CN118036417B - Non-integral-order vibration damping design method based on circumferential detuning of adjustable stationary blade - Google Patents
Non-integral-order vibration damping design method based on circumferential detuning of adjustable stationary blade Download PDFInfo
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Abstract
The application provides a non-integral-order vibration damping design method based on circumferential detuning of an adjustable stationary blade, which belongs to the technical field of compressor design and comprises the steps of establishing a multi-stage compressor full-ring non-constant numerical simulation model and a rotor blade finite element model, and obtaining a rotor blade first vibration stress and a rotor blade dynamic frequency F S under a non-integral-order vibration working condition; the installation angle of the adjustable stator blade of the adjusting part is adjusted to carry out circumferential detuning design of the adjustable stator blade, an unsteady numerical simulation model is established, and aerodynamic performance and unsteady airflow non-integer multiple excitation frequency F R of the rotor blade tip are obtained; repeating the detuning design until F R and F S meet preset requirements; and acquiring a second vibration stress of the rotor blade under the circumferential detuning of the adjustable stator blade, and changing the installation angle of the adjustable stator blade in a fitting way if the aerodynamic performance and the second vibration stress meet the design requirements. The application realizes the vibration damping design of non-integral order vibration, can avoid the change of the vane profile of the adjustable stationary blade, and has good practical value and wide application prospect.
Description
Technical Field
The application relates to the technical field of compressor design, in particular to a non-integral-order vibration damping design method based on circumferential detuning of an adjustable stationary blade.
Background
The performance requirements of the advanced aeroengine on the compressor components are continuously improved, the lightweight design enables the pneumatic load of the compressor design to be continuously improved, and the inter-stage adopts smaller axial spacing. The rotor blade bears centrifugal load and also bears upstream and downstream stator wake and potential flow, tip separation vortex and other unsteady pneumatic loads, so that the vibration stress of the blade is increased, and the problem of high cycle fatigue failure caused by flow-induced vibration of the blade is more and more prominent. Therefore, in order to ensure safe operation of the compressor components, the design of the blades must take into account aerodynamic, structural and strength properties.
The flow induced vibration nature of the compressor blades is a pneumatic elastic process of unstable fluid and blade structural coupling, and common pneumatic elastic problems of compressor blades mainly include forced vibration and non-full order vibration. The forced vibration mainly comes from the aerodynamic excitation of the circumferential variation of the compressor, such as the periodic unsteady aerodynamic force generated by the upstream blade wake and the potential flow between blade rows, and is characterized in that the airflow excitation frequency and the rotation frequency are in an integral multiple relation. The non-integral order vibration mainly comes from airflow excitation of the circumferential unstable flow of the rotor blade tip, and because the unstable flow moves around the rotor, the airflow excitation frequency and the rotation frequency are not synchronous and are in a non-integral multiple relationship, and meanwhile, the non-integral order vibration also has the characteristics of frequency locking and phase locking, so that larger vibration stress can be generated, and serious threat is formed to the reliability and the safety of the blade. Compared with forced vibration, because the excitation frequency of the circumferentially unstable air flow cannot be given in advance, the non-full-order vibration is more difficult to predict in engineering, and therefore, the rotor blade non-full-order vibration damping design method is required to be developed urgently.
Disclosure of Invention
In view of the above, the embodiment of the application provides a non-integral-order vibration damping design method based on circumferential detuning of an adjustable stationary blade, which at least partially solves the problem that non-integral-order vibration in the prior art is difficult to predict in engineering.
The embodiment of the application provides a non-integral-order vibration damping design method based on circumferential detuning of an adjustable stationary blade, which comprises the following steps:
Establishing a multistage compressor full-ring unsteady numerical simulation model and a finite element model of a rotor blade, and acquiring a first vibration stress of the rotor blade;
Acquiring a dynamic frequency F S of the rotor blade under a non-full-order vibration working condition based on the finite element model of the rotor blade;
Performing adjustable stator blade circumferential detuning design by adjusting part of the adjustable stator blade mounting angles based on the first vibration stress, wherein the adjustable stator blade mounting angles in two adjacent sectors are different based on the circumferential division of the mounting angles of the adjustable stator blade into a plurality of sectors;
Based on the adjustable stator vanes of the multiple sectors, establishing an unsteady numerical simulation model of circumferential detuning of the adjustable stator vanes of the multistage compressor, and obtaining the excitation frequency F R of unstable airflow of the rotor blade tip;
Repeating the circumferential detuning design of the adjustable stator blade until the F R and the F S meet preset requirements;
Based on the circumferential detuning design of the adjustable stator blade meeting the preset requirement, obtaining a second vibration stress of the rotor blade under the circumferential detuning of the adjustable stator blade, and judging whether the aerodynamic performance of the compressor under the circumferential detuning of the adjustable stator blade and the second vibration stress meet the design requirement;
and based on the circumferential detuning design of the adjustable stator vanes meeting the design requirements, adaptively changing the installation angle of the adjustable stator vanes in each sector, and completing the structural design of the compressor with the circumferential detuning of the adjustable stator vanes.
