CN110909433B - Optimization method for fir-type tenon-mortise connection structure of gas turbine compressor rotor - Google Patents
Optimization method for fir-type tenon-mortise connection structure of gas turbine compressor rotor Download PDFInfo
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- CN110909433B CN110909433B CN201911269375.7A CN201911269375A CN110909433B CN 110909433 B CN110909433 B CN 110909433B CN 201911269375 A CN201911269375 A CN 201911269375A CN 110909433 B CN110909433 B CN 110909433B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
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- 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
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Abstract
A gas turbine compressor rotor fir-type tenon-mortise connection structure optimization method relates to the technical field of gas turbine compressor rotor blade wheel disc structures, and comprises the following steps: step one: constructing a geometric model of the blade profile according to the blade geometric blade profile of the aerodynamic scheme; step two: taking the constructed sectional profile of the blade root of the blade profile as a basic parameter to obtain a corresponding installation angle; step three: and (3) keeping the slot of the fir-type tenon and the slot unchanged, and designing a rotor blade tenon and wheel disc slot connecting structure according to the blade root profile mounting angle obtained in the step two. The invention solves the problem of low strength caused by the stress distribution deterioration of the connecting structure due to the pneumatic blade profile of the fir-tree type tenon-mortise connecting structure of the blade wheel disc of the gas turbine compressor, and has high strength.
Description
Technical Field
The invention relates to the technical field of gas turbine compressor rotor blade wheel disc structures, in particular to a stress optimization design method suitable for a gas turbine compressor rotor fir-type tenon-mortise connection structure.
Background
The gas turbine compressor is a complex power mechanical system with compressed gas flowing at high speed and rotor system rotating at high speed and working under high temperature and high pressure conditions. Under the combined action of severe service environment (such as ocean salt fog, low temperature, desert environment and the like) and pneumatic, mechanical and thermal (temperature) loads, the hydraulic oil pump has the requirement of long service life. The structural reliability of the compressor directly determines the structural integrity of the gas turbine engine. With the continuous development of gas turbines, compressor blades today have higher load capacity and blade tip tangential speed. Therefore, centrifugal load of the moving blades of the compressor is increased greatly, and stress concentration is easy to occur at the connection part of the blades and the wheel disc.
When the compressor structure is designed, the previous stages are generally designed into a fir-type tenon-mortise structure, so that the load action of the strong centrifugal force of the blade on the wheel disc mortise can be effectively relieved, and the resonance problem of the blade can be effectively relieved. Therefore, the method ensures that the stress distribution of the connecting part of the rotor blade and the wheel disc of the air compressor is good, and the stress reserve is sufficient, thereby being an important link and guarantee for realizing the structural design index of the air compressor.
When the optimization design, the grading design and the like of the blade profile of the compressor are carried out, the existing groove type structure (verified by the operation check of the real machine) is often used as the first choice of tenon-mortise connection, and the stress distribution of the fir-tree type tenon-mortise structure can be ensured. When the blade body is increased and the design rotating speed of the unit is increased, the original reference structure possibly shows the condition that the stress concentration does not meet the design requirement. Therefore, development is suitable for engineering design application, and on the premise of considering good processing universality, the tenon-mortise structure form can be quickly adjusted to optimize stress distribution, so that the method has very important significance.
Disclosure of Invention
The purpose of the invention is that: the method solves the problem that the strength of the structure is low due to the fact that the stress distribution of the connecting structure is deteriorated due to the pneumatic blade profile, and provides an optimization method for the rotor fir-type tenon-mortise connecting structure of the gas turbine compressor.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the optimization method of the fir-tree type tenon-mortise connection structure of the gas turbine compressor rotor comprises the following steps:
step one: constructing a geometric model of the blade profile according to the blade geometric blade profile of the aerodynamic scheme;
step two: taking the constructed sectional profile of the blade root of the blade profile as a basic parameter to obtain a corresponding installation angle;
step three: and (3) keeping the slot of the fir-type tenon and the slot unchanged, and designing a rotor blade tenon and wheel disc slot connecting structure according to the blade root profile mounting angle obtained in the step two.
