CN113468788B - Deformation coordination design method for engine blisk - Google Patents

Deformation coordination design method for engine blisk Download PDF

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Publication number
CN113468788B
CN113468788B CN202110817084.8A CN202110817084A CN113468788B CN 113468788 B CN113468788 B CN 113468788B CN 202110817084 A CN202110817084 A CN 202110817084A CN 113468788 B CN113468788 B CN 113468788B
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Prior art keywords
blisk
deformation
blade
delta
design
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CN113468788A (en
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孙涛
冯引利
蒋文婷
李佳琦
莫古云
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Institute of Engineering Thermophysics of CAS
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Institute of Engineering Thermophysics of CAS
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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]
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Abstract

The invention discloses a deformation coordination design method for an engine blisk, relates to the technical field of strength of aero-engines, can solve the problem that the deformation difference of the blade tip of the blisk from the air inlet side to the air outlet side is large, and can quickly optimize a structure meeting the deformation requirement on the premise of not changing the structure of the blisk. The design method is simple, is very suitable for engineering design and application, has wide application range, and can be used for strength design of the blisk of an aircraft engine and a gas turbine.

Description

Deformation coordination design method for engine blisk
Technical Field
The invention belongs to the technical field of strength of aero-engines and gas turbines, and relates to a method for coordinately designing deformation of an engine blisk.
Background
Rotor and stator clearance control is the guarantee of aeroengine high performance, high reliability. After the blade tip of the rotor blade and the inner wall surface of the casing are calculated and selected, the gap is examined through the whole engine and can be finally determined after being adjusted for many times.
During engineering design, deformation of the blade tips from the air inlet side to the air exhaust side is kept consistent, namely, no axial deformation difference exists, and the fact that the overall deformation of the rotor blade meets the matching requirement of the blade tip clearance is guaranteed. Under the actual service condition, due to the influence of factors such as temperature gradient, bending deformation, load transfer and the like, the blade tip deformation has difference along the axial direction, the rotor and stator clearance is not uniform, and the performance and the safety of the engine are not good if the difference is large. In addition, if the rotor rotates to generate whirling motion, gaps in the sealing cavity are uneven, sealing gap airflow excitation can be caused, the rotor is unstable in motion, abnormal vibration occurs, and blade tip deformation is uneven along the axial direction, so that the control of the rotor and stator gaps is more challenging.
When the overall scheme of the engine and the pneumatic design of components are determined, a design method capable of enabling the blade tips to deform in the axial direction is urgently needed, the uniformity of deformation of the inlet and outlet blade tips is improved in the design stage, the overall deformation of the rotor blades is guaranteed to meet the requirement of gap control, the gap is convenient to reduce, and the pneumatic performance is improved.
Disclosure of Invention
Aiming at the technical defects in the prior art, the invention provides a deformation coordination design method for an engine blisk, which aims to solve the problem that the deformation difference of the blade tip of the blisk from the air inlet side to the air outlet side is large in the design process, and can meet the requirement of deformation uniformity by adjusting the axial relative position of a blade and the blisk on the premise of not changing the structure of the blisk. The design method is simple, is very suitable for engineering design and application, has wide application range, and can be used for strength design of the blisk of an aircraft engine and a gas turbine.
The invention discloses a method for coordinately designing deformation of an engine blisk, which is used for solving the technical problem and is characterized by comprising the following implementation steps of:
SS1, establishing a finite element model of the blisk based on a three-dimensional geometric model of the blisk, and performing strength calculation on the structure of the blisk by taking a temperature field, a pneumatic load, a cavity pressure and a centrifugal load under the most severe design working condition as load input;
SS2. radial deformation U for extracting integral blade disc blade tip air inlet edge X1 Radial deformation of the exhaust edge of the blade tip U X2 Let a delta U X ＝U X1 -U X2 ；
SS3, extracting the barycentric coordinate axial value of the blade, and recording as Z 1 Axial value of the coordinates of the center line of the wheel disk is recorded as Z 2 Let Δ Z equal to Z 1 -Z 2 . Within an allowable range, adjusting delta Z according to a linear change rule, and respectively calculating the corresponding U of the blisk model X1 And U X2 ；
SS4. analysis of different DeltaZ vs. DeltaU X And fitting out delta Z and delta U by linear interpolation X Quantitative relationship between adjustments, in combination with DeltaU X Determining a delta Z and an axial adjustment scheme of a blade and a wheel disc according to design requirements;
