Method for deciding margin of single line blade of axial flow compressor

An axial flow compressor, compressor technology, applied in pump control, mechanical equipment, machine/engine, etc., to achieve the effect of easy application and intuitive understanding

Active Publication Date: 2008-02-13
中科思道(南京)储能技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to overcome the blindness of margin performance control in the existing axial flow compressor design process, based on the understanding of the factors affecting the margin of axial flow compressor, through the appropriate development of the basic unit performance in the whole working condition range To achieve a given margin requirement, a compromise can be made to meet the structural strength conditions, thus providing a custom margin design method for single-row blades of axial flow compressors

Method used

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  • Method for deciding margin of single line blade of axial flow compressor
  • Method for deciding margin of single line blade of axial flow compressor

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] For a compressor blade, the process of designing to achieve the margin target includes the following steps:

[0029] 1) Interpret the succession of each section of the blade to reach the stall directly from the calculation results of the three-dimensional flow field;

[0030] 2) The flow-load characteristics of each section are drawn in the same figure; according to the full three-dimensional flow calculation results of the entire blade design condition, the positions of the design points on the flow-load characteristic line of each section shown in Figure 3 are determined, and are shown in Figure 3 4, namely shown in curve 13 among Fig. 4;

[0031] 3) Calculate the entire blade to the near-stall point by using the full three-dimensional flow field, and then determine the actual positions of the operating points of each section of the entire blade at the near-stall point, as shown in the points on the curve 15 in Figure 4;

[0032] 4) As shown in Figure 7, it represent...

Embodiment 2

[0038] For a compressor blade, the process of designing to achieve the margin target includes the following steps:

[0039]1) The compressor blades are regarded as an infinite number of small compressors with infinitely small heights matched in the span direction, and each small compressor has a corresponding flow-load characteristic line, as shown in the curves 9a, 9b, and Shown in 9c; the maximum flow state corresponds to the point on the line 11 (dotted line 11 in Fig. 3) of the near blockage condition, and the right end of each flow-load characteristic line in Fig. 3 is represented by a hollow circle; the minimum flow state corresponds to the point near On the stall condition line 12 (dotted line 12 in Fig. 3), the left end of each flow-load characteristic line in Fig. 3 is represented by a solid circle; a certain intermediate flow point corresponds to the design condition line 10 (in Fig. Solid line 10), in Fig. 3, represent with the solid rectangular box on each flow-loa...

Embodiment 3

[0047] For a compressor blade, the process of designing to achieve the margin target includes the following steps:

[0048] 1) Interpret the succession of each section of the blade to reach the stall directly from the results of the three-dimensional calculation of the fluid;

[0049] 2) The flow-load characteristics of each section are drawn in the same figure. According to the full three-dimensional flow calculation results of the entire blade design condition, the positions of the design points on the flow-load characteristic line of each section shown in Fig. 3 are determined, and are shown in Fig. 4, as shown in curve 13 in Fig. 4;

[0050] 3) The entire blade is calculated to the near-stall point by using full three-dimensional flow calculation, and then the actual position of each cross-section operating point of the entire blade is determined when the entire blade is near the stall point, as shown in the point on the curve 15 in Figure 4;

[0051] 4) As shown in Figur...

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Abstract

The invention discloses a method for making vane of an axial flow type air compressor have given tolerance, mainly comprising the steps as follows: taking flow-load characteristics of root, middle and tip sections or more sections of the vane and drawing them in the same diagram, and determining positions of design points on the flow-load characteristic line of each section according to the full 3D flow calculated results of design working conditions of the whole vane; making full 3D flow calculation on the whole vane to near stall points, and then determining actual positions of working points of each section as the whole vane is at the near stall points; judging which section tolerance or which ones are not enough, and adopting corresponding measures comprising moving this / these sections forward and in the rotating direction and modifying vane shapes of this / these sections to make pneumatic load barycenters of this / these sections move backward. And it implements tolerance control by physical essence of influencing tolerance of single row of vanes of a fan / air compressor.

Description

technical field [0001] The invention relates to a design method of an axial flow compressor blade, in particular to a method for making the axial flow compressor blade have a given margin performance. Background technique [0002] The known axial flow compressor is an important component widely used in the fields of aviation, aerospace, navigation, energy, chemical industry, etc. The blades include rotor blades 3 that rotate around the shaft and stator blades 4 that are fixed on the casing 2. As shown in Figure 2, all blades are formed by stacking primitive cascades 5 along the center of gravity stacking line 6 in the span direction, and the leading and trailing edges 7 and 8 of the blades are formed by stacking the front and rear parts of the cascades, as shown in Fig. As shown in 1 and 2, the pressure of the working fluid gas is increased after passing through the passage containing the rotor and stator vanes. A practical axial flow compressor should have the performance...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D27/00
Inventor 季路成陈江
Owner 中科思道(南京)储能技术有限公司
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