CN103729547A - Method for computing bending rigidity of disc and drum combination interface of rotor of aero-engine - Google Patents

Abstract

The invention discloses a method for computing the bending rigidity of a disc and drum combination interface of a rotor of an aero-engine, and belongs to the field of structural mechanics for determining the rigidity of combination interfaces. The method includes particular steps of 1), performing equivalence on external bending moment; 2), analyzing stress on drums; 3), deriving an analytical expression for deflection angles of connecting rings of the drums under the effect of the bending moment by the aid of an elastic deformation theory; 4), determining values of contact parameters in the expression for the deflection angles psi1 on the basis of nonlinear finite element simulation analysis; 5), deriving a relative rotation angle of the disc and drum combination interface from the deflection angles of the connecting rings of the drums and further acquiring an analytical expression for the bending rigidity of the disc and drum combination interface. The method for computing the bending rigidity of the disc and drum combination interface of the rotor of the aero-engine has the advantages that the bending rigidity of the disc and drum combination interface is computed in an analytical manner, and accordingly influence of structural parameters of the disc and drum combination interface, pre-tightening force and the external bending moment on the disc and drum connection rigidity can be visually reflected; contact-related parameters in the analytical expressions are acquired by means of nonlinear finite element analysis, so that the computed bending rigidity of the disc and drum combination interface is close to actual conditions.

Description

A kind of aeroengine rotor dish drum combined interface bending stiffness computing method

Technical field

The invention belongs to the structural mechanics technical field of determining combined interface rigidity, particularly a kind of aeroengine rotor dish drum combined interface bending stiffness computing method.

Background technology

In aeromotor, dish drum type rotor is comprised of wheel disc, drum barrel and axle, is bolted or soldering group is combined between wheel discs at different levels and drum barrel.Certain type aerial engine fan section dish drum type rotor is comprised of one-level wheel disc 1, one-level drum barrel 2, secondary wheel disc 3, secondary drum barrel 5, three grades of wheel discs 6 as shown in Figure 1, one-level drum barrel 2, secondary drum barrel 5 are thin-walled short cylindrical shell structure, connect one-level wheel disc 1, secondary wheel disc 3, three grades of wheel discs 6, play the effect of transmitting torque; Between one-level wheel disc 1 and one-level drum barrel 2, by soldering group, be combined, between secondary wheel disc 3, secondary drum barrel 5, three grades of wheel discs 6, by coupling bolt 4, link together.Bolted existence can cause coiling bulging combined interface stiffness degradation, and combined interface rigidity value can change along with the change of load and operating mode, in dish drum type rotor, introduce local nonlinearity, change whirling motion characteristic and the vibratory response of rotor-support-foundation system, even bring out nonlinear vibration of rotor systems, affect aeromotor overall performance.Therefore, calculate aeroengine rotor dish drum combined interface rigidity, the relation between foundation dish drum combined interface rigidity and structural parameters, pretightning force and external applied load, tool is of great significance.

1988, document [willow of looking after one's family, Xia Songbo, open literary composition. the present situation of rotor dynamics research and prospect. vibration engineering journal, 1988,1 (2): 63-70.] just point out that the existence of syndeton makes the dynamic behavior of rotor-support-foundation system become complicated, should carry out further investigation.But, about the non-linear connection performance of rotor bolt syndeton and that rotor-support-foundation system dynamic characteristic is affected to the research of aspect is little.The calculating of existing rotor disk drum combined interface rigidity value, all measures by experiment or the matching of finite element analysis result curve obtains, and finds no the Analytic Calculation Method of aeroengine rotor dish drum combined interface bending stiffness.Adopt experiment measuring and finite element analysis to determine that the method for combined interface bending stiffness need to expend a large amount of time and expense, and can only obtain a certain group of rigidity value under special parameter, cannot reflect structure parameter and load-up condition on coiling the rule that affects of bulging combined interface rigidity.

Summary of the invention

For above-mentioned the deficiencies in the prior art, the present invention proposes a kind of computing method of aeroengine rotor dish drum combined interface bending stiffness, it is characterized in that, the method comprises the following steps:

1) by additional moment equivalence;

2) to drum barrel is stressed, analyze;

3) use elastic deformation theory, the deflection angle analytical expression of derivation drum barrel abutment ring under Moment;

4), based on Nonlinear FEM Simulation analysis, determine deflection angle ψ ¹the value of undetermined parameter in expression formula;

5) by drum barrel abutment ring deflection angle derivation dish drum combined interface relative rotation, further obtain coiling the analytical expression of bulging combined interface bending stiffness.

In described step 1), it by additional moment equivalence, is the axial force along the circumferential direction distributing by cosine rule; Take Moment plane as initial plane, by coupling bolt number in dish drum combined interface, drum barrel is along the circumferential direction divided into some basic sectors, each sector comprises a bolt hole, and the serial number of each basic sector is 1,2, i ..., be similar to and think that the equivalent axial force on basic sector is uniformly distributed circumferentially.

In described step 1), with the expression formula of the axial force of additional moment equivalence be:

F _e=F ₀cosφ；

Wherein, F _efor circumferentially press the axial force of cosine distribution along combined interface, φ is F _eapplication point and F ₀the folded central angle of application point,

for the maximum axial force in unit arc length, M is additional moment of flexure, R _sfor the middle radius surface of drum barrel post shell.

Described step 2) in, drum barrel is divided into abutment ring and cylindrical shell two parts, cylindrical shell is considered as to the constraint of abutment ring, by abutment ring cross section

with

the distortion of constraint abutment ring, wherein

for the axial force on post shell and abutment ring cross section,

for the tangential force on post shell and abutment ring cross section,

for the moment of flexure on post shell and abutment ring cross section.

