Method for altering the law of twist of the aerodynamic surface of a gas turbine engine fan blade

Patent metadata

Field	Value
Publication number	US-11499432-B2
Application number	US-201615741374-A
Country	US
Kind code	B2
Filing date	Jul 1, 2016
Priority date	Jul 3, 2015
Publication date	Nov 15, 2022
Grant date	Nov 15, 2022

Abstract

A method of altering the twisting relationship for the aerodynamic surface of a fan blade of a gas turbine engine, wherein the following steps are performed: establishing, for a portion of the aerodynamic surface of the fan blade, an alteration relationship defined by variation of a pitch angle of the blade as a function of radial height along the blade, the alteration relationship including alterations that are each defined by a height along with the radial height of the fan blade and by an amplitude; and applying the alteration relationship as established in this way to an initial twisting relationship of the fan blade so as to obtain an altered twisting relationship for the fan blade, the initial twisting relationship being defined by a polynomial for the radial height of the fan blade as a function of its pitch angle.

First claim

The invention claimed is:

1. A method of fabricating a fan blade of a gas turbine engine, the method comprising:
establishing, for a portion of the aerodynamic surface of the fan blade, an alteration relationship defined by variation of a pitch angle of the blade as a function of radial height along the blade, said alteration relationship comprising alterations that are each defined by a height along with the radial height of the fan blade and by a twisting amplitude;
applying the alteration relationship as previously established to an initial twisting relationship of the blade so as to obtain an altered twisting relationship for the fan blade, said initial twisting relationship being defined by a polynomial for the radial height of the fan blade as a function of a pitch angle of the fan blade;
locally modifying fluid angles at a leading edge and a trailing edge of the fan blade comprising the altered twisting relationship previously obtained without modifying the altered twisting relationship by iteratively measuring on a reference blade constructed with the initial twisting relationship the fluid angles at the leading edge and the trailing edge of blade sections in the portion of the aerodynamic surface of the fan blade and, after applying the altered twisting relationship, deforming the blade sections to impose the fluid angles that were measured while conserving the altered twisting relationship and performing aerodynamic calculations in trailing zones of the blade sections in the portion of the aerodynamic surface of the fan blade; and
fabricating the fan blade comprising the altered twisting relationship previously obtained and the locally modified fluid angles,
wherein the alteration relationship is applied to a predetermined portion of the aerodynamic surface of the fan blade that extends from the root of the blade to a height corresponding to 30% of the total radial height of the blade and is defined as a mathematical function in such a manner as to be zero and to have a derivative of zero at at least one end of said predetermined portion, and
wherein a number of alterations and the height and the twisting amplitude of each alteration are selected so as to comply with minimum frequency distances between a first twisting mode IT and fan blade harmonics nearest to the first twisting mode IT for various different stabilized operating points of the gas turbine engine, a frequency of the first twisting mode IT increasing as an alteration amplitude and an alteration slope of the alteration relationship increases without modifying a frequency of a first bending mode IF of the fan blade.

2. The method according to claim 1 , wherein the alteration relationship is also defined in such a manner that the twisting amplitude of each alteration is of absolute value that is less than or equal to 5°.

3. The method according to claim 1 , wherein the alteration relationship is also defined as a mathematical function in such a manner as to present a maximum slope of the order of 0.05° /mm.

4. The method according to claim 1 , wherein the alteration relationship is a function for which the number of alterations corresponds to a number of local minimums and maximums of said function.

5. The method according to claim 1 , wherein the alteration relationship comprises at least two alterations in opposite directions.

6. The method according to claim 1 , wherein the step of applying the alteration relationship to the initial twisting relationship of the fan blade consists in adding the alteration relationship to the initial twisting relationship.

Assignees

• Safran Aircraft Engines

Inventors

• Courtier Vivien Mickaël
• Laurenceau Adrien Louis Nicolas
• Mayhew Dominique Gerhadt
• Vlastuin Jonathan Evert

Classifications

• Y02T50/60

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

• F01D5/141

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

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title