CN109598032A - A kind of helicopter blade root bushing magnitude of interference determines method - Google Patents
A kind of helicopter blade root bushing magnitude of interference determines method Download PDFInfo
- Publication number
- CN109598032A CN109598032A CN201811361269.7A CN201811361269A CN109598032A CN 109598032 A CN109598032 A CN 109598032A CN 201811361269 A CN201811361269 A CN 201811361269A CN 109598032 A CN109598032 A CN 109598032A
- Authority
- CN
- China
- Prior art keywords
- bushing
- magnitude
- interference
- blade root
- neck bush
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 27
- 230000003068 static effect Effects 0.000 claims abstract description 9
- 238000012545 processing Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 25
- 238000012423 maintenance Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 9
- 238000006073 displacement reaction Methods 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000010200 validation analysis Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 238000012795 verification Methods 0.000 description 3
- 238000010998 test method Methods 0.000 description 2
- 230000005483 Hooke's law Effects 0.000 description 1
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003340 mental effect Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
- G06F17/11—Complex mathematical operations for solving equations, e.g. nonlinear equations, general mathematical optimization problems
-
- 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
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
-
- 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
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Mathematical Physics (AREA)
- Evolutionary Computation (AREA)
- Computer Hardware Design (AREA)
- Data Mining & Analysis (AREA)
- Operations Research (AREA)
- Algebra (AREA)
- Databases & Information Systems (AREA)
- Software Systems (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of helicopter blade root bushing magnitude of interference to determine method, belongs to helicopter blade structure-design technique field.The described method includes: obtaining the internal diameter and outer diameter of blade root Outer Diameter of lining, the neck bush being set in blade root bushing, and obtain the elasticity modulus of bushing；Determine the magnitude of interference between blade root bushing and neck bush and the relationship between pressure；Determine the relationship between maximum static friction force and pressure；Obtain the axial thrust load of the bushing root under helicopter blade rotation status；In the case where the axial thrust load is less than or equal to the pressure, magnitude of interference is calculated, the internal-and external diameter of blade root bushing and neck bush is designed according to magnitude of interference.The present invention carries out magnitude of interference calculating using assembled tubes theoretical model, computation model is closer practical, calculated result is more acurrate, it can effectively solve the problems, such as successive ignition in the design of bushing magnitude of interference, in the just many-sided consideration of design initial stage, maintenance maintenance and the change in design work of subsequent failure are avoided.
Description
Technical field
The invention belongs to helicopter blade structure-design technique fields, and in particular to a kind of helicopter blade root bushing mistake
The amount of being full of determines method.
Background technique
In helicopter rotor system, main blade passes through bushing at main blade blade root by blade pin and is connected on propeller hub；?
Maintenance neck bush generally is configured in main blade blade root bushing, main function is to prevent blade pin from directly existing with blade root bushing
It is worn in use process；After abrasion or other damages occur for neck bush, impaired neck bush boring is fallen first, it is then right
Blade root bushing carries out reaming, finally assembles new neck bush using temperature differential method, that completes neck bush reprocesses replacement.
The magnitude of interference of neck bush outer diameter and blade root bushing inner diameter is one of the important indicator in propeller shank liner Analysis of Nested Design,
The size of magnitude of interference largely influences neck bush safety in use and maintainability, if neck bush is using
Process slides, and will influence the use of helicopter user.Helicopter is in flight course, between neck bush and blade pin
Contact condition be it is heterogeneous, neck bush mainly by blade pin shaft to load (the namely component of centrifugal force)；Therefore exist
The size relation that the maximum static friction force and blade centrifugal force component that neck bush is generated by magnitude of interference are considered in design process is to set
Meter constraint.
Summary of the invention
In order to solve the design problem of helicopter blade root bushing magnitude of interference, assembled tubes theory is introduced into goes straight up to for the first time
Machine propeller shank bushing assembles in the calculating of magnitude of interference, effectively and really simulates the mechanical behavior of elastic conjunction, and adopt
It is verified with test method and random take a flight test, solves the problems, such as the selection of the magnitude of interference in propeller shank bushing design.
