front edge simulated arc sections are symmetrically distributed on the left side and the right side of the symmetrical line of the blade back simulated arc sections oppositely, the radius R2 of the front edge simulated arc sections is equal to the radius of a tangent circle at the position with the maximum front edge modal vibration stress in the blade root section of the designed turbine blade model, the distance between the centers of the two front edge simulated arc sections is L1, an included angle theta 1 is arranged between the centers of the two front edge simulated arc sections and the middle point of the blade back simulated arc section,
the inverted circular section is consistent with the concave-convex direction of the blade back simulation circular arc section, and the circle center of the inverted circular section is positioned on the symmetrical line of the blade back simulation circular arc section;
and the tangent straight line is tangentially connected between the two front edge simulation arc sections and the blade back simulation arc section as well as between the two front edge simulation arc sections and the rounding section.
Further, the included angle theta 1, the circle center distance L1 and the radius R4 of the rounding section are obtained through iterative modal analysis until the vibration stress ratio of the blade back root to the leading edge root is equal to the vibration stress ratio of the blade basin/back danger point of the designed turbine blade model through vibration modal analysis.
Further, the length L of the blade body section is obtained through iterative modal analysis until the first-order bending natural frequency of the turbine blade vibration fatigue simulation piece is the same as that of the designed turbine blade model.
The invention also provides a design method of the turbine blade vibration fatigue simulation piece, which comprises the following steps:
obtaining a root rounding radius according to a designed turbine blade model to be used as a simulated root rounding of a turbine blade vibration fatigue simulation piece;
carrying out vibration mode analysis of a near-service condition on the designed turbine blade model to obtain a blade front edge and a blade back danger part, inherent frequency and a blade basin/back danger point vibration stress ratio, wherein the blade front edge and the blade back danger part are respectively a blade back mode vibration stress maximum part and a front edge mode vibration stress maximum part in a blade root section of the designed turbine blade model;
and according to the root rounding radius, the dangerous positions of the front edge and the back of the blade, the natural frequency and the vibration stress ratio of the dangerous points of the blade basin/back, and by combining modal analysis, obtaining the structural characteristics of the turbine blade vibration fatigue simulation part, and completing the design of the turbine blade vibration fatigue simulation part.
Further, according to the blade root radius, the blade front edge and the blade back danger position, the natural frequency and the blade basin/back danger point vibration stress ratio, the structural characteristics of the turbine blade vibration fatigue simulation piece are obtained, and the method specifically comprises the following steps:
and taking the root rounding radius of the designed turbine blade model as a simulated root rounding of the turbine blade vibration fatigue simulation piece.
Further, according to the blade root radius, the blade front edge and the blade back danger position, the natural frequency and the blade basin/back danger point vibration stress ratio, the structural characteristics of the turbine blade vibration fatigue simulation piece are obtained, and the method specifically comprises the following steps:
and carrying out iterative modal analysis on the turbine blade vibration fatigue simulation piece, and obtaining the length L of the blade body section of the turbine blade vibration fatigue simulation piece when the first-order bending natural frequency of the turbine blade vibration fatigue simulation piece is the same as the first-order bending natural frequency of the designed turbine blade model.
Further, according to the blade root radius, the blade front edge and the blade back danger position, the natural frequency and the blade basin/back danger point vibration stress ratio, the structural characteristics of the turbine blade vibration fatigue simulation piece are obtained, and the method specifically comprises the following steps:
respectively obtaining the radiuses of tangent circles of the front edge and the dangerous part of the blade back of the blade, and determining two front edge simulation arc sections and two blade back simulation arc sections in the cross section outline of the blade body section of the turbine blade vibration fatigue simulation part according to the radiuses of the tangent circles of the front edge and the dangerous part of the blade back of the blade;
and carrying out iterative modal analysis on the turbine blade vibration fatigue simulation part, and when the vibration stress ratio of the blade back root and the leading edge root of the turbine blade vibration fatigue simulation part is equal to the vibration stress ratio of the blade basin/back danger point of the designed turbine blade model in the vibration modal analysis, obtaining an included angle theta 1, a circle center distance L1, a radius R4 of a rounded section and the length value of each tangent straight line in the cross section profile of the blade body section of the turbine blade vibration fatigue simulation part.