Described step 2) concrete steps be:

21) force analysis is carried out in the i that to get with Moment plane included angle be φ basic sector, and drum barrel bottom abutment ring is got to chorista, and in unit arc length, external applied load to the resultant moment of abutment ring Inner edge is

$m_r^i=p_t^i{\mathrm{\&Delta;R}}_f+q_t^{i^{\mathrm{<figure-callout\; id="2"\; label="t\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">t</figure-callout>}}}\frac{f}{}\frac{}{2}{\text{+}{m}_t^i-p_b^i\frac{{\mathrm{\&Delta;R}}_b}{R_s\sin \mathrm{\&theta;}}+p_c^i{r}_c^i}_{\text{;}}$

Wherein,

for the axial force on post shell and abutment ring cross section,

for the tangential force on post shell and abutment ring cross section, for the moment of flexure on post shell and abutment ring cross section,

for the normal direction contact force in drum barrel abutment ring and wheel disc unit's arc length, for the axial constraint power of bolt to drum barrel abutment ring, Δ R _ffor semidiameter inside and outside drum barrel abutment ring, t _ffor drum barrel abutment ring thickness, Δ R _bfor bolt hole center and drum barrel abutment ring outer rim distance, θ be basic sector institute to central angle,

for drum barrel and wheel disc normal direction contact force point of resultant force are apart from the radial distance of drum barrel abutment ring inner edge;

22) under moment M effect, drum barrel abutment ring deflects in radial section, makes to produce in abutment ring radial section the stress distribution of a side tension, a side pressurized, and this stress distribution has formed the internal force moment of flexure on the radial section of basic sector internal force moment of flexure

with deflection angle ψ ⁱbetween there is following relation:

$M_a^i=\frac{{\mathrm{EI}}_r}{R_f}{\mathrm{\&psi;}}^i;$

Wherein, E is drum barrel elasticity modulus of materials, R _ffor abutment ring mean radius,

for the inertia square of abutment ring radial section.

In described step 3), the equalising torque relation according to external applied load on drum barrel abutment ring to abutment ring inner edge moment and radial section internal force moment of flexure, the deflection angle of derivation drum barrel abutment ring; According to drum barrel abutment ring radial section size, much smaller than its mean radius, adopt elastic deformation theory's distortion of calculating abutment ring.

Described step 3) concrete steps are:

31) by balance equation and the drum barrel abutment ring of basic sector, be out of shape the characteristic about plane of bending symmetry, obtain on the 1st basic sector

with

between relation:

$M_a^1=\frac{m_r^1{R}_s}{k_m};$

Wherein, k _m=1+I _p/ [2 (1+ ν) I _r],

for the utmost point inertia square of abutment ring radial section to deflection center;

32) by post columella, to equilibrium equation, obtained

$p_t^i=\frac{M\cos \mathrm{\&phi;}}{{\mathrm{\&pi;<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s^{}};$

33) ignore the internal shear power on the radial section of basic sector, by abutment ring axial force balance equation, obtained

$p_c^i=\frac{P_b^i}{R_s\sin \mathrm{\&theta;}}-p_t^i;$

34) by the cross section condition of continuity between post shell and abutment ring, obtained

$\begin{array}{c}{m}_t^i=\frac{\mathrm{v\&xi;}{R}_s{p}_t^i-{\mathrm{Et}}_s{\mathrm{\&psi;}}^i}{{2\mathrm{\&xi;}}^3{{\mathrm{<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s}^2};\\ q_t^i=\frac{2\mathrm{v\&xi;}{R}_s{p}_t^i-{\mathrm{Et}}_s{\mathrm{\&psi;}}^i}{{2\mathrm{\&xi;}}^2{{\mathrm{<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s}^2};\end{array}$

Wherein,

for attenuation coefficient, ν is the Poisson ratio of drum barrel material, t _sfor the thickness of drum barrel post shell;

35) by step 32)～34) in

with

expression formula substitution step 21) in expression formula in, and by external force resultant moment with internal force moment of flexure in expression formula, each parameter subscript i replaces with 1, obtains in the 1st basic sector

with

expression formula;

36) will

with

expression formula substitution step 31) relational expression in, obtain drum barrel abutment ring maximum deflection angle

${\mathrm{\&psi;}}^1=\frac{({\mathrm{\&Delta;R}}_f+r_f-r_c^1)\frac{M}{\mathrm{\&pi;}{R}_s^2}-({\mathrm{\&Delta;R}}_b-r_c^1)\frac{P_b^1}{R_s\sin \mathrm{\&theta;}}}{k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+{\mathrm{<figure-callout\; id="2"\; label="k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">k</figure-callout>}}_f};$

Wherein, k _f1=EI _r/ R _fr _s, k _f2=Et _s(ξ t _f+ 2) 4/ ξ ³r _s ², r _f=ν (ξ t _f+ 1)/2 ξ ²r _s.

Described step 4), by foundation dish drum unitized construction three dimensional non-linear finite element model, is carried out the nonlinear static simulation analysis under Different structural parameters and load-up condition, based on simulation result, determines deflection angle ψ ¹exposure parameter in expression formula

with

value.

