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

An aero-engine, bending stiffness technology, applied in the direction of calculation, special data processing applications, instruments, etc., can solve problems such as time-consuming and expensive, unable to reflect the influence law of the interface stiffness of the disk-drum combination, etc.

Inactive Publication Date: 2014-04-16
TSINGHUA UNIV
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

The method of using experimental measurement and finite element analysis to determine the bending stiffness of the combined interface takes a lot of time and cost, and can only obtain the stiffness value u

Method used

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  • Method for computing bending rigidity of disc and drum combination interface of rotor of aero-engine
  • Method for computing bending rigidity of disc and drum combination interface of rotor of aero-engine
  • Method for computing bending rigidity of disc and drum combination interface of rotor of aero-engine

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Embodiment

[0123] by Figure 5 The structural form of the combined structure of the drum shown in the finite element model is taken as an example to further illustrate the effectiveness of the method of the present invention. In this structure, the wheel disc is connected to the drums on the left and right sides by 30 bolts uniformly distributed along the circumference, and the structural parameters are listed in Table 1.

[0124] Table 1 The main parameters of a certain type of disc-drum combination structure

[0125]

[0126] About the maximum deflection angle ψ of the drum connecting ring 1 The expression of and the bending stiffness K of the disc-drum combination interface m The expressions of the formulas listed in Step 1) Applied Bending Moment Equivalent, Step 2) Drum Force Analysis, Step 3) Derivation of Connecting Ring Deflection Deformation and Step 5) Calculation of Bending Stiffness of Drum Combination Interface can be directly obtained .

[0127] Here we focus on step...

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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

technical field [0001] The invention belongs to the technical field of structural mechanics for determining combined interface stiffness, in particular to a method for calculating the bending stiffness of an aero-engine rotor-drum-drum combined interface. Background technique [0002] In an aero-engine, the disc-drum rotor consists of a disc, a drum and a shaft, and the discs and drums at all levels are bolted or welded together. Such as figure 1 The disc-drum rotor in the fan section of a certain type of aero-engine shown is composed of a first-stage disc 1, a first-stage drum 2, a second-stage disc 3, a second-stage drum 5, and a third-stage disc 6. The first-stage drum 2, The secondary drum 5 is a thin-walled short cylindrical shell structure, which connects the primary wheel 1, the secondary wheel 3, and the third wheel 6 to transmit torque; the primary wheel 1 and the primary drum 2 They are combined together by welding, and the secondary disc 3, the secondary drum 5,...

Claims

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Application Information

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IPC IPC(8): G06F19/00G06F17/50
Inventor 秦朝烨褚福磊
Owner TSINGHUA UNIV
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