CN110909433A - Gas turbine compressor rotor fir-shaped tenon-mortise connection structure optimization method - Google Patents
Gas turbine compressor rotor fir-shaped tenon-mortise connection structure optimization method Download PDFInfo
- Publication number
- CN110909433A CN110909433A CN201911269375.7A CN201911269375A CN110909433A CN 110909433 A CN110909433 A CN 110909433A CN 201911269375 A CN201911269375 A CN 201911269375A CN 110909433 A CN110909433 A CN 110909433A
- Authority
- CN
- China
- Prior art keywords
- blade
- mortise
- tenon
- profile
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A gas turbine compressor rotor fir-shaped 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: the method comprises the following steps: constructing a geometric model of the blade profile according to the blade geometric blade profile of the pneumatic scheme; step two: taking the constructed profile of the section of the blade root of the blade profile as a basic parameter to obtain a corresponding installation angle; step three: and D, keeping the groove type of the fir-shaped 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 step two. The invention solves the problem of low strength of the gas turbine compressor blade wheel disk fir-shaped tenon-mortise connecting structure due to the worsening of stress distribution of the connecting structure caused by the pneumatic blade profile, and the connecting structure 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-shaped tenon-mortise connecting structure.
Background
The gas compressor of the gas turbine is a power mechanical system which is complex, high-speed in flow of compressed gas, high-speed in rotation of a rotor system and works under the conditions of high temperature and high pressure. Under the combined action of severe use environment (such as ocean salt spray, low temperature, desert environment and the like) and pneumatic, mechanical and thermal (temperature) loads, the device has the requirement of long service life. The structural reliability of the compressor directly determines the structural integrity of the whole gas turbine. With the continuous development of gas turbines, compressor moving blades have higher load capacity and blade tip tangential speed nowadays. Therefore, the centrifugal load of the moving blade of the compressor is greatly increased, so that stress concentration is easily generated at the connecting part of the blade and the wheel disc.
When the structure of the air compressor is designed, the former stages are generally designed into a fir-shaped tenon-mortise structure, so that the load effect 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 stress distribution at the connecting part of the rotor blade and the wheel disc of the compressor is good, the stress reserve is sufficient, and the method is an important link and guarantee for realizing the structural design index of the compressor.
When the optimized design, the grading design and the like of the blade profile of the compressor are carried out, the existing groove-shaped structure (verified by the operation examination of the real machine) is often used as the first choice of the tenon-mortise connection, and the stress distribution of the fir-type tenon-mortise structure can be guaranteed. When the blade body is enlarged and the designed rotating speed of the unit is increased, the original reference structure may present the condition that the stress concentration does not meet the design requirement. Therefore, the method is suitable for engineering design and application, and has very important significance in quickly adjusting the tenon-mortise structural form to optimize stress distribution on the premise of considering good processing universality.
Disclosure of Invention
The purpose of the invention is: the method solves the problem that the gas turbine compressor rotor disk fir-shaped tenon-mortise connecting structure is low in structural strength due to the fact that stress distribution of the connecting structure is worsened due to pneumatic blade profiles, and provides the gas turbine compressor rotor fir-shaped tenon-mortise connecting structure optimization method.
The technical scheme adopted by the invention to solve the technical problems is as follows:
the gas turbine compressor rotor fir-type tenon-mortise connection structure optimization method comprises the following steps:
the method comprises the following steps: constructing a geometric model of the blade profile according to the blade geometric blade profile of the pneumatic scheme;
step two: taking the constructed profile of the section of the blade root of the blade profile as a basic parameter to obtain a corresponding installation angle;
step three: and D, keeping the groove type of the fir-shaped 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 step two.
Further, the detailed steps of the first step are as follows: firstly, a plurality of space curves are constructed according to leaf profile data points obtained by a pneumatic scheme, and then a leaf body entity is formed through a curve group.
