초록 ▼

A reduced order model called the Fundamental Mistuning Model (FMM) accurately predicts vibratory response of a bladed disk system. The FMM software may describe the normal modes and natural frequencies of a mistuned bladed disk using only its tuned system frequencies and the frequency mistuning of e

A reduced order model called the Fundamental Mistuning Model (FMM) accurately predicts vibratory response of a bladed disk system. The FMM software may describe the normal modes and natural frequencies of a mistuned bladed disk using only its tuned system frequencies and the frequency mistuning of each blade/disk sector (i.e., the sector frequencies). The FMM system identification methods--basic and advanced FMM ID methods--use the normal (i.e., mistuned) modes and natural frequencies of the mistuned bladed disk to determine sector frequencies as well as tuned system frequencies. FMM may predict how much the bladed disk will vibrate under the operating (rotating) conditions. Field calibration and testing of the blades may be performed using traveling wave analysis and FMM ID methods. The FMM model can be generated completely from experimental data. Because of FMM's simplicity, no special interfaces are required for FMM to be compatible with a finite element model. Because of the rules governing abstracts, this abstract should not be used to construe the claims.

대표청구항 ▼

What is claimed is: 1. A method, comprising: obtaining vibration information that provides frequency deviation of each blade of a bladed disk system from the tuned frequency value of said blade and nominal frequencies of said bladed disk system when tuned; and calculating the mistuned modes and nat

What is claimed is: 1. A method, comprising: obtaining vibration information that provides frequency deviation of each blade of a bladed disk system from the tuned frequency value of said blade and nominal frequencies of said bladed disk system when tuned; and calculating the mistuned modes and natural frequencies of said bladed disk system from only said blade frequency deviations and said nominal frequencies. 2. The method of claim 1, wherein each said blade includes a corresponding blade-disk sector in said disk system. 3. The method of claim 2, wherein said calculating includes solving: description="In-line Formulae" end="lead"(Ω∘2+2Ω∘ ΩΩ∘){right arrow over (β)}j=ωj2{right arrow over (β)}j description="In-line Formulae" end="tail" where Ω∘ is a diagonal matrix of the nominal frequencies of said bladed disk system when tuned; Ω is a matrix containing the discrete Fourier transforms of the blade frequency deviations; {right arrow over (β)}j is a vector containing weighting factors that describe the jth mistuned mode as a sum of tuned modes; and ωj is the natural frequency of the jth mistuned mode. 4. The method of claim 2, wherein physical displacements of the nth blade in the jth mistuned mode are proportional to: where xn represents physical displacements of the nth blade; βjm is a weighting factor for the jth mistuned mode with m=0, 1, . . . , N-1. 5. The method of claim 1, wherein said obtaining includes receiving a set of vibration measurements for an isolated family of modes of said disk system. 6. The method of claim 1, further comprising: further obtaining a set of values for modal damping and excitation force for said bladed disk system; further calculating a forced response due to mistuning for at least one blade in said bladed disk system using values for said modal damping and said excitation force. 7. The method of claim 6 wherein said excitation force is an engine order excitation. 8. The method of claim 6 additionally comprising dividing said calculated forced response of the bladed disk system by a forced response that said bladed disk system would exhibit if tuned, to obtain an amplitude magnification due to mistuning. 9. The method of claim 1, wherein said obtaining includes generating said nominal frequencies of said bladed disk system when tuned using a finite element analysis. 10. The method of claim 1, wherein said obtaining includes importing calculated values to form at least a part of said vibration information. 11. The method of claim 1, wherein said obtaining includes exciting a plurality of blades in said bladed disk system and measuring the vibration of each of said plurality of blades. 12. The method of claim 1, wherein said obtaining includes randomly generating at least a part of said vibration information. 13. The method of claim 12, wherein said randomly generating includes randomly generating at least said part of said vibration information using a Monte Carlo simulation. 14. The method of claim 1 wherein said calculating the mistuned modes and natural frequencies of said bladed disk system are calculated with the bladed disk system at rest, the method further comprising: extrapolating said mistuning to apply to a condition when said bladed disk is rotating; predicting from said extrapolation vibratory response of said bladed disk under operating conditions. 15. The method of claim 14 wherein said extrapolating includes using the formula: where ωψ∘ is the average tuned system frequency. 16. A computer-readable data storage medium containing a program code, which, when executed by a processor, causes said processor to perform the following: receive a vibration information that provides frequency deviation of each blade of a bladed disk system from the tuned frequency value of said blade and nominal frequencies of said bladed disk system when tuned; calculate the mistuned modes and natural frequencies of at least one blade in said bladed disk system from only said blade frequency deviations and said nominal frequencies; and save said calculated mistuned modes and natural frequencies. 17. The computer readable data storage medium of claim 16 additionally comprising program code, which, when executed by a processor, causes said processor to perform the following: calculate the mistuned modes and natural frequencies of at least one blade in said bladed disk system when said disk is not rotating; extrapolate said mistuning to apply to a condition when said bladed disk is rotating; predict from said extrapolation vibratory response of said bladed disk under operating conditions; and save said vibratory response of said bladed disk under operating conditions. 18. The storage medium of claim 17 wherein said extrapolating includes using the formula: where ωψ∘ is the average tuned system frequency. 19. A method, comprising: obtaining vibration information that provides frequency deviation of each blade of a bladed disk system from the tuned frequency value of said blade, nominal frequencies of said bladed disk system when tuned, a set of values for modal damping of said bladed disk system, and excitation force for said bladed disk system; and calculating a forced response for at least one blade in said bladed disk system using values for only said blade frequency deviations, said nominal frequencies, said modal damping and said excitation force. 20. The method of claim 19, wherein said excitation force is an engine order excitation. 21. The method of claim 19, wherein said calculated forced response of the bladed disk system is divided by a forced response that said bladed disk system would exhibit if tuned, to obtain an amplitude magnification due to mistuning.