Further, the detailed steps of the first step are as follows: firstly, constructing a plurality of space curves according to leaf profile data points obtained by a pneumatic scheme, and then forming a leaf body entity through curve groups.
Further, the blade root section profile in the second step is obtained according to the following method:
firstly, selecting a plane line type which is within 2% of the height of the blade root plate and is in the height direction, then extending the plane line type to the required height in pneumatic design, and projecting the blade root section line type to the required height plane to obtain the blade root section line type of the blade profile.
Further, the blade root section profile in the second step is obtained according to the following method:
firstly, selecting a plane line type which is within 2% of the blade height and is in the height direction and is close to the blade root plate, and then obtaining the section line of the blade profile blade root through plane cutting according to the existing blade body entity.
Further, the slot direction of the fir-type tenon-mortise of the rotor of the second-step compressor is parallel to the center line of the rotor.
Further, the step three is realized by keeping the slot shape of the fir-tree type tenon-mortise unchanged in the following way:
firstly, selecting the groove type which is checked through the operation of a real machine as an original groove type, and then, keeping the shape and the size of each part of the groove type unchanged when the structural design is carried out.
Further, the method further comprises a verification step, wherein the verification step comprises the following steps:
step four: and performing grid dispersion on the newly designed blade and wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, comprehensively considering temperature load, pneumatic load and centrifugal load, performing nonlinear contact statics analysis to obtain a stress calculation result, performing comparative analysis on the stress calculation result and structural stress before optimization, and verifying a stress distribution optimization result of a tenon-mortise stress concentration part.
Further, the kinetic equation of the finite element model in the fourth step is:
[M]{x”}+[C]{x’}+[K]{x}＝{F(t)}
wherein [ M ] is a mass matrix, [ C ] is a damping matrix, and [ K ] is a stiffness matrix; { x } is a displacement vector, { F (t) } is a force load vector, such as centrifugal load, temperature load, pneumatic load, etc.; { x' } is a velocity vector; { x "} is an acceleration vector.
The beneficial effects of the invention are as follows:
(1) The invention uses the used slot type of the fir-type connecting structure as the primary factor when the pneumatic optimization, the grading design and the like of the gas turbine compressor are redesigned, only uses the slot angle as the optimizing condition, and constructs the stress optimizing method of the fir-type tenon-mortise connecting structure of the gas turbine compressor blade wheel disc based on the slot angle. The invention keeps the slot shape unchanged, retains the original design and processing advantages, improves the design efficiency and the process processing universality, has important engineering application value, and solves the problem of low strength caused by the stress distribution deterioration of the connecting structure due to the pneumatic blade shape of the gas turbine compressor blade wheel disc fir-type tenon-mortise connecting structure.
(2) The stress optimization method for the fir-tree type tenon-mortise connection structure of the compressor rotor has universality, is not only limited to the compressor blades and the wheel discs of the gas turbine, but also is suitable for the optimization design of the similar blade wheel disc connection structure of the aeroengine compressor.
Drawings
FIG. 1 is a flow chart of the present invention.
Detailed Description
The first embodiment is as follows: referring to FIG. 1, a specific embodiment of a gas turbine compressor rotor fir tree type dovetail-mortise connection method is implemented by:
step one: taking the blade geometric leaf profile of the pneumatic design scheme as a design leaf profile, and constructing a geometric model of a new design leaf profile;
step two: taking a newly designed profile blade root section line (a profile section close to a blade root plate) as a basic parameter to obtain a corresponding installation angle;
step three: the groove type of the used fir-type tenon-mortise is kept unchanged, and a rotor blade tenon and wheel disc mortise connecting structure is redesigned according to the blade root profile mounting angle obtained in the second step;
step four: performing grid dispersion on the newly designed blade and wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, comprehensively considering temperature load, pneumatic load and centrifugal load, and performing nonlinear contact statics analysis to obtain a stress calculation result;
step five: and comparing and analyzing the structural stress before optimization, and verifying the stress distribution optimization result of the tenon-mortise stress concentration part, so that the design requirement is finally met to prolong the service life of the operation.