The application helicopter blade root bushing magnitude of interference determines method, comprising:
Step S1, the internal diameter and outer diameter of blade root Outer Diameter of lining, the neck bush being set in blade root bushing are obtained, and is obtained
The elasticity modulus of bushing；
Step S2, the magnitude of interference between blade root bushing and neck bush and the relationship between pressure are determined；
Step S3, the relationship between maximum static friction force and pressure is determined；
Step S4, the axial thrust load of the bushing root under helicopter blade rotation status is obtained；
Step S5, in the case where the axial thrust load is less than or equal to the pressure, magnitude of interference is calculated, is set according to magnitude of interference
Count the internal-and external diameter of blade root bushing and neck bush.
Preferably, the relationship between magnitude of interference and pressure in step S2, between blade root bushing and neck bush are as follows:
Wherein, c is blade root Outer Diameter of lining, a is the internal diameter of neck bush, the outer diameter that b is neck bush, and E is elasticity modulus, and p is
Pressure, Δ are magnitude of interference.
Preferably, in the step S5, the axial thrust load is less than or equal to the pressure representative are as follows:
Fa≤kFμ
Wherein, FaFor axial thrust load, FμFor pressure, k is the corrected parameter as caused by processing error.
Preferably, the k is 0.9~1.
The beneficial effect of the design method is: computation model and passes through examination closer to the stress model of actual bushing
Verifying and accidental validation, it is as a result more reliable, it is more acurrate that also there is higher applicability.
Key point of the invention:
Assembled tubes theory is introduced into the calculating of bushing magnitude of interference, model is more acurrate；
A set of propeller shank bushing magnitude of interference and release force testing program and test tool are devised, magnitude of interference is carried out and tests
Card；
It is taken a flight test and is verified at random using bushing installation.
Having the technical effect that for the design method carries out magnitude of interference calculating using assembled tubes theoretical model, and computation model more connects
Close practical, calculated result is more acurrate；Ground experiment scheme and tooling and Flight are devised, carries out calculating magnitude of interference most
It determines eventually and application, final design result is more reliable.The design method is simple and effective, accurately and reliably, have passed through the experience of model
Verifying can effectively solve the problems, such as successive ignition in the design of bushing magnitude of interference, and at design initial stage, just various aspects consider, after avoiding
The continuous maintenance maintenance to break down and change in design work.
Detailed description of the invention
Fig. 1 is the flow chart for the preferred embodiment that the application helicopter blade root bushing magnitude of interference determines method.
Fig. 2 is that magnitude of interference analyzes schematic diagram between neck bush and blade root bushing.
Fig. 3 is to establish blade root external bushing and neck bush model schematic.
Fig. 4 is the propeller shank bushing stress condition schematic diagram under rated speed.
Fig. 5 is cell cube stress analysis schematic diagram.
Fig. 6 is cell cube deformation schematic diagram.
Fig. 7 is that magnitude of interference and radial load change schematic diagram.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
Helicopter blade root bushing magnitude of interference of the present invention determines method, as shown in Figure 1, specifically including that
Step S1, the internal diameter and outer diameter of blade root Outer Diameter of lining, the neck bush being set in blade root bushing are obtained, and is obtained
The elasticity modulus of bushing；
Step S2, the magnitude of interference between blade root bushing and neck bush and the relationship between pressure are determined；
Step S3, the relationship between maximum static friction force and pressure is determined；
Step S4, the axial thrust load of the bushing root under helicopter blade rotation status is obtained；
Step S5, in the case where the axial thrust load is less than or equal to the pressure, magnitude of interference is calculated, is set according to magnitude of interference
Count the internal-and external diameter of blade root bushing and neck bush.
Referring initially to Fig. 4, propeller shank is fixed by bushing, and external bushing, band in diagram are also referred to as below the bushing
Oblique line is external bushing, and external bushing is internally provided with neck bush, constitutes combined sleeve, and the two is interference fitted, theoretically, magnitude of interference
Bigger, the two compression is more serious, is less susceptible to that being mutually disengaged for interior external bushing occurs, the goal of the invention of the application is that
It prevents in blade rotary course, drives neck bush to be detached from external bushing, it is therefore desirable to determine a suitable magnitude of interference.