and SS5, further finely adjusting the axial relative positions of the blade and the wheel disc, and performing accounting on the deformation of the blade tip so as to ensure the design requirement of blade tip harmony and determine the final scheme of the integral blade disc.
In a further embodiment, in step SS1, the intensity calculation is performed based on finite element calculation analysis program Ansys.
In a further embodiment, in said step SS3, the barycentric coordinates are obtained by a three-dimensional modeling program UG.
In a further embodiment, the step SS4 is controlled within + -1 mm, and the distance of each adjustment is + -0.1-0.5 mm.
In a further embodiment, in step SS5, the tip deformation coordination design requirement is |. DELTA.U X |≤0.05mm。
The invention provides a deformation coordination design method for an engine blisk, which changes the radial displacement distribution of a blade tip from the angle of the relative axial position of a blade and the blisk in the design stage, can quickly optimize and design a blisk structure meeting the design requirement of the deformation coordination of the blade tip on the premise of not changing the structure by summarizing the association rule of the relative axial position of the blade and the blisk and the deformation of the blade tip, and simplifies the optimization process of the blisk structure. The design method is simple, is very suitable for engineering design and application, has wide application range, and can be used for the structural strength design of the blisk of an aeroengine and a gas turbine.
Drawings
FIG. 1 is a flow chart of a method for designing deformation coordination of an engine blisk according to an embodiment of the present invention;
FIG. 2 is a cloud of loads imposed by a blisk structure to which embodiments of the present invention are directed;
FIG. 3 is a schematic diagram of adjustment parameters of a blisk structure according to an embodiment of the present invention;
FIG. 4 is a comparison graph of deformation distributions before and after blisk optimization for which embodiments of the present invention are directed.
Detailed Description
In order that the invention may be better understood, the following further description is provided, taken in conjunction with the accompanying examples, so that the advantages and features of the invention will be more readily understood by those skilled in the art. It should be noted that the following description is only a preferred embodiment of the present invention, but the present invention is not limited to the following embodiment. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. Therefore, it is intended that the present invention encompass such modifications and variations within the scope of the appended claims and their equivalents.
According to the implementation process shown in fig. 1, the deformation coordination design of a blisk structure is realized, which includes the following steps:
SS1, establishing a finite element model of the blisk based on a three-dimensional geometric model of the blisk, taking a temperature field, a pneumatic load, a cavity pressure and a centrifugal load under the most severe design working condition as load input, wherein the temperature field and the pneumatic load are shown in a figure 2, and performing strength calculation on the blisk structure;
SS2. radial deformation U for extracting integral blade disc blade tip air inlet edge X1 Radial deformation of exhaust edge of blade tip U X2 Let a delta U X ＝U X1 -U X2 ；
SS3, extracting the barycentric coordinate axial value of the blade, and recording as Z 1 Axial value of the coordinates of the center line of the wheel disk is recorded as Z 2 Let Δ Z equal to Z 1 -Z 2 As shown in fig. 3. Within an allowable range, adjusting delta Z according to a linear change rule, and respectively calculating U corresponding to the corresponding blisk model X1 And U X2 ；
SS4. analysis of different DeltaZ vs. DeltaU X And fitting out delta Z and delta U by linear interpolation X Quantitative relationship between adjustments, in combination with DeltaU X Determining a delta Z and an axial adjustment scheme of a blade and a wheel disc according to design requirements;
and SS5, further finely adjusting the axial relative positions of the blade and the wheel disc, and performing accounting on the deformation of the blade tip to ensure the design requirement of blade tip coordination and determine the final scheme of the integral wheel disc. FIG. 4 is comparison of radial deformation of the blade before and after optimization, and the blade tip inlet and outlet deformation coordination effect is obvious by adopting the design method provided by the patent.
In summary, the invention provides a deformation coordination design method for an engine blisk, which changes the radial displacement distribution of the blade tips from the angle of the relative axial position of the blade and the blisk in the design stage, and can rapidly optimize and design the blisk structure meeting the design requirement of the deformation coordination of the blade tips on the premise of not changing the structure by summarizing the association rule of the relative axial position of the blade and the blisk and the deformation of the blade tips, thereby simplifying the optimization process of the blisk structure. The design method is simple, is very suitable for engineering design and application, has wide application range, and can be used for structural strength design of the blisk of an aircraft engine and a gas turbine.
Furthermore, it should be noted that all equivalent or simple changes made to the structure, features and principles described in the present patent concept are included in the protection scope of the present patent. Various modifications, additions and substitutions for the specific embodiments described may be made by those skilled in the art without departing from the scope of the invention as defined in the accompanying claims.