Further, according to the blade root radius, the blade front edge and the blade back danger position, the natural frequency and the blade basin/back danger point vibration stress ratio, the structural characteristics of the turbine blade vibration fatigue simulation piece are obtained, and the method specifically comprises the following steps:
and obtaining the structural characteristics of a blade body section, a simulated blade root fillet and a clamping section of the turbine blade vibration fatigue simulation piece according to the obtained root radius, the two front edge simulated arc sections and the blade back simulated arc section, the included angle theta 1, the circle center distance L1, the radius R4 of the radius section and the length value of each tangent straight line, and completing the design of the turbine blade vibration fatigue simulation piece.
The invention has the following beneficial effects:
according to the invention, the turbine blade vibration fatigue simulation part is designed for the dangerous part of the turbine blade in the turbine blade design stage, and the vibration fatigue test is carried out through the turbine blade vibration fatigue simulation part, so that the vibration characteristics of the blade can be simulated without a full-size blade, the vibration fatigue performance of the blade can be rapidly obtained, the evaluation period is short, and the cost is low. The turbine blade vibration fatigue simulation part designed by the invention has the advantages of simple structural form, no complex high-order curved surface, no need of manufacturing a time-consuming and expensive casting mold, low manufacturing, processing and testing cost and short period, and the vibration reliability of the blade can be fully evaluated by developing a sufficient number of structural simulation part tests.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a perspective view of a turbine blade vibration fatigue simulator in accordance with a preferred embodiment of the present invention;
FIG. 2 is a schematic view of the leading edge, the blade back root of a turbine blade vibration fatigue simulator in accordance with a preferred embodiment of the present invention.
FIG. 3 is a schematic view of a turbine blade root designed for increased vibratory stress in the blade root section.
FIG. 4 is a schematic cross-sectional view of a blade section of a turbine blade vibration fatigue simulator in accordance with a preferred embodiment of the present invention.
FIG. 5 is a flow chart of a method for designing a turbine blade vibration fatigue simulator in accordance with a preferred embodiment of the present invention.
FIG. 6 is a flow chart of a method for designing a turbine blade vibration fatigue simulator according to another preferred embodiment of the present invention.
In the figure: 1. a clamping section; 2. a blade body section; 21. the front edge simulates a circular arc section; 22. a tangent line; 23. simulating a circular arc section on the leaf back; 24. a rounding section; 3. simulating a blade root fillet; 4. the maximum modal vibration stress of the blade back; 5. the maximum position of the front edge modal vibration stress; 6. leaf back root; 7. a leading edge root.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 and 2, a turbine blade vibration fatigue simulation includes:
the clamping section 1 is used for being fixed on a test bed during testing;
the blade body section 2 is fixed on the clamping section 1, the cross section of the blade body section 2 is symmetrical in shape, the vibration stress ratio of a blade back root 6 and a leading edge root 7 in the root of the blade body section 2 is equal to the vibration stress ratio of a blade basin/back danger point analyzed by the vibration mode of a designed turbine blade model, and the length L of the blade body section 2 enables the first-order bending natural frequency of a turbine blade vibration fatigue simulation piece to be the same as the first-order bending natural frequency of the designed turbine blade model;
and the simulated blade root fillet 3 is arranged at the joint of the root of the blade body section 2 and the clamping section 1, and the radius R3 of the simulated blade root fillet 3 is the same as the root rounding radius of the designed turbine blade model.
The turbine blade vibration fatigue simulation part is designed for the dangerous part of the turbine blade in the design stage of the turbine blade, the turbine blade vibration fatigue simulation part is subjected to a vibration fatigue test, real full-size blades are not needed, the vibration characteristics of the blade can be simulated, the vibration fatigue performance of the blade is rapidly obtained, the evaluation period is greatly shortened, and the test cost is reduced. The turbine blade vibration fatigue simulation piece designed by the embodiment is simple in structural form, free of complex high-order curved surfaces, free of manufacturing time-consuming and expensive casting molds, low in manufacturing, processing and testing cost, short in period, and capable of fully evaluating blade vibration reliability by developing a sufficient number of structural simulation piece tests.
In a preferred embodiment of the invention, the clamping section 1 is in a cubic shape, so that the clamping section is convenient to clamp on a testing machine, and the clamping section is sized to contain the blade body section 2, as shown in fig. 1, the blade body section 2 and the clamping section 1 are arranged, and the blade body section 2 is completely positioned in the connecting surface of the clamping section 1, so that the blade body section is similar to a real blade.