Based on above-mentioned purpose, in the present embodiment, neck bush and external bushing mutual extrusion, it is first determined magnitude of interference and the extruding
Pressure dependence determine that neck bush skids off the critical value of external bushing, last base later according to the relationship between pressure and frictional force
Magnitude of interference is determined in this critical value.
Assembled tubes theory is introduced into the calculating of helicopter blade root bushing assembly magnitude of interference by the application, effective and true
Real simulates the mechanical behavior of elastic conjunction, and is verified using test method and random take a flight test, and solves in paddle
In blade root bushing design the problem of the selection of magnitude of interference.
Technical solution used by the design method is:
Step 1: the theoretical model that external bushing is depressed by internal pressure or outside in carrying out first derives, the position of interior external bushing is obtained
It moves.
Step 2: introducing assembled tubes theory, regard the interior external bushing of elastic conjunction as two thick cylinders respectively, according to bushing
The displacement coordination of faying face constrains, available interior external bushing elastic conjunction formula, the pressure between bushing.According to the material of bushing
The roughness of attribute and assembly surface obtains its contact surface coefficient of friction, and then obtains its maximum static friction force.
Step 3: according under helicopter blade rotation status, the actual loading situation of propeller shank bushing, to root bushing
Carry out force analysis, it is desirable that under bushing working condition, axial loosening does not occur for bushing.The wherein axial force of bushing root point
Amount is mainly centrifugal component.In helicopter normal flight envelope curve, it should be ensured that bushing maximum static friction force be greater than its axial direction from
Mental and physical efforts component does not occur to loosen slippage.The choosing of bushing assembly magnitude of interference is carried out according to the limitation of above-mentioned limitation and matching requirements
It selects.
4th step devises a set of helicopter blade root bushing magnitude of interference and loosens according to magnitude of interference obtained above
The magnitude of interference being calculated is carried out ground experiment verifying, served as a contrast when applying actual flight state by power testing program and test tool
The stress load of set.Ground experiment carries out accidental validation after passing through, and finally determines magnitude of interference.
The beneficial effect of the design method is: computation model and passes through examination closer to the stress model of actual bushing
Verifying and accidental validation, it is as a result more reliable, it is more acurrate that also there is higher applicability.It is described in detail below.
Magnitude of interference force analysis between neck bush and blade root bushing is establishment of coordinate system schematic diagram, it is assumed that interior with reference to Fig. 2
Bushing inside radius is a, and external bushing outer radius is b, and pressure p in uniform is born in bushing, and bushing both ends are Open architecture.?
Interior pressure is used down, and the cylindrical surface of radius r is deformed into the cylindrical surface that radius is r+u.Here u is the radial displacement at radius r, u
The only function of r, unrelated with polar angle θ, u, which is displaced outwardly, to be positive.
With reference to Fig. 5, it is cell cube stress analysis schematic diagram, a cell cube of θ angle is taken on neck bush, cell cube
Front and back (is not drawn into) perpendicular to z-axis perpendicular to paper, in the active force of cell cube and external bushing contact position by four sides, difference
For direct stress σrAnd σθ, without shearing stress.σθIt is circumferential stress for the tangential direction for the circle that radius is r；σrFor radial direction
Radial stress.
