CN110197025A - The design method of aero-engine casing bolt fastening structure - Google Patents
The design method of aero-engine casing bolt fastening structure Download PDFInfo
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Abstract
The invention discloses a kind of design methods of aero-engine casing bolt fastening structure, comprising the following steps: estimates the aperture of bolt hole, and is pressed according to the chamber of casing and determine bolt number；The type selecting that bolt is carried out according to the external axial load that single bolt is subjected to, determines the diameter of bolt；Judge whether the diameter of bolt matches with the aperture for the bolt hole estimated, select the aperture of the bolt hole to match with the diameter of bolt to repeat the above steps as the bolt hole aperture estimated if mismatching, if matching carries out following step；Estimate the first installation while and second installation while thickness；Force analysis is carried out to bolt, locking assessment, static strength assessment and Fatigue Assessment are carried out to bolt fastening structure according to the force analysis result of bolt；If the locking assessment of bolt fastening structure, static strength assessment and Fatigue Assessment meet the requirements, the number of bolt, the type selecting of bolt, the first installation while thickness and when the second installation with a thickness of final design result.
Description
Technical field
The present invention relates to aero-engine technology fields, particularly, are related to a kind of aero-engine casing bolted-on attachment
The design method of structure.
Background technique
Bolt fastening structure is widely used on aero-engine casing, due to the harsh building ring of aero-engine
The problems such as border, bolt fastening structure design needs to comprehensively consider intensity, sealing.The bolt of domestic air mail engine crankcase connects at present
It connects Intensity Design and still rests on the design phase earlier, by reference to Project R&D experience, lack succinct bolt fastening structure
Sizing method；Existing bolt fastening structure strength design considers the locking design of bolt fastening structure insufficient；Temperature
Poor load calculation method uses a large amount of structural parameters and calculates connector, connected piece rigidity, and calculation method is cumbersome and calculates essence
Degree is difficult to ensure, lead to problems such as the bolt fastening structure of design occur loosening in use process, service life it is short, to influence
The normal operation of aero-engine.
Summary of the invention
The present invention provides a kind of design methods of aero-engine casing bolt fastening structure, to solve existing aviation
The technical problem that the bolt fastening structure of engine crankcase easily loosens in use and service life is short.
According to an aspect of the present invention, a kind of design method of aero-engine casing bolt fastening structure, spiral shell are provided
Bolt connecting structure include the first installation in, the second installation and the first installation of connection while and bolt when the second installation, it is special
Sign is, comprising the following steps: estimates the aperture of bolt hole, and is pressed according to the chamber of the chamber press casket of casing and determine bolt number；
According to the external axial force that bolt number and the first installation side and the second installation are subject to, determine that single bolt is subjected to outer
Portion's axial load, and the type selecting for the external axial load progress bolt being subjected to according to single bolt, so that it is determined that bolt
Diameter；Judge whether the diameter of bolt matches with the aperture for the bolt hole estimated, selection and diameter of bolt phase if mismatching
The aperture for the bolt hole matched repeats above-mentioned all steps as the bolt hole aperture estimated, until the diameter of the bolt determined and pre-
The aperture for the bolt hole estimated matches, and carries out following step if matching；According to the first installation while and when the second installation be subject to
External axial force, the aperture of bolt hole and bolt number, estimate the first installation while thickness and second installation while thickness；It is right
Bolt carries out force analysis, carries out locking assessment to bolt fastening structure according to the force analysis result of bolt, static strength is assessed
And Fatigue Assessment；Judge whether the locking assessment, static strength assessment and Fatigue Assessment of bolt fastening structure meet the requirements,
Above-mentioned all steps are repeated if any one is undesirable, until bolt fastening structure locking assessment, static strength assessment with
And Fatigue Assessment meets the requirements, if the locking assessment of bolt fastening structure, static strength assessment and Fatigue Assessment conform to
Ask, then the number of bolt, the type selecting of bolt, first installation while thickness and second installation while with a thickness of final design knot
Fruit.
