Splitter for aeronautic turbomachine
AssigneeSafran Aircraft Engines
InventorsDamien Daniel Sylvain Lourit, Adrien Jacques Philippe Fabre, Pierre Jean-Baptiste Metge
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Abstract
A splitter between a primary flow and a secondary flow of a dual flow turbomachine includes a single-piece structure including an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle.
Claims10
A splitter between a primary flow and a secondary flow of a dual flow turbomachine, wherein the splitter is formed by additive manufacturing and has a single-piece structure comprising an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle,
- wherein the splitter has at least one radial or axial rib between the radial annular wall and the inner annular baffle arranged for guiding a flow of hot air during operation of the splitter and for providing mechanical strength of the splitter during manufacturing of the splitter.
A splitter between a primary flow and a secondary flow of a dual flow turbomachine, wherein the splitter is formed by additive manufacturing and has a single-piece structure comprising an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle,
- wherein the splitter comprises at least one air cell formed at least partially in the radial annular wall.
A straightener for an aeronautical turbomachine having a single-piece structure comprising an inner ferrule, vanes, and a splitter formed by additive manufacturing, wherein the splitter has:
- a single-piece structure comprising an outer annular wall, an inner annular wall, a radial annular wall, and an inner annular baffle,
- a first cavity between the outer annular wall and the inner annular baffle, and
- a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle, and
- at least one radial or axial rib between the radial annular wall and the inner annular baffle arranged for guiding a flow of hot air during operation of the splitter and for providing mechanical strength of the splitter during manufacturing of the splitter.
Dependencies are inferred from the claim text.