Described step 4) deflection angle ψ ¹in expression formula,

with

value along with the change of moment M, change; Based on simulation result, will

with

with moment M, change and be divided into two stages, two stage flex point place, M ₀=π R _sp _b0/ 2sin θ;

Work as M<M ₀time,

remain unchanged,

value along with the increase approximately linear of moment of flexure reduces; Work as M=M ₀time, wherein

for the radius of drum barrel abutment ring upper bolt hole; Work as M>M ₀time,

along with moment of flexure is linear, increase,

value slightly decline, be decreased to

The axial constraint power of described bolt to drum barrel abutment ring expression formula be:

${\mathrm{<figure-callout\; id="1"\; label="P\; b"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">P</figure-callout>}}_b^{}={\mathrm{<figure-callout\; id="0"\; label="P\; b"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">P</figure-callout>}}_b+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b{\mathrm{\&psi;}}^1;$

Wherein, P _b0for the suffered pulling force of bolt under pretightning force independent role, k _θ=θ _c/ θ _nbe the ratio of a basic sector inner bolt confining region and confining region corresponding circle round angle, θ _cfor angle of circumference corresponding to bolt hole, θ _nbe that inner bolt hole, a basic sector is with angle of circumference corresponding to exterior domain, k _b=E _ba _b/ l _befor bolt tension rigidity, E _bfor the elastic modulus of bolt material, A _bfor body of bolt cross-sectional area, l _be=t _f+ t _c/ 2 is the effective length of bolt, t _cfor wheel disc thickness.

The concrete steps of described step 5) are:

51) under the effect of internal force moment M, the distortion that deflects of drum barrel abutment ring tension side; Compression-side abutment ring and wheel disc close contact, do not deflect, and wheel disc rigidity is much larger than drum barrel, is considered as rigid body, obtains coiling bulging combined interface relative rotation Φ and drum barrel abutment ring maximum deflection angle ψ ¹relation:

$\mathrm{\&Phi;}=\frac{{\mathrm{\&Delta;R}}_f}{{2R}_s}{\mathrm{\&psi;}}^1;$

52) by M=M ₀,

with

substitution deflection angle ψ ¹expression formula, obtain flex point place abutment ring maximum deflection angle

substitution step 51) formula in, obtain M=M ₀hour indicator drum combined interface relative rotation

${\mathrm{\&Phi;}}_0=\frac{({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b+r_f-r_h)({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b)}{{4\mathrm{<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s^{}\sin \mathrm{\&theta;}(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})}{\mathrm{<figure-callout\; id="0"\; label="P\; b"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">P</figure-callout>}}_b;$

M≤M ₀hour indicator drum combined interface bending stiffness

${\mathrm{<figure-callout\; id="1"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">K</figure-callout>}}_m=\frac{2\mathrm{\&pi;}{R}_s^3(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})}{({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b+r_f-r_h)({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b)};$

Work as M>M ₀time, will

with

expression formula substitution deflection angle ψ ¹expression formula in, further substitution step 51) in the expression formula of mid-game drum combined interface relative rotation Φ, obtain at subordinate phase dish drum combined interface relative rotation

${\mathrm{\&Phi;}}_2^r=\frac{{\mathrm{\&Delta;R}}_f\sin \mathrm{\&theta;}}{2[R_s\sin \mathrm{\&theta;}(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b({\mathrm{\&Delta;R}}_b-{\mathrm{<figure-callout\; id="0"\; label="r\; c"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">r</figure-callout>}}_c^0)]}[({\mathrm{\&Delta;R}}_f+r_f-{\mathrm{<figure-callout\; id="0"\; label="r\; c"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">r</figure-callout>}}_c^0)\frac{M}{\mathrm{\&pi;}{R}_s^2}-\frac{({\mathrm{\&Delta;R}}_b-r_c^1)}{R_s\sin \mathrm{\&theta;}}{P}_{b0}];$

M>M ₀hour indicator drum combined interface bending stiffness

${\mathrm{<figure-callout\; id="2"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">K</figure-callout>}}_m=\frac{2\mathrm{\&pi;}{R}_s^2[R_s\sin \mathrm{\&theta;}(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b({\mathrm{\&Delta;R}}_b-r_c^1)]}{{\mathrm{\&Delta;R}}_f\sin \mathrm{\&theta;}({\mathrm{\&Delta;R}}_f+r_f-r_c^1)};$

53) consider that internal force moment M and dish rouse the dull corresponding relation of the relative deflection angle Φ of combined interface, distinguish two linear stages of bending stiffness with the variation of deflection angle

$K_m=\left\{\begin{array}{cc}{\mathrm{<figure-callout\; id="1"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">K</figure-callout>}}_m,& \left|\mathrm{\&Phi;}\right|\&le;{\mathrm{\&Phi;}}_0\\ {\mathrm{<figure-callout\; id="2"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">K</figure-callout>}}_m& \left|\mathrm{\&Phi;}\right|>{\mathrm{\&Phi;}}_{0.}\end{array}\right.$

The beneficial effect of the invention:

(1) to the analytic relationship between placing drum combined interface bending stiffness and drum barrel structural parameters, pretightning force and additional moment of flexure, can reflect intuitively said structure parameter and the load-up condition rule that affects on bending stiffness;

(2) based on non linear finite element analysis, determine exposure parameter

with

with the variation relation of additional moment of flexure, make the bending stiffness analytical expression that obtains more accurate;

(3) with analytical expression form, to placing, rouse combined interface bending stiffness, be convenient to be incorporated into containing in dish drum combined interface rotor dynamics model, acquisition dish drum connects the rule that affects on rotor dynamics characteristic, makes rotor dynamics property calculation more approach actual conditions.

Accompanying drawing explanation

Fig. 1 is certain type aerial engine fan section dish drum type rotor structural representation;

Wherein, 1-one-level wheel disc; 2-one-level drum barrel; 3-secondary wheel disc; 4-coupling bolt; 5-secondary drum barrel; Tri-grades of wheel discs of 6-;

Fig. 2 is the process flow diagram of the inventive method;

Fig. 3 a is additional moment equivalence axial load distribution schematic diagram;

Fig. 3 b is that schematic diagram is divided in the basic sector of drum barrel;

Fig. 4 is drum barrel i basic sector force diagram under Moment;

Fig. 5 is dish drum unitized construction finite element model;

Fig. 6 is the perspective view of drum barrel abutment ring deflection distortion on Moment face under Moment;

Fig. 7 is under different pretightning force conditions

with moment M Changing Pattern;

Fig. 8 is under different pretightning force conditions

with moment M Changing Pattern;

Fig. 9 is under different drum barrel radius conditions with moment M Changing Pattern;

Figure 10 is under different drum barrel radius conditions with moment M Changing Pattern;

Figure 11 is analytic model and the contrast of finite element analysis result under different pretightning forces and drum barrel radius condition.

