Abstract: A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.

Abstract: A turbomachine rotor blade is formed of plural blade sections stacked along an axis extending from a blade root to a blade tip. Each blade section located at various heights along the blade is designed to have a given ratio between a maximum thickness, which is measured between a suction side and pressure side of the blade, and a chord, which is defined by a line connecting a leading edge and a trailing edge of the blade. Each blade section is further designed to have a ratio of the maximum thickness to the chord at a given height of the blade relative to a ratio of the maximum thickness to the chord of another blade section located at a different height of the blade.

Abstract: An acoustic treatment panel intended to be disposed on at least one wall of a turbojet in contact with a fluid flow, the panel comprising a first sheet, a second sheet parallel to the first sheet and having a first face intended to be in contact with a fluid flow and a second face facing the first sheet, and acoustic treatment cells extending between the first and second sheets and each including an enclosure and a cavity delimited by the enclosure. The enclosure of each cell comprises two openings facing one another, at least one of the openings being coincident with an opening of the enclosure of an adjacent cell.

Abstract: A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.

Abstract: The invention relates to a turbomachine rotor blade which is characterized in that:—the ratio between the maximum thickness and the chord at 30% of the height of the blade is between 20% and 42% of the ratio between the maximum thickness and the chord at the blade root,—the ratio between the maximum thickness and the chord at 70% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root,—the ratio between the maximum thickness and the chord at 90% of the height of the blade is between 10% and 30% of the ratio between the maximum thickness and the chord at the blade root,—the ratio between the maximum thickness and the chord at the blade head is between 3% and 21% of the ratio between the maximum thickness and the chord at the blade root.

Abstract: A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge (16) and a trailing edge (17) and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that: the ratio of the chord at mid-height and of the chord at the blade root is comprised between 140% and 160%; the ratio of the chord at the blade tip and of the chord at the blade root is comprised between 115% and 135%; the chord is locally constant in a blade root zone and in a blade mid-height zone.

Abstract: A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge (16) and a trailing edge (17) and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that: the ratio of the chord at mid-height and of the chord at the blade root is comprised between 140% and 160%; the ratio of the chord at the blade tip and of the chord at the blade root is comprised between 115% and 135%; the chord is locally constant in a blade root zone and in a blade mid-height zone.