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Airfoil Design Method for Axial Flow Turbine Large and Small Blade Combination Cascades

A blade combination and design method technology, which is applied to blade support components, mechanical equipment, machines/engines, etc., can solve the difficulty of airfoil shape data parameterization, poor stability of blade aerodynamic performance, weak correlation of blade design, etc. problems, to achieve the effect of low dependence on personal experience, good stability of aerodynamic performance, and small workload

Active Publication Date: 2021-05-25
AECC SHENYANG ENGINE RES INST
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0005] However, in the prior art airfoil design method for designing combined cascades with large and small blades, the airfoil design correlation between the large and small blades is weak, and secondly, it is difficult to parameterize the airfoil shape data of the large blade 2 obtained by extending the small blade 3, The airfoil design results are highly dependent on the designer's experience and habits, and the aerodynamic performance stability of the airfoil is poor

Method used

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  • Airfoil Design Method for Axial Flow Turbine Large and Small Blade Combination Cascades
  • Airfoil Design Method for Axial Flow Turbine Large and Small Blade Combination Cascades
  • Airfoil Design Method for Axial Flow Turbine Large and Small Blade Combination Cascades

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Embodiment Construction

[0037] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0038] This application provides a method for designing the blade cascade of axial-flow turbines with large and small blades, such as Figure 4 , including the following steps:

[0039] Step 1. Select the number of blades

[0040] Determine the number N of large blades evenly distributed in the circumferential direction, and place the same number m of small blades evenly between every two large blades, so as to determine the total number of blades m·N+N.

[0041] This step is the same as the prior art solution.

[0042] Step 2. Complete the parametric design of the large blade airfoil

[0043] From this step, it is different from the prior art scheme. In this step, it is first assumed that the total blade...

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Abstract

The present application discloses a method for designing an axial-flow turbine blade cascade with a combination of large and small blades. The number of blades; step 2, assuming that the total number of blades determined in step 1 are all large blades, and using the parameter method to complete the parametric design of large blade blades; step 3, in all the large blade cascades designed in step 2, determine The distribution of the number of large blades in the circumferential direction; step 4, establishing the relationship between the key blade shape parameters of large blades and small blades, and determining the parameters of small blades, and finally using the parameter method to complete the parametric design of large and small blades. Compared with the prior art, this application has a high degree of parameterization and strong correlation of airfoil parameters. Both large and small blade airfoils are designed parametrically. The design process is less dependent on the personal experience of the designer, and the aerodynamic performance of the scheme is stable. Good sex.

Description

technical field [0001] The invention relates to the airfoil design of an aero-engine, in particular to an airfoil design method for an axial-flow turbine blade cascade with large and small blades combined. Background technique [0002] In order to meet the aircraft structure design and aerodynamic performance requirements at the same time, and to achieve the compact structure requirements, the low-pressure turbine and flow path support plate of the aero-engine axial flow turbine will adopt a blade design in the form of a combination of large and small blades, such as figure 1 As shown, both the large blade 2 and the small blade 3 are arranged on the wheel disk 1 . In this combined cascade, the large blades 2 are evenly distributed along the circumference, and the same number of small blades 3 are evenly placed between every two adjacent large blades 2, and the alignment of the large and small blades is trailing edge alignment. [0003] At present, the airfoil design of larg...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14F01D9/04F01D25/00
CPCF01D5/141F01D9/041F01D25/00
Inventor 马广健陈云王刚王雷李鑫张兵兵
Owner AECC SHENYANG ENGINE RES INST
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