Axial turbomachine blade with platforms having an angular profile
AssigneeSafran Aero Boosters SA
InventorFrederick Thise
Life of this patent
Estimating the term…
Abstract
The present application relates to a splitter nose of an axial turbomachine designed to separate an annular flow into the turbomachine into a primary flow and a secondary flow for undergoing a thermodynamic cycle. The nose includes a de-icing device with a wall defining, at least partially, an annular channel. A hot oil stream created by the turbomachine circulates in this latter. The oil runs through the circular nose and de-ices it while itself getting cooled. The wall is located so as to form the leading edge of the said splitter nose. The wall is an open or closed strip such as a tube which can be fixed by bonding, welding or recessing. The present application also relates to a multi-flow turbomachine with splitter noses fitted with de-icing devices.
Claims14
A splitter nose of an axial turbomachine for separating an annular flow into a turbomachine into a primary flow and a secondary flow, the splitter nose comprising:
- an annular leading edge:
- guide walls for the primary and secondary flows, extending from the leading edge;
- and
- a leading edge de-icing channel extending annularly along the leading edge, the channel being configured to conduct a fluid;
- wherein the channel includes a wall forming the leading edge;
- wherein a cross-section of the wall of the de-icing channel has a closed contour;
- and
- wherein the wall of the de-icing channel is partially housed in a recess formed on the guide walls for the primary and secondary flows.
A compressor of an axial turbomachine comprising:
- a splitter nose configured to separate an annular flow entering the turbomachine into a primary flow and a secondary flow, the splitter nose comprising:
- an annular leading edge:
- guide walls for the primary and secondary flows, extending from the leading edge;
- and
- a leading edge de-icing channel extending annularly along the leading edge, the channel being configured to conduct a fluid;
- wherein the channel includes a wall forming the leading edge;
- wherein a cross-section of the wall of the de-icing channel has a closed contour;
- and
- wherein the wall of the de-icing channel is partially housed in a recess formed on the guide walls for the primary and secondary flows.
An axial turbomachine comprising:
- an inlet fan;
- and
- a compressor following the inlet fan, the compressor comprising:
- a splitter nose configured to separate an annular flow entering the turbomachine into a primary flow and a secondary flow, the splitter nose comprising:
- an annular leading edge:
- guide walls for the primary and secondary flows, extending from the leading edge;
- and
- a leading edge de-icing channel extending annularly along the leading edge, the channel being configured to conduct a fluid;
- wherein the channel includes a wall forming the leading edge;
- wherein a cross-section of the wall of the de-icing channel has a closed contour;
- and
- wherein the wall of the de-icing channel is partially housed in a recess formed on the guide walls for the primary and secondary flows.
Dependencies are inferred from the claim text.