US 2019/0168862 A1Published application

Part and method for producing a part having reduced drag by non-constant riblets

AssigneeSafran Aircraft Engines

InventorsWilliam Henri Joseph RIERA, Jerome Jean-Yves TALBOTEC, Julien Roger Marcel MARTY

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Abstract

Part comprising a wall which comprises a first zone (541), a first zone (541) and the second zone (542), a network of riblets being formed on the first zone (541), the second zone (542) and also on the transition zone (54t) so as to reduce the drag of the part when a flow of air flows along said wall; the height, the width and the spacing of the riblets formed on the transition zone (54t) changing along said transition zone (54t) so as to pass from the height, width and spacing of the riblets formed on the first zone at a first end of the transition zone to the height, width and spacing of the riblets formed on the second zone (542) at a second end of the transition zone (54t), the transition zone (54t) comprising a central portion on which the riblets comprise on one hand the height and the width that are respectively equal to the height and width of the riblets on the first zone (541), and on the other hand a spacing equal to the spacing of the riblets of the second zone (542).

Claims11

Dependent claims

A turbomachine part (1) for an aircraft comprising a wall which comprises a first zone (541), a second zone (542), and a transition zone (54t) located between the first zone (541) and the second zone (542),

an array of riblets (6) being formed on the first zone (541), on the second zone (542), and also on the transition zone (54t), the riblets being oriented parallel to the principal direction of airflow;
the riblets (6) comprising an apex (S), a height (H1, H2, Ht), a width (L1, L2, Lt), and a spacing (E1, E2, Et) which corresponds to the distance between the apices (S) of adjacent riblets (6);
the height (H1), the width (L1), and the spacing (E1) of the riblets (6) of the first zone (541) being constant on the first zone (541);
the height (H2), the width (L2), and the spacing (E2) of the riblets (6) of the second zone (542) being constant on the second zone (542);
the height (Ht), the width (Lt), and the spacing (Et) of the riblets (6) of the transition zone (54t) evolving along said transition zone (54t) so as to move from the height (H1), the width (L1), and the spacing (E1) of the riblets (6) formed on the first zone (541) at a first end of the transition zone (54t), to the height (H2), the width (L2), and the spacing (E2) of the riblets (6) formed on the second zone (542) at a second end of the transition zone (54t);
characterized in that the transition zone (54t) comprises a central portion located between the first and the second end on which the riblets (6) comprise both the height (Ht) and the width (Lt) which are respectively equal to the height (H1) and the width (L1) of the riblets (6) of the first zone (541), and also a spacing (Et) equal to the spacing (E2) of the riblets (6) of the second zone (542).

3 more elements

A manufacturing method of a turbomachine part (1), said method comprising the following steps:

(100) forming an array of riblets (6) on a first zone (541) of a wall of the part, the riblets (6) comprising an apex (S), a height (H1), a width (L1), and a spacing (E1) which corresponds to the distance between the apices (S) of adjacent riblets (6), the height (H1), the width (L1), and the spacing (E1) of the riblets (6) of the first zone (541) being constant on the entire first zone (541);
(200) forming an array of riblets (6) on a second zone (542) of the wall, the riblets (6) comprising an apex (S), a height (H2), a width (L2), a spacing (E2) corresponding to the distance between the apices (S) of adjacent riblets (6), the height (H2), the width (L2), and the spacing (E2) of the riblets (6) of the second zone (542) being constant on the entire second zone (542);
(300) forming an array of riblets (6) on a transition zone (54t) of the wall located between the first zone (541) and the second zone (542), the riblets (6) comprising an apex (S), a height (Ht), a width (Lt), and a spacing (Et) corresponding to the distance between the apices (S) of adjacent riblets (6), the height (Ht), the width (Lt), and the spacing (Et) of the riblets (6) of the transition zone (54t) evolving along said transition zone (54t) so as to move from the height (H1), the width (L1), and the spacing (E1) of the riblets (6) of the first zone (541) at a first end of the transition zone (54t), to the height (H2), the width (L2), and the spacing (E2) of the riblets (6) of the second zone (542) at a second end of the transition zone (54t), the transition zone (54t) comprising a central portion located between the first and the second end on which the riblets (6) comprise both the height (Ht) and the width (Lt) which are respectively equal to the height (H1) and the width (L1) of the riblets (6) of the first zone (541), and also a spacing (Et) equal to the spacing (E2) of the riblets (6) of the second zone (542).

Dependencies are inferred from the claim text.

Facts

Application: 16/313,722Filed 27 Jun 2017
Priority: FR 165602528 Jun 2016
Published: 6 Jun 2019
Term ends: Not estimatedThe source records don’t support an estimate.

Classification21 codes

B64C 21/10
Influencing air flow over aircraft surfaces by affecting boundary layer flow: using other surface properties, e.g. roughness
F01D 5/145
Shape, i.e. outer, aerodynamic form: means for influencing boundary layers or secondary circulations
F01D 5/147
Form or construction: construction, i.e. structural features, e.g. of weight-saving hollow blades
F01D 9/041
Forming ring or sector: using blades

Family

US 11,220,326 B2Related patent
US 2019/0168862 A1This patent

From the US filing history. Foreign family members aren’t listed.

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