CN112287477B - Turbine guide device large and small blade layout method based on airflow excitation - Google Patents
Turbine guide device large and small blade layout method based on airflow excitation Download PDFInfo
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Abstract
The application provides a turbine guide vane and large vane layout method based on airflow excitation, which comprises the following steps: obtaining a layout scheme of at least two guide vane large and small vanes; respectively carrying out flow field numerical simulation on the layout schemes of the large and the small blades of the at least two deflectors to obtain the flow field characteristic of the outlet of the deflector in the maximum state of the engine, wherein the flow field characteristic of the outlet of the deflector comprises total pressure data and total temperature data; extracting total pressure data of the guider outlet flow field in the maximum state of the engine at a preset position relative to the cavity height according to the characteristics of the guider outlet flow field; respectively carrying out spectrum analysis on total pressure data at a preset position of a relative cavity height of an outlet flow field under the large and small blade layout scheme of each guider to obtain corresponding amplitude-frequency characteristics of the airflow exciting force; and carrying out comparative analysis on the amplitude-frequency characteristics of the airflow exciting force corresponding to the large and small blade layout schemes of each guider, and screening out an optimal design scheme as a final large and small blade layout scheme of the guider.
Description
Technical Field
The application relates to the field of aero-engines, in particular to a layout method of large and small blades of a turbine guide device based on airflow excitation.
Background
The turbine guider structure with the large blades replaces part of the blades in a conventional guider with the large blades, has the functions of a support plate and the guider, can realize good pneumatic performance under the condition of meeting structural requirements, and is of a better compact design. However, the large blades are thick in shape and are special-shaped blades relative to the small blades, so that a turbine pneumatic channel with good convergence and formed by the small blades is damaged, circumferential nonuniformity of a flow field at the outlet of the guider is increased, a new blade vibration inducement is formed, and potential adverse effects are brought to the dynamic strength design of the rotor blades of the engine.
The unreasonable blade layout design of the turbine guide vane can cause the fault of blade crack and even fracture due to the excessive pneumatic excitation force. Therefore, the layout design of the large and small blades becomes one of the important technical difficulties for the design of the turbine guide with the large blades. At present, the turbine guide vane with the large vane is applied to an engine and has less reference to public data, and the layout scheme of the large vane and the small vane of the guide vane cannot be effectively evaluated in the design stage. How to establish an accurate and effective analysis method in the design stage, accurately analyze and evaluate the layout design of the turbine guide device with large blades, realize the forward design of the structure, and is a problem which has great significance and is urgently needed to be solved.
Disclosure of Invention
The invention provides a layout method of large and small blades of a turbine guide vane based on air flow excitation, which can be used for designing the turbine guide vane with large blades and provides basic support for the layout design of the large and small blades of the turbine guide vane.
The application provides a turbine guide vane large and small blade layout method based on airflow excitation, which is characterized by comprising the following steps:
according to the functional characteristics and space constraints of the engine guider, the layout scheme of the large and small blades of the at least two guider is obtained by adjusting the circumferential distribution of the large and small blades of the guider;
respectively carrying out flow field numerical simulation on the layout schemes of the large and small blades of the at least two deflectors to obtain the outlet flow field characteristics of the deflectors in the maximum state of the engine, wherein the outlet flow field characteristics of the deflectors comprise total pressure data and total temperature data;
extracting total pressure data of the guider outlet flow field in the maximum state of the engine at a preset position relative to the cavity height according to the characteristics of the guider outlet flow field;
respectively carrying out spectrum analysis on total pressure data at a preset position of a relative cavity height of an outlet flow field under the large and small blade layout scheme of each guider to obtain corresponding amplitude-frequency characteristics of the airflow exciting force;
and carrying out comparative analysis on the airflow excitation force amplitude-frequency characteristics corresponding to the large and small blade layout schemes of each guider, and screening out an optimal design scheme to be used as a final large and small blade layout scheme of the guider.
Specifically, the predetermined relative lumen height position includes a 50% relative lumen height.