According to a specific implementation manner of the embodiment of the present application, the establishing a full-ring unsteady numerical simulation model of a multi-stage compressor and a finite element model of a rotor blade, obtaining a first vibration stress of the rotor blade, includes:
according to the multistage compressor full-ring unsteady flow field numerical simulation model, carrying out compressor unsteady flow field numerical simulation aiming at the working condition that the rotor blade of the compressor vibrates in an uneven order, and obtaining a first simulation result;
According to the first simulation result, obtaining the surface pressure distribution of the rotor blade at different moments, and forming first pressure load data at different moments;
And applying the first pressure load data at different moments to the solid surface of the rotor blade according to time sequence based on the finite element model of the rotor blade, and carrying out harmonic response analysis under unsteady airflow excitation of the rotor blade to obtain the first vibration stress of the rotor blade.
According to a specific implementation manner of the embodiment of the present application, the establishing an unsteady numerical simulation model of circumferential detuning of an adjustable stator blade of a multi-stage compressor, obtaining a non-integer multiple excitation frequency F R of pneumatic performance of the multi-stage compressor and unstable airflow of a rotor blade tip under different circumferential detuning of the adjustable stator blade, includes:
Establishing an unsteady numerical simulation model of circumferential detuning of the adjustable stator blade of the multistage compressor to obtain a second simulation result;
post-processing the second simulation result to obtain the pneumatic performance;
Extracting the surface pressure distribution of the rotor blade at different moments based on the second simulation result and forming second pressure load data at different moments;
And obtaining the non-integer multiple excitation frequency F R of the unstable airflow of the rotor blade tip under a relative coordinate system by using the second pressure load data through a fast Fourier transform method.
According to a specific implementation manner of the embodiment of the application, all the adjustable stator blade installation angles in the same sector are set to be in a biased-close state, a biased-open state or an original blade state.
According to a specific implementation manner of the embodiment of the application, the installation angle offset angles of different adjustable vanes in the same sector are different, and/or the installation angle offset angles of different adjustable vanes in the same sector are different.
According to a specific implementation manner of the embodiment of the present application, the adaptive changing of the installation angle of the adjustable stator blade in each sector includes:
A rocker arm structure is arranged on the rotating shaft of the adjustable stationary blade;
And driving the adjustable stationary blade to rotate by rotating the rocker arm structure until the designed installation angle is reached.
According to a specific implementation manner of the embodiment of the application, the rocker arm structure comprises a claw part which is clamped and arranged on the rotating shaft and a rod part for externally applying force, and the claw part and the rod part are integrally designed.
According to a specific implementation manner of the embodiment of the present application, the preset requirements satisfied by the F R and the F S are:
(FR-FS)/FS＞10%。
According to a specific implementation manner of the embodiment of the application, the multistage compressor full-loop unsteady numerical simulation model is established through CFD software.
According to a specific implementation of an embodiment of the application, the finite element model of the rotor blade is built by means of three-dimensional geometrical modeling software.
The beneficial effects are that:
According to the non-integral-order vibration damping design method based on circumferential detuning of the adjustable stator blade, the vibration frequency and the vibration stress of the rotor blade are calculated by calculating the non-integral-multiple excitation frequency of the non-integral-multiple airflow of the full ring of the multistage compressor and the unstable airflow of the rotor blade tip, and the vibration stress of the rotor blade under the original adjustable stator blade and the detuned adjustable stator blade is obtained by utilizing finite element software, so that the vibration damping design of the non-integral-order vibration of the rotor blade is realized. Meanwhile, the application also realizes the circumferential detuning of the mounting angle of the adjustable stationary blade, and the method can avoid the change of the blade profile of the adjustable stationary blade, and has good practical value and wide application prospect.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of an adjustable vane mounting angle being off or biased closed in accordance with an embodiment of the present invention;
FIG. 2 is a schematic view of a circumferential sector arrangement of adjustable vanes according to an embodiment of the present invention;
FIG. 3 is a schematic view illustrating the adjustment of the mounting angle of an adjustable vane according to an embodiment of the present invention.