Further, bolt number is determined according to the aperture of the chamber of casing pressure and bolt hole, specifically includes the following steps: in advance
The range for estimating the aperture of bolt hole is 5mm~11mm；If the chamber of the chamber press casket of casing is forced down in 0.69MPa, bolt is determined
Number n:If the chamber pressure of the chamber press casket of casing is higher than 0.69MPa and is lower than 1.38MPa, the number of bolt is determined
N:If the chamber pressure of the chamber press casket of casing is higher than 1.38MPa, the number n of bolt is determined:Wherein, d0For the aperture of bolt hole, D is the diameter of bolthole circle.
Further, the type selecting of bolt and judge whether the diameter of bolt matches with the aperture for the bolt hole estimated, have
Body comprises steps of determining that the external axial load Pa that single bolt is born:Wherein, n is bolt
Number, P ' are the external axial force of casing,For load amplification coefficient, a be bolt-center to install side outer rim away from
From b is distance of the bolt-center to casing inner wall；Bolt is carried out according to the external axial load Sa that single bolt is subjected to
Type selecting, determine the diameter d of bolt；The diameter d of the bolt and diameter d of bolt hole0Match, meet: 0.4mm≤(d0-d)≤
0.1mm。
Further, estimate the first installation while thickness and second installation while thickness, specifically includes the following steps: according to
The external axial force of casing, the aperture of bolt hole and bolt number, determine the first installation while and second installation while overall thickness；
According to first installation while and second installation while overall thickness, estimate the first installation while thickness and second installation while thickness.
Further, it is determined that first installation while and second installation while total thickness t:Its
In, P ' is the external axial force of casing, σ0.2For the first installation while and when the second installation in relatively low Materials Yield Limit, d
For the diameter of bolt, n is bolt number, and r is the radius of bolthole circle, and b is distance of the bolt-center to casing inner wall,
K value range is 0.7~1.
Further, estimate the first installation while thickness and second installation while thickness: if first installation side and second peace
The material of rim is identical, then thickness of first installation while with the second installation is equal；If first installs while with the second installation
Material is different, then the small installation of elasticity modulus while thickness be greater than elasticity modulus small installation while thickness.
Further, the force analysis of bolt, specifically includes the following steps: according to first installation while and second installation while
Overall thickness, first installation while thickness, second installation while thickness, first installation side work when temperature, second peace rimmer
Temperature when making and the first installation while and material property when the second installation, determine the Temperature Difference Load that bolt is born；According to spiral shell
The strength characteristics for external axial load, Temperature Difference Load and the bolt itself that bolt is born, pretightning force needed for determining bolt, thus
Determine the screw-down torque of bolt；According to external axial load, Temperature Difference Load and pretightning force that bolt is born, determine that bolt is born
Total axial force.
Further, the Temperature Difference Load Pt that bolt is born are as follows:
Wherein, AeIt is effective for bolt
Cross-sectional area, d are the diameter of bolt, lbFor bolt length, l1For the thickness on the first installation side, l2The thickness for installing side for second,
a1For the linear expansion coefficient on the first installation side, a2For the linear expansion coefficient on the second installation side, abFor the linear expansion coefficient of bolt, E1
For the elasticity modulus on the first installation side, E2For the elasticity modulus on the second installation side, EbFor the elasticity modulus of bolt, TbFor bolt work
Temperature when making, T1For the operating temperature on the first installation side, T2Operating temperature when working for the second installation side, T0For room temperature.
Further, locking assessment is carried out to bolt fastening structure, specifically includes the following steps: obtaining by FEM calculation
Obtain the remaining pretightning force that bolt is subject under operating temperature；Determine the clamping load and loosen load that bolt is subject to: what bolt was subject to
Clamping load is remaining pretightning force, and it is the sum of external axial load and Temperature Difference Load that bolt was subject to, which loosens load,；If bolt by
To clamping load be greater than that bolt is subject to loosen load, then the locking design of bolt fastening structure meets the requirements, otherwise, then spiral shell
The locking different design of bolt connecting structure closes the aperture for requiring then to estimate bolt hole again.