Specifically, the performing a spectrum analysis on the total pressure data of the outlet flow field under the layout scheme of the large and small blades of each guider respectively to obtain the corresponding amplitude-frequency characteristics of the airflow exciting force specifically includes:
acquiring total pressure data of an outlet flow field of the guider;
and respectively carrying out spectrum analysis on the total pressure data of the outlet flow field under the large and small blade layout scheme of each guider according to the total pressure data of the outlet flow field of the guider and the rotating speed of the engine to obtain corresponding amplitude-frequency characteristics of the gas flow exciting force.
In particular, the method of spectral analysis includes fourier transformation.
Specifically, the method for acquiring the characteristics of the flow field at the outlet of the guider comprises finite element numerical simulation.
Specifically, the layout scheme of the large and small vanes of the guide comprises that the large and small vanes are uniformly distributed.
Specifically, the layout scheme of the large blades and the small blades of the guider comprises non-uniform distribution of the large blades and the small blades.
Specifically, the layout scheme of the large and small vanes of the guider screens the amplitude including the airflow exciting force.
In conclusion, when the turbine guide vane is designed, the forward and quantitative analysis and evaluation of the guide vane layout design are realized, the result is reliable, and the structural fatigue failure risk is reduced.
The method is successfully used for the optimization design of the low-pressure turbine guider of a certain small high-speed military engine, and a dynamic stress test is carried out in the environment of the whole machine, so that the optimization effect is remarkable, and the engineering requirement is met. The establishment of the technology further perfects an engine design system, and provides a solid technical foundation for the improvement and modification of turbine parts of the in-service engine and the design of turbine parts of the in-service type.
Drawings
Fig. 1 is a schematic diagram of a technical solution provided in an embodiment of the present application;
FIG. 2 is a schematic view of a turbine nozzle having large blades according to an embodiment of the present disclosure;
FIG. 3 is a schematic view of a layout of a large vane and a small vane of a vane according to an embodiment of the present application;
fig. 4 is a schematic view illustrating a numerical simulation of finite elements of a flow field according to an embodiment of the present application;
fig. 5 is a schematic diagram of total pressure data of an outlet flow field according to an embodiment of the present disclosure;
fig. 6 is a schematic diagram of amplitude-frequency characteristics of a fluid excitation force provided in an embodiment of the present application.
Detailed Description
The invention realizes the scheme of the above purpose:
the quality of the flow field at the exit of the nozzle has a direct influence on the fatigue life of the downstream rotor blades. The exciting force of the turbine blade is mainly from the outlet flow field of the turbine guider. Therefore, by comprehensively comparing and analyzing the excitation force of the outlet flow field under different layout schemes of the large and small vanes of the guider, the difference of each scheme can be obtained quantitatively, and the optimal layout scheme of the guider can be screened out. The technical scheme of the invention is schematically shown in figure 1.
In order to achieve the purpose, the method for arranging the large and small blades of the turbine guide vane based on airflow excitation comprises the following steps:
and 2, respectively carrying out flow field finite element numerical simulation on the layout schemes of the large blade and the small blade of each guider to obtain flow field characteristics under different structural layout schemes. The part needs to extract total pressure data of the flow field of the outlet of the guide device at a preset position relative to the cavity height in the maximum state of the engine according to the numerical analysis result of the flow field. A flow field finite element numerical simulation schematic diagram please refer to fig. 4, and an outlet flow field total pressure data schematic diagram please refer to fig. 5;
and 3, carrying out frequency spectrum analysis on total pressure data at a preset position of the outlet flow field relative to the cavity height under the large and small blade layout scheme of each guider by using a Fourier transform method to obtain the amplitude-frequency characteristic of the fluid exciting force. Please refer to fig. 6 for a schematic diagram of amplitude-frequency characteristics of the fluid exciting force;
and 4, comparing and analyzing the flow field excitation force amplitude-frequency characteristics of the large and small blade layout schemes of each guider, and taking the layout scheme with relatively small excitation force amplitude as the layout scheme of the large and small blades of the optimal guider.