Further, in the second step, the profile of the blade root section is obtained according to the following method:
firstly, selecting a plane line which is within 2 percent of the blade height of the blade body close to the blade root marginal plate of the blade and is in the height direction, then extending the plane line to the required height during pneumatic design, and projecting the blade root section molded line to the plane with the required height to obtain the blade root section molded line of the blade.
Further, in the second step, the profile of the blade root section is obtained according to the following method:
firstly, selecting a plane line which is within 2 percent of the blade body height close to the blade root marginal plate of the blade and is in the height direction, and then obtaining a blade root section molded line of the blade profile through plane cutting according to the existing blade body entity.
Further, the groove direction of the fir-shaped tenon-mortise of the compressor rotor in the second step is parallel to the central line of the rotor.
Further, the step three is to keep the groove shape of the fir-shaped tenon-mortise unchanged by the following steps:
firstly, selecting a groove type which is examined through real machine operation as an original groove type, and then keeping the shape and the size of each part of the groove type unchanged during structural design.
Further, the method further comprises a verification step, wherein the verification step comprises the following steps:
step four: carrying out grid dispersion on the newly designed blade and the newly designed wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, carrying out nonlinear contact static analysis by comprehensively considering temperature load, pneumatic load and centrifugal load to obtain a stress calculation result, carrying out comparative analysis on the stress calculation result and the structural stress before optimization, and verifying the stress distribution optimization result of the tenon-mortise stress concentration part.
Further, the dynamic equation of the finite element model in the fourth step is as follows:
[M]{x”}+[C]{x’}+[K]{x}＝{F(t)}
in the formula, [ M ] is a mass matrix, [ C ] is a damping matrix, and [ K ] is a rigidity matrix; { x } is a displacement vector, { f (t) } is a force load vector, such as a centrifugal load, a temperature load, a pneumatic load, etc.; { x' } is the velocity vector; { x "} is the acceleration vector.
The invention has the beneficial effects that:
(1) the stress optimization method of the fir-type tenon-mortise connection structure of the gas turbine compressor blade disc is constructed on the basis of the principle that the used groove type of the fir-type connection structure is kept as a primary factor and only the groove direction angle is used as an optimization condition when the gas turbine compressor is designed again, such as pneumatic optimization, grading design and the like. The groove type is kept unchanged, the original design and processing advantages are kept, the design efficiency and the process processing universality are improved, and the method has important engineering application value, solves the problem that the strength of a gas turbine compressor blade wheel disc fir-type tenon-mortise connecting structure is low due to the fact that the stress distribution of the connecting structure is worsened due to the aerodynamic blade profile, and is high in connecting structure strength.
(2) The method for optimizing the stress of the compressor rotor fir-shaped tenon-mortise connecting structure has universality, is not limited to the gas turbine compressor blade and the wheel disc, and is also suitable for the optimization design of the connecting structure of the aero-engine compressor similar to the blade wheel disc.
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 the gas turbine compressor rotor fir-type tenon-mortise connection structure optimization method is realized by the following steps:
the method comprises the following steps: taking the geometric blade profile of the blade in the pneumatic design scheme as a design blade profile, and constructing a geometric model of the newly designed blade profile;
step two: taking a newly designed blade profile blade root section molded line (a blade profile section close to a blade root flange plate) as a basic parameter to obtain a corresponding installation angle;
step three: the groove type of the used fir-shaped tenon-mortise can be kept unchanged, and the rotor blade tenon and wheel disc mortise connecting structure is redesigned according to the blade root molded surface installation angle obtained in the step two;
step four: carrying out grid dispersion on the newly designed blade and the newly designed wheel disc, forming a finite element model according to the performance parameters of the blade and wheel disc material, and carrying out nonlinear contact static analysis by comprehensively considering temperature load, pneumatic load and centrifugal load to obtain a stress calculation result;
step five: and comparing and analyzing the structural stress before optimization, verifying the stress distribution optimization result of the tenon-mortise stress concentration part, and finally meeting the design requirement to prolong the service life of the operation.
