Method for manufacturing a turbomachine fan having a reduced noise level at multiple rotational frequencies of said turbomachine

Patent metadata

Field	Value
Publication number	US-10865645-B2
Application number	US-201615580243-A
Country	US
Kind code	B2
Filing date	Jun 8, 2016
Priority date	Jun 8, 2015
Publication date	Dec 15, 2020
Grant date	Dec 15, 2020

Abstract

The invention relates to a method ( 100 ) for manufacturing a turbomachine fan comprising a plurality of blades mounted on a disc extending along a longitudinal axis, said method comprising the following steps of: —measuring ( 102 ) at least one structural parameter of each of the blades in the cold state, and, for each of the blades, estimating ( 103 ) at least one structural parameter in operation relating to a blade from the structural parameter(s) measured on said blade in the cold state, —determining ( 104 ) an optimal sequence of the blades around the disc from the structural parameters estimated in operation for each of the blades, and —mounting ( 105 ) the blades on the disc in the optimal sequence thus determined.

First claim

The invention claimed is:

1. A method for manufacturing a turbomachine fan including a plurality of blades mounted on a disk extending around a longitudinal axis, said method comprising:
measuring in a cold state, when said turbomachine fan is in a non-operational state, at least one structural parameter on each of the plurality of blades,
for each of the plurality of blades, estimating at least one structural parameter relating to each said blade when said turbomachine is in an operational state from the at least one measured structural parameter for each said blade,

determining an optimal sequence (ORD) of the plurality of blades around the disk from the at least one estimated structural parameter obtained for each of the plurality of blades,
mounting the plurality of blades on the disk in the optimal sequence (ORD) thus determined,

wherein when said turbomachine fan is in said operational state, a reduced noise level at multiple rotational frequencies (FMR) is obtained as compared to a noise level that would be produced by a turbomachine fan in which the plurality of blades are mounted in a sequence determined based on said at least one measured structural parameter on each of the plurality of blades.

2. The method according to claim 1 , wherein the estimation in operation of the at least one structural parameter of each said blade is performed from the structural parameter(s) measured in the cold state on each said blade and from a predictive response surface previously generated by a response surface method (RSM) to which are applied the at least one structural parameter measured in the cold state of each said blade.

3. The method according to claim 1 , wherein the at least one structural parameter measured in the cold state on each said blade are selected from at least one of:
a position of the center of gravity (X Gs , Y Gs ) of a section of each said blade at a cross-sectional height (h c ) of each said blade, and
a stagger angle (CHORD_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a leading edge angle (LE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a trailing edge angle (TE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade.

4. The method according to claim 1 , wherein the at least one structural parameter measured in the cold state on each said blade is selected from at least one of:
a position of the center of gravity (X Gs , Y Gs ) of a section of each said blade at a cross-sectional height (h c ) of each said blade, and
a length (L, L 1 , L 2 ) of the chord of each said blade at the cross-sectional height (h c ) of each said blade, and
a stagger angle (CHORD_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a leading edge angle (LE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a trailing edge angle (TE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a total height (H) of each said blade, and
at least one of a radial (R), an (A) and a tangential (T) static moment of each said blade, and
a mass of each said blade.

5. The method according to claim 1 , wherein the at least one structural parameter estimated in operation of each said blade is selected from at least one of:
a stagger angle (CHORD_ANGLE) of each said blade at a cross-sectional height (h c ) of each said blade, and
a leading edge angle (LE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a trailing edge angle (TE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade.

6. The method according to claim 1 , wherein the at least one structural parameter estimated in operation of each said blade are selected from at least one of:
a position of the center of gravity (X Gs , Y Gs ) of a section of each said blade at a cross-sectional height (h c ) of each said blade, and
a length (L, L 1 , L 2 ) of the chord of each said blade at the cross-sectional height (h c ) of each said blade, and
a stagger angle (CHORD_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a leading edge angle (LE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a trailing edge angle (TE_ANGLE) of each said blade at the cross-sectional height (h c ) of each said blade, and
a total height (H) of each said blade, and
at least one of a radial (R), an xial (A) and a tangential (T) static moment of each said blade, and
a mass of each said blade.

7. The method according to claim 3 , wherein the cross-sectional height (h c ) is taken as 90% of a total height (H) of each said blade from a root of each said blade.

8. A turbomachine fan obtained by the implementation of the manufacturing method according to claim 1 .

9. A turbomachine comprising the fan according to claim 8 .

Assignees

• Safran Aircraft Engines

Inventors

• Lafitte Anthony Bernard Germain
• Bruhat Jean-Frederic Pierre Joseph
• Pouzadoux Frederic Jean-Bernard
• Roux Jean-Michel

Classifications

• F05D2240/303

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

• Y02T50/60

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

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• F04D29/327

  with non identical blades · CPC title