Further, to the carry out static strength assessment of bolt fastening structure, comprising the following steps:
Determine the stress σ that bolt is subject to:Wherein, P0_maxFor
The pretightning force maximum value that bolt is subject to, Pa are the external axial load that bolt is born, and Pt is the Temperature Difference Load that bolt is subject to, and d is
The diameter of bolt；The stress σ that bolt is subject to is compared with stress [σ] perhaps of bolt, if the stress σ that bolt is subject to is no more than bolt
Permitted stress [σ], then bolt fastening structure static strength assessment meet the requirements, otherwise, then the static strength of bolt fastening structure is commented
Estimate undesirable, estimates the aperture of bolt hole again.
Further, Fatigue Assessment is carried out to bolt, specifically includes the following steps:
Determine the minimum load P that bolt is subject tomin: Pmin=P0_min, wherein P0_minFor pretightning force minimum value；Determine bolt
The maximum load P being subject tomax: Pmax=P0_max+Pa, wherein P0_maxFor pretightning force maximum value, PaIt is born for bolt external axial
Load；Determine the static load P that bolt is subject tosta:Determine the dynamic load P that bolt is subject todyn:The satisfactory condition of the Fatigue Assessment of bolt fastening structure are as follows:Wherein, σbFor the ultimate strength of bolt, σ0.2For the yield limit of bolt.
The invention has the following advantages:
The design method of aero-engine casing bolt fastening structure of the invention estimates the aperture of bolt hole and root first
It is pressed according to the chamber of casing and determines bolt number, be subject to further according to bolt number and the first installation side and the second installation external axial
Power, so that it is determined that the single bolt external axial load being subjected to and the external axial load being subjected to according to single bolt
Carry out the type selecting of bolt, and then determine the diameter of bolt, when selection bolt diameter and the aperture of bolt hole estimated not
Timing then selects the aperture of the bolt hole to match with the diameter of bolt to readjust bolt number as the bolt hole aperture estimated
And the type selecting of bolt is carried out, until the diameter of the bolt redefined is matched with the aperture for the bolt hole estimated, then carry out next
Step design, i.e., according to first installation while and second installation while be subject to external axial force, bolt hole aperture and bolt number
Estimate the first installation while thickness and thickness when the second installation, so as to complete the Preliminary design of bolt fastening structure, then right
Bolt carries out force analysis, carries out locking assessment to bolt fastening structure according to the force analysis result of bolt, static strength is assessed
And Fatigue Assessment, it is wanted if any one of the locking assessment of bolt fastening structure, static strength assessment and Fatigue Assessment is not met
It asks, estimates diameter of bolt hole again and be designed, until the locking assessment of bolt fastening structure, static strength assessment and fatigue
Assessment meets the requirements, if the locking assessment of bolt fastening structure, static strength assessment and Fatigue Assessment, the number of bolt,
The type selecting of bolt, first installation while thickness and second installation while with a thickness of final design result, so that it is guaranteed that finally
The bolt fastening structure of design is not susceptible to loosen in use, long service life, guarantees aero-engine stable operation.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the process signal of the design method of the aero-engine casing bolt fastening structure of the preferred embodiment of the present invention
Figure.
Specific embodiment
The embodiment of the present invention is described in detail below in conjunction with attached drawing, but the present invention can be limited by following and
The multitude of different ways of covering is implemented.
Fig. 1 is the process signal of the design method of the aero-engine casing bolt fastening structure of the preferred embodiment of the present invention
Figure.
