Patent ID: 9657640
Date: 2017-05-23
CPC Classifications: B64D,F01D,F02C,F05D,Y02T,Y10T

Claim:
1. A splitter nose of an axial turbomachine configured to separate a flow entering the axial turbomachine into a primary flow and a secondary flow, the splitter nose comprising: a generally circular leading edge; an outer annular wall extending from the generally circular leading edge and bounding the secondary flow said outer annular wall comprising a support wall and a constant thickness sheet attached to the support wall at an aft edge of the constant thickness sheet; an inner annular wall extending from the generally circular leading edge and bounding the primary flow, said inner annular wall connecting with said outer annular wall proximal to the generally circular leading edge; wherein the constant thickness sheet defines an outer boundary of at least one duct for a de-icing fluid for the splitter nose extending substantially axially along the outer annular wall and opening into the primary flow; wherein an inner boundary of the at least one duct is substantially parallel to the constant thickness sheet, the inner boundary of the at least one duct comprising one of the support wall or a second annular sheet; and wherein the generally circular leading edge of the splitter nose is formed by the constant thickness sheet.