In the figure: 1. original stationary blade; 2. an original stationary blade rocker arm; 3. detuning the stationary vane rocker arm.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present application by way of illustration, and only the components related to the present application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the application provides a non-integral-order vibration damping design method based on circumferential detuning of an adjustable stationary blade, and provides a structural design implementation method of a compressor with circumferential detuning of the adjustable stationary blade, which can be applied to the vibration damping design of non-integral-order vibration of a rotor blade of the compressor, and has good practical value and wide application prospect. The following describes in detail with reference to fig. 1 to 3.
Referring to fig. 1, the non-full-order vibration damping design method based on the circumferential detuning of the adjustable stator blade of the present embodiment includes the following steps:
Step 1, establishing a multistage compressor full-ring unsteady numerical simulation model and a finite element model of a rotor blade, and acquiring first vibration stress of the rotor blade, wherein the first vibration stress is initial vibration stress of the rotor blade.
Specifically, a multistage compressor full-ring unsteady flow field numerical simulation model is established through CFD software, and a compressor unsteady flow field numerical simulation is carried out aiming at the working condition that the rotor blade of the compressor vibrates in an uneven order, so that a first simulation result is obtained; according to the first simulation result, obtaining the surface pressure distribution of the rotor blade at different moments, and forming first pressure load data at different moments; the first simulation result is an unsteady flow field simulation result, and the first pressure load data is initial pressure load data;
And establishing a finite element model of the rotor blade through three-dimensional geometric modeling software, applying initial pressure load data at different moments to the solid surface of the blade according to time sequence based on the finite element model of the rotor blade, and carrying out harmonic response analysis under the excitation of the rotor blade unsteady airflow to obtain the vibration stress of the rotor blade.
And step 2, acquiring the dynamic frequency F S of the rotor blade under the non-full-order vibration working condition based on the finite element model of the rotor blade.
Specifically, based on a finite element model of the rotor blade, the finite element software is utilized to carry out the blade modal analysis, and the dynamic frequency F S and the resonance rotating speed diagram of the rotor blade under the non-full-order vibration working condition are obtained.
And 3, carrying out circumferential detuning design of the adjustable stator blade by adjusting the installation angle of the part of the adjustable stator blade based on the first vibration stress, wherein the installation angle of the adjustable stator blade is divided into a plurality of sectors along the circumferential direction, and the installation angles of the adjustable stator blade in two adjacent sectors are different.
Specifically, the circumferential detuning design of the adjustable stator blade is realized through the off state or the off state of the mounting angle of the part of the adjustable stator blade, an unsteady numerical simulation model of the circumferential detuning of the adjustable stator blade of the multi-stage compressor is established, unsteady flow fields of different circumferential sectors and different detuning amounts are calculated, the off state or the off state of the mounting angle of the adjustable stator blade can be referred to as fig. 1, the off state of the adjustable stator blade in different circumferential sectors can be referred to as fig. 2, the blades in the sector 1 in the fig. 2 are all set to be in an angle off state, the blades in the sector 2 are set to be in an original blade state, namely, the blade angles are not adjusted, the blades in the sector 3 are set to be in an angle off state, and the blades in the sector 4 are set to be in an original blade state. The specific positions of the blades in the angularly off-set condition and the angularly off-set condition are shown with reference to fig. 1.
In a specific design, all the adjustable stator blade installation angles in the same sector are set to be in a biased-close state, a biased-open state or an original blade state.
Further, the mounting angle offset angles of different adjustable vanes in the same sector are different, and/or the mounting angle offset angles of different adjustable vanes in the same sector are different.
And 4, based on the adjustable stator blades of the multiple sectors, establishing an unsteady numerical simulation model of circumferential detuning of the adjustable stator blades of the multi-stage compressor, and obtaining the pneumatic performance of the multi-stage compressor and the excitation frequency F R of unstable airflow of the rotor blade tip under different circumferential detuning of the adjustable stator blades.