Embodiment

In order to make object of the present invention, mensuration process more clear, below in conjunction with drawings and Examples, the present invention is described in further detail.

Be illustrated in figure 2 the process flow diagram of the inventive method, the method concrete steps are as follows:

1) by additional moment equivalence

Adopt and along the circumferential direction press the axial force F that cosine rule distributes _e=F ₀the additional moment M of cos φ equivalence, as shown in Figure 3 a, wherein,

for the maximum axial force in unit arc length, φ is F _eapplication point and F ₀the folded central angle of application point, R _sfor the middle radius surface of drum barrel post shell.

With F ₀place plane is initial surface, i.e. Moment plane, by the bolt number connecting in dish drum combined interface, is along the circumferential direction divided into some basic sectors shown in Fig. 3 b by drum barrel, and each sector comprises a bolt hole.By each basic sector serial number, be 1,2 ..., i ..., be similar to and think that the equivalent axial force on basic sector is uniformly distributed circumferentially.

2) to drum barrel is stressed, analyze

Drum barrel is divided into abutment ring and cylindrical shell two parts, cylindrical shell is considered as to the constraint of abutment ring, by abutment ring cross section

with

the distortion of constraint abutment ring, wherein

for the axial force on post shell and abutment ring cross section,

for the tangential force on post shell and abutment ring cross section,

for the moment of flexure on post shell and abutment ring cross section.

Force analysis is carried out in the i that to get with Moment plane included angle be φ basic sector, and drum barrel bottom abutment ring is got to chorista, and chorista is as shown in Figure 4 stressed.In unit arc length, external applied load to the resultant moment of abutment ring Inner edge is

$m_r^i=p_t^i{\mathrm{\&Delta;R}}_f+q_t^{{\mathrm{<figure-callout\; id="2"\; label="i\; t\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">i</figure-callout>}}^t}\frac{f}{}\frac{}{2}{\text{+}{m}_t^i-p_b^i\frac{{\mathrm{\&Delta;R}}_b}{R_s\sin \mathrm{\&theta;}}+p_c^i{r}_c^i}_{\text{;}}$

Wherein,

for the axial force on post shell and abutment ring cross section,

for the tangential force on post shell and abutment ring cross section,

for the moment of flexure on post shell and abutment ring cross section, for the normal direction contact force in drum barrel abutment ring and wheel disc unit's arc length,

for the axial constraint power of bolt to drum barrel abutment ring, Δ R _ffor semidiameter inside and outside drum barrel abutment ring, t _ffor drum barrel abutment ring thickness, Δ R _bfor bolt hole center and drum barrel abutment ring outer rim distance, θ be basic sector institute to central angle,

for drum barrel and wheel disc normal direction contact force point of resultant force are apart from the radial distance of drum barrel abutment ring inner edge.

Under moment M effect, abutment ring deflects in radial section, makes to produce in abutment ring radial section the stress distribution of a side tension, a side pressurized.This stress distribution has formed the internal force moment of flexure on the radial section of basic sector internal force moment of flexure

with deflection angle ψ ⁱbetween there is following relation:

$M_a^i=\frac{{\mathrm{EI}}_r}{R_f}{\mathrm{\&psi;}}^i;$

Wherein, E is drum barrel elasticity modulus of materials, R _ffor abutment ring mean radius,

for the inertia square of abutment ring radial section.

3) use elastic deformation theory, the deflection angle analytical expression of derivation drum barrel abutment ring under Moment;

Equalising torque relation according to external applied load on drum barrel abutment ring to abutment ring inner edge moment and radial section internal force moment of flexure, the deflection angle of derivation drum barrel abutment ring.In view of drum barrel abutment ring radial section size is much smaller than its mean radius, adopt the theoretical distortion of calculating abutment ring of annulus.

By the balance equation of the basic sector of abutment ring and distortion thereof, about the characteristic of plane of bending symmetry, obtained on the 1st basic sector with

between relation:

$M_a^1=\frac{m_r^1{R}_s}{k_m};$

Wherein, k _m=1+I _p/ [2 (1+ ν) I _r], for the utmost point inertia square of abutment ring radial section to deflection center.

By post columella, to equilibrium equation, obtained

$p_t^i=\frac{M\cos \mathrm{\&phi;}}{{\mathrm{\&pi;<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s^{}};$

Ignore the internal shear power on the radial section of basic sector, by abutment ring axial force balance equation, obtained

$p_c^i=\frac{P_b^i}{R_s\sin \mathrm{\&theta;}}-p_t^i;$

By the cross section condition of continuity between post shell and abutment ring, obtained

$\begin{array}{c}{m}_t^i=\frac{\mathrm{v\&xi;}{R}_s{p}_t^i-{\mathrm{Et}}_s{\mathrm{\&psi;}}^i}{{2\mathrm{\&xi;}}^3{{\mathrm{<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s}^2};\\ q_t^i=\frac{2\mathrm{v\&xi;}{R}_s{p}_t^i-{\mathrm{Et}}_s{\mathrm{\&psi;}}^i}{{2\mathrm{\&xi;}}^2{{\mathrm{<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s}^2};\end{array}$

Wherein,

for attenuation coefficient, ν is the Poisson ratio of drum barrel material, t _sfor the thickness of drum barrel post shell.By above-mentioned

with

expression formula substitution expression formula in, and by external force resultant moment

with internal force moment of flexure

in expression formula, each parameter subscript i replaces with 1, obtains in the 1st basic sector

with

expression formula.Further, will

with

expression formula substitution both sides relation formula in, obtain drum barrel abutment ring maximum deflection angle

${\mathrm{\&psi;}}^1=\frac{({\mathrm{\&Delta;R}}_f+r_f-r_c^1)\frac{M}{\mathrm{\&pi;}{R}_s^2}-({\mathrm{\&Delta;R}}_b-r_c^1)\frac{P_b^1}{R_s\sin \mathrm{\&theta;}}}{k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+{\mathrm{<figure-callout\; id="2"\; label="k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">k</figure-callout>}}_f};$

Wherein, k _f1=EI _r/ R _fr _s, k _f2=Et _s(ξ t _f+ 2)/4 ξ ³r _s ², r _f=ν (ξ t _f+ 1)/2 ξ ²r _s.

