Method of designing blade of axial flow fluid machine and blade

Patent metadata

Field	Value
Publication number	US-11333167-B2
Application number	US-201916587456-A
Country	US
Kind code	B2
Filing date	Sep 30, 2019
Priority date	Apr 17, 2017
Publication date	May 17, 2022
Grant date	May 17, 2022

Abstract

To provide a method of designing a blade of an axial flow fluid machine that has a blade surface whose radius of curvature is continuous at a leading edge thereof and has a high aerodynamic performance. The method includes a step of determining a pressure surface curve and a suction surface curve as curves capable of first to third order differentiations at respective connection points to a leading edge curve, that is, a pressure surface connection point and a suction surface connection point, and a step of forming the leading edge curve as a fifth order Bezier curve that is defined by a first control point, a second control point, a third control point, a fourth control point, a fifth control point and a sixth control point. The first control point is the suction surface connection point. The sixth control point is the pressure surface connection point. Provided that an intersection of a tangent to the pressure surface curve at the pressure surface connection point and a tangent to the suction surface curve at the suction surface connection point is referred to as a point ahead of the blade, the second and fifth control points are points that internally divide line segments connecting the point ahead of the blade to the suction surface connection point and the pressure surface connection point, respectively. The third and fourth control points are points having coordinates that are determined as solutions of simultaneous equations obtained by applying continuity conditions for first to third differential coefficients at the first and sixth control points to a fifth order Bezier function.

First claim

The invention claimed is:

1. A blade having an airfoil that is formed by a leading edge curve, a trailing edge curve, a pressure surface curve and a suction surface curve,
wherein the pressure surface curve is a curve that is connected to the leading edge curve at a pressure surface connection point and whose first to third order differential coefficients at the pressure surface connection point are known,
the suction surface curve is a curve that is connected to the leading edge curve at a suction surface connection point and whose first to third order differential coefficients at the suction surface connection point are known;
the leading edge curve is formed as a fifth order Bezier curve,
the fifth order Bezier curve is defined by a first control point, a second control point, a third control point, a fourth control point, a fifth control point and a sixth control point,
the first control point coincides with the suction surface connection point,
the sixth control point coincides with the pressure surface connection point,
provided that an intersection of a tangent to the pressure surface curve at the pressure surface connection point and a tangent to the suction surface curve at the suction surface connection point is referred to as a point ahead of the blade,
the second control point is a point that internally divides a line segment connecting the point ahead of the blade and the suction surface connection point with a ratio of p to (1−p) (where 0<p<1),
the fifth control point is a point that internally divides a line segment connecting the point ahead of the blade and the pressure surface connection point with a ratio of q to (1−q) (where 0<q<1), and
the third control point and the fourth control point are points having coordinates that are determined as solutions of simultaneous equations obtained by applying continuity conditions for first to third differential coefficients at the first control point and the sixth control point to a fifth order Bezier function that defines the fifth order Bezier curve.

Assignees

• Ihi Corp

Inventors

• Okada Ryuichi
• Enoki Tomonori
• Murooka Takeshi
• Kato Dai

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F04D29/384 Primary

  characterised by form · CPC title

• F04D29/38

  Blades {(for axial flow compressors F04D29/324)} · CPC title