The third step is that the groove shape of the used fir-shaped 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 needed to be adjusted, so that the universality of the existing groove shape is ensured, and great convenience is brought to the processing production of future parts.
In the second step, "the corresponding installation angle is obtained by taking the newly designed blade root section (the blade section close to the blade root flange plate) as a basic parameter", and the existing design and use experience show that the groove direction of the compressor rotor fir-shaped tenon-mortise is generally parallel to the center line of the rotor for the purposes of processing the pull groove and facilitating the installation of the blade. For design requirements such as blade profile improvement and grading design, the original tenon-mortise connection structure parallel to the central line of the rotor often generates a stress concentration phenomenon. And a new groove direction is determined by determining a mounting angle according to the section of the root of the blade profile, so that the stress concentration of the connecting structure can be effectively relieved.
The blade modeling, the grid discretization and the finite element solution in all the steps of the method can be completed by using general commercial software.
The second embodiment is as follows: this embodiment mode is a further description of the first embodiment mode, and the difference between this embodiment mode and the first embodiment mode is that the detailed procedure of the first step mode is: firstly, a plurality of space curves are constructed according to leaf profile data points obtained by a pneumatic scheme, and then a leaf body entity is formed through a curve group.
The third concrete implementation mode: the embodiment is further described with respect to the first embodiment, and the difference between the embodiment and the first embodiment is that the profile of the blade root section in the second step is obtained according to the following method:
firstly, selecting a plane line which is within 2 percent of the blade height of the blade body close to the blade root marginal plate of the blade and is in the height direction, then extending the plane line to the required height during pneumatic design, and projecting the blade root section molded line to the plane with the required height to obtain the blade root section molded line of the blade.
The fourth concrete implementation mode: the embodiment is further described with respect to the first embodiment, and the difference between the embodiment and the first embodiment is that the profile of the blade root section in the second step is obtained according to the following method:
firstly, selecting a plane line which is within 2 percent of the blade body height close to the blade root marginal plate of the blade and is in the height direction, and then obtaining a blade root section molded line of the blade profile through plane cutting according to the existing blade body entity.
The fifth concrete implementation mode: the third or fourth embodiment is further explained, and the difference between the first embodiment and the second embodiment is that the slot direction of the fir-type tenon-mortise of the compressor rotor in the second step is parallel to the center line of the rotor.
The sixth specific implementation mode: the present embodiment is further described with respect to the first embodiment, and the difference between the present embodiment and the first embodiment is that the retaining of the groove shape of the fir-tree type tenon-mortise in the third step is realized by:
firstly, selecting a groove type which is examined through real machine operation as an original groove type, and then keeping the shape and the size of each part of the groove type unchanged during structural design.
The 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, which is as follows:
step four: carrying out grid dispersion on the newly designed blade and the newly designed wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, carrying out nonlinear contact static analysis by comprehensively considering temperature load, pneumatic load and centrifugal load to obtain a stress calculation result, carrying out comparative analysis on the stress calculation result and the structural stress before optimization, and verifying the stress distribution optimization result of the tenon-mortise stress concentration part.
The specific implementation mode is eight: the present embodiment is further described with respect to a seventh embodiment, and the difference between the present 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)}
in the formula, [ M ] is a mass matrix, [ C ] is a damping matrix, and [ K ] is a rigidity matrix; { x } is a displacement vector, { f (t) } is a force load vector, such as a centrifugal load, a temperature load, a pneumatic load, etc.; { x' } is the velocity vector; { x "} is the acceleration vector.
It should be noted that the detailed description is only for explaining and explaining the technical solution of the present invention, and the scope of protection of the claims is not limited thereby. It is intended that all such modifications and variations be included within the scope of the invention as defined in the following claims and the description.