Specifically, a non-steady numerical simulation model of circumferential detuning of the adjustable stator blade of the multi-stage compressor is established through CFD software, and a second simulation result is obtained, wherein the second simulation result is a simulation result of the non-steady flow field of the circumferential detuning of the adjustable stator blade;
Performing post-treatment on the second simulation result to obtain the pneumatic performance of the multistage compressor under different circumferential detuning of the adjustable stationary blade;
based on the second simulation result, extracting pressure distribution of the surface of the rotor blade at different moments and forming second pressure load data at different moments, wherein the second pressure load data is the pressure load data under circumferential detuning of the adjustable stator blade;
And obtaining the non-integer multiple excitation frequency F R of the unstable airflow of the rotor blade tip under a relative coordinate system by using the second pressure load data through a fast Fourier transform method.
And 5, repeating the circumferential detuning design of the adjustable stationary blade until the F R and the F S meet preset requirements.
Specifically, the preset requirements satisfied by the F R and the F S are:
(FR-FS)/FS＞10%。
And 6, acquiring second vibration stress of the rotor blade under the circumferential detuning of the adjustable stator blade based on the circumferential detuning design of the adjustable stator blade meeting the preset requirement, and judging whether the aerodynamic performance of the compressor under the circumferential detuning of the adjustable stator blade and the second vibration stress meet the design requirement or not, wherein the second vibration stress is the vibration stress under the circumferential detuning of the adjustable stator blade.
And 7, based on the circumferential detuning design of the adjustable stator vanes meeting the design requirement, adaptively changing the installation angle of the adjustable stator vanes in each sector, and completing the structural design of the compressor with the circumferential detuning of the adjustable stator vanes.
Specifically, the adaptive change of the installation angle of the adjustable stator blade in each sector can be realized through the following steps:
a rocker arm structure is arranged on the rotating shaft of the adjustable stationary blade; and driving the adjustable stationary blade to rotate by rotating the rocker arm structure until the designed installation angle is reached. The rocker arm structure is shown by referring to fig. 3, the position of the original stator blade 1 is shown, the rocker arm structure comprises a claw part clamped on a rotating shaft of a blade, and a rod part used for externally applying force, the claw part and the rod part are integrally designed, the original stator blade 2 is moved to the position of the detuned stator blade rocker arm 3 by applying force to the rod part through an external tool, and at the moment, the angle of the stator blade is changed from alpha to alpha *,α* > alpha, so that detuning adjustment of the adjustable stator blade is completed.
According to the embodiment of the application, based on computational fluid dynamics and structural dynamics simulation software, numerical simulation is carried out on the unsteady flow field and the structural response of the original adjustable stator and the circumferential detuned adjustable stator, circumferential propagation of unstable flow of the downstream rotor blade tip is restrained by utilizing the circumferential detuned adjustable stator blade, and vibration reduction of rotor blade non-integral order vibration is further realized. Meanwhile, by means of the non-axisymmetric rocker arm structure design, circumferential detuning of the mounting angle of the stator blade is achieved through changing the included angle of the rocker arm structure of the circumferential detuned stator blade, circumferential detuning of the adjustable stator blade is achieved, and the structural design does not need to change the blade profile of the circumferential detuned adjustable stator blade, so that the stator blade has good practical value and wide application prospect.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (10)
1. The non-integral order vibration damping design method based on the circumferential detuning of the adjustable stator blade is characterized by comprising the following steps of:
Establishing a multistage compressor full-ring unsteady numerical simulation model and a finite element model of a rotor blade, and acquiring a first vibration stress of the rotor blade;
Acquiring a dynamic frequency F S of the rotor blade under a non-full-order vibration working condition based on the finite element model of the rotor blade;
Performing adjustable stator blade circumferential detuning design by adjusting part of the adjustable stator blade mounting angles based on the first vibration stress, wherein the adjustable stator blade mounting angles in two adjacent sectors are different based on the circumferential division of the mounting angles of the adjustable stator blade into a plurality of sectors;
Based on the adjustable stator blades of the multiple sectors, establishing an unsteady numerical simulation model of circumferential detuning of the adjustable stator blades of the multi-stage compressor, and obtaining the pneumatic performance of the multi-stage compressor and the excitation frequency F R of unstable airflow of the rotor blade tip under different circumferential detuning of the adjustable stator blades;
Repeating the circumferential detuning design of the adjustable stator blade until the F R and the F S meet preset requirements;
Based on the circumferential detuning design of the adjustable stator blade meeting the preset requirement, acquiring a second vibration stress of the rotor blade under the circumferential detuning of the adjustable stator blade, and judging whether the aerodynamic performance and the second vibration stress meet the design requirement;
and based on the circumferential detuning design of the adjustable stator vanes meeting the design requirements, adaptively changing the installation angle of the adjustable stator vanes in each sector, and completing the structural design of the compressor with the circumferential detuning of the adjustable stator vanes.
