CN115270334A - Bearing case rigidity simulation piece and design method thereof - Google Patents

Bearing case rigidity simulation piece and design method thereof Download PDF

Info

Publication number
CN115270334A
CN115270334A CN202210902485.8A CN202210902485A CN115270334A CN 115270334 A CN115270334 A CN 115270334A CN 202210902485 A CN202210902485 A CN 202210902485A CN 115270334 A CN115270334 A CN 115270334A
Authority
CN
China
Prior art keywords
bearing case
case
bearing
fan
simulation
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
Application number
CN202210902485.8A
Other languages
Chinese (zh)
Other versions
CN115270334B (en
Inventor
沈锡钢
王绍明
储建恒
韩方军
苗艳
许洪明
周战璇
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Engine Research Institute
Original Assignee
AECC Shenyang Engine Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN202210902485.8A priority Critical patent/CN115270334B/en
Publication of CN115270334A publication Critical patent/CN115270334A/en
Application granted granted Critical
Publication of CN115270334B publication Critical patent/CN115270334B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • 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]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • 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

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Computational Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

The application provides a method for designing a bearing case simulation piece, which is used for an aeroengine containment test and comprises the following steps: obtaining the structural size of the connecting part of the fan case and the bearing case according to the geometric models of the fan case and the bearing case; establishing a finite element combination model of the fan casing and the bearing casing, and loading a pressure load in an impact area of the fan casing in the finite element combination model to obtain a fan casing impact area deformation cloud picture under the influence of the rigidity of the bearing casing; determining the initial size of the bearing case rigidity simulation piece according to the structural size of the connecting part, and constructing a geometric model of the bearing case rigidity simulation piece; establishing a finite element model of a bearing case rigidity simulation piece to obtain a fan case impact area deformation cloud picture under the influence of the rigidity of the bearing case rigidity simulation piece; comparing and analyzing the deformation cloud pictures of the impact area of the fan case, selecting a radial deformation value for comparison, and finishing the design if the deformation difference meets the requirement; and if the deformation difference meets the composite requirement, determining the size parameter of the key structure.