In a preferred embodiment of the invention, as shown in fig. 4, the cross-sectional profile of the main blade section 2 comprises:
the blade back simulation circular arc section 23 is characterized in that the radius R1 of the blade back simulation circular arc section 23 is equal to the radius of a tangent circle of a blade back modal vibration stress maximum position 4 in the blade root section of the designed turbine blade model;
the concave surfaces of the two front edge simulated arc sections 21 are symmetrically distributed on the left side and the right side of the symmetrical line of the blade back simulated arc section 23 oppositely, the radius R2 of the front edge simulated arc section 21 is equal to the radius of a tangent circle of a position 5 with the maximum front edge modal vibration stress in the blade root section of the designed turbine blade model, the distance between the circle centers of the two front edge simulated arc sections 21 is L1, an included angle theta 1 is arranged between the connection line of the circle centers of the two front edge simulated arc sections 21 and the midpoint of the blade back simulated arc section 23,
the inverted circular section 24 is consistent with the concave-convex direction of the blade back simulation circular arc section 23, and the circle center of the inverted circular section is positioned on the symmetrical line of the blade back simulation circular arc section 23;
and the tangent straight line 22 is tangentially connected between the two leading edge simulated arc sections 21 and the blade back simulated arc section 23 and between the two leading edge simulated arc sections 21 and the radius section 24.
For the turbine blade, the dangerous part typically refers to a place where a large vibration stress occurs, the dangerous part generally occurs at the leading edge of the blade root section, such as the maximum point 4 of the blade back modal vibration stress and the maximum point 5 of the leading edge modal vibration stress in fig. 3, and the radius dimensions of the tangent circles at the maximum point 4 of the blade back modal vibration stress and the maximum point 5 of the leading edge modal vibration stress in the blade root section are extracted as the radius R1 of the blade back simulated arc segment 23 and the radius R2 of the leading edge simulated arc segment 21 of the cross section of the blade body segment 2, respectively.
In the embodiment, the cross section profile of the blade body section 2 is entirely crescent, is composed of circular arcs and straight lines, has no complex high-order curved surface, is easy to process, does not need to manufacture a time-consuming and expensive casting mold, has low cost and short period, and in addition, because the radiuses of the blade back simulation circular arc section 23 and the two front edge simulation circular arc sections 21 are determined according to the tangent circle radiuses of the blade back modal vibration stress maximum part 4 and the front edge modal vibration stress maximum part 5 in the blade root section of the designed turbine blade model, the turbine blade vibration fatigue simulation piece of the embodiment can simulate the structural characteristics of the dangerous part of the blade, and the vibration stress distribution conforms to the real blade, thereby realizing the perfect substitution of the designed turbine blade model, needing no full-size blade, simulating the vibration characteristics of the blade through the simulation piece, and rapidly obtaining the vibration fatigue performance of the blade, greatly shortens the evaluation period and reduces the test cost.
Specifically, the included angle θ 1, the circle center distance L1 and the radius R4 of the rounded section 24 are obtained through iterative modal analysis until the vibration stress ratio of the blade back root 6 to the leading edge root 7 is equal to the vibration stress ratio of the blade basin/back danger point of the designed turbine blade model through vibration modal analysis.
In this embodiment, the sizes of other portions in the cross-sectional profile of the blade body section 2, such as the included angle θ 1, the circle center distance L1, and the radius R4 of the rounded section 24, are obtained through iterative modal analysis, and the end condition of the iterative modal analysis is that the vibration stress ratio between the blade back root 6 and the leading edge root 7 is equal to the vibration stress ratio between the blade basin and the back danger point in the vibration modal analysis of the designed turbine blade model, so that the blade back root 6 and the leading edge root 7 of the turbine blade vibration fatigue simulator of this embodiment can simulate the structural characteristics of the real blade danger site, and the vibration stress distribution conforms to the real blade, thereby achieving effective replacement of the designed turbine blade model.
Specifically, the length L of the blade body section 2 is obtained by iterative modal analysis until the first order bending natural frequency of the turbine blade vibration fatigue simulator is the same as the first order bending natural frequency of the designed turbine blade model.