As shown in Figure 1, a kind of design method of aero-engine casing bolt fastening structure of the present embodiment, is bolted
Structure include the first installation in, the second installation and the first installation of connection while and bolt when the second installation, including following step
It is rapid: to estimate the aperture of bolt hole, and pressed according to the chamber of casing and determine bolt number；According to bolt number and first installation side and
The external axial force that second installation is subject to, determines the external axial load that single bolt is subjected to, and according to single bolt institute
The external axial load being subjected to carries out the type selecting of bolt, so that it is determined that the diameter of bolt；Judge the diameter of bolt and estimates
Whether the aperture of bolt hole matches, and selects the aperture of the bolt hole to match with the diameter of bolt as the spiral shell estimated if mismatching
Keyhole aperture repeats above-mentioned all steps, until the aperture of the diameter and the bolt hole estimated of the bolt determined matches, if
With then carrying out following step；According to first installation while and second installation while be subject to external axial force, bolt hole aperture and
Bolt number, estimate the first installation while thickness and second installation while thickness；Force analysis is carried out to bolt, according to bolt
Force analysis result carries out locking assessment, static strength assessment and Fatigue Assessment to bolt fastening structure；Judge bolted-on attachment
Whether locking assessment, static strength assessment and the Fatigue Assessment of structure meet the requirements, and repeat if any one is undesirable
All steps are stated, until the locking assessment of bolt fastening structure, static strength assessment and Fatigue Assessment meet the requirements, if bolt
The locking assessment of connection structure, static strength assessment and Fatigue Assessment meet the requirements, then the number of bolt, the type selecting of bolt,
First installation while thickness and second installation while with a thickness of final design result.Aero-engine casing spiral shell of the invention
The design method of bolt connecting structure estimates the aperture of bolt hole first and presses determining bolt number according to the chamber of casing, further according to
Bolt number and the first installation side and the second external axial force for being subject to of installation, so that it is determined that single bolt be subjected to outside
Portion's axial load and the type selecting that bolt is carried out according to the external axial load that single bolt is subjected to, and then determine the straight of bolt
Diameter then selects the spiral shell to match with the diameter of bolt when the aperture mismatch of the diameter of the bolt of selection and the bolt hole estimated
The aperture of keyhole readjusts bolt number as the bolt hole aperture estimated and carries out the type selecting of bolt, until redefine
The diameter of bolt is matched with the aperture for the bolt hole estimated, then carries out next step design, i.e., according to the first installation side and the second peace
The aperture of external axial force, bolt hole that rim is subject to and bolt number estimate the first installation while thickness and second installation while
Thickness, so as to complete the Preliminary design of bolt fastening structure, then force analysis is carried out to bolt, according to the stress of bolt point
It analyses result and locking assessment, static strength assessment and Fatigue Assessment is carried out to bolt fastening structure, if bolt fastening structure is locking
Any one of assessment, static strength assessment and Fatigue Assessment is undesirable, estimates diameter of bolt hole again and is designed, directly
It is assessed to the locking assessment of bolt fastening structure, static strength and Fatigue Assessment meets the requirements, if bolt fastening structure is anti-
Pine assessment, static strength assessment and Fatigue Assessment, then the number of bolt, the type selecting of bolt, the first installation side thickness and the
Two installation sides with a thickness of final design result, so that it is guaranteed that the bolt fastening structure of final design is not easy in use
It gets loose, long service life, guarantees aero-engine stable operation.
Bolt number is determined according to the aperture of the chamber of casing pressure and bolt hole, specifically includes the following steps: estimating bolt hole
Aperture range be 5mm~11mm；If the chamber of casing forces down the number n for determining bolt in 0.69MPa:If machine
The chamber pressure of casket is higher than 0.69MPa and is lower than 1.38MPa, determines the number n of bolt:If the chamber of casing
Pressure is higher than 1.38MPa, determines the number n of bolt:Wherein, d0 is the aperture of bolt hole, and D is bolt pore size distribution
Diameter of a circle.Optionally, the aperture of bolt hole is estimated from small to large in the range of 5mm~11mm.
The type selecting of bolt and judge whether the diameter of bolt matches with the diameter for the bolt hole estimated, specifically includes following
Step: the external axial load Pa that single bolt is subjected to is determined:Wherein, n is bolt number,
P ' is the external axial force of casing,For load amplification coefficient, a is distance of the bolt-center to installation side outer rim, b
For bolt-center to the distance of casing inner wall；The choosing of bolt is carried out according to the external axial load Sa that single bolt is subjected to
Type determines the diameter d of bolt；The diameter d of the bolt and diameter d of bolt hole0Match, meet: 0.4mm≤(d0-d)≤
0.1mm.Optionally, when the aperture of the external axial load Sa being subjected to according to the single bolt bolt hole redefined is greater than
The aperture 1mm for the bolt hole estimated before, by increasing the diameter of bolt hole and redefining bolt according to the chamber pressure of casing
Several or bolt hole aperture is constant and increases bolt number.As the external axial load Sa being subjected to according to single bolt
The aperture 0.4mm for the bolt hole that the aperture of the bolt hole redefined is estimated before being less than, by reducing the diameter of bolt hole simultaneously
The aperture for redefining bolt number or bolt hole according to the chamber pressure of casing is constant and reduces bolt number.
