Rectifier for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction
AssigneeSafran Aircraft Engines
InventorClément Simon Martin Lemaire
Life of this patent
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Abstract
The invention relates to a rectifier (1) for an aircraft turbomachine compressor, the rectifier comprising an inner ferrule (24), an outer ferrule (26), and stator blades (28) secured to the inner and outer ferrules, the rectifier also comprising a flange (34) secured to a downstream end of the outer ferrule (26) and designed to be fixed to a compressor housing (36), the flange being provided with air extraction openings (50) arranged at a distance from each other in a peripheral direction (52). According to the invention, at least one of the air extraction openings (50) has a stretched form in the peripheral direction (52).
Claims15
A rectifier for an aircraft turbomachine compressor, said rectifier comprising an inner ferrule, an outer ferrule and stator vanes rigidly connected to the inner and outer ferrules said rectifier further comprising a flange rigidly connected to a downstream end of the outer ferrule and for attachment to a compressor casing, said flange being provided with air intake ports spaced from each other in a circumferential direction of the rectifier, wherein said flange is outwardly protruding from said outer ferrule and said air intake ports are arranged through said flange at a location radially outside of said outer ferrule, and
- wherein at least one of the air intake ports has a shape stretched in the circumferential direction, and
- wherein both an inlet and an outlet of the air intake ports are outside a primary jet.
A rectifier sector for an aircraft turbomachine compressor, said rectifier sector having an inner ferrule sector, an outer ferrule sector as well as stator vanes rigidly connected to the inner and outer ferrule sectors, said rectifier sector further comprising a flange sector rigidly connected to a downstream end of the outer ferrule sector and intended to be attached to a compressor housing, said flange sector being provided with at least one air intake port,
- wherein said air intake port is centrally disposed on the flange sector in a circumferential direction of the rectifier sector, and has a shape oblong along said circumferential direction, and
- wherein both an inlet and an outlet of said air intake port are outside a primary jet.
A rectifier sector for an aircraft turbomachine compressor, said rectifier sector having an inner ferrule sector, an outer ferrule sector as well as stator vanes rigidly connected to the inner and outer ferrule sectors, said rectifier sector further comprising a flange sector rigidly connected to a downstream end of the outer ferrule sector and intended to be attached to a compressor housing,
- wherein said flange sector has a first circumferential end and a second circumferential end opposite the first end, said first end having a first portion of an air intake port and said second end having a second portion of another air intake port, the first and second port portions each being open outwardly in a circumferential direction of the rectifier sector, and in that the sum of the circumferential dimensions Dc1, Dc2 of the first and second portions of the ports is greater than the radial dimension Dr of each of them, and
- wherein both an inlet and an outlet of the air intake port are outside a primary jet.
Dependencies are inferred from the claim text.