In this embodiment, the length L of the blade body section 2 is obtained through iterative modal analysis, and the end condition of the iterative modal analysis is that the first-order bending natural frequency of the turbine blade vibration fatigue simulation piece is the same as the first-order bending natural frequency of the designed turbine blade model, so that the length L of the turbine blade vibration fatigue simulation piece of this embodiment can simulate the structural characteristics of the real blade length, and the first-order bending natural frequency conforms to the real blade, thereby realizing effective replacement of the designed turbine blade model.
As shown in FIG. 5, another aspect of the present invention further provides a method for designing a turbine blade vibration fatigue simulator, comprising the steps of:
s1, obtaining a root rounding radius according to the designed turbine blade model to serve as a simulated root fillet 3 of the turbine blade vibration fatigue simulation piece;
s2, carrying out vibration mode analysis of near service conditions on the designed turbine blade model, and obtaining a blade front edge and blade back danger part, inherent frequency and a blade basin/back danger point vibration stress ratio, wherein the blade front edge and the blade back danger part are respectively a blade back mode vibration stress maximum part 4 and a front edge mode vibration stress maximum part 5 in a blade root section of the designed turbine blade model;
and S3, obtaining the structural characteristics of the turbine blade vibration fatigue simulation part according to the root rounding radius, the blade front edge and blade back danger positions, the natural frequency and the blade basin/back danger point vibration stress ratio by combining modal analysis, and completing the design of the turbine blade vibration fatigue simulation part.
The turbine blade vibration fatigue simulation piece designed by the embodiment is simple in structural form, free of complex high-order curved surfaces, free of manufacturing time-consuming and expensive casting molds, low in manufacturing, processing and testing cost, short in period, and capable of fully evaluating blade vibration reliability by developing a sufficient number of structural simulation piece tests. The turbine blade vibration fatigue simulation part is designed for the dangerous part of the turbine blade in the design stage of the turbine blade, the turbine blade vibration fatigue simulation part is subjected to a vibration fatigue test, real full-size blades are not needed, the vibration characteristics of the blade can be simulated, the vibration fatigue performance of the blade is rapidly obtained, the evaluation period is greatly shortened, and the test cost is reduced.
Specifically, as shown in fig. 6, in a preferred embodiment of the present invention, the method for obtaining the structural characteristics of the turbine blade vibration fatigue simulation piece according to the root rounding radius, the blade leading edge and the blade back risk part, the natural frequency and the blade basin/back risk point vibration stress ratio specifically includes the following steps:
taking the root rounding radius of the designed turbine blade model as a simulated root fillet 3 of the turbine blade vibration fatigue simulation piece;
and carrying out iterative modal analysis on the turbine blade vibration fatigue simulation piece, and obtaining the length L of the blade body section 2 of the turbine blade vibration fatigue simulation piece when the first-order bending natural frequency of the turbine blade vibration fatigue simulation piece is the same as the first-order bending natural frequency of the designed turbine blade model.
Respectively obtaining the radiuses of tangent circles of the front edge and the dangerous part of the blade back of the blade, and determining two front edge simulation arc sections 21 and two blade back simulation arc sections 23 in the cross section outline of the blade body section 2 of the turbine blade vibration fatigue simulation part according to the radiuses of the tangent circles of the front edge and the dangerous part of the blade back of the blade;
performing iterative modal analysis on the turbine blade vibration fatigue simulation part, and when the vibration stress ratio of a blade back root 6 and a leading edge root 7 of the turbine blade vibration fatigue simulation part is equal to the vibration stress ratio of a blade basin/back danger point analyzed by the vibration modal analysis of a designed turbine blade model, obtaining an included angle theta 1, a circle center distance L1, a radius R4 of a rounding section 24 and the length value of each tangent straight line 22 in the cross section profile of a blade body section 2 of the turbine blade vibration fatigue simulation part;
and obtaining the structural characteristics of the blade body section 2, the simulated blade root fillet 3 and the clamping section 1 of the turbine blade vibration fatigue simulation piece according to the obtained root radius, the two leading edge simulated arc sections 21 and the blade back simulated arc section 23, the included angle theta 1, the circle center distance L1, the radius R4 of the radius section 24 and the length value of each tangent straight line 22, and completing the design of the turbine blade vibration fatigue simulation piece.