Estimate the first installation while thickness and thickness when the second installation, specifically includes the following steps: according to the outer of casing
Portion's axial force, the aperture of bolt hole and bolt number, determine the first installation while and second installation while overall thickness；According to first
Install while and second installation while overall thickness, estimate the first installation while thickness and second installation while thickness.
Determine the first installation while and second installation while total thickness t:Wherein, P ' is machine
The external axial force of casket, σ0.2For the first installation while and when the second installation in relatively low Materials Yield Limit, d is bolt
Diameter, n are bolt number, and r is the radius of bolthole circle, and b is distance of the bolt-center to casing inner wall, k value model
Enclose is 0.7~1.When the first installation side is identical with the second installation sapwood material, then σ0.2For the yield limit of the material；When first
Install side and second installation sapwood material it is not identical when, then select first installation while and second installation while in relatively low material yield
The limit.
Estimate the first installation while thickness and second installation while thickness: if first installation while and second installation while material
Identical, then thickness of first installation while with the second installation is equal；If material of first installation while from the second installation is different,
Elasticity modulus it is small installation while thickness be greater than elasticity modulus it is small installation while thickness.Optionally, the first installation side and second
The thickness on installation side is all larger than 2.5mm.When first installation while with second install while material it is different, then the small installation of elasticity modulus
While thickness be greater than elasticity modulus small installation while thickness, to reduce the Temperature Difference Load that bolt in the course of work is born.
The force analysis of bolt, specifically includes the following steps: according to the first installation while and overall thickness when the second installation, the
One installation while thickness, second installation while thickness, first installation while work when temperature, second installation while work when temperature
And first installation while and second installation while material property, determine bolt bear Temperature Difference Load；It is born according to bolt outer
The strength characteristics of portion's axial load, Temperature Difference Load and bolt itself, pretightning force needed for determining bolt, and then determine that bolt is twisted
Clamp force square；According to external axial load, Temperature Difference Load and pretightning force that bolt is born, total axial direction that bolt is born is determined
Power.According to the strength characteristics for external axial load, Temperature Difference Load and the bolt itself that bolt is born, determine pre- needed for bolt
The allowed band of clamp force: Pt+Pa≤P0≤0.7*σ0.2*As, Pa is the external axial load that bolt is subject to, and Pt is what bolt was subject to
Temperature Difference Load, σ0.2For the yield limit of bolt, AsSectional area is calculated for bolt；The permission model of the pretightning force according to needed for bolt
The range for choosing Bolt Tightening Force square is enclosed, so that it is determined that the pretightning force that bolt is born, the pretightning force of bolt and the pass of screw-down torque
System are as follows: P0=M/Kd, wherein M is screw-down torque, and K is to tighten coefficient, and d is the diameter of bolt.The Temperature Difference Load Pt that bolt is born
Are as follows:
Wherein, AeFor bolt effective cross section product, d is the diameter of bolt, lbFor bolt length, l1For the first installation side
Thickness, l2For the thickness on the second installation side, a1For the linear expansion coefficient on the first installation side, a2Line for the second installation side expands system
Number, abFor the linear expansion coefficient of bolt, E1For the elasticity modulus on the first installation side, E2For the elasticity modulus on the second installation side, EbFor
The elasticity modulus of bolt, TbTemperature when for working bolt, T1For the operating temperature on the first installation side, T2For the second peace rimmer
Operating temperature when making, T0For room temperature.Temperature is very high during the work time for aero-engine casing, due to first installation side,
Second installation side and bolt expanded by heating or cooling meat, the axial load for causing bolt to be subject to and radial load can occur
Variation, impacts the service life of bolted stability and bolt fastening structure, therefore to ensure bolted-on attachment
Structure is in whole work process bolt fastening structure energy stable connection and long service life, it is necessary to obtain accurate Temperature Difference Load.Spiral shell
It is Temperature Difference Load that bolt connecting structure is unable to restraining force caused by free wxpansion after temperature rising, due to bolt, the first installation
While and second installation while elasticity modulus and/or thermal expansion coefficient difference caused by.The calculating of the Temperature Difference Load of the present embodiment
The parameter of formula, input is few, and error after the result of the Temperature Difference Load of acquisition is verified by three-dimensional finite element analysis
Within 10%, so make it is subsequent locking assessment, static strength assessment are carried out to bolt fastening structure and when Fatigue Assessment, assessment
Result it is also more accurate.