4), based on Nonlinear FEM Simulation analysis, determine deflection angle ψ ¹the value of undetermined parameter in expression formula;

Deflection angle ψ ¹in expression formula,

with

value along with the change of moment M, change, by foundation dish drum unitized construction three dimensional non-linear finite element model, carry out the nonlinear static simulation analysis under Different structural parameters and load-up condition, based on simulation result, determine deflection angle ψ ¹exposure parameter in expression formula

with

value.

In ANSYS software, set up the dish drum unitized construction three dimensional non-linear finite element model shown in Fig. 5, by clamped left side drum barrel left end, the mode that adopts substep to load applies pretightning force and moment of flexure to finite element model.In first load step, adopt " falling temperature method " to apply bolt pretightening, in follow-up load step, at right side drum barrel right-hand member, apply the bending load that the cycle changes.Adjust structural parameters, pretightning force and the moment of flexure of finite element model, carry out the nonlinear static simulation analysis under different parameters.

Based on simulation result, conclude

with

with the Changing Pattern of moment M, will

with

with moment M, change and be divided into two stages, at two stage flex point place, M ₀=π R _sp _b0/ 2sin θ.Work as M<M ₀time,

remain unchanged,

value along with the increase approximately linear of moment of flexure reduces; Work as M=M ₀time,

wherein r _hfor the radius of drum barrel abutment ring upper bolt hole; Work as M>M ₀time,

along with moment of flexure is linear, increase,

value slightly decline, be decreased to

bolt constraining force

expression formula be:

${\mathrm{<figure-callout\; id="1"\; label="P\; b"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">P</figure-callout>}}_b^{}={\mathrm{<figure-callout\; id="0"\; label="P\; b"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">P</figure-callout>}}_b+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b{\mathrm{\&psi;}}^1;$

Wherein, P _b0for the suffered pulling force of bolt under pretightning force independent role, k _θ=θ _c/ θ _nbe the ratio of a basic sector inner bolt confining region and confining region corresponding circle round angle, θ _cfor angle of circumference corresponding to bolt hole, θ _nbe that inner bolt hole, a basic sector is with angle of circumference corresponding to exterior domain, k _b=E _ba _b/ l _befor bolt tension rigidity, E _bfor the elastic modulus of bolt material, A _bfor body of bolt cross-sectional area, l _be=t _f+ t _c/ 2 is the effective length of bolt, t _cfor wheel disc thickness.

5) by drum barrel abutment ring deflection angle derivation dish drum combined interface relative rotation, further obtain coiling the analytical expression of bulging combined interface bending stiffness;

Under moment M effect, the distortion that deflects of drum barrel abutment ring tension side; Compression-side abutment ring and wheel disc close contact, do not deflect, as shown in Figure 6.Wheel disc rigidity, much larger than drum barrel, is considered as rigid body, obtains coiling bulging combined interface relative rotation Φ and drum barrel abutment ring maximum deflection angle ψ ¹relation:

$\mathrm{\&Phi;}=\frac{{\mathrm{\&Delta;R}}_f}{{2R}_s}{\mathrm{\&psi;}}^1;$

By M=M ₀, with

substitution deflection angle ψ ¹expression formula, obtain flex point place abutment ring maximum deflection angle

substitution above formula, obtains M=M ₀hour indicator drum combined interface relative rotation

${\mathrm{\&Phi;}}_0=\frac{({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b+r_f-r_h)({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b)}{{4\mathrm{<figure-callout\; id="2"\; label="R\; s"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">R</figure-callout>}}_s^{}\sin \mathrm{\&theta;}(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})}{\mathrm{<figure-callout\; id="0"\; label="P\; b"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">P</figure-callout>}}_b;$

Further, obtain M≤M ₀hour indicator drum combined interface bending stiffness

${\mathrm{<figure-callout\; id="1"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">K</figure-callout>}}_m=\frac{2\mathrm{\&pi;}{R}_s^3(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})}{({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b+r_f-r_h)({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b)};$

Work as M>M ₀time, will

with

expression formula substitution deflection angle ψ ¹expression formula in, further, in the expression formula of substitution dish drum combined interface relative rotation Φ, obtain at subordinate phase dish drum combined interface relative rotation

${\mathrm{\&Phi;}}_2^r=\frac{{\mathrm{\&Delta;R}}_f\sin \mathrm{\&theta;}}{2[R_s\sin \mathrm{\&theta;}(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b({\mathrm{\&Delta;R}}_b-{\mathrm{<figure-callout\; id="0"\; label="r\; c"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">r</figure-callout>}}_c^0)]}[({\mathrm{\&Delta;R}}_f+r_f-{\mathrm{<figure-callout\; id="0"\; label="r\; c"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">r</figure-callout>}}_c^0)\frac{M}{\mathrm{\&pi;}{R}_s^2}-\frac{({\mathrm{\&Delta;R}}_b-r_c^1)}{R_s\sin \mathrm{\&theta;}}{P}_{b0}];$

