Compressor, blade, two-dimensional blade profile design method of blade and computer equipment

A design method and axial flow compressor technology, applied in mechanical equipment, machine/engine, design optimization/simulation, etc., can solve problems such as changes and adjustment parameters

Active Publication Date: 2020-12-11
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In order to improve the characteristics of the angle of attack, it is usually necessary to update the center arc and the thickness distributio...

Method used

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  • Compressor, blade, two-dimensional blade profile design method of blade and computer equipment
  • Compressor, blade, two-dimensional blade profile design method of blade and computer equipment
  • Compressor, blade, two-dimensional blade profile design method of blade and computer equipment

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Embodiment Construction

[0032] figure 1 Airfoil thickness distribution is shown. figure 2 A two-dimensional airfoil is shown. like figure 2 As shown, the airfoil surface consists of suction side 1 and pressure side 2. Superimposed along the normal direction N of the middle arc 3 as figure 1 The thickness curve c1 of the suction surface and the thickness curve c2 of the pressure surface are shown to generate the suction surface 1 and the pressure surface 2. The point where the suction surface 1 and the pressure surface 2 intersect on the front side is the leading edge 4, and the point where the suction surface intersects on the rear side is the rear edge. Edge 5, the process of superposition can be understood as the process of coordinate transformation. figure 1 The thickness shown is distributed along the direction of chord 45, the chord length of this chord 45 is equal to figure 2 The length of the middle arc 3 in . The thickness curve c1 of the suction surface and the thickness curve c2 of...

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Abstract

The invention provides a compressor, a blade, a two-dimensional blade profile design method of the blade, computer equipment and a two-dimensional blade profile design method of the compressor. The compressor is an axial flow compressor, and in the design steps of the two-dimensional blade profile design method, thickness distribution is superposed along the normal direction of a mean line to generate a suction surface and a pressure surface; wherein the structure of any one of the suction surface thickness curve and the pressure surface thickness curve comprises defining five position pointsand a curve connecting the five position points, the first-order derivatives of the suction surface thickness curve and the pressure surface thickness curve at the five position points are continuous,and the second-order derivatives of the suction surface thickness curve and the pressure surface thickness curve at the maximum thickness position point are continuous; calculating and determining four sections of curves according to the existing constraint conditions to obtain a suction surface thickness curve or a pressure surface thickness curve; and adjusting each first-section curve, keepingthe first-order derivative of each thickness curve at the front connection point continuous and the mean line of the two-dimensional blade profile unchanged, adjusting the first-section curves of thesuction surface thickness curve and the pressure surface thickness curve into asymmetric curves, and improving the attack angle characteristic.

Description

technical field [0001] The invention relates to a compressor, a blade, and a two-dimensional blade design method for the blade, and also relates to computer equipment for the auxiliary design method. Background technique [0002] Axial flow compressor is a multi-stage compression equipment in which the flow direction of the air flow is consistent or nearly consistent with the direction of the rotating axis of the working wheel. It is composed of a series of stators and rotors arranged alternately, and is often used in aero-engines or gas turbines. The blade of the axial flow compressor is an important part of the airflow channel of the compressor to realize the conversion of the airflow function and change the direction of the airflow. The leaf shape (Cascade) of the blade is the basic unit of the blade, and the blade is formed by stacking the leaf shape along the stacking line. [0003] Aeroengine blades have the characteristics of complex blade surface, large blade body t...

Claims

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Application Information

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IPC IPC(8): G06F30/17G06F30/28F04D29/38G06F119/14
CPCF04D29/324G06F30/17G06F30/28G06F2119/14
Inventor 曹传军李斌李继保尹泽勇翟志龙姜逸轩李游
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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