1. geometry equation
With reference to Fig. 6, before being deformed along any radius r direction line taking member AB=dr, A point and B point are moved respectively to after deformation
A ' and B ', radial displacement is u and u+du respectively.The radial strain of line element AB:
Due to A ' B '=dr+ (u+du)-u=dr+du, then
The circle of radius OA is deformed into the circle that radius is OA ', wherein 0 is the center of circle, the circumferential strain at A ' is:
2. physical equation
Poisson's ratio symbol is ν herein, is obtained according to Hooke's law and geometry equation:
3. equilibrium equation
In order to facilitate analysis, it is assumed that the vertical height of cell cube is 1.List edgeThe radial equilibrium equation of angle:
In low-angleTherefore above formula can be with abbreviation are as follows:
(σr+dσr) (r+dr) d θ=σrrdθ+σθdrdθ
Above formula is unfolded, can arrange to obtain after omitting a small amount of drd θ of high-order therein:
It finally obtains:
Three unknown quantity σ can be solved after two physical equations of simultaneousr、σθAnd u
Formula 3 is substituted into formula 1 and formula 2, arrangement can obtain
Formula 5 differentiates to r, then with 4 simultaneous of formula, can obtain:
(form r2The differential equation of y "+ry '-y=0)
The form of above formula solution isIntegral constant C1 and C2 bushing can be found out by interior according to boundary condition
Pressure:
Bushing is by external pressure:
Based on above-mentioned model inference, blade root external bushing and liner set of model can establish, as shown in Figure 3.
The radial displacement u of neck bush under external pressure1Are as follows:
The radial displacement u of external bushing under external pressure2Are as follows:
Due to magnitude of interference Δ=u2-u1, following relational expression can be obtained by bringing the displacement of interior external bushing into solution:
Since neck bush is identical as blade root lagging material, institute's above formula be can simplify are as follows:
Δ indicates that magnitude of interference, a indicate that neck bush internal diameter, b indicate that external bushing outer diameter, c indicate neck bush outer diameter in above formula.Root
According to the material properties of bushing and the roughness of assembly surface, its contact surface coefficient of friction is obtained, and then obtains it and maximum quiet rubs
Wipe power:
Fμ=2 π cLp μ (4)
C is the outer diameter of neck bush in above formula, and the axial length of L bushing interface, μ is neck bush and blade root bushing interface
Coefficient of friction.
As shown in figure 4, the propeller shank bushing stress condition according to helicopter blade under rated speed, to root bushing
Carry out force analysis, it is desirable that under bushing working condition, axial loosening does not occur for bushing.The wherein axial force of bushing root point
Amount mainly centrifugal component, such as following formula:
Fa=1/2 (FcSin θ °) (note: there are two blade pins for one piece blade, therefore are herein 1/2.)
F in above formulacThe centrifugal force that bushing is subject to when rotating for blade, θ are the angle of busing axis and blade Plane of rotation.
In helicopter normal flight envelope curve, it should be ensured that bushing maximum static friction force is greater than its axial centrifugal force component, and pine does not occur
It is dynamic to slip.It is general to require in view of technique Machinability Evaluation:
Fa≤ (0.9~1.0) Fμ (6)
The selection of bushing assembly magnitude of interference is carried out according to the limitation of above formula and matching requirements.The application also brings following
Advantage: magnitude of interference is suitable for multiple rework process after change, and the maximum static friction force that maximum neck bush provides after reaming can omit
It is slightly variable greatly, effect is preferable.
With reference to Fig. 7, abscissa is magnitude of interference selected value, and unit mm, ordinate is radial load, unit N, at specified turn
In fast situation, interior external bushing begins have the radial load of 11000N or so, and oblique line indicates that different interference magnitudes are able to bear most
Big radial load, such as when 0.07mm, revolving speed is more than certain value, is detached from radial load i.e. when reaching about 10000N, and
The magnitude of interference of 0.1mm can satisfy the radial load of 14000N or more.
In the attached drawing, after inside and outside liner wear, need to carry out reaming to neck bush, to increase its outer diameter, diagram looks for that
Three oblique lines are indicated from bottom to top by reaming twice, it is to be understood that the outer diameter of neck bush are increased after reaming, accordingly
Magnitude of interference is increased, therefore effect can be more preferable.
The beneficial effect of the design method is: computation model and passes through examination closer to the stress model of actual bushing
Verifying and accidental validation, it is as a result more reliable, it is more acurrate that also there is higher applicability.
Key point of the invention
2. the present invention has following three key points:
(1) a set of accurate neck bush magnitude of interference force analysis model is established；
(2) the plan boundary condition that design neck bush magnitude of interference is chosen has been determined；
(3) it reprocesses replacement to neck bush to be analyzed, it is ensured that feasibility.