Claims (8)
1. The gas turbine compressor rotor fir-type tenon-mortise connection structure optimization method is characterized by comprising the following steps of:
the method comprises the following steps: constructing a geometric model of the blade profile according to the blade geometric blade profile of the pneumatic scheme;
step two: taking the constructed profile of the section of the blade root of the blade profile as a basic parameter to obtain a corresponding installation angle;
step three: and D, keeping the groove type of the fir-shaped 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 step two.
2. The gas turbine compressor rotor fir-tree type tenon-mortise connection structure optimization method according to claim 1, wherein the detailed steps of the first step are as follows: firstly, a plurality of space curves are constructed according to leaf profile data points obtained by a pneumatic scheme, and then a leaf body entity is formed through a curve group.
3. The gas turbine compressor rotor fir-tree tenon-mortise connection structure optimization method according to claim 1, wherein in the second step, the blade root section profile is obtained according to the following method:
firstly, selecting a plane line which is within 2 percent of the blade height of the blade body close to the blade root marginal plate of the blade and is in the height direction, then extending the plane line to the required height during pneumatic design, and projecting the blade root section molded line to the plane with the required height to obtain the blade root section molded line of the blade.
4. The gas turbine compressor rotor fir-tree tenon-mortise connection structure optimization method according to claim 1, wherein in the second step, the blade root section profile is obtained according to the following method:
firstly, selecting a plane line which is within 2 percent of the blade body height close to the blade root marginal plate of the blade and is in the height direction, and then obtaining a blade root section molded line of the blade profile through plane cutting according to the existing blade body entity.
5. The method for optimizing a compressor rotor firtree-mortise joint structure of a gas turbine according to claim 3 or 4, wherein the slot direction of the compressor rotor firtree-mortise in the second step is parallel to the rotor centerline.
6. The gas turbine compressor rotor fir-tree tenon-and-mortise connection structure optimization method according to claim 1, wherein the step three for keeping the fir-tree tenon-and-mortise groove shape unchanged is realized by the following steps:
firstly, selecting a groove type which is examined through real machine operation as an original groove type, and then keeping the shape and the size of each part of the groove type unchanged during structural design.
7. The gas turbine compressor rotor firtree-type tenon-and-mortise joint structure optimization method of claim 1, further comprising the step of verifying, said step of verifying comprising:
step four: carrying out grid dispersion on the newly designed blade and the newly designed wheel disc, forming a finite element model according to the material performance parameters of the blade wheel disc, carrying out nonlinear contact static analysis by comprehensively considering temperature load, pneumatic load and centrifugal load to obtain a stress calculation result, carrying out comparative analysis on the stress calculation result and the structural stress before optimization, and verifying the stress distribution optimization result of the tenon-mortise stress concentration part.
8. The method for optimizing a fir-tree-shaped tenon-mortise connection structure of a gas turbine compressor rotor according to claim 7, wherein the dynamic equation of the finite element model in the fourth step is as follows:
[M]{x”}+[C]{x’}+[K]{x}＝{F(t)}
