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Blade type design method for axial-flow type turbine large and small blade combined blade lattice

A technology of blade combination and design method, which is applied in the directions of blade supporting elements, mechanical equipment, stators, etc., can solve the problems of difficult parameterization of blade shape data, poor stability of blade aerodynamic performance, and weak correlation of blade design. Achieve the effect of low dependence on personal experience, good stability of aerodynamic performance, and small workload

Active Publication Date: 2019-02-19
AECC SHENYANG ENGINE RES INST
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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

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  • Blade type design method for axial-flow type turbine large and small blade combined blade lattice
  • Blade type design method for axial-flow type turbine large and small blade combined blade lattice
  • Blade type design method for axial-flow type turbine large and small blade combined blade lattice

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Embodiment Construction

[0037] In order to make the purpose, technical solutions and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below in conjunction with the drawings in the embodiments of the present application.

[0038] This application provides a method for designing an axial-flow turbine blade combined cascade blade type, such as Figure 4 , Including the following steps:

[0039] Step 1: Select the number of blades

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

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

[0042] Step two, complete the parameterized design of large blades

[0043] Starting from this step, it is different from the existing technical solution. In this step, it is f...

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Abstract

The invention discloses a blade type design method for an axial-flow type turbine large and small blade combined blade lattice. The blade type design method comprises the steps that step1, the numberof large blades and the number of same small blades evenly placed between every two large blades are confirmed, and the total number of the blades is confirmed; step2, the total number of the blades confirmed in step1 is assumed to be all large blades, and parametric design of the large-blade blade type is completed using a parametric method; step3, in the blade lattice of all the large blades designed and completed in the step2, distribution of the number of the large blades in the peripheral direction is confirmed; and step4, an incidence relation expression of key blade type parameters of the large blades and the small blades is established, the parameters of the small blades are confirmed, and large and small blade parametric design can be finally completed using the parametric method.Compared with the prior art, the blade type design method for the axial-flow type turbine large and small blade combined blade lattice is high in parametric degree and blade type parameter relatedness, the blade types of the large and small blades are all of parametric design, the design process is less dependent on the personal experience of designers, and the blade type design method for the axial-flow type turbine large and small blade combined blade lattice has good aerodynamic stability.

Description

Technical field [0001] The invention relates to aeroengine blade shape design, in particular to a blade shape design method of an axial-flow turbine blade combined cascade. Background technique [0002] In order to meet the requirements of aircraft structure design and aerodynamic performance at the same time, and achieve the requirements of compact structure, the low pressure turbine and runner support plate of the aero engine axial turbine will adopt the blade design of the combined cascade of large and small blades, such as figure 1 As shown, both the large blades 2 and the small blades 3 are arranged on the wheel disc 1. In this combined cascade, the large blades 2 are evenly distributed along the circumferential direction, and the same number of small blades 3 are evenly placed between two adjacent large blades 2, and the large and small blades are aligned in a tail-edge alignment. [0003] At present, the blade shape design of the large and small blade combined cascade is mai...

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Application Information

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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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