Method for calculating the thickness of the trailing and leading edges on a blade profile

Patent metadata

Field	Value
Publication number	US-12005666-B2
Application number	US-202017634716-A
Country	US
Kind code	B2
Filing date	Aug 7, 2020
Priority date	Aug 13, 2019
Publication date	Jun 11, 2024
Grant date	Jun 11, 2024

Abstract

A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.

First claim

The invention claimed is:

1. A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method comprising:
for a plurality of sections of the real blade, determining a thickness of the real blade and a thickness of the corresponding theoretical blade at a plurality of points along a camber line of the corresponding blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line;
comparing the thickness of the real blade with the thickness of the theoretical blade for each point of the camber line of each section; and
determining whether the aerodynamic profile of the real blade is in compliance from the result of the comparison of each point of the camber line of each section of the real blade with the theoretical blade;
wherein, for each section, a thickness of the real blade and a thickness of the corresponding theoretical blade for a plurality of points along a camber line of the corresponding blade are determined by:
constructing a camber line of the theoretical blade and constructing a camber line of the real blade;
constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade;
superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade by using a least-squares superposition function; and
extracting the leading-edge and trailing-edge thicknesses of the real blade at the blade section, the leading-edge and the trailing-edge thicknesses of the real blade being extracted by determining the values on the thickness relationship of the real blade that correspond respectively to the predetermined positions of a leading edge point and of a trailing edge point on the theoretical blade,
the least-squares superposition function corresponding to the following equation:
S ( x )=min ΣReal Thickness X −Theoretical Thickness X

where “Real Thickness x ” is the thickness of the real blade at a position x along the camber line of the real blade, “Theoretical Thickness x ” is the thickness of the theoretical blade at the same position x along the camber line of the theoretical blade, “min” is a minimum function, and S(x) is a difference for each position x along the camber line.

2. The method of fabricating a blade for an aircraft turbine engine, the method comprising molding a real blade, performing a verification method according to claim 1 for verifying whether the aerodynamic profile of the real blade complies with a theoretical blade, and machining the real blade if the blade is considered as being in compliance at the end of said verification method.

Assignees

• Safran Aero Composite
• Safran Aircraft Engines
• Safran Aerospace Composites

Inventors

• Le Cloarec Damien Vincent
• Giacovelli Clement
• Sherman Jeffrey Steven
• Thomas Mickaelle Lucie Alicia

Classifications

• B23P15/02

  turbine or like blades from one piece · CPC title

• Y10T29/49336

  Blade making · CPC title

• Y10T29/49771

  Quantitative measuring or gauging · CPC title

• G05D5/02

  of thickness, e.g. of rolled material (of specific materials B21B, B29C, B32B, C03B, D21F) · CPC title

• F05D2230/18

  Manufacturing tolerances · CPC title