Patent ID: 7931235

Claim:
A system for deicing the leading edge of a nose inlet cowl for a turbine engine of an aircraft, said leading edge being hollow and defining an annular chamber closed by a first internal bulkhead, and said deicing system comprising: a pressurized hot air supply duct designed to be connected, at its rear end opposed to said leading edge, to a pressurized hot air circuit and, at its front end toward said leading edge, to an injector injecting said pressurized hot air into said annular chamber of the leading edge, said supply duct passing through a compartment of said nose inlet cowl that is defined, at the front, by said first internal bulkhead and, at the rear, by a second internal bulkhead; an internal protective envelope arranged in said compartment and defining an isolation volume enclosing said supply duct; and two elements, a first of said two elements formed by said supply duct and by said protective envelope is longitudinally rigid, and a second of said two elements comprises at least two parts nested one inside the other and configured to slide relative to one another in a sealed manner, wherein said two elements are, on one side, rigidly fastened to one of said first and second internal bulkheads, and, on the other side, said two elements are rigidly connected to one another and are designed to slide jointly relative to a sliding bearing provided in the other of said first and second internal bulkhead, said sliding bearing comprising a stop designed to limit the sliding movement of said supply duct and of said protective envelope toward the outside of said compartment.