CN113987812A - Method for quantifying vortex scale of dynamic distortion flow field at inlet of aircraft engine - Google Patents

Method for quantifying vortex scale of dynamic distortion flow field at inlet of aircraft engine Download PDF

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CN113987812A
CN113987812A CN202111275253.6A CN202111275253A CN113987812A CN 113987812 A CN113987812 A CN 113987812A CN 202111275253 A CN202111275253 A CN 202111275253A CN 113987812 A CN113987812 A CN 113987812A
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inlet
aircraft engine
flow field
dynamic
vortex
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王勤
齐鹏
付岩
刘世官
邢志国
孙海龙
张天浩
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AECC Shenyang Engine Research Institute
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Abstract

A method for quantifying the vortex scale of a dynamic distortion flow field at an inlet of an aircraft engine comprises the following steps: based on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, calculating a distribution curve of vortex scales in the dynamic distorted flow field at the inlet of the aircraft engine along the circumferential direction by an autocorrelation coefficient curve algorithm, and calculating a distribution curve of the vortex scales in the dynamic distorted flow field at the inlet of the aircraft engine by an autocorrelation coefficient function
Figure DDA0003329859080000011
Quantifying the vortex scale of the dynamic distortion flow field at the inlet of the aircraft engine at the time tau of the first intersection point of the vortex scale and the X axis; wherein: rx(τ) is the correlation value of the autocorrelation function at the time instances of time variables τ and τ + d τ; rx(0) The autocorrelation function value at the time when d τ is 0; rhox(τ) is the autocorrelation coefficient function at times τ and τ + d τThe value is obtained. The result of quantifying the vortex scale of the dynamic distortion flow field at the inlet of the aircraft engine by the method has extremely high coincidence with the result completed by the assistance of foreign technical experts, and can be used for measuring the turbulent flow field at the inlet of the aircraft engine by combining the total pressure pulsation intensity and accurately evaluating the dynamic distortion flow field generated at the inlet of the aircraft engine.

