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Simulation Method of Compressor Aerodynamic Instability Signal

A simulation method and compressor technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as difficult to meet the comprehensive assessment of aerodynamic instability detection devices, narrow feature coverage, etc., to achieve easy implementation and simple method Effect

Active Publication Date: 2017-06-20
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Obtaining a large sample of aerodynamic instability signals using the above method requires a lot of manpower, financial resources and time, which is not only unnecessary, but also has a narrow feature coverage, making it difficult to meet the requirements of a comprehensive assessment of aerodynamic instability detection devices

Method used

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  • Simulation Method of Compressor Aerodynamic Instability Signal
  • Simulation Method of Compressor Aerodynamic Instability Signal
  • Simulation Method of Compressor Aerodynamic Instability Signal

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0054] The simulation method of the aerodynamic instability signal of the compressor in this embodiment includes the following steps:

[0055] Step 1: Build the basic set of signals {f i (t)}: The basic signal set consists of the following 4 signal subsets: (1) a small amount of aerodynamic instability signals obtained through experiments, CFD numerical simulation or analytical numerical simulation {s i (t)}; (2) decaying sinusoidal signal {g i (t)}; (3) half-sine pulse {h i (t)}; (4) noise {n i (t)}; where {s i In (t)}, there are compressor stall signals obtained from experiments such as figure 1 .

[0056] decaying sinusoidal signal {g i (t)} is expressed as:

[0057]

[0058] where ζ i is the damping ratio, the typical value range is -1~1, f i is the frequency, the typical value range is 0~300Hz, is the initial phase, and its value ranges from -π to π.

[0059] half sine pulse {h i (t)} is expressed as:

[0060]

[0061] where T i is the width of the ha...

Embodiment 2

[0090] The simulation method of the aerodynamic instability signal of the compressor in this embodiment includes the following steps:

[0091] Step 1: Build the basic set of signals {f i (t)}: The basic signal set consists of the following 4 signal subsets: (1) a small amount of aerodynamic instability signals obtained through experiments, CFD numerical simulation or analytical numerical simulation {s i (t)}; (2) decaying sinusoidal signal {g i (t)}; (3) half-sine pulse {h i (t)}; (4) noise {n i (t)}.

[0092] decaying sinusoidal signal {g i (t)} is expressed as:

[0093]

[0094] where ζ i is the damping ratio, the typical value range is -1~1, f i is the frequency, the typical value range is 0~300Hz, is the initial phase, and its value ranges from -π to π.

[0095] half sine pulse {h i (t)} is expressed as:

[0096]

[0097] where T i is the width of the half-sine pulse.

[0098] Step 2: Take f(t) as the aerodynamic instability signal to be generated, and ...

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Abstract

The invention provides a method for simulating aerodynamic instability signals of a compressor and belongs to the technical field of impeller mechanical surge prevention. The method for simulating the aerodynamic instability signals of the compressor comprises the following steps: 1) constructing a basic signal set {f(t)}, which consists of four subsets, including (a) a subset{s(t)} of a small amount of aerodynamic instability signals obtained through testing, CFD (Computational Fluid Dynamics) numerical simulation or analytical numerical simulation, (b) a subset {g(t)}of damped sine signals, (c) a subset{h(t)} of half-sine pulses, and (d) a subset{n(t)} of noises; 2) selecting basic signals; 3) conducting waveform transformation and superposition by adopting operations such as multiple transformation, scaling transformation, translation transformation and time domain superposition. The method can be used for generating a great number of aerodynamic instability signals covering characteristics such as different frequencies, amplitudes and stall inception modes at an extremely small production cost, and can be used for assessment and evaluation of aerodynamic instability detection / control devices of compressors.

Description

technical field [0001] The invention relates to anti-surge technology of impeller machinery, in particular to a method for simulating the aerodynamic instability signal of a compressor. Background technique [0002] Compressor aerodynamic instability mainly includes two phenomena: stall and surge. Aerodynamic instability not only reduces the performance of turbomachinery, but also brings strong vibration, which may cause structural damage and cause major accidents. In the assessment and evaluation of the aerodynamic instability detection / control device, the aerodynamic instability signal plays a very important role. It is always desirable to obtain as many samples as possible to assess the accuracy and reliability of detection / control devices. [0003] Generally speaking, there are three ways to obtain the aerodynamic instability signal of the compressor: (1) Obtained by compressor test measurement; (2) Obtained by numerical simulation based on computational fluid dynamics...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 李长征许思琦胡智琦
Owner NORTHWESTERN POLYTECHNICAL UNIV