In the embodiment, when specific structural characteristics of the turbine blade vibration fatigue simulation are designed, the diameter R3 of the simulated blade root fillet 3 is the same as the root radius of the designed turbine blade model, the length L of the blade body section 2 is obtained through iterative modal analysis, and the iteration end condition is that the first-order bending natural frequency of the turbine blade vibration fatigue simulation piece is the same as the first-order bending natural frequency of the designed turbine blade model, two leading edge simulated arc sections 21 and two blade back simulated arc sections 23 in the cross-sectional profile of the blade body section 2 are determined by the tangent circle radii of the leading edge and the blade back danger part of the real blade, the included angle θ 1, the circle center distance L1, the radius R4 of the rounded section 24 and the length value of each tangent straight line 22 in the cross-sectional profile of the blade body section 2 are obtained through iterative modal analysis, and the iteration end condition is that the vibration stress ratio of the blade back root 6 and the leading edge root 7 of the turbine blade vibration fatigue simulation piece is the same as the vibration stress ratio of the designed turbine blade model The vibration stress ratios of the separated blade basin/back danger points are equal, so that the designed turbine blade vibration fatigue simulation piece can simulate the structural characteristics of the length of a real blade, the relevant characteristics are consistent with those of the real blade, and the designed turbine blade model is effectively replaced. Through carrying out the vibration fatigue test to turbine blade vibration fatigue simulation piece, need not real full-size blade, can simulate blade vibration characteristic to obtain blade vibration fatigue performance fast, shorten evaluation cycle, reduce test cost by a wide margin.
The method is used for designing the structural feature simulation piece for the dangerous part of the designed turbine blade in the design stage of the turbine blade, and the vibration fatigue performance of the blade is rapidly obtained through the vibration fatigue test of the structural feature simulation piece. The designed simulation part has no complex high-order curved surface, simple structure, low manufacturing, processing and testing cost and is convenient for fully evaluating the vibration reliability of the blade.
The invention can be used for rapidly developing the turbine blade structure simulation part test at low cost in the turbine blade design stage to obtain the vibration fatigue resistance of the turbine blade, and can also be used for evaluating the vibration fatigue resistance of the blade by adopting the designed structure characteristic simulation part for the blade which is designed.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A turbine blade vibration fatigue simulation, comprising:
the clamping section (1) is used for being fixed on a test bed during testing;
the blade body section (2) is fixed on the clamping section (1) and has symmetrical cross section shape, the vibration stress ratio of a blade back root (6) and a leading edge root (7) in the root part of the blade body section (2) is equal to the vibration stress ratio of a blade basin/back danger point of a designed turbine blade model in vibration mode analysis, and the length L of the blade body section (2) enables the first-order bending natural frequency of a turbine blade vibration fatigue simulation piece to be the same as the first-order bending natural frequency of the designed turbine blade model;
the simulated blade root fillet (3) is arranged at the joint of the root of the blade body section (2) and the clamping section (1), and the radius R3 of the simulated blade root fillet (3) is the same as the blade root rounding radius of the designed turbine blade model;
the clamping section (1) is in a cubic shape, and the size of the clamping section can contain the blade body section (2);
the cross-sectional profile of the blade section (2) comprises:
the blade back simulation circular arc section (23) is characterized in that the radius R1 of the blade back simulation circular arc section (23) is equal to the radius of a tangent circle of a blade back modal vibration stress maximum position (4) in the blade root section of the designed turbine blade model;
the concave surfaces of the two front edge simulation circular arc sections (21) are symmetrically distributed on the left side and the right side of the symmetry line of the blade back simulation circular arc section (23) oppositely, the radius R2 of the front edge simulation circular arc sections (21) is equal to the radius of a tangent circle of a position (5) with the maximum front edge modal vibration stress in the blade root section of the designed turbine blade model, the distance between the circle centers of the two front edge simulation circular arc sections (21) is L1, an included angle theta 1 is formed between the middle of the connecting line of the circle centers of the two front edge simulation circular arc sections (21) and the midpoint of the blade back simulation circular arc section (23),
the inverted circular section (24) is consistent with the concave-convex direction of the blade back simulation circular arc section (23) and the circle center of the inverted circular section is positioned on the symmetrical line of the blade back simulation circular arc section (23);
and the tangent straight line (22) is tangentially connected between the two front edge simulation circular arc sections (21) and the blade back simulation circular arc section (23) and between the two front edge simulation circular arc sections (21) and the rounding section (24).
