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Supersonic blade profile modeling design optimization method

An optimization method and supersonic technology, applied in the field of mechanical processing, can solve the problems of supersonic airfoil design and low optimization efficiency, and achieve the effect of reducing shock loss, reducing difficulty and simple process

Pending Publication Date: 2022-03-01
HARBIN TURBINE +1
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Problems solved by technology

[0003] In order to solve the problem that most of the traditional supersonic airfoils rely on the oblique cutting of the blade steam outlet side to control the flow path, and often rely on the experience of designers, resulting in low efficiency in the design and optimization of supersonic airfoils, the invention further proposes A supersonic airfoil shape design optimization method

Method used

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  • Supersonic blade profile modeling design optimization method
  • Supersonic blade profile modeling design optimization method
  • Supersonic blade profile modeling design optimization method

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specific Embodiment approach 1

[0022] Specific implementation mode one: combine Figure 1 to Figure 7 To illustrate this embodiment, a supersonic airfoil shape design optimization method described in this embodiment is realized through the following steps:

[0023] Step 1, parameterize the blade shape based on UG software;

[0024] Step 2, CFX pneumatic calculation;

[0025] Step three, optimize the algorithm.

specific Embodiment approach 2

[0026] Specific implementation mode two: combination Figure 1 to Figure 7 To illustrate this embodiment, the process of parameterizing the blade shape based on UG software in step 1 of a supersonic airfoil shape design optimization method described in this embodiment is:

[0027] In step a, the inner and back arc curves of the airfoil adopt NURBS curves respectively, and the steam inlet and outlet adopt circular arcs to design the shape of the supersonic airfoil;

[0028] Step b. According to the shape design in step a, UG software is used to correlate control points to realize the continuous closure of the curve, so that the blade shape is fully parameterized and adjustable.

specific Embodiment approach 3

[0029] Specific implementation mode three: combination Figure 1 to Figure 7 To illustrate this embodiment, the CFX aerodynamic calculation process in Step 2 of a supersonic airfoil shape design optimization method described in this embodiment is: drive the CFX software through UG, and establish a calculation process, including geometry generation, mesh division, and previous Processing settings, smooth post-processing.

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Abstract

The invention discloses a supersonic blade profile modeling design optimization method, and relates to a design optimization method, in particular to the supersonic blade profile modeling design optimization method. The invention aims to solve the problem that most of the traditional supersonic blade profiles are used for obliquely cutting off a control flow channel by virtue of the steam outlet sides of the blades, which often depends on the experience of designers, so that the supersonic blade profile design and optimization efficiency is relatively low. The method comprises the following specific steps: step 1, parameterizing a blade profile based on UG software; step 2, CFX pneumatic calculation; and step 3, optimizing an algorithm. The invention belongs to the field of machining.

Description

technical field [0001] The invention relates to a design optimization method, in particular to a supersonic airfoil shape design optimization method, which belongs to the field of mechanical processing. Background technique [0002] With the continuous increase of the installed capacity of the generator, the demand for the final stage blade of the steam turbine is higher, and the design difficulty of the final stage blade mainly lies in the design of the supersonic blade shape on the upper part of the blade; the Mach number changes from subsonic to supersonic, and the blade The flow path of the type is changed from tapered to zoomed. Most of the traditional supersonic airfoils rely on the oblique cutting of the steam outlet side of the blade to control the flow path, often relying on the experience of the designer; therefore, the efficient supersonic airfoil design and optimization is blank. Contents of the invention [0003] In order to solve the problem that most of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/23G06F111/04G06F111/06
CPCG06F30/17G06F30/23G06F2111/04G06F2111/06
Inventor 赵洪羽关淳李鸿博翁振宇潘春雨王健郭魁俊张玥历雪邬晓静
Owner HARBIN TURBINE
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