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Gas turbine compressor blade frequency modulation design method

A gas turbine and design method technology, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve problems such as the first-order resonance of compressor blades, achieve stable and reliable operation, simplify the frequency modulation process, and simple design methods

Active Publication Date: 2019-10-01
中国船舶重工集团公司第七0三研究所
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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of first-order resonance of compressor blades in the normal operating speed range, and to provide a frequency modulation design method for gas turbine compressor blades

Method used

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  • Gas turbine compressor blade frequency modulation design method
  • Gas turbine compressor blade frequency modulation design method
  • Gas turbine compressor blade frequency modulation design method

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specific Embodiment approach

[0024] Specific implementation method: combined figure 1 To describe this embodiment,

[0025] A method for designing frequency modulation of a gas turbine compressor blade provided in this embodiment specifically includes the following steps:

[0026] Step 1, using the finite element calculation and analysis program Ansys Workbench to perform vibration calculations on the compressor blades (original blades) with resonance problems.

[0027] Step 2. In the blade vibration design criteria, the first-order bending resonance has the following requirements: within the steady-state operating speed range of the engine, there should be no exciting forces from the first to fourth orders of the engine and the known structural factors (previously The resonance caused by the fundamental frequency excitation force generated by the two-stage stator, the last-stage stator, the support plate, etc.); if this type of resonance is unavoidable, the frequency margin and rotational speed margin o...

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Abstract

The invention discloses a gas turbine compressor blade frequency modulation design method, and belongs to the technical field of compressor blade reliability research. The purpose of the method is tosolve the problem that the compressor blade resonates within the rotating speed range where the compressor blade works frequently. The method comprises the steps that firstly, carrying out vibration calculation on compressor blades with the resonance problem; determining risks existing in blade vibration according to a calculation result and a blade vibration design criterion, and further determining a target frequency value of the blade; according to the qualitative relation between the blade frequency change and the blade profile thickness adjustment, and giving the specific thickness valueof the blade preliminarily; performing vibration calculation on the blade, summarizing a quantitative relationship between the blade frequency change and blade profile thickness adjustment, and givinga scheme II according to the relationship and an initially determined target frequency value; and finally finding out a reasonable blade profile adjustment scheme through fine adjustment. The methodis suitable for the frequency modulation design of compressor blades of various gas turbines and aero-engines in ships and industries.

Description

technical field [0001] The invention relates to a frequency modulation design method for compressor blades, belonging to the technical field of compressor blade reliability research. Background technique [0002] The problem of blade vibration has been a common and serious problem in engines for a long time. Almost all engines have blade vibration problems in the process of development and use. Gas turbine compressor blades are subject to large centrifugal loads under working conditions. If the alternating vibration loads caused by abnormal working conditions are superimposed, it is very likely to cause premature fatigue fracture failure of the blades. In fact, most rotor blade accidents such as cracks, breakage, etc. are caused by various types of vibrations. [0003] When the excitation frequency is equal to the natural vibration frequency of the blade, the blade resonates. Once strong resonance occurs, it is easy to cause high-cycle fatigue of the blade, causing damage ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/23
Inventor 刘震孙勇王琦初曙光于景磊
Owner 中国船舶重工集团公司第七0三研究所
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