Having the technical effect that for the design method carries out theoretical model foundation for neck bush and blade root bushing and carries out interference
Meter point counting analysis, for computation model closer to reality, calculated result is more acurrate；By verification experimental verification, show final design result more
Reliably.By the empirical verification of model, successive ignition in the design of bushing magnitude of interference can be effectively solved the problems, such as, at design initial stage
Various aspects are considered, maintenance maintenance and the change in design work of subsequent failure are avoided.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (4)
1. a kind of helicopter blade root bushing magnitude of interference determines method characterized by comprising
Step S1, the internal diameter and outer diameter of blade root Outer Diameter of lining, the neck bush being set in blade root bushing are obtained, and obtains bushing
Elasticity modulus；
Step S2, the magnitude of interference between blade root bushing and neck bush and the relationship between pressure are determined；
Step S3, the relationship between maximum static friction force and pressure is determined；
Step S4, the axial thrust load of the bushing root under helicopter blade rotation status is obtained；
Step S5, in the case where the axial thrust load is less than or equal to the pressure, magnitude of interference is calculated, paddle is designed according to magnitude of interference
The internal-and external diameter of root bushing and neck bush.
2. helicopter blade root bushing magnitude of interference as described in claim 1 determines method, which is characterized in that in step S2,
The relationship between magnitude of interference and pressure between blade root bushing and neck bush are as follows:
Wherein, c is blade root Outer Diameter of lining, a is the internal diameter of neck bush, the outer diameter that b is neck bush, and E is elasticity modulus, and p is pressure,
Δ is magnitude of interference.
3. helicopter blade root bushing magnitude of interference as described in claim 1 determines method, which is characterized in that the step S5
In, the axial thrust load is less than or equal to the pressure representative are as follows:
Fa≤kFμ
Wherein, FaFor axial thrust load, FμFor pressure, k is the corrected parameter as caused by processing error.
4. helicopter blade root bushing magnitude of interference as claimed in claim 3 determines method, which is characterized in that the k is 0.9
~1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811361269.7A CN109598032A (en) | 2018-11-15 | 2018-11-15 | A kind of helicopter blade root bushing magnitude of interference determines method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811361269.7A CN109598032A (en) | 2018-11-15 | 2018-11-15 | A kind of helicopter blade root bushing magnitude of interference determines method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109598032A true CN109598032A (en) | 2019-04-09 |
Family
ID=65958465
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811361269.7A Pending CN109598032A (en) | 2018-11-15 | 2018-11-15 | A kind of helicopter blade root bushing magnitude of interference determines method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109598032A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110781568A (en) * | 2019-11-28 | 2020-02-11 | 重庆市超群工业股份有限公司 | Rim cutting length calculation method |
| CN112434417A (en) * | 2020-11-20 | 2021-03-02 | 哈尔滨汽轮机厂有限责任公司 | Intelligent calculation method for strength of sleeve of steam turbine valve |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4709155A (en) * | 1984-11-22 | 1987-11-24 | Babcock-Hitachi Kabushiki Kaisha | Flame detector for use with a burner |
| CN1875204A (en) * | 2004-12-13 | 2006-12-06 | 东洋橡胶工业株式会社 | Viberation isolation device and method of installing same |
| CN101944143A (en) * | 2010-08-25 | 2011-01-12 | 一重集团大连设计研究院有限公司 | Interference magnitude parameterized designing method of double-layer circular extruding cylinder |
| CN101966552A (en) * | 2010-10-11 | 2011-02-09 | 上海保捷汽车零部件锻压有限公司 | Cold forging die externally provided with meridian components and forging method thereof |