2. The method for designing vibration damping of non-full-order vibration based on circumferential detuning of adjustable stator vanes according to claim 1, wherein the establishing a full-ring unsteady numerical simulation model of the multi-stage compressor and a finite element model of the rotor blade, obtaining a first vibration stress of the rotor blade, comprises:
according to the multistage compressor full-ring unsteady flow field numerical simulation model, carrying out compressor unsteady flow field numerical simulation aiming at the working condition that the rotor blade of the compressor vibrates in an uneven order, and obtaining a first simulation result;
According to the first simulation result, obtaining the surface pressure distribution of the rotor blade at different moments, and forming first pressure load data at different moments;
And applying the first pressure load data at different moments to the solid surface of the rotor blade according to time sequence based on the finite element model of the rotor blade, and carrying out harmonic response analysis under unsteady airflow excitation of the rotor blade to obtain the first vibration stress of the rotor blade.
3. The method for designing non-integral order vibration damping based on adjustable stator blade circumferential mismatch of claim 1, wherein the step of establishing an unsteady numerical simulation model of the adjustable stator blade circumferential mismatch of the multi-stage compressor to obtain the multi-stage compressor aerodynamic performance and the rotor blade tip unstable airflow non-integral multiple excitation frequency F R under different circumferential mismatch of the adjustable stator blade comprises the steps of:
Establishing an unsteady numerical simulation model of circumferential detuning of the adjustable stator blade of the multistage compressor to obtain a second simulation result;
post-processing the second simulation result to obtain the pneumatic performance;
Extracting the surface pressure distribution of the rotor blade at different moments based on the second simulation result and forming second pressure load data at different moments;
And obtaining the non-integer multiple excitation frequency F R of the unstable airflow of the rotor blade tip under a relative coordinate system by using the second pressure load data through a fast Fourier transform method.
4. The non-full order vibration damping design method based on adjustable vane circumferential detuning of claim 1, wherein all adjustable vane mounting angles in a same sector are set to off state, off state or original vane state.
5. The non-full order vibration damping design method based on adjustable vane circumferential detuning of claim 3, wherein the mounting angle offset angles of different adjustable vanes within the same sector are different and/or the mounting angle offset angles of different adjustable vanes within the same sector are different.
6. The method of claim 1, wherein said adaptively changing the mounting angle of the adjustable vane in each of said sectors comprises:
A rocker arm structure is arranged on the rotating shaft of the adjustable stationary blade;
And driving the adjustable stationary blade to rotate by rotating the rocker arm structure until the designed installation angle is reached.
7. The non-full order vibration damping design method based on adjustable vane circumferential detuning according to claim 6, wherein the rocker arm structure comprises a claw portion clamped on the rotating shaft and a lever portion for external force application, and the claw portion and the lever portion are integrally designed.
8. The non-full order vibration damping design method based on adjustable vane circumferential detuning of claim 1, wherein the preset requirements satisfied by F R and F S are:
(FR-FS)/FS＞10%。
9. the non-integer order vibration damping design method based on adjustable stator blade circumferential detuning according to any one of claims 1-8, wherein the multistage compressor full-ring unsteady numerical simulation model is established through CFD software.
10. The non-full order vibration damping design method based on adjustable vane circumferential detuning according to any one of claims 1-8, wherein the finite element model of the rotor blade is built by three-dimensional geometric modeling software.
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| CN202410444674.4A CN118036417B (en) | 2024-04-15 | 2024-04-15 | Non-integral-order vibration damping design method based on circumferential detuning of adjustable stationary blade |
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| US7082371B2 (en) * | 2003-05-29 | 2006-07-25 | Carnegie Mellon University | Fundamental mistuning model for determining system properties and predicting vibratory response of bladed disks |
| CN115640649B (en) * | 2022-11-09 | 2023-10-20 | 中国航发沈阳发动机研究所 | Blisk and active detuning vibration reduction design method thereof |
| CN115859536B (en) * | 2023-03-02 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Method for simulating asynchronous vibration frequency locking value of rotor blade of air compressor |
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Non-Patent Citations (2)
| Title |
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| Influence of mistuning on aerodynamic damping of blade in transonic compressor;Yang, XD等;《PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING》;20161130;230(13);2523-2534 * |
| 基于声模态分解的风扇叶盘同步振动辨识;文璧 等;《航空学报》;20230325;第44卷(第6期);1-11 * |
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