in the formula, [ M ] is a mass matrix, [ C ] is a damping matrix, and [ K ] is a rigidity matrix; { x } is a displacement vector, { f (t) } is a force load vector, such as a centrifugal load, a temperature load, a pneumatic load, etc.; { x' } is the velocity vector; { x "} is the acceleration vector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911269375.7A CN110909433B (en) | 2019-12-11 | 2019-12-11 | Optimization method for fir-type tenon-mortise connection structure of gas turbine compressor rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911269375.7A CN110909433B (en) | 2019-12-11 | 2019-12-11 | Optimization method for fir-type tenon-mortise connection structure of gas turbine compressor rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110909433A true CN110909433A (en) | 2020-03-24 |
| CN110909433B CN110909433B (en) | 2023-06-20 |
Family
ID=69824812
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911269375.7A Active CN110909433B (en) | 2019-12-11 | 2019-12-11 | Optimization method for fir-type tenon-mortise connection structure of gas turbine compressor rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110909433B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111579396A (en) * | 2020-04-29 | 2020-08-25 | 南京航空航天大学 | Optimization method of turbine joggling fretting fatigue test piece |
| CN112287580A (en) * | 2020-10-27 | 2021-01-29 | 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 |
| CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
| CN112685852A (en) * | 2020-12-22 | 2021-04-20 | 中国船舶重工集团公司第七0三研究所 | Axial flow compressor load customized pneumatic optimization method capable of keeping continuity of through-flow structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203308525U (en) * | 2013-05-07 | 2013-11-27 | 中国航空动力机械研究所 | Fir tree-shaped tenon structure |
| CN204312392U (en) * | 2014-11-15 | 2015-05-06 | 哈尔滨广瀚燃气轮机有限公司 | For installing novel tenon and the tongue-and-groove linkage structure of compressor blade and drum-type wheel disc |
| CN105756719A (en) * | 2016-01-08 | 2016-07-13 | 北京航空航天大学 | Gas compressor stator blade root slotting method based on optimization algorithm |
| CN107301268A (en) * | 2017-05-18 | 2017-10-27 | 哈尔滨工程大学 | A kind of ship gas turbine variable stator vane angle compressor deflection angle optimization method |
| CN110489925A (en) * | 2019-09-02 | 2019-11-22 | 杭州汽轮动力集团有限公司 | A kind of Gas Turbine fir-tree root leaf slot modular design method |
-
2019
- 2019-12-11 CN CN201911269375.7A patent/CN110909433B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203308525U (en) * | 2013-05-07 | 2013-11-27 | 中国航空动力机械研究所 | Fir tree-shaped tenon structure |
| CN204312392U (en) * | 2014-11-15 | 2015-05-06 | 哈尔滨广瀚燃气轮机有限公司 | For installing novel tenon and the tongue-and-groove linkage structure of compressor blade and drum-type wheel disc |
| CN105756719A (en) * | 2016-01-08 | 2016-07-13 | 北京航空航天大学 | Gas compressor stator blade root slotting method based on optimization algorithm |
| CN107301268A (en) * | 2017-05-18 | 2017-10-27 | 哈尔滨工程大学 | A kind of ship gas turbine variable stator vane angle compressor deflection angle optimization method |
| CN110489925A (en) * | 2019-09-02 | 2019-11-22 | 杭州汽轮动力集团有限公司 | A kind of Gas Turbine fir-tree root leaf slot modular design method |
Non-Patent Citations (11)
| Title |
|---|
| LING J 等: ""Optimal Turbulent Schmidt Number for RANS Modeling of Trailing Edge Slot Film Cooling"", 《JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER》 * |
| 倪长辉 等: ""基于接触应力的高参数汽轮机叶片枞树形叶根型线优化"", 《计算机辅助工程》 * |
| 唐钊: ""发动机冷却风扇叶片参数的研究和优化"", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
| 宗洪明 等: "某型燃气轮机枞树形榫接结构多齿形参数优化分析" * |
| 张明辉 等: ""基于三维热弹性接触的汽轮机调节级叶片枞树型叶根轮缘结构的优化"", 《动力工程学报》 * |
| 张晓磊: ""重型燃气轮机压气机叶片机械加工技术研究"", 《中国优秀硕士学位论文全文数据库工程科技Ⅰ辑》 * |
| 李骏;宋友辉;刘汉斌;徐凌志;郭昊雁;: "涡轮叶片-榫头-轮盘的蠕变与低循环疲劳寿命预测" * |
| 杨敏超 等: "涡轮榫头／榫槽的结构优化设计" * |
| 王斌: ""涡轮盘枞树型叶根榫槽切削刀具结构优化及强度预测"", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
| 王琦 等: ""定制叶型在多级压气机中的应用研究"", 《热能动力工程》 * |