Description

Bearing case rigidity simulation piece and design method thereof
Technical Field
The application belongs to the technical field of aero-engines, and particularly relates to a bearing casing rigidity simulation piece and a design method thereof.
Background
The large-bypass-ratio turbofan engine is provided with a fan rotor blade with a larger size, and when the large-size fan blade works under severe conditions of high load and high rotating speed for a long time and is simultaneously impacted by foreign objects such as birds, ice blocks, gravels and the like or is accidentally broken and separated due to fatigue of blade materials and the like, the broken part of the rotor blade can impact on the engine case at a high speed under the action of huge centrifugal force. If the casing can not contain the fragments, the high-speed and high-energy fragments flying out of the engine nacelle can puncture the body and the fuel tank of the airplane, if the fragments are light, the airplane loses part of power, and if the fragments are heavy, secondary damages such as fuel tank leakage and fire, system component failure, equipment failure and the like are caused, so that accidents such as machine damage and casualties are caused. Therefore, it is necessary to perform a containment test of the fan casing to verify whether the fan casing meets the containment requirement.
The existing fan case containment test selects an adjacent real engine case part as a support, and the real engine bearing case has a complex structure, a long processing period and high cost.
Disclosure of Invention
The present application is directed to a method for designing a bearing case simulator, which solves or reduces at least one of the problems of the related art.
The technical scheme of the application is as follows: a method for designing a bearing case simulation piece is used for an aeroengine containment test, and comprises the following steps:
s1, acquiring geometric models of a fan casing and a bearing casing, and acquiring the structural size of a connecting part of the fan casing and the bearing casing according to the geometric models of the fan casing and the bearing casing;
s2, establishing a finite element combination model of the fan case and the bearing case according to a drawing and/or a geometric model of the fan case and the bearing case, loading a pressure load in an impact area of the fan case in the finite element combination model, and acquiring a deformation cloud picture of the impact area of the fan case under the influence of the rigidity of the bearing case;
s3, determining the initial size of the strength-bearing case rigidity simulation part according to the structural size of the connecting part of the strength-bearing case and the fan case, selecting a material with the same or similar elasticity modulus as the strength-bearing case, and constructing a geometric model of the strength-bearing case rigidity simulation part;
s4, establishing a finite element model of the bearing case stiffness simulation part according to the geometric model of the bearing case stiffness simulation part, and obtaining a fan case impact area deformation cloud chart under the influence of the bearing case stiffness simulation part stiffness through the finite element model;
s5, carrying out rigidity equivalence on the bearing case by adjusting the key structure size of the bearing case rigidity simulation part;
s6, comparing and analyzing the deformation cloud pictures of the fan case impact areas in the step S2 and the step S4, selecting radial deformation values of multiple points uniformly distributed in the fan case impact area along the axis direction of the engine for comparison, and if the deformation difference is within a required value, finishing the design of the bearing case rigidity simulation piece; and if the deformation difference is not within the required value, adjusting the key structure size parameter of the bearing case rigidity simulation piece until the requirement of the deformation difference is met.
Further, in the finite element combination model, the fan case and the bearing case are connected according to the assembly mode or the assembly process of the fan case and the bearing case.
Further, the pressure load is a unit load.
Further, on the whole, the bearing casing rigidity simulation piece one side with the installation department that the fan casing is connected, the width of installation department is L1, the opposite side of bearing casing rigidity simulation piece is the entity portion that is used for simulating bearing casing rigidity, the width of entity portion is L3, radial height is L4, the installation department with the axial width of the transition portion between the entity portion is L2, and thickness is B.
Further, when the initial size of the bearing case rigidity simulation piece is determined, the structural size of the mounting part of the bearing case rigidity simulation piece is consistent with that of the mounting edge of the bearing case.
Furthermore, the grid density in the finite element model of the bearing case stiffness simulation part is consistent with the unit size.
Further, the key structural dimensions of the bearing casing rigidity simulation piece comprise a connecting part width L1, a transition part axial width L2, a casing thickness B, a solid part width L3 and a radial height L4.
Furthermore, in the process of adjusting the key structure size parameters of the bearing casing stiffness simulation piece, the axial width L2 of the transition part, the width L3 of the solid part and the radial height L4 are preferentially adjusted, and the width L1 of the connecting part and/or the thickness B of the casing are/is adjusted on the basis that the adjustment of the key parameters cannot meet the requirement of deformation difference.
Furthermore, the number of the radial deformation value position points uniformly distributed along the axial direction of the engine is not less than three.
In addition, the application also provides a bearing case rigidity simulation piece, and the bearing case rigidity simulation test piece is realized by any one of the bearing case simulation piece design methods.
According to the design method of the bearing case stiffness simulation piece, reference is adjusted according to the radial deformation influence of the bearing case on the fan case impact area, the radial deformation of the fan case impact area is analyzed by adopting finite element comparison through adjusting parameters such as the mounting part structure size, the axial size and the case thickness of the bearing case stiffness simulation piece, the radial deformation influence of the bearing case stiffness simulation piece on the fan case impact area is ensured to be similar to that of the bearing case, and the final size of the bearing case stiffness simulation piece is determined.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
Fig. 1 is a schematic view of a design process of a bearing case simulation part in the present application.
Fig. 2 is a schematic structural diagram of a force-bearing casing simulator in an embodiment of the present application.
Fig. 3a is a cloud view of deformation of a fan case under the influence of a bearing case according to an embodiment of the present application.