The groove type of the used fir-type tenon-mortise can be kept unchanged, and the groove direction of the wheel disc relative to the central line of the wheel disc is only required to be adjusted, so that the universality of the existing groove type is ensured, and great convenience is brought to the processing and production of future parts.
In the second step, "the blade root section of the new design blade profile (the blade profile section close to the blade root plate) is taken as a basic parameter, and the corresponding installation angle is obtained", and the prior design and use experience show that in order to process the pull groove and facilitate the installation of the blade, the groove direction of the fir-tree type tenon-mortise of the compressor rotor is generally parallel to the central line of the rotor. For the design requirements of blade profile improvement, stage design and the like, the stress concentration phenomenon is often generated in the original tenon-mortise connection structure parallel to the central line of the rotor. And the new groove direction is determined according to the installation angle determined by the section of the blade root, so that the stress concentration of the connecting structure can be effectively relieved.
Blade modeling, grid discretization and finite element solution in each step of the invention can be accomplished by using general commercial software.
The second embodiment is as follows: this embodiment is further described with respect to the first embodiment, and the difference between this embodiment and the first embodiment is that the detailed steps of the first step are as follows: firstly, constructing a plurality of space curves according to leaf profile data points obtained by a pneumatic scheme, and then forming a leaf body entity through curve groups.
And a third specific embodiment: this embodiment is further described in the first embodiment, and the difference between this embodiment and the first embodiment is that the profile of the section of the blade root in the second step is obtained according to the following method:
firstly, selecting a plane line type which is within 2% of the height of the blade root plate and is in the height direction, then extending the plane line type to the required height in pneumatic design, and projecting the blade root section line type to the required height plane to obtain the blade root section line type of the blade profile.
The specific embodiment IV is as follows: this embodiment is further described in the first embodiment, and the difference between this embodiment and the first embodiment is that the profile of the section of the blade root in the second step is obtained according to the following method:
firstly, selecting a plane line type which is within 2% of the blade height and is in the height direction and is close to the blade root plate, and then obtaining the section line of the blade profile blade root through plane cutting according to the existing blade body entity.
Fifth embodiment: this embodiment is further described with respect to the third or fourth embodiment, and differs from the first embodiment in that the slot direction of the fir-tree-shaped dovetail-mortise of the second compressor rotor is parallel to the rotor center line.
Specific embodiment six: this embodiment is further described with respect to the first embodiment, and the difference between this embodiment and the first embodiment is that the step three is implemented in such a manner that the slot shape of the fir tree type tenon-mortise is maintained unchanged by:
firstly, selecting the groove type which is checked through the operation of a real machine as an original groove type, and then, keeping the shape and the size of each part of the groove type unchanged when the structural design is carried out.
Seventh embodiment: this embodiment is a further description of the first embodiment, and the difference between this embodiment and the first embodiment is that the method further includes a verification step, where the verification step is as follows:
step four: and performing grid dispersion on the newly designed blade and wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, comprehensively considering temperature load, pneumatic load and centrifugal load, performing nonlinear contact statics analysis to obtain a stress calculation result, performing comparative analysis on the stress calculation result and structural stress before optimization, and verifying a stress distribution optimization result of a tenon-mortise stress concentration part.
Eighth embodiment: this embodiment is further described in the seventh embodiment, and the difference between this embodiment and the seventh embodiment is that the kinetic equation of the finite element model in the fourth step is:
[M]{x”}+[C]{x’}+[K]{x}＝{F(t)}
wherein [ M ] is a mass matrix, [ C ] is a damping matrix, and [ K ] is a stiffness matrix; { x } is a displacement vector, { F (t) } is a force load vector, such as centrifugal load, temperature load, pneumatic load, etc.; { x' } is a velocity vector; { x "} is an acceleration vector.
It should be noted that the detailed description is merely for explaining and describing the technical solution of the present invention, and the scope of protection of the claims should not be limited thereto. All changes which come within the meaning and range of equivalency of the claims and the specification are to be embraced within their scope.