Above formula obtains

do not comprise first stage moment of flexure and load the relative rotation causing, only represent that subordinate phase moment of flexure increases the dish drum combined interface relative rotation causing

increment.Therefore, the bending stiffness of subordinate phase is expressed as:

${\mathrm{<figure-callout\; id="2"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">K</figure-callout>}}_m=\frac{M-{\mathrm{<figure-callout\; id="0"\; label="M"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">M</figure-callout>}}_0}{{\mathrm{\&Phi;}}_2^r\left(M\right)-{\mathrm{\&Phi;}}_2^r\left(M_0\right);}$

? expression formula substitution K _m2expression formula in, obtain M>M ₀hour indicator drum combined interface bending stiffness

${\mathrm{<figure-callout\; id="2"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">K</figure-callout>}}_m=\frac{2\mathrm{\&pi;}{R}_s^2[R_s\sin \mathrm{\&theta;}(k_{\mathrm{<figure-callout\; id="1"\; label="m\; k\; f"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">m</figure-callout>}}{k}_f{1}_{}+k_{f2})+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b({\mathrm{\&Delta;R}}_b-r_c^1)]}{{\mathrm{\&Delta;R}}_f\sin \mathrm{\&theta;}({\mathrm{\&Delta;R}}_f+r_f-r_c^1)};$

Consider the dull corresponding relation of moment M and relative deflection angle Φ, with the variation of deflection angle, distinguish two linear stages of bending stiffness,

$K_m=\left\{\begin{array}{cc}{\mathrm{<figure-callout\; id="1"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">K</figure-callout>}}_m,& \left|\mathrm{\&Phi;}\right|\&le;{\mathrm{\&Phi;}}_0\\ {\mathrm{<figure-callout\; id="2"\; label="K\; m"\; filenames="HDA0000436355800000021.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">K</figure-callout>}}_m& \left|\mathrm{\&Phi;}\right|>{\mathrm{\&Phi;}}_{0.}\end{array}\right.$

Embodiment:

To coil the version of rousing unitized construction shown in Fig. 5 finite element model as example, further set forth the validity of the inventive method.In this structure, wheel disc is with left and right sides drum barrel by being connected along 30 circumferentially uniform bolts, and structural parameters are listed in table 1.

Certain type dish drum unitized construction major parameter of table 1

About drum barrel abutment ring maximum deflection angle ψ ¹expression formula and dish drum combined interface bending stiffness K _mexpression formula respectively with reference to the additional moment equivalence of step 1), step 2) drum barrel force analysis, step 3) abutment ring deflection distortion are derived and step 5) dish drum combined interface bending stiffness is listed in calculating formula can directly obtain.

Here introduce step 4) deflection angle ψ ¹in expression formula, undetermined parameter is determined.With reference to the modeling method foundation dish drum unitized construction three dimensional non-linear finite element model in step 4), wherein, wheel disc, drum barrel and bolt all adopt solid element SOLID95 modeling, the surface of contact of each inter-module is characterized by osculating element CONTA173 and object element TARGE170, and model comprises 408301 nodes and 112321 unit altogether.

Based on the finite element model of setting up, calculate the Changing Pattern with moment of flexure under different drum barrel radiuses and pretightning force effect, as shown in Fig. 7-10.From scheming, can find out,

with

with moment M, change and be divided into two stages, at two stage flex point place, M ₀=π R _sp _b0/ 2sin θ.Work as M<M ₀time,

remain unchanged,

value along with the increase approximately linear of moment of flexure reduces; Work as M=M ₀time,

wherein r _hfor the radius of drum barrel abutment ring upper bolt hole; Work as M>M ₀time,

along with moment of flexure is linear, increase,

value slightly decline, be decreased to 2mm.Bolt constraining force

expression formula be:

${\mathrm{<figure-callout\; id="1"\; label="P\; b"\; filenames="HDA0000436355800000021.png,HDA0000436355800000032.png"\; state="\{\{state\}\}">P</figure-callout>}}_b^{}={\mathrm{<figure-callout\; id="0"\; label="P\; b"\; filenames="HDA0000436355800000022.png,HDA0000436355800000033.png"\; state="\{\{state\}\}">P</figure-callout>}}_b+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b{\mathrm{\&psi;}}^1;$

In formula, P _b0for the suffered pulling force of bolt under pretightning force independent role, k _θ=θ _c/ θ _nbe the ratio of a basic sector inner bolt confining region and confining region corresponding circle round angle, θ _cfor angle of circumference corresponding to bolt hole, θ _nbe that inner bolt hole, a basic sector is with angle of circumference corresponding to exterior domain, k _b=E _ba _b/ l _befor bolt tension rigidity, E _bfor the elastic modulus of bolt material, A _bfor body of bolt cross-sectional area, l _be=t _f+ t _c/ 2 is the effective length of bolt, t _cfor wheel disc thickness.

By in the rigidity expression formula in parameter value substitution step 5) definite finite element analysis, obtain coiling bulging unitized construction bend stiffness.Under different loads and structural parameters, the contrast of the moment of flexure that computing method of the present invention obtain and dish drum combined interface relative rotation relation curve and finite element analysis result as shown in figure 11.As can be seen from the figure, two kinds of result of calculations are coincide better, thereby have verified the correctness of computing method of the present invention.

The above; only for preferably embodiment of the present invention, but protection scope of the present invention is not limited to this, is anyly familiar with in technical scope that those skilled in the art disclose in the present invention; the variation that can expect easily or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.

Claims (11)

1. aeroengine rotor dish drum combined interface bending stiffness computing method, is characterized in that, the method comprises the following steps:

1) by additional moment equivalence;

2) to drum barrel is stressed, analyze;

3) use elastic deformation theory, the deflection angle analytical expression of derivation drum barrel abutment ring under Moment;

4), based on Nonlinear FEM Simulation analysis, determine deflection angle ψ ¹the value of undetermined parameter in expression formula;

5) by drum barrel abutment ring deflection angle derivation dish drum combined interface relative rotation, further obtain coiling the analytical expression of bulging combined interface bending stiffness.

2. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as claimed in claim 1, is characterized in that, in described step 1), are the axial force along the circumferential direction distributing by cosine rule by additional moment equivalence; Take Moment plane as initial plane, by coupling bolt number in dish drum combined interface, drum barrel is along the circumferential direction divided into some basic sectors, each sector comprises a bolt hole, and the serial number of each basic sector is 1,2, i ..., be similar to and think that the equivalent axial force on basic sector is uniformly distributed circumferentially.

3. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method according to claim 1 and 2, is characterized in that, in described step 1), with the expression formula of the axial force of additional moment equivalence are

F _e=F ₀cosφ；

Wherein, F _efor circumferentially press the axial force of cosine distribution along combined interface, φ is F _eapplication point and F ₀the folded central angle of application point,

for the maximum axial force in unit arc length, M is additional moment of flexure, R _sfor the middle radius surface of drum barrel post shell.

4. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method according to claim 1, it is characterized in that described step 2) in, drum barrel is divided into abutment ring and cylindrical shell two parts, cylindrical shell is considered as to the constraint of abutment ring, by abutment ring cross section

with

the distortion of constraint abutment ring, wherein for the axial force on post shell and abutment ring cross section, for the tangential force on post shell and abutment ring cross section, for the moment of flexure on post shell and abutment ring cross section.

5. according to a kind of aeroengine rotor dish drum combined interface bending stiffness computing method described in claim 1 or 4, it is characterized in that described step 2) concrete steps be:

21) force analysis is carried out in the i that to get with Moment plane included angle be φ basic sector, and drum barrel bottom abutment ring is got to chorista, and in unit arc length, external applied load to the resultant moment of abutment ring Inner edge is

$m_r^i=p_t^i{\mathrm{\&Delta;R}}_f+q_t^{i^t}\frac{f}{2}{\text{+}{m}_t^i-p_b^i\frac{{\mathrm{\&Delta;R}}_b}{R_s\sin \mathrm{\&theta;}}+p_c^i{r}_c^i}_{\text{;}}$

Wherein,

for the axial force on post shell and abutment ring cross section,

for the tangential force on post shell and abutment ring cross section, for the moment of flexure on post shell and abutment ring cross section,

for the normal direction contact force in drum barrel abutment ring and wheel disc unit's arc length, for the axial constraint power of bolt to drum barrel abutment ring, Δ R _ffor semidiameter inside and outside drum barrel abutment ring, t _ffor drum barrel abutment ring thickness, Δ R _bfor bolt hole center and drum barrel abutment ring outer rim distance, θ be basic sector institute to central angle,

for drum barrel and wheel disc normal direction contact force point of resultant force are apart from the radial distance of drum barrel abutment ring inner edge;

22) under moment M effect, drum barrel abutment ring deflects in radial section, makes to produce in abutment ring radial section the stress distribution of a side tension, a side pressurized, and this stress distribution has formed the internal force moment of flexure on the radial section of basic sector

internal force moment of flexure with deflection angle ψ ⁱbetween there is following relation:

$M_a^i=\frac{{\mathrm{EI}}_r}{R_f}{\mathrm{\&psi;}}^i;$

Wherein, E is drum barrel elasticity modulus of materials, R _ffor abutment ring mean radius,

for the inertia square of abutment ring radial section.

6. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as claimed in claim 1, it is characterized in that, in described step 3), equalising torque relation according to external applied load on drum barrel abutment ring to abutment ring inner edge moment and radial section internal force moment of flexure, the deflection angle of derivation drum barrel abutment ring; According to drum barrel abutment ring radial section size, much smaller than its mean radius, adopt elastic deformation theory's distortion of calculating abutment ring.

7. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as described in claim 1 or 6, is characterized in that, described step 3) concrete steps are:

31) by balance equation and the drum barrel abutment ring of basic sector, be out of shape the characteristic about plane of bending symmetry, obtain on the 1st basic sector

with

between relation:

$M_a^1=\frac{m_r^1{R}_s}{k_m};$

Wherein, k _m=1+I _p/ [2 (1+ ν) I _r],

for the utmost point inertia square of abutment ring radial section to deflection center;

32) by post columella, to equilibrium equation, obtained

$p_t^i=\frac{M\cos \mathrm{\&phi;}}{{\mathrm{\&pi;R}}_s^2};$

33) ignore the internal shear power on the radial section of basic sector, by abutment ring axial force balance equation, obtained

$p_c^i=\frac{P_b^i}{R_s\sin \mathrm{\&theta;}}-p_t^i;$

34) by the cross section condition of continuity between post shell and abutment ring, obtained

$\begin{array}{c}{m}_t^i=\frac{\mathrm{v\&xi;}{R}_s{p}_t^i-{\mathrm{Et}}_s{\mathrm{\&psi;}}^i}{{2\mathrm{\&xi;}}^3{R_s}^2};\\ q_t^i=\frac{2\mathrm{v\&xi;}{R}_s{p}_t^i-{\mathrm{Et}}_s{\mathrm{\&psi;}}^i}{{2\mathrm{\&xi;}}^2{R_s}^2};\end{array}$

Wherein,

for attenuation coefficient, ν is the Poisson ratio of drum barrel material, t _sfor the thickness of drum barrel post shell;

35) by step 32)～34) in

with

expression formula substitution step 21) in

expression formula in, and by external force resultant moment

with internal force moment of flexure

in expression formula, each parameter subscript i replaces with 1, obtains in the 1st basic sector

with

expression formula;

36) will

with

expression formula substitution step 31) relational expression in, obtain drum barrel abutment ring maximum deflection angle

${\mathrm{\&psi;}}^1=\frac{({\mathrm{\&Delta;R}}_f+r_f-r_c^1)\frac{M}{\mathrm{\&pi;}{R}_s^2}-({\mathrm{\&Delta;R}}_b-r_c^1)\frac{P_b^1}{R_s\sin \mathrm{\&theta;}}}{k_m{k}_{f1}+k_{f2}};$

Wherein, k _f1=EI _r/ R _fr _s, k _f2=Et _s(ξ t _f+ 2)/4 ξ ³r _s ², r _f=ν (ξ t _f+ 1)/2 ξ ²r _s.

8. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as claimed in claim 1, it is characterized in that, described step 4) is by foundation dish drum unitized construction three dimensional non-linear finite element model, carry out the nonlinear static simulation analysis under Different structural parameters and load-up condition, based on simulation result, determine deflection angle ψ ¹exposure parameter in expression formula

with value.

9. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as described in claim 1 or 8, is characterized in that described step 4) deflection angle ψ ¹in expression formula,

with

value along with the change of moment M, change; Based on simulation result, will

with

with moment M, change and be divided into two stages, two stage flex point place, M ₀=π R _sp _b0/ 2sin θ;

Work as M<M ₀time,

remain unchanged,

value along with the increase approximately linear of moment of flexure reduces; Work as M=M ₀time,

wherein r _hfor the radius of drum barrel abutment ring upper bolt hole; Work as M>M ₀time,

along with moment of flexure is linear, increase,

value slightly decline, be decreased to

10. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as claimed in claim 9, is characterized in that the axial constraint power of described bolt to drum barrel abutment ring

expression formula be:

$P_b^1=P_{b0}+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b{\mathrm{\&psi;}}^1;$

Wherein, P _b0for the suffered pulling force of bolt under pretightning force independent role, k _θ=θ _c/ θ _nbe the ratio of a basic sector inner bolt confining region and confining region corresponding circle round angle, θ _cfor angle of circumference corresponding to bolt hole, θ _nbe that inner bolt hole, a basic sector is with angle of circumference corresponding to exterior domain, k _b=E _ba _b/ l _befor bolt tension rigidity, E _bfor the elastic modulus of bolt material, A _bfor body of bolt cross-sectional area, l _be=t _f+ t _c/ 2 is the effective length of bolt, t _cfor wheel disc thickness.

11. a kind of aeroengine rotor dish drum combined interface bending stiffness computing method as claimed in claim 1, is characterized in that, the concrete steps of described step 5) are:

51) under the effect of internal force moment M, the distortion that deflects of drum barrel abutment ring tension side; Compression-side abutment ring and wheel disc close contact, do not deflect, and wheel disc rigidity is much larger than drum barrel, is considered as rigid body, obtains coiling bulging combined interface relative rotation Φ and drum barrel abutment ring maximum deflection angle ψ ¹relation:

$\mathrm{\&Phi;}=\frac{{\mathrm{\&Delta;R}}_f}{{2R}_s}{\mathrm{\&psi;}}^1;$

52) by M=M ₀,

with

substitution deflection angle ψ ¹expression formula, obtain flex point place abutment ring maximum deflection angle

substitution step 51) formula in, obtain M=M ₀hour indicator drum combined interface relative rotation

${\mathrm{\&Phi;}}_0=\frac{({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b+r_f-r_h)({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b)}{{4R}_s^2\sin \mathrm{\&theta;}(k_m{k}_{f1}+k_{f2})}{P}_{b0};$

M≤M ₀hour indicator drum combined interface bending stiffness

$K_{m1}=\frac{2\mathrm{\&pi;}{R}_s^3(k_m{k}_{f1}+k_{f2})}{({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b+r_f-r_h)({\mathrm{\&Delta;R}}_f-{\mathrm{\&Delta;R}}_b)};$

Work as M>M ₀time, will

with

expression formula substitution deflection angle ψ ¹expression formula in, further substitution step 51) in the expression formula of mid-game drum combined interface relative rotation Φ, obtain at subordinate phase dish drum combined interface relative rotation

${\mathrm{\&Phi;}}_2^r=\frac{{\mathrm{\&Delta;R}}_f\sin \mathrm{\&theta;}}{2[R_s\sin \mathrm{\&theta;}(k_m{k}_{f1}+k_{f2})+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b({\mathrm{\&Delta;R}}_b-r_{c0}^1)]}[({\mathrm{\&Delta;R}}_f+r_f-r_{c0}^1)\frac{M}{\mathrm{\&pi;}{R}_s^2}-\frac{({\mathrm{\&Delta;R}}_b-r_c^1)}{R_s\sin \mathrm{\&theta;}}{P}_{b0}];$

M>M ₀hour indicator drum combined interface bending stiffness

$K_{m2}=\frac{2\mathrm{\&pi;}{R}_s^2[R_s\sin \mathrm{\&theta;}(k_m{k}_{f1}+k_{f2})+k_b{k}_{\mathrm{\&theta;}}{\mathrm{\&Delta;R}}_b({\mathrm{\&Delta;R}}_b-r_c^1)]}{{\mathrm{\&Delta;R}}_f\sin \mathrm{\&theta;}({\mathrm{\&Delta;R}}_f+r_f-r_c^1)};$

53) consider that internal force moment M and dish rouse the dull corresponding relation of the relative deflection angle Φ of combined interface, distinguish two linear stages of bending stiffness with the variation of deflection angle

$K_m=\left\{\begin{array}{cc}{K}_{m1},& \left|\mathrm{\&Phi;}\right|\&le;{\mathrm{\&Phi;}}_0\\ K_{m2}& \left|\mathrm{\&Phi;}\right|>{\mathrm{\&Phi;}}_{0.}\end{array}\right.$

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