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A Correction Method for Influence of Blade End Rounding on Flow Rate

A blade and flow technology, applied in the field of axial flow turbines, can solve the problems such as the change of the rounding flow at the end of the blade, which can shorten the design cycle, facilitate the promotion and application, and achieve the effect of wide application.

Active Publication Date: 2022-07-05
HARBIN TURBINE +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the problem that the engineering method in the prior art cannot solve the influence of the flow change caused by the rounding of the blade end and correct the height of the working part of the blade, it further provides a correction method for the influence of the rounding of the blade end on the flow rate

Method used

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  • A Correction Method for Influence of Blade End Rounding on Flow Rate
  • A Correction Method for Influence of Blade End Rounding on Flow Rate
  • A Correction Method for Influence of Blade End Rounding on Flow Rate

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specific Embodiment approach 1

[0062] Embodiment 1: Combining Figure 1 to Figure 16 Describe this embodiment, a method for correcting the influence of blade end rounding on flow rate of this embodiment, which includes the following steps:

[0063] Step 1. Determine the calculation formula used for the correction according to the relative size of the blade throat width O and the blade radius R at the end of the blade:

[0064] When the blade throat width O at the blade end is greater than or equal to 2R, this is the case A, and the calculation formula used for the correction is:

[0065] A 01 =2(R 2 -πR 2 / 4)=0.4292R 2 (1);

[0066] When the blade throat width O at the blade end is less than 2R, it is the case B, and the calculation formula used for the correction is:

[0067]

[0068] Step 2. Calculate the reduction value A of the flow area b :

[0069] Since the value of the blade rounding is small relative to the height of the working part of the blade, it is considered that along the blade h...

specific Embodiment approach 2

[0095] Specific implementation mode 2: Combining Figure 4 to Figure 6 Illustrating this embodiment, in step 2 of this embodiment, when the root rounded area is case A, the area is A 1 The calculation formula is,

[0096] A 1 =2(R 1 2 -πR 1 2 / 4)=0.4292R 1 2 (8);

[0097] In step 2, when the root rounded area is case B, the area is A 2 ;

[0098]

[0099] Others are the same as the first embodiment.

specific Embodiment approach 3

[0100] Specific implementation three: combination Figure 8 to Figure 10 Illustrating this embodiment, in step 2 of this embodiment, when the top rounded area is case A, the area is A 3 ;

[0101] A 3 =2(R 3 2 -πR 3 2 / 4)=0.4292R 3 2 (10);

[0102] In step 2, when the top rounded area is case B, the area is A 4 :

[0103]

[0104] Others are the same as in the first or second embodiment.

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Abstract

A correction method for the influence of blade end rounding on flow. Specifically related to axial flow turbines. The present invention overcomes the problems that the engineering method of the prior art cannot solve the influence of the flow change caused by the rounding of the blade end and the problems of correcting the height of the working part of the blade. According to the relative size of the blade throat width O at the blade end and the blade rounding radius R, the invention determines the calculation formula used for correction, and calculates the reduction value A of the flow area. b , the integral method is used to calculate the total flow area A of the blade without considering the rounding 0 , calculate the area correction coefficient Δ A , according to the full 3D CFD loss library, calculate the efficiency correction coefficient Δ b , calculate the total correction coefficient Δ, calculate the partial height ΔL of the corrected blade, calculate the corrected blade height as the original leaf height, repeat the above steps 1 to 8, when the result of the correction coefficient is convergence, the final corrected blade work is obtained section height. The invention is used in the field of axial flow turbines.

Description

technical field [0001] The invention relates to the field of axial flow turbines, in particular to a method for correcting the influence of blade end rounding on flow. Background technique [0002] With the advancement of technology, the design of axial flow turbines is changing from "extensive" to "fine", which makes the flow control requirements higher, especially the first few stages of flow control are very critical, which need to be between turbine output and efficiency. Make a balance: the flow rate is too large, the equipment efficiency is low; the flow rate is too small, the equipment output is insufficient. The first few stages of the axial flow turbine have the smallest height of the working part, and the rounding of the end has a great influence. If it is not considered, it will cause problems of efficiency and output. Take the blade with a working part of 20mm high and a rounded root tip of R3mm as an example, considering that the flow rate is reduced by about 1...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14F01D21/00F01D25/00
CPCF01D5/141F01D5/147F01D21/003F01D25/00Y02P70/50
Inventor 刘云锋马天吟翁振宇刘长春李宇峰马义良熊继龙王健潘春雨关淳刘鑫李昂徐洪峰
Owner HARBIN TURBINE
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