2. The turbine blade vibration fatigue simulator of claim 1, wherein the included angle θ 1, the circle center distance L1, and the radius R4 of the rounded section (24) are obtained by iterative modal analysis until the ratio of the vibration stress of the blade back root (6) to the leading edge root (7) is equal to the ratio of the vibration stress of the blade basin/back hazard point of the designed turbine blade model by vibration modal analysis.
3. The turbine blade vibratory fatigue simulator of claim 1, wherein the length L of the main blade section (2) is sized by iterative modal analysis until the first order bending natural frequency of the turbine blade vibratory fatigue simulator is the same as the first order bending natural frequency of the designed turbine blade model.
4. A design method of a turbine blade vibration fatigue simulation piece is characterized by comprising the following steps:
obtaining a root rounding radius as a simulated root fillet (3) of the turbine blade vibration fatigue simulation piece according to the designed turbine blade model;
carrying out vibration mode analysis of a near-service condition on a designed turbine blade model to obtain a blade leading edge and a blade back danger part, inherent frequency and a blade basin/back danger point vibration stress ratio, wherein the blade leading edge and the blade back danger part are respectively a blade back modal vibration stress maximum part (4) and a leading edge modal vibration stress maximum part (5) in a blade root section of the designed turbine blade model;
according to the root rounding radius, the blade front edge and the blade back danger part, the natural frequency and the blade basin/back danger point vibration stress ratio, and in combination with modal analysis, obtaining the structural characteristics of the turbine blade vibration fatigue simulation part, and completing the design of the turbine blade vibration fatigue simulation part;
according to blade root radius, blade leading edge and the dangerous position of blade back, natural frequency and blade basin/back danger point vibration stress ratio try to obtain the structural feature of turbine blade vibration fatigue analog, specifically include the step:
taking the root rounding radius of the designed turbine blade model as a simulated root fillet (3) of the turbine blade vibration fatigue simulation piece;
according to blade root radius, blade leading edge and the dangerous position of blade back, natural frequency and blade basin/back danger point vibration stress ratio try to obtain the structural feature of turbine blade vibration fatigue analog, specifically include the step:
performing iterative modal analysis on the turbine blade vibration fatigue simulation piece, and obtaining the length L of the blade body section (2) of the turbine blade vibration fatigue simulation piece when the first-order bending natural frequency of the turbine blade vibration fatigue simulation piece is the same as the first-order bending natural frequency of the designed turbine blade model;
according to blade root radius, blade leading edge and the dangerous position of blade back, natural frequency and blade basin/back danger point vibration stress ratio try to obtain the structural feature of turbine blade vibration fatigue analog, specifically include the step:
respectively obtaining the radiuses of tangent circles of the front edge and the dangerous part of the blade back of the blade, and determining two front edge simulation arc sections (21) and two blade back simulation arc sections (23) in the cross section profile of the blade body section (2) of the turbine blade vibration fatigue simulation part according to the radiuses of the tangent circles of the front edge and the dangerous part of the blade back of the blade;
iterative modal analysis is carried out on the turbine blade vibration fatigue simulation piece, and when the vibration stress ratio of a blade back root (6) and a leading edge root (7) of the turbine blade vibration fatigue simulation piece is equal to the vibration stress ratio of a blade basin/back danger point of the designed turbine blade model in the vibration modal analysis, the included angle theta 1, the circle center distance L1, the radius R4 of the rounding section (24) and the length value of each tangent straight line (22) in the cross section profile of the blade body section (2) of the turbine blade vibration fatigue simulation piece are obtained.
5. The design method according to claim 4, wherein the structural characteristics of the turbine blade vibration fatigue simulation piece are obtained according to the root rounding radius, the blade leading edge and the blade back danger part, the natural frequency and the blade basin/back danger point vibration stress ratio, and the design method specifically comprises the following steps:
and according to the obtained root radius, the two front edge simulated arc sections (21) and the blade back simulated arc section (23), the included angle theta 1, the circle center distance L1, the radius R4 of the radius section (24) and the length value of each tangent straight line (22), obtaining the structural characteristics of the blade body section (2), the simulated blade root fillet (3) and the clamping section (1) of the turbine blade vibration fatigue simulation piece, and completing the design of the turbine blade vibration fatigue simulation piece.
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