Description

Method for quantifying vortex scale of dynamic distortion flow field at inlet of aircraft engine
Technical Field
The application belongs to the technical field of assessment of dynamic distorted flow fields of aircraft engine inlets, and particularly relates to a vortex scale quantification method for the dynamic distorted flow fields of the aircraft engine inlets.
Background
The dynamic distortion flow field generated at the inlet of the aero-engine is a turbulent flow field, and the turbulent flow field is accurately evaluated, so that the method has important significance for the design and improvement of the aero-engine.
The turbulent flow field at the inlet of the aero-engine consists of countless vortexes with different sizes, the total pressure pulsation strength and the vortex scale are two important indexes for measuring the turbulent flow field, currently, the turbulent flow field is evaluated only by the total pressure pulsation in China, the characteristics of the turbulent flow field cannot be completely reflected, and the accurate evaluation of a dynamic distortion flow field generated at the inlet of the aero-engine cannot be realized.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a quantification method of the vortical dimension of an aircraft engine inlet dynamic distortion flow field, so as to overcome or alleviate technical defects of at least one aspect of the known existence.
The technical scheme of the application is as follows:
a method for quantifying the vortex scale of a dynamic distortion flow field at an inlet of an aircraft engine comprises the following steps:
based on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, calculating a distribution curve of vortex scales in the dynamic distorted flow field at the inlet of the aircraft engine along the circumferential direction by an autocorrelation coefficient curve algorithm, and calculating a distribution curve of the vortex scales in the dynamic distorted flow field at the inlet of the aircraft engine by an autocorrelation coefficient function
Figure BDA0003329859060000021
Quantifying the vortex scale of the dynamic distortion flow field at the inlet of the aircraft engine at the time tau of the first intersection point of the vortex scale and the X axis;
wherein:
Rx(τ) is the correlation value of the autocorrelation function at the time instances of time variables τ and τ + d τ;
Rx(0) the autocorrelation function value at the time when d τ is 0;
ρx(τ) is the autocorrelation coefficient function value at times τ and τ + d τ.
According to at least one embodiment of the application, in the above method for quantifying the swirl scale of the dynamic distortion flow field at the inlet of the aircraft engine, the method further includes:
the total pressure pulsation data volume of the dynamic distortion flow field at the inlet of the aircraft engine is selected, each autocorrelation calculation is not less than 1K, and the smoothing times are not less than 20.
According to at least one embodiment of the application, in the above method for quantizing the swirl scale of the dynamic distorted flow field at the inlet of the aircraft engine, digital filtering selection is performed on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, wherein:
the digital filter function is a Butterworth fourth-order band-pass;
the lower limit of the filtering is 5 Hz;
the upper limit of the filter is
Figure BDA0003329859060000022
Wherein the content of the first and second substances,
Vmaxthe average speed of the maximum state of the inlet of the aircraft engine is;
d is the diameter of the inlet of the aircraft engine.
The application has at least the following beneficial technical effects:
the method is used for quantifying the vortex scale of the dynamic distortion flow field at the inlet of the aero-engine, the quantified result has extremely high coincidence with the result completed by the assistance of foreign technical experts, the method can be used for measuring the turbulent flow field at the inlet of the aero-engine by combining the total pressure pulsation intensity, accurately evaluating the dynamic distortion flow field generated at the inlet of the aero-engine and providing guidance for the design and improvement of the domestic engine.
Drawings
FIG. 1 is a schematic diagram comparing distribution curves of vortex scales along the circumferential direction in a dynamic distorted flow field at an inlet of an aircraft engine calculated by an autocorrelation coefficient curve algorithm, a modified power spectrum algorithm and an autocorrelation function integral algorithm based on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine provided by the embodiment of the application;
fig. 2 is a schematic diagram illustrating a comparison between a result of quantifying the vortex scale of the dynamic distortion flow field at the aircraft engine inlet by the method for quantifying the vortex scale of the dynamic distortion flow field at the aircraft engine inlet provided by the embodiment of the application and a result of assistance of a foreign technical expert.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
In practice, based on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, a distribution curve of the vortex scale in the dynamic distorted flow field at the inlet of the aircraft engine along the circumferential direction is calculated by an autocorrelation coefficient curve algorithm, and a distribution curve of the vortex scale in the dynamic distorted flow field at the inlet of the aircraft engine along the circumferential direction can be calculated by a modified power spectrum algorithm and an autocorrelation function integral algorithm, as shown in fig. 1.
Through comparison, an autocorrelation coefficient curve algorithm is selected, based on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, a distribution curve of the vortex scale in the dynamic distorted flow field at the inlet of the aircraft engine along the circumferential direction is calculated, and an autocorrelation coefficient function is used
Figure BDA0003329859060000041
And (3) quantifying the vortex scale of the dynamic distorted flow field at the inlet of the aircraft engine at the time tau at the first intersection point of the vortex scale and the X axis, wherein the smaller the gas quality is, the smaller the static average vortex scale of the dynamic distorted flow field at the inlet of the aircraft engine is.
In the dynamic distorted flow field of the aircraft engine inlet, the total pressure pulsation data in the same vortex has larger correlation, after the vortex passes through the dynamic total pressure sensor, the correlation of the measured total pressure pulsation data is very small, the average time tau of different sizes of vortices existing in the dynamic distorted flow field of the aircraft engine inlet flowing through the dynamic total pressure sensor in a stable process is used as the static average vortex scale of the dynamic distortion of the aircraft engine inlet, the dynamic distorted flow field vortex scale of the aircraft engine inlet is quantitatively measured, the quantitative result of the dynamic distorted flow field vortex scale of the aircraft engine inlet is obtained in the way, the result of the quantitative result of the dynamic distorted flow field vortex scale of the aircraft engine inlet and the result of assistance of foreign technical experts, such as shown in figure 2, has extremely high coincidence, and the dynamic distorted flow field generated at the aircraft engine inlet can be accurately evaluated by combining the total pressure pulsation intensity and measuring the turbulent flow field at the aircraft engine inlet, and guidance is provided for the design and improvement of domestic engines.
In some optional embodiments, in the above method for quantifying the swirl scale of the dynamic distortion flow field at the inlet of the aircraft engine, the method further includes:
the total pressure pulsation data volume of the dynamic distortion flow field at the inlet of the aircraft engine is selected, each autocorrelation calculation is not less than 1K, and the smoothing times are not less than 20, so that the calculation accuracy is ensured.
In some optional embodiments, in the above method for quantizing the swirl scale of the dynamic distorted flow field at the inlet of the aircraft engine, digital filtering selection is performed on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, where:
the digital filter function is a Butterworth fourth-order band-pass;
the lower limit of the filtering is 5 Hz;
the upper limit of the filter is
Figure BDA0003329859060000051
Wherein the content of the first and second substances,
Vmaxthe average speed of the maximum state of the inlet of the aircraft engine is;
d is the diameter of the inlet of the aircraft engine.
In the method for quantizing the vortex scale of the dynamic distorted flow field at the inlet of the aircraft engine, the digital filtering function is a Butterworth fourth-order band-pass, the total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine is digitally filtered and selected, the total pressure pulsation data is obtained by screening a large amount of data, the lower filtering limit is set to be 5Hz, and the upper filtering limit is set to be 5Hz
Figure BDA0003329859060000061
The method is a main frequency range obtained by analyzing a large number of dynamic distortion flow fields of the inlet of the aircraft engine, has strong universality, and relevant technicians can analyze and determine the dynamic distortion flow fields according to specific conditions when applying the technical scheme disclosed by the application.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.