Locking assessment is carried out to bolt fastening structure, specifically includes the following steps: obtaining work temperature by FEM calculation
Spend the remaining pretightning force that lower bolt is subject to；Determine the clamping load and loosen load that bolt is subject to: the compression that bolt is subject to carries
Lotus is remaining pretightning force, and it is the sum of external axial load and Temperature Difference Load that bolt was subject to, which loosens load,；What if bolt was subject to
Clamping load loosens load greater than what bolt was subject to, then the locking design of bolt fastening structure meets the requirements, and otherwise, then bolt connects
The locking different design of binding structure closes the aperture for requiring then to estimate bolt hole again.The present embodiment carries out bolt fastening structure
The precision of calculation method existing for the calculating ratio of remaining pretightning force improves 5% in locking assessment, it is ensured that finally designs
Bolt fastening structure stable connection during the work time, is not easy to loosen.
Carry out static strength assessment to bolt fastening structure, comprising the following steps: determine the stress σ that bolt is subject to:Wherein P0_maxFor the pretightning force maximum value that bolt is subject to, Pa is spiral shell
The external axial load that bolt is born, Pt are the Temperature Difference Load that bolt is subject to, and d is the diameter of bolt；The stress σ and spiral shell that bolt is subject to
Permitted stress [σ] of bolt compares, if the stress σ that is subject to of bolt is permitted stress [σ] no more than bolt, bolt fastening structure it is quiet strong
Degree assessment meets the requirements, and otherwise, then the static strength assessment of bolt fastening structure is undesirable, then estimates the hole of bolt hole again
Diameter.Optionally, if the static strength of bolt fastening structure assesses undesirable, the allowed band of the pretightning force according to needed for bolt
The screw-down torque for reselecting bolt, when the stress σ that bolt is subject to be greater than bolt permitted stress [σ], then turn tightening for bolt down
Torque, to reduce the pretightning force that bolt is subject to.
Fatigue Assessment is carried out to bolt, specifically includes the following steps:
Determine the minimum load P that bolt is subject tomin: Pmin=P0_min, wherein P0_minFor pretightning force minimum value；Determine bolt
The maximum load P being subject tomax: Pmax=P0_max+Pa, wherein P0_maxFor pretightning force maximum value, PaIt is born for bolt external axial
Load；Determine the static load P that bolt is subject tosta:
Determine the dynamic load P that bolt is subject todyn:The Fatigue Assessment of bolt fastening structure meets
It is required that condition are as follows:Wherein, σbFor the ultimate strength of bolt, σ0.2For the surrender pole of bolt
Limit.The screw-down torque for the bolt that the allowed band of the pretightning force according to needed for bolt selects is a value range, and pretightning force is minimum
Value is the pretightning force obtained according to minimum screw-down torque, and pretightning force maximum value is the pretightning force obtained according to maximum screw-down torque.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (11)
1. a kind of design method of aero-engine casing bolt fastening structure, bolt fastening structure includes the first installation side, the
Two installation while and connection first installation while and second installation side bolt, which comprises the following steps:
The aperture of bolt hole is estimated, and is pressed according to the chamber of casing and determines bolt number；
According to the external axial force that bolt number and the first installation side and the second installation are subject to, determine that single bolt is subjected to
External axial load, and the external axial load being subjected to according to single bolt carries out the type selecting of bolt, so that it is determined that spiral shell
The diameter of bolt, judges whether the diameter of bolt matches with the aperture for the bolt hole estimated, selection and the diameter of bolt if mismatching
The aperture of the bolt hole to match repeats above-mentioned all steps as the bolt hole aperture estimated, until the diameter of bolt with estimate
Bolt hole aperture matching, if matching if carry out following step；
According to first installation while and second installation while be subject to external axial force, bolt hole aperture and bolt number, estimate
First installation while thickness and second installation while thickness；
Force analysis is carried out to bolt, locking assessment, quiet strong is carried out to bolt fastening structure according to the force analysis result of bolt
Degree assessment and Fatigue Assessment；
Judge whether the locking assessment, static strength assessment and Fatigue Assessment of bolt fastening structure meet the requirements, if any one
It is undesirable, above-mentioned all steps are repeated, until the locking assessment of bolt fastening structure, static strength assessment and fatigue are commented
Estimate and meets the requirements, if the locking assessment of bolt fastening structure, static strength assessment and Fatigue Assessment meet the requirements, bolt
Number, the type selecting of bolt, first installation while thickness and second installation while with a thickness of final design result.