| CN104077470A (en) * | 2014-06-05 | 2014-10-01 | 合肥通用机械研究院 | Risk based design method of magnitude of interference of end portion structure of ultrahigh pressure tubular reactor |
| CN104408242A (en) * | 2014-11-14 | 2015-03-11 | 一重集团大连设计研究院有限公司 | Double-layer round extrusion container magnitude of interference parametrization design method |
-
2018
- 2018-11-15 CN CN201811361269.7A patent/CN109598032A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4709155A (en) * | 1984-11-22 | 1987-11-24 | Babcock-Hitachi Kabushiki Kaisha | Flame detector for use with a burner |
| CN1875204A (en) * | 2004-12-13 | 2006-12-06 | 东洋橡胶工业株式会社 | Viberation isolation device and method of installing same |
| CN101944143A (en) * | 2010-08-25 | 2011-01-12 | 一重集团大连设计研究院有限公司 | Interference magnitude parameterized designing method of double-layer circular extruding cylinder |
| CN101966552A (en) * | 2010-10-11 | 2011-02-09 | 上海保捷汽车零部件锻压有限公司 | Cold forging die externally provided with meridian components and forging method thereof |
| CN104077470A (en) * | 2014-06-05 | 2014-10-01 | 合肥通用机械研究院 | Risk based design method of magnitude of interference of end portion structure of ultrahigh pressure tubular reactor |
| CN104408242A (en) * | 2014-11-14 | 2015-03-11 | 一重集团大连设计研究院有限公司 | Double-layer round extrusion container magnitude of interference parametrization design method |
Non-Patent Citations (2)
| Title |
|---|
| 华东纺织工学院 编: "《纺织机械设计原理 第三分册》", 30 September 1963 * |
| 孙远国 等: "双层圆挤压筒过盈量参数优化设计和分析", 《一重技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110781568A (en) * | 2019-11-28 | 2020-02-11 | 重庆市超群工业股份有限公司 | Rim cutting length calculation method |
| CN112434417A (en) * | 2020-11-20 | 2021-03-02 | 哈尔滨汽轮机厂有限责任公司 | Intelligent calculation method for strength of sleeve of steam turbine valve |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10787275B2 (en) | Propeller health monitoring | |
| Ramasamy | Hover performance measurements toward understanding aerodynamic interference in coaxial, tandem, and tilt rotors | |
| Subramanian et al. | Rotordynamic characteristics of rotating labyrinth gas turbine seal with centrifugal growth | |
| JP5506420B2 (en) | Torque calculation method, calculation device, and calculation program for 4-point contact ball bearings | |
| US11708175B2 (en) | Propeller health monitoring | |
| Wang et al. | Dynamic characteristics of ball bearing-coupling-rotor system with angular misalignment fault | |
| CN113343357B (en) | Method for calculating radial clearance between high-low pressure rotors of aero-engine | |
| CN109598032A (en) | A kind of helicopter blade root bushing magnitude of interference determines method | |
| CN207335967U (en) | A kind of dynamic balancing clamping device | |
| CN113153439B (en) | Compact turbine shaft structure with torsion measuring function | |
| CN107662704B (en) | Unmanned helicopter main rotor hub mechanism | |
| CN112507576A (en) | Rotor blade crack damage identification method based on blade end displacement-displacement transfer ratio | |
| CN207374654U (en) | A kind of unmanned helicopter main rotor propeller hub mechanism | |
| Crawley et al. | Stagger angle dependence of inertial and elastic coupling in bladed disks | |
| Baker | The effects of various parameters, including Mach number, on propeller-blade flutter with emphasis on stall flutter | |
| CN105547534B (en) | It can measure the elastic bearing of rotor axial load | |
| CN109505779A (en) | The experimental provision and method that back blade cornerite size influences centrifugal pump axial force | |
| CN110645097B (en) | Gas turbine generating set rotor subassembly and gas turbine generating set | |
| CN205841518U (en) | Inner ring hole axis and the uneven roller bearing of shaft center line | |
| CN106289893B (en) | A kind of manufacturing method of wheel disc core hole fatigue test piece | |
| CN108931167A (en) | The measurement method of main shaft bearing spacer ring precision | |
| CN109583062B (en) | Steel ring type elastic support structure rigidity optimization design method | |
| CN207960688U (en) | Rotary engine bindiny mechanism and Small Gas Turbine Engine rotor | |
| CN106516101B (en) | A kind of lifting airscrew tower rotor connector | |
| CN110030154A (en) | A kind of resilient movement steering system |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190409 |
|
| RJ01 | Rejection of invention patent application after publication |