Fig. 3b is a cloud view of deformation of the fan case under the influence of the bearing case stiffness simulator in an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In the design of the fan casing containment test, in order to verify the containment of the fan casing more accurately, adjacent engine bearing casings need to be selected and matched, the processing period is long, and the cost is high. Therefore, the design method for replacing the engine bearing case at the rigidity conversion stage can ensure the effectiveness of the fan case containment test and reduce the test cost.
As shown in fig. 1, the method for designing the bearing casing stiffness simulation part for the aeroengine containment test provided by the application comprises the following steps:
s1, obtaining geometric models of the fan case and the bearing case, and obtaining the structural size of the connecting part of the two cases according to the geometric models of the fan case and the bearing case.
S2, establishing a finite element combination model of the fan casing and the bearing casing according to a drawing and/or a geometric model of the fan casing and the bearing casing, connecting the fan casing and the bearing casing in the finite element combination model according to an assembly mode or an assembly process of the fan casing and the bearing casing, and then loading a pressure load in an impact area of the fan casing to obtain a fan casing impact area deformation cloud picture under the influence of the rigidity of the bearing casing.
In the preferred embodiment of the application, the pressure load is generally a unit load instead of a real impact load, and the unit load is applied, so that the calculation process of the real impact load is reduced, and the time cost is reduced.
S3, determining the initial size of the strength-bearing case rigidity simulation part according to the material performance of the strength-bearing case and the structural size of the connecting part of the strength-bearing case and the fan case, and selecting the material property which is the same as or similar to the elasticity modulus of the strength-bearing case to construct a geometric model of the strength-bearing case rigidity simulation part.
Fig. 2 is a schematic view of a force-bearing casing stiffness simulation element in the embodiment of the present application, the force-bearing casing stiffness simulation element is cylindrical as a whole, a mounting portion connected to a fan casing is disposed on the left side of the force-bearing casing stiffness simulation element, the mounting portion has a width of L1, the fan casing is connectable to the mounting portion through a bolt, a solid portion for simulating force-bearing casing stiffness is disposed on the other side of the force-bearing casing stiffness simulation element, the solid portion has a width of L3 and a radial height of L4, and a transition portion between the mounting portion and the solid portion has an axial width of L2 and a thickness of B.
When the initial size of the bearing case rigidity simulation piece is determined, the structural size of the mounting part of the bearing case rigidity simulation piece needs to be kept consistent with that of the mounting edge of the bearing case. The structural dimension of the mounting part of the stiffness simulation part, which is consistent with the structural dimension of the mounting edge of the bearing casing, includes the dimension of the step of the transition region Z on the left side of the transition part, the dimension of the transition angle and the like, in addition to the width L1 of the mounting part.
S4, establishing a finite element model of the bearing case stiffness simulation part according to the geometric model of the bearing case stiffness simulation part, wherein the grid density in the finite element model is consistent with the unit size, and obtaining a fan case impact area deformation cloud picture under the influence of the bearing case stiffness simulation part stiffness through the finite element model;
and S5, carrying out rigidity equivalence on the bearing case by adjusting the key structure size of the bearing case rigidity simulation piece.
Wherein the critical feature size comprises: the width L1 of the connecting part, the axial width L2 of the transition part, the thickness B of the casing, the width L3 of the solid part and the radial height L4.
S6, comparing and analyzing the deformation cloud pictures of the fan case impact areas in the step S2 and the step S4, selecting radial deformation values of multiple points uniformly distributed in the fan case impact area along the axis direction of the engine for comparison, and if the deformation difference is within a required value, finishing the design of the bearing case rigidity simulation piece; and if the deformation difference is not within the required value, adjusting the key structure size parameter of the bearing case rigidity simulation piece until the requirement of the deformation difference is met.
Wherein, the radial deformation value position points uniformly distributed along the axis direction of the engine are not less than three.
As shown in fig. 3a, the maximum deformation value of the fan casing at a certain point of the impact area under the influence of the bearing casing stiffness is 31.07. As shown in fig. 3b, the maximum deformation value of the same position of the impact area of the fan casing under the influence of the bearing casing stiffness simulation piece with the initial size is 34.67, and the deformation difference exceeds 10%, so that the initial size of the bearing casing stiffness simulation piece is adjusted, and the above process is performed again until the deformation difference is within 5%, thereby obtaining the structural size of the bearing casing stiffness simulation piece.
In the preferred embodiment of the application, in the process of adjusting the key structural dimension parameters of the bearing casing stiffness simulation piece, the axial width L2 of the transition part, the width L3 of the solid part and the radial height L4 are preferentially adjusted, and on the basis that the key parameters cannot meet the requirement of deformation difference, the width L1 of the connecting part and/or the thickness B of the casing can be adjusted.
According to the design method of the bearing case stiffness simulation piece, reference is adjusted according to the radial deformation influence of the bearing case on the fan case impact area, the radial deformation of the fan case impact area is analyzed by adopting finite element comparison through adjusting parameters such as the mounting part structure size, the axial size and the case thickness of the bearing case stiffness simulation piece, the radial deformation influence of the bearing case stiffness simulation piece on the fan case impact area is ensured to be similar to that of the bearing case, and the final size of the bearing case stiffness simulation piece is determined.
Finally, the application also provides a bearing case rigidity simulation piece for the aeroengine containment test, and the bearing case rigidity simulation piece is obtained by the bearing case rigidity simulation piece design method.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (10)

1. A method for designing a bearing case simulation part is used for an aeroengine containment test, and is characterized by comprising the following steps:
s1, acquiring geometric models of a fan casing and a bearing casing, and acquiring the structural size of a connecting part of the fan casing and the bearing casing according to the geometric models of the fan casing and the bearing casing;
s2, establishing a finite element combination model of the fan case and the bearing case according to a drawing and/or a geometric model of the fan case and the bearing case, loading a pressure load in an impact area of the fan case in the finite element combination model, and acquiring a deformation cloud picture of the impact area of the fan case under the influence of the rigidity of the bearing case;
s3, determining the initial size of the bearing case stiffness simulation part according to the structural size of the connecting part of the bearing case and the fan case, selecting a material with the same or similar elastic modulus as the bearing case, and constructing a geometric model of the bearing case stiffness simulation part;
s4, establishing a finite element model of the bearing case stiffness simulation part according to the geometric model of the bearing case stiffness simulation part, and obtaining a fan case impact area deformation cloud chart under the influence of the bearing case stiffness simulation part stiffness through the finite element model;
s5, carrying out rigidity equivalence on the bearing case by adjusting the key structure size of the bearing case rigidity simulation part;
s6, comparing and analyzing the deformation cloud pictures of the fan case impact areas in the step S2 and the step S4, selecting radial deformation values of multiple points uniformly distributed in the fan case impact area along the axis direction of the engine for comparison, and if the deformation difference is within a required value, finishing the design of the bearing case rigidity simulation piece; and if the deformation difference is not within the required value, adjusting the key structure size parameter of the bearing case rigidity simulation piece until the requirement of the deformation difference is met.
2. The method for designing a bearing case simulation element according to claim 1, wherein in the finite element combination model, the fan case and the bearing case are connected according to an assembly mode or an assembly process of the fan case and the bearing case.
3. The bearing case simulation piece design method as set forth in claim 1 or 2, wherein the pressure load is a unit load.
4. The design method of the bearing case simulation piece according to claim 3, wherein the bearing case stiffness simulation piece is integrally provided with a mounting part connected with the fan case at one side, the mounting part has a width of L1, the bearing case stiffness simulation piece is provided with a solid part for simulating the bearing case stiffness at the other side, the solid part has a width of L3 and a radial height of L4, and a transition part between the mounting part and the solid part has an axial width of L2 and a thickness of B.
5. The method for designing a bearing case simulator according to claim 4, wherein the mounting part structure size of the bearing case rigidity simulator is consistent with the mounting edge structure size of the bearing case when determining the preliminary size of the bearing case rigidity simulator.
6. The method for designing a bearing case simulator of claim 5 wherein the grid density in the finite element model of the bearing case stiffness simulator is consistent with the unit size.
7. The design method of the bearing case simulation piece according to claim 6, wherein the key structural dimensions of the bearing case stiffness simulation piece comprise a connecting part width L1, a transition part axial width L2, a case thickness B, a solid part width L3 and a radial height L4.
8. The design method of the bearing case simulation member as claimed in claim 7, wherein during the adjustment of the key structural dimension parameters of the bearing case stiffness simulation member, the axial width L2 of the transition portion, the width L3 of the solid portion and the radial height L4 are preferably adjusted, and the width L1 of the connecting portion and/or the thickness B of the case are/is adjusted on the basis that the adjustment of the key parameters cannot meet the requirement of deformation difference.
9. The method for designing a bearing case simulator according to claim 7, wherein the number of radial deformation value position points uniformly distributed along the axial direction of the engine is not less than three.
10. A bearing case rigidity simulation piece, which is characterized in that the bearing case rigidity simulation test piece is realized by the bearing case rigidity simulation piece design method as claimed in any one of claims 1 to 9.
CN202210902485.8A 2022-07-29 2022-07-29 Rigidity simulation piece of bearing casing and design method thereof Active CN115270334B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210902485.8A CN115270334B (en) 2022-07-29 2022-07-29 Rigidity simulation piece of bearing casing and design method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210902485.8A CN115270334B (en) 2022-07-29 2022-07-29 Rigidity simulation piece of bearing casing and design method thereof

Publications (2)

Publication Number Publication Date
CN115270334A true CN115270334A (en) 2022-11-01
CN115270334B CN115270334B (en) 2023-05-16

Family

ID=83771077

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210902485.8A Active CN115270334B (en) 2022-07-29 2022-07-29 Rigidity simulation piece of bearing casing and design method thereof

Country Status (1)

Country Link
CN (1) CN115270334B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115544674A (en) * 2022-11-30 2022-12-30 南京航空航天大学 Intermediate casing rapid modeling method based on Abaqus secondary development
CN116432536A (en) * 2023-04-19 2023-07-14 沈阳航空航天大学 Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170212979A1 (en) * 2015-10-23 2017-07-27 Jinquan Cheng Method for quickly full-scale analyzing and designing the processing parameters and deposit strategy on temperature field for 3D printing/Additive manufacturing
CN112541230A (en) * 2020-12-23 2021-03-23 南京航空航天大学 Casing containment analysis method for blade deviation loss

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170212979A1 (en) * 2015-10-23 2017-07-27 Jinquan Cheng Method for quickly full-scale analyzing and designing the processing parameters and deposit strategy on temperature field for 3D printing/Additive manufacturing
CN112541230A (en) * 2020-12-23 2021-03-23 南京航空航天大学 Casing containment analysis method for blade deviation loss

Non-Patent Citations (6)

* Cited by examiner, † Cited by third party
Title
宣海军;何泽侃;牛丹丹;苗艳;柏汉松;洪伟荣;: "航空发动机软壁风扇机匣包容性研究" *
徐峰;马艳红;张力;洪杰;: "航空发动机承力系统抗变形能力评估" *
柴象海;张晓云;侯亮;杨宵毅;: "航空发动机风扇机匣包容性等效试验与分析方法" *
温登哲;陈予恕;: "航空发动机机匣动力学研究进展与展望", 动力学与控制学报 *
范志强;高德平;姜涛;覃志贤;王维;: "模型机匣的包容性试验和数值模拟" *
黎飞龙;吴宝勤;范志强;: "航空发动机叶片包容性瞬态响应的数值仿真" *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115544674A (en) * 2022-11-30 2022-12-30 南京航空航天大学 Intermediate casing rapid modeling method based on Abaqus secondary development
CN115544674B (en) * 2022-11-30 2023-05-23 南京航空航天大学 Intermediate case rapid modeling method based on Abaqus secondary development
CN116432536A (en) * 2023-04-19 2023-07-14 沈阳航空航天大学 Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing
CN116432536B (en) * 2023-04-19 2024-03-08 沈阳航空航天大学 Limiting optimization method for structural parameters of impact resistance of aero-engine connecting casing

Also Published As

Publication number Publication date
CN115270334B (en) 2023-05-16

Similar Documents

Publication Publication Date Title
CN115270334A (en) Bearing case rigidity simulation piece and design method thereof
CN109815521B (en) Method for evaluating FOD resistance of aero-engine blade
CN109583147B (en) Design method of centrifugal impeller pre-rotation disk center gradient simulation piece
Heidari et al. An efficient multi-disciplinary simulation of engine fan-blade out event using MD Nastran
US20080148706A1 (en) Method of maintaining aircraft gas turbine engine
Chen et al. Mode shape recognition of complicated spatial beam-type structures via polynomial shape function correlation
KR101733361B1 (en) An analysis method for rotor
Batailly et al. Minimising clearance consumption: a key factor for the design of blades robust to rotor/stator interactions?
CN111104713A (en) Leaf-disc structure coupling vibration characteristic analysis method
Mironov et al. The demonstrator of structural health monitoring system of helicopter composite blades
Ning et al. Blade forced response prediction for industrial gas turbines: Part 2—verification and application
CN113418709B (en) Cartridge container holding test device and design method thereof
Bai et al. Research on centrifugal compressor disk containment of auxiliary power unit
Moradi et al. Crack growth simulation in 13th row of compressor blades under foreign object damage and resonant vibration condition
Honisch et al. Modelling of industrial blade integrated disks (blisks) with regard to mistuning
Arkhipov et al. Analysis of the Impact of Fan Blade Geometric Deviations on the Strength Properties
CN110987388B (en) Method for equivalent machining notch based on notch fatigue strength
Day et al. Parametric evaluation of compressor blade blending
Firrone et al. A reliable pre-processing for the simulation of friction joints in turbomachineries and its validation: a case study with policontact
Lombard et al. Mistuning phenomena on bladed disk: Industrial methods and applications
Gao et al. Engine vibration certification
CA2572444C (en) Method of maintaining aircraft gas turbine engine
Lepeshkin et al. The blade releasing method for test of engine casing containment
CN115907381A (en) High-energy rotor blasting risk evaluation method based on digital model
RU2710811C2 (en) Method for repairing fan housing

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
GR01 Patent grant
GR01 Patent grant