Claims (3)
1. A turbine guide vane large and small blade layout method based on airflow excitation is characterized by comprising the following steps:
according to the functional characteristics and space constraints of the engine guider, the layout scheme of the large and small blades of the at least two guider is obtained by adjusting the circumferential distribution of the large and small blades of the guider;
respectively carrying out flow field numerical simulation on the layout schemes of the large and small blades of the at least two deflectors to obtain the outlet flow field characteristics of the deflectors in the maximum state of the engine, wherein the outlet flow field characteristics of the deflectors comprise total pressure data and total temperature data;
extracting total pressure data of the guider outlet flow field in the maximum state of the engine at a preset position relative to the cavity height according to the characteristics of the guider outlet flow field;
respectively carrying out spectrum analysis on total pressure data at a preset position of a relative cavity height of an outlet flow field under the large and small blade layout scheme of each guider to obtain corresponding amplitude-frequency characteristics of the airflow exciting force;
comparing and analyzing the airflow excitation force amplitude-frequency characteristics corresponding to the large and small blade layout schemes of each guider, and screening out an optimal design scheme as a final large and small blade layout scheme of the guider;
the preset position relative to the cavity height comprises a position 50% relative to the cavity height;
the method comprises the following steps of respectively carrying out spectrum analysis on total pressure data of an outlet flow field under a large and small blade layout scheme of each guider to obtain corresponding amplitude-frequency characteristics of the gas flow exciting force, and specifically comprises the following steps:
acquiring total pressure data of an outlet flow field of the guider;
respectively carrying out spectrum analysis on the total pressure data of the outlet flow field under the large and small blade layout scheme of each guider according to the total pressure data of the outlet flow field of the guider and the rotating speed of the engine to obtain corresponding amplitude-frequency characteristics of the airflow exciting force;
the method of spectral analysis includes fourier transform;
the method for acquiring the characteristics of the flow field at the outlet of the guider comprises finite element numerical simulation;
the layout scheme of the large and small vanes of the guide device screens the amplitude of the exciting force of the airflow.
2. The method of claim 1, wherein the pilot size vane placement scheme comprises a uniform distribution of size vanes.
3. The method of claim 1, wherein the guide vane size blade placement scheme comprises a non-uniform distribution of size blades.
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| CN202011106915.2A CN112287477B (en) | 2020-10-16 | 2020-10-16 | Turbine guide device large and small blade layout method based on airflow excitation |
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| CN114151146B (en) * | 2021-10-20 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Method for acquiring airflow exciting force parameters of multi-connection shrouded turbine rotor blade |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573469A (en) * | 2013-10-20 | 2014-02-12 | 中国科学院工程热物理研究所 | Fan pneumatic layout structure and method of turbofan engine |
| CN103726890A (en) * | 2014-01-05 | 2014-04-16 | 中国科学院工程热物理研究所 | High-low pressure turbine transition section layout structure and design method thereof |
| CN104573199A (en) * | 2014-12-19 | 2015-04-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Topological optimization method for constraining and damping blades of aeroengine |
| CN105422190A (en) * | 2015-12-03 | 2016-03-23 | 中国科学院工程热物理研究所 | Gas compressor or turbine outlet guider |
| CN109514146A (en) * | 2019-01-11 | 2019-03-26 | 中国民航大学 | Blade of aviation engine REPAIR WELDING flexibility runner cooling system |
-
2020
- 2020-10-16 CN CN202011106915.2A patent/CN112287477B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573469A (en) * | 2013-10-20 | 2014-02-12 | 中国科学院工程热物理研究所 | Fan pneumatic layout structure and method of turbofan engine |
| CN103726890A (en) * | 2014-01-05 | 2014-04-16 | 中国科学院工程热物理研究所 | High-low pressure turbine transition section layout structure and design method thereof |
| CN104573199A (en) * | 2014-12-19 | 2015-04-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Topological optimization method for constraining and damping blades of aeroengine |
| CN105422190A (en) * | 2015-12-03 | 2016-03-23 | 中国科学院工程热物理研究所 | Gas compressor or turbine outlet guider |
| CN109514146A (en) * | 2019-01-11 | 2019-03-26 | 中国民航大学 | Blade of aviation engine REPAIR WELDING flexibility runner cooling system |
Non-Patent Citations (3)
| Title |
|---|
| 某型发动机高压压气机进气导向器叶片转动卡滞故障分析与排除;唐秀娟 等;《航空维修与工程》;20181220;91-92 * |
| 结合不确定度的发动机模型辨识气路诊断;白磊等;《航空动力学报》;20160705(第07期);1623-1629 * |
| 航空发动机叶片高循环疲劳失效研究;李其汉等;《航空发动机》;20031230(第04期);16-18+41 * |
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