| 高翔 等: ""航空发动机榫槽拉刀快速设计系统研究与开发"", 《机械制造与自动化》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111579396A (en) * | 2020-04-29 | 2020-08-25 | 南京航空航天大学 | Optimization method of turbine joggling fretting fatigue test piece |
| CN111579396B (en) * | 2020-04-29 | 2021-08-06 | 南京航空航天大学 | Optimization method of turbine joggling fretting fatigue test piece |
| CN112287580A (en) * | 2020-10-27 | 2021-01-29 | 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 |
| CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
| 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 |
| CN112685852A (en) * | 2020-12-22 | 2021-04-20 | 中国船舶重工集团公司第七0三研究所 | Axial flow compressor load customized pneumatic optimization method capable of keeping continuity of through-flow structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110909433B (en) | 2023-06-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110909433A (en) | Gas turbine compressor rotor fir-shaped tenon-mortise connection structure optimization method | |
| Ma et al. | A review on dynamic characteristics of blade–casing rubbing | |
| Mikolajczak et al. | Advances in fan and compressor blade flutter analysis and predictions | |
| Rezaei et al. | Modal-based damage identification for the nonlinear model of modern wind turbine blade | |
| CN110929357A (en) | Pneumatic design method for high-performance ship gas turbine compressor | |
| CN114117849B (en) | Blade crown damping vibration attenuation analysis method of low-pressure turbine blade/disk rotor | |
| CN106777783B (en) | Method for predicting blade cracks of aircraft engine | |
| Schoenenborn et al. | Contribution to free and forced vibration analysis of an intentionally mistuned blisk | |
| CN105156155A (en) | Vibration reducing and pressure bearing damping structure for blade root platform of movable blades | |
| CN114492107A (en) | Fatigue test simulation piece design method for checking turbine disc rim convex block | |
| CN112182802B (en) | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning | |
| CN115270567B (en) | Vibration characteristic analysis method for fan rotor blade with shoulder | |
| JPS59131704A (en) | Blade for combustion turbine | |
| Keller et al. | Influence of geometric imperfections on aerodynamic and aeroelastic behavior of a compressor blisk | |
| CN111046490B (en) | Grid size inversion method in foreign object damage notch analysis | |
| Algolfat et al. | Dynamic responses analysis of a 5MW NREL wind turbine blade under flap-wise and edge-wise vibrations | |
| CN110925030A (en) | Low-pressure turbine simulation blade with embedded blade shroud damping | |
| CN111143982B (en) | Particle erosion resistance optimization method for turbine mechanical blade flow passage structure | |
| CN111832126A (en) | Low-pressure cylinder last-stage blade static stress analysis method | |
| Lübbe et al. | Design and Validation of a Large Steam Turbine End-Stage Blade to Meet Current and Future Market Demands | |
| CN117131608A (en) | Excitation disk method based on optimal annular quantity distribution | |
| CN114154363B (en) | Vibration damping characteristic analysis method for high-pressure turbine blade edge plate damper | |
| Riemenschneider et al. | Smart trailing edges for wind turbines | |
| Lottini et al. | Flutter stability assessment of a low pressure turbine rotor: A comparison between cantilever and interlocked configurations | |
| CN110688797B (en) | Finite element calculation method for fork-type blade root blade of steam turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Xu Ning Inventor after: Zhang Liang Inventor after: Zhang Zhibo Inventor after: Wang Ting Inventor after: Wang Qi Inventor after: Wang Zuoxin Inventor after: Zhang Zhou Inventor after: Jin Peng Inventor after: Chu Shuguang Inventor before: Zhang Liang Inventor before: Xu Ning Inventor before: Zhang Zhibo Inventor before: Wang Ting Inventor before: Wang Qi Inventor before: Wang Zuoxin Inventor before: Zhang Zhou Inventor before: Jin Peng Inventor before: Chu Shuguang |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |