Multi-condition propulsion performance optimization design method for a composite propeller

A composite material and optimization design technology, applied in calculation, instrumentation, geometric CAD, etc., can solve problems such as imperfect design methods of composite material propellers

Inactive Publication Date: 2019-10-22
HARBIN INST OF TECH
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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 propose a multi-working-condition propulsion performance optimization design method for a composite material propeller in order to solve the problem that the existing composite material propeller design method is not perfect

Method used

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  • Multi-condition propulsion performance optimization design method for a composite propeller
  • Multi-condition propulsion performance optimization design method for a composite propeller

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specific Embodiment approach 1

[0024] Specific implementation mode one: combine figure 1 To illustrate this embodiment, a multi-working-condition propulsion performance optimization design method for a composite material propeller in this embodiment is specifically prepared according to the following steps:

[0025] Step 1. Start;

[0026] Step 2. Determine the design speed J of the composite material propeller 0 The pitch value under p i 0 , where i=1,2...n, n is the radial radius number of the composite material propeller, and the value is a positive integer;

[0027] Step 3. Use the panel method to determine the design speed of the metal propeller at J 1 When , the incoming flow angle θ of the blade section at 0.75R 0 . 75R ;

[0028] Step 4. Calculate the incoming flow attack angle α of the maximum propulsion efficiency of the blade section at 0.75R of the main blade of the metal propeller 0.75R ;

[0029] Step 5. According to Step 3 and Step 4, determine that the design speed of the metal prop...

specific Embodiment approach 2

[0036] Specific embodiment two: the difference between this embodiment and specific embodiment one is: in the said step two, determine the design advance speed J of the composite material propeller 0 The pitch value under p i 0 , where i=1,2...n, n is the number of radial radii of the composite material propeller; the specific process is:

[0037] Taking the geometry of the metal propeller as the basic parameter, the design advance speed of the metal propeller is J 0 , the radial pitch value is p i 0 , where i=1,2...n, n is the radial radius number of the metal propeller; the radial pitch value p of the metal propeller i 0 Determined as the design speed J of the composite material propeller 0 The pitch value under p i 0 (Composite material propeller at the design advance speed of J 0 The pitch value after torsion deformation occurs at p i 0 ).

[0038] Other steps and parameters are the same as those in Embodiment 1.

specific Embodiment approach 3

[0039] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that in the step three, the panel method is used to determine the metal propeller at a design advance speed of J 1 , the incoming flow angle at the leading edge of the blade section leading edge at 0.75R; the specific process is:

[0040] Based on Green's formula, use the Fortran language to write the metal propeller surface element method program, according to the solution model of the metal propeller velocity field Solve the velocity field 4πV(p) of the metal propeller, and solve the disturbance velocity V(p) of the watershed where the metal propeller is located according to the velocity field 4πV(p) of the metal propeller;

[0041] Among them, p is an arbitrary point in the flow field, V(p) is the disturbance velocity of the water domain where the metal propeller is located, Q is a point on the surface of the propeller, is the disturbance potential, is the velo...

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Abstract

The present invention relates to a multiple-condition propulsion performance optimum design method of a composite material propeller, and aims at solving the problem that an existing composite material propeller design method is imperfect. The multiple-condition propulsion performance optimum design method comprises the steps of (1) starting; (2) determining a pitch value pi<0> of the composite material propeller at a design advance of J<0>; (3) determining [theta]0.75R at a 0.75R position when the design advance is J<1>; (4) calculating [alpha]0.75R; (5) determining a geometrical pitch angle [theta]1 of the composite material propeller at the 0.75R position when the design advance is J<1>; (6) determining a geometrical pitch angle [theta]1 of the composite material propeller when the design advance is J<1>; (7) selecting a ply orientation angle and sequence of a composite material; (8) designing initial geometry of the composite material propeller; (9) calculating a geometrical pitch angle [theta]1' of the composite material propeller when the design advance is J<1>; and (10) determining the pitch angle |[theta]1'-[theta]1|, if |[theta]1'-[theta]1| >= 0.1 DEG, executing the step (7), and if |[theta]1'-[theta]1| < 0.1 DEG, over. The multiple-condition propulsion performance optimum design method is applied to the propeller field.

Description

technical field [0001] The invention relates to a multi-working-condition propulsion performance optimization design method for a composite material propeller. Background technique [0002] In the design process of traditional metal propellers, the propulsion performance under common working conditions is prioritized as the goal. This goal determines the basic value of the metal propeller, and the propulsion performance under other working conditions cannot be further optimized. Due to the special bending-torsion coupling effect of the composite material propeller, multi-objective optimization can be carried out by designing the layup of the composite material to achieve the design goal that the metal propeller cannot achieve. [0003] The design method of composite material propeller is different from traditional metal propeller, and the design method of metal propeller is no longer satisfied with composite material propeller. At present, research on composite material pro...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/17Y02T90/00
Inventor 王荣国张旭婷刘文博赫晓东洪毅矫维成
Owner HARBIN INST OF TECH
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