Claims (7)
1. The optimization method of the fir-tree type tenon-mortise connection structure of the gas turbine compressor rotor is characterized by comprising the following steps of:
step one: constructing a geometric model of the blade profile according to the blade geometric blade profile of the aerodynamic scheme;
step two: taking the constructed sectional profile of the blade root of the blade profile as a basic parameter to obtain a corresponding installation angle;
step three: keeping the slot of the fir-type tenon-mortise unchanged, and designing a rotor blade tenon and wheel disc mortise connecting structure according to the blade root profile mounting angle obtained in the second step;
the blade root section molded line in the second step is obtained according to the following method:
firstly, selecting a plane line type which is within 2% of the blade height and is in the height direction and close to a blade root plate, then extending the plane line type to a required height during pneumatic design, and projecting a blade root section line to a required height plane to obtain a blade root section line of the blade profile;
step four: performing grid dispersion on the newly designed blade and wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, comprehensively considering temperature load, pneumatic load and centrifugal load, and performing nonlinear contact statics analysis to obtain a stress calculation result;
step five: comparing and analyzing the structural stress before optimization, and verifying the stress distribution optimization result of the tenon-mortise stress concentration part, so as to finally meet the design requirement and prolong the service life of operation;
the groove type of the fir-type tenon-mortise is kept unchanged, and the groove direction of the wheel disc relative to the central line of the wheel disc is only adjusted; the shape and the size of each part of the groove are kept unchanged when the structural design is carried out.
2. The optimization method of fir-tree type tenon-mortise connection structure of gas turbine compressor rotor according to claim 1, characterized in that the detailed steps of the step one are: firstly, constructing a plurality of space curves according to leaf profile data points obtained by a pneumatic scheme, and then forming a leaf body entity through curve groups.
3. The optimization method of a fir-tree type tenon-mortise connection structure of a gas turbine compressor rotor according to claim 1, wherein in the step two, a blade root section profile is obtained according to the following method:
firstly, selecting a plane line type which is within 2% of the blade height and is in the height direction and is close to the blade root plate, and then obtaining the section line of the blade profile blade root through plane cutting according to the existing blade body entity.
4. A gas turbine compressor rotor fir tree-type dovetail-mortise connection optimization method according to claim 1 or 3, characterized in that the slot direction of the step two compressor rotor fir tree-type dovetail-mortise is parallel to the rotor center line.
5. The gas turbine compressor rotor fir-tree type tenon-mortise connection structure optimizing method according to claim 1, characterized in that in the third step, the keeping of the fir-tree type tenon-mortise type is achieved by:
firstly, selecting the groove type which is checked through the operation of a real machine as an original groove type, and then, keeping the shape and the size of each part of the groove type unchanged when the structural design is carried out.
6. The gas turbine compressor rotor fir tree type dovetail-dovetail groove connection optimization method according to claim 1, characterized in that said method further includes a verification step of:
step four: and performing grid dispersion on the newly designed blade and wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, comprehensively considering temperature load, pneumatic load and centrifugal load, performing nonlinear contact statics analysis to obtain a stress calculation result, performing comparative analysis on the stress calculation result and structural stress before optimization, and verifying a stress distribution optimization result of a tenon-mortise stress concentration part.
7. The optimization method of fir-tree type tenon-mortise connection structure of gas turbine compressor rotor according to claim 6, characterized in that the kinetic equation of the finite element model in the fourth step is:
[M]{x”}+[C]{x’}+[K]{x}＝{F(t)}
wherein [ M ] is a mass matrix, [ C ] is a damping matrix, and [ K ] is a stiffness matrix; { x } is the displacement vector, { F (t) } is the force load vector; { x' } is a velocity vector; { x "} is an acceleration vector.
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| CN112287580B (en) * | 2020-10-27 | 2022-11-29 | 中国船舶重工集团公司第七0三研究所 | Axial flow compressor surge boundary calculation method based on full three-dimensional numerical simulation |
| CN112324520B (en) * | 2020-10-27 | 2022-08-30 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
| CN112685852B (en) * | 2020-12-22 | 2021-12-17 | 中国船舶重工集团公司第七0三研究所 | Load customization pneumatic optimization method for axial flow compressor |
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