2. the design method of aero-engine casing bolt fastening structure according to claim 1, which is characterized in that according to
The chamber pressure of casing and the aperture of bolt hole determine bolt number, specifically includes the following steps:
The range for estimating the aperture of bolt hole is 5mm~11mm；
If the chamber of the chamber press casket of casing forces down the number n for determining bolt in 0.69MPa:
If the chamber pressure of the chamber press casket of casing is higher than 0.69MPa and is lower than 1.38 MPa, the number n of bolt is determined:
If the chamber pressure of the chamber press casket of casing is higher than 1.38MPa, the number n of bolt is determined:
Wherein, d0For the aperture of bolt hole, D is the diameter of bolthole circle.
3. the design method of aero-engine casing bolt fastening structure according to claim 1, which is characterized in that bolt
Type selecting and judge whether the diameter of bolt matches with the aperture for the bolt hole estimated, specifically includes the following steps:
Determine the external axial load Pa that single bolt is born:Wherein, n is bolt number, and P ' is machine
The external axial force of casket,For load amplification coefficient, a is distance of the bolt-center to installation side outer rim, and b is bolt
Distance of the center to casing inner wall；
The type selecting that bolt is carried out according to the external axial load Sa that single bolt is subjected to, determines the diameter d of bolt；
The diameter d of the bolt and diameter d of bolt hole0Match, meet: 0.4mm≤(d0-d)≤0.1mm。
4. the design method of aero-engine casing bolt fastening structure according to claim 1, which is characterized in that estimate
First installation while thickness and second installation while thickness, specifically includes the following steps:
According to the external axial force of casing, the aperture of bolt hole and bolt number, determine the first installation while and when the second installation
Overall thickness；
According to first installation while and second installation while overall thickness, estimate the first installation while thickness and second installation while thickness
Degree.
5. the design method of aero-engine casing bolt fastening structure according to claim 4, which is characterized in that
Determine the first installation while and second installation while total thickness t:Wherein, P ' is casing
External axial force, σ0.2For the first installation while and when the second installation in relatively low Materials Yield Limit, d is the diameter of bolt,
N is bolt number, and r is the radius of bolthole circle, and b is distance of the bolt-center to casing inner wall, and k value range is
0.7~1.
6. the design method of aero-engine casing bolt fastening structure according to claim 4, which is characterized in that
Estimate the first installation while thickness and second installation while thickness:
If material of first installation while with the second installation is identical, thickness of first installation while with the second installation is equal；
If material of first installation while from the second installation is different, the thickness on the small installation side of elasticity modulus is greater than elasticity modulus
The thickness on small installation side.
7. the design method of aero-engine casing bolt fastening structure according to claim 1, which is characterized in that bolt
Force analysis, specifically includes the following steps:
According to first installation while and second installation while overall thickness, first installation while thickness, second installation while thickness, first
Install while work when temperature, second installation while work when temperature and first installation while and second installation while material spy
Property, determine the Temperature Difference Load that bolt is born；
According to the strength characteristics for external axial load, Temperature Difference Load and the bolt itself that bolt is born, determine needed for bolt
Pretightning force；
According to external axial load, Temperature Difference Load and pretightning force that bolt is born, total axial force that bolt is born is determined.
8. the design method of aero-engine casing bolt fastening structure according to claim 7, which is characterized in that
The Temperature Difference Load Pt that bolt is born are as follows:
Wherein, AeFor bolt effective cross section product, d is the diameter of bolt, lbFor bolt length, l1The thickness for installing side for first,
l2For the thickness on the second installation side, a1For the linear expansion coefficient on the first installation side, a2For the linear expansion coefficient on the second installation side, ab
For the linear expansion coefficient of bolt, E1For the elasticity modulus on the first installation side, E2For the elasticity modulus on the second installation side, EbFor bolt
Elasticity modulus, TbTemperature when for working bolt, T1For the operating temperature on the first installation side, T2When working for the second installation side
Operating temperature, T0For room temperature.