Claims (5)

1. A method for coordinately designing deformation of an engine blisk is characterized by comprising the following implementation steps:
SS1, establishing a finite element model of the blisk based on a three-dimensional geometric model of the blisk, and performing strength calculation on the structure of the blisk by taking a temperature field, a pneumatic load, a cavity pressure and a centrifugal load under the most severe design working condition as load input;
SS2. radial deformation U for extracting integral blade disc blade tip air inlet edge X1 Radial deformation of exhaust edge of blade tip U X2 Let a delta U X ＝U X1 -U X2 ；
SS3, extracting the barycentric coordinate axial value of the blade, and recording as Z 1 Axial value of the coordinates of the center line of the wheel disk is recorded as Z 2 Let Δ Z equal to Z 1 -Z 2 (ii) a Within an allowable range, adjusting delta Z according to a linear change rule, and respectively calculating the corresponding U of the blisk model X1 And U X2 ；
SS4. analysis of different DeltaZ vs. DeltaU X And fitting out delta Z and delta U by linear interpolation X Quantitative relationship between adjustments, binding Δ U X Determining a delta Z and an axial adjustment scheme of a blade and a wheel disc according to design requirements;
and SS5, further finely adjusting the axial relative positions of the blade and the wheel disc, and performing accounting on the deformation of the blade tip so as to ensure the design requirement of blade tip harmony and determine the final scheme of the integral blade disc.
2. The method of claim 1, wherein in step SS1, the strength calculation is performed based on Ansys.
3. The method according to claim 1, wherein in step SS3, the barycentric coordinates are obtained by a three-dimensional modeling program UG.
4. The method for designing the deformation coordination of the engine blisk according to claim 1, wherein in the step SS4, the Δ Z is controlled within +/-1 mm, and the distance of each adjustment is +/-0.1-0.5 mm.
5. The method for designing the deformation coordination of the engine blisk according to claim 1, wherein in the step SS5, the design requirement for the deformation coordination of the blade tip is | [ Delta ] U X |≤0.05mm。
CN202110817084.8A 2021-07-20 2021-07-20 Deformation coordination design method for engine blisk Active CN113468788B (en)

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US20010046530A1 (en) * 2000-03-27 2001-11-29 Herbert Toews Variable forming assembly for continuous laminate post former machine
FR2903921B1 (en) * 2006-07-19 2009-06-05 Snecma Sa METHOD FOR MANUFACTURING A MONOBLOCK AND MOLDING BLADE DISK FOR CARRYING OUT THE METHOD
CN104096889B (en) * 2014-07-07 2016-07-27 西安工业大学 A kind of aerial blade processing method based on error compensation
CN104526503A (en) * 2014-12-15 2015-04-22 中国燃气涡轮研究院 Integrated blade disk and blade tip curved surface numerical control grinding device and method
CN104675443A (en) * 2014-12-15 2015-06-03 中国燃气涡轮研究院 Natural frequency adjusting method of turbine blisk
CN107132049B (en) * 2017-06-24 2019-03-22 东北大学 Aero-engine's overall blade rotating vibration test platform and application based on laser vibration measurer
CN109590523B (en) * 2018-11-26 2020-04-24 中国航发沈阳黎明航空发动机有限责任公司 Reverse correction method for torsion and bending deformation of blisk blade

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