Claims (3)

1. A method for quantifying the vortex scale of a dynamic distortion flow field at an inlet of an aircraft engine is characterized by comprising the following steps:
based on total pressure pulsation data of the dynamic distorted flow field at the inlet of the aircraft engine, calculating a distribution curve of vortex scales in the dynamic distorted flow field at the inlet of the aircraft engine along the circumferential direction by an autocorrelation coefficient curve algorithm, and calculating a distribution curve of the vortex scales in the dynamic distorted flow field at the inlet of the aircraft engine by an autocorrelation coefficient function
Figure FDA0003329859050000011
Quantifying the vortex scale of the dynamic distortion flow field at the inlet of the aircraft engine at the time tau of the first intersection point of the vortex scale and the X axis;
wherein:
Rx(τ) is the correlation value of the autocorrelation function at the time instances of time variables τ and τ + d τ;
Rx(0) the autocorrelation function value at the time when d τ is 0;
ρx(τ) is the autocorrelation coefficient function value at times τ and τ + d τ.
2. The method for quantifying vortex dimensions in an aircraft engine inlet dynamic distortion flow field according to claim 1,
further comprising:
the total pressure pulsation data volume of the dynamic distortion flow field at the inlet of the aircraft engine is selected, each autocorrelation calculation is not less than 1K, and the smoothing times are not less than 20.
3. The method for quantifying vortex dimensions in an aircraft engine inlet dynamic distortion flow field according to claim 1,
carrying out digital filtering selection on total pressure pulsation data of a dynamic distortion flow field at an inlet of an aircraft engine, wherein:
the digital filter function is a Butterworth fourth-order band-pass;
the lower limit of the filtering is 5 Hz;
the upper limit of the filter is
Figure FDA0003329859050000021
Wherein the content of the first and second substances,
Vmaxthe average speed of the maximum state of the inlet of the aircraft engine is;
d is the diameter of the inlet of the aircraft engine.
CN202111275253.6A 2021-10-29 2021-10-29 Method for quantifying vortex scale of dynamic distortion flow field at inlet of aircraft engine Pending CN113987812A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114459764A (en) * 2022-03-10 2022-05-10 中国人民解放军空军工程大学 Rotatable total pressure distortion generating device

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114459764A (en) * 2022-03-10 2022-05-10 中国人民解放军空军工程大学 Rotatable total pressure distortion generating device
CN114459764B (en) * 2022-03-10 2023-12-08 中国人民解放军空军工程大学 Rotatable total pressure distortion generating device

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