9. the design method of aero-engine casing bolt fastening structure according to claim 7, which is characterized in that spiral shell
Bolt connecting structure carries out locking assessment, specifically includes the following steps:
The remaining pretightning force that bolt is subject under operating temperature is obtained by FEM calculation；
Determine clamping load that bolt is subject to and loosen load: the clamping load that bolt is subject to is remaining pretightning force, bolt by
Loosen load be the sum of external axial load and Temperature Difference Load；
If the clamping load that bolt is subject to loosens load greater than what bolt was subject to, the locking design of bolt fastening structure is conformed to
It asks, otherwise, then the locking different design of bolt fastening structure, which closes, requires, then estimates the aperture of bolt hole again.
10. the design method of aero-engine casing bolt fastening structure according to claim 7, which is characterized in that right
The carry out static strength assessment of bolt fastening structure, comprising the following steps:
Determine the stress σ that bolt is subject to:
Wherein, P0_maxFor the pretightning force maximum value that bolt is subject to, Pa is the external axial load that bolt is born, Pt for bolt by
Temperature Difference Load, d be bolt diameter；
The stress σ that bolt is subject to is compared with stress [σ] perhaps of bolt, if the stress σ that bolt is subject to is permitted to answer no more than bolt
Power [σ], then the static strength assessment of bolt fastening structure meets the requirements, and otherwise, then the static strength assessment of bolt fastening structure is not inconsistent
It closes and requires, then estimate the aperture of bolt hole again.
11. the design method of aero-engine casing bolt fastening structure according to claim 7, which is characterized in that right
Bolt carries out Fatigue Assessment, specifically includes the following steps:
Determine the minimum load P that bolt is subject tomin: Pmin=P0_min, wherein P0_minFor pretightning force minimum value；
Determine the maximum load P that bolt is subject tomax: Pmax=P0_max+Pa, wherein P0_maxFor pretightning force maximum value, PaIt is held for bolt
The external axial load received；
Determine the static load P that bolt is subject tosta:
Determine the dynamic load P that bolt is subject todyn:The Fatigue Assessment of bolt fastening structure meets the requirements
Condition are as follows:Wherein, σbFor the ultimate strength of bolt, σ0.2For the yield limit of bolt.
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| CN112528425A (en) * | 2020-11-09 | 2021-03-19 | 东风汽车集团有限公司 | Method for selecting and checking bolt of main bearing cap of automobile engine |
| CN112580156A (en) * | 2020-11-09 | 2021-03-30 | 东风汽车集团有限公司 | Gasoline engine cylinder head bolt type selection and checking method |
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| CN109583076A (en) * | 2018-11-26 | 2019-04-05 | 中国船舶重工集团公司第七0四研究所 | Polar ice grade ship is promoted mainly into pitch propeller device design method |
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| US7219044B1 (en) * | 2004-10-07 | 2007-05-15 | Surface Technology Holdings, Ltd. | Method and system for improving a part's resistance to stress induced failure |
| CN108897959A (en) * | 2018-07-04 | 2018-11-27 | 北京航空航天大学 | A kind of seaworthiness airworthiness compliance method of combustion box |
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| CN112528425A (en) * | 2020-11-09 | 2021-03-19 | 东风汽车集团有限公司 | Method for selecting and checking bolt of main bearing cap of automobile engine |
| CN112580156A (en) * | 2020-11-09 | 2021-03-30 | 东风汽车集团有限公司 | Gasoline engine cylinder head bolt type selection and checking method |
| CN112528425B (en) * | 2020-11-09 | 2022-04-15 | 东风汽车集团有限公司 | Method for selecting and checking bolt of main bearing cap of automobile engine |
| CN112580156B (en) * | 2020-11-09 | 2022-04-26 | 东风汽车集团有限公司 | Gasoline engine cylinder head bolt type selection and checking method |
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