Duct for hot air

Claim 2

A duct within a hollow aerostructural component of an aircraft, the duct serving to convey hot air to a selected area on the inside surface of the skin of the component for preventing the accumulation of ice on the external surface of the skin in the selected area, wherein the duct is double-walled, in that it comprises an inner duct through which the hot air flows, an outer duct which contains the inner duct and which is connected to the periphery of an opening in the skin, thereby to contain such hot air as escapes from the inner duct, upon a rupture of the inner duct, and a door by which the opening in the skin is normally closed, which door is displaceable upon rupture of the inner duct, by the flow of hot air along the outer duct to the said opening, the displacement of the door serving to provide an indication of the rupture of the inner duct.

Claim 3

A duct as claimed in claim 1 including a hinge by which the door is connected to the skin, which hinge retains the open door to the skin after rupture of the inner duct has caused the door to open.

Claim 4

A duct as claimed in claim 2 including a spring-biased latch to retain the door in its normal closed position, prior to said rupture.

Claim 5

A duct within an inlet cowl of a turbo-fan engine of an aircraft, the duct serving to convey hot air to a selected area on the inside surface of the skin of the leading edge of the inlet cowl for preventing the accumulation of ice on the external surface of the skin in the selected area, wherein the duct is double-walled, in that it comprises an inner duct through which the hot air flows and an outer duct which contains the inner duct and which is connected to the periphery of an opening in the skin, thereby to contain such hot air as escapes from the inner duct, upon a rupture of the inner duct, and channel the said hot air so that it issues from the opening and thereby provides an indication of said rupture, and wherein the duct runs lengthwise of the inlet cowl and spans the space between a rear bulkhead and a front bulkhead for delivery of hot air to a spray ring in a cavity forward of the front bulkhead, the duct including at its forward end a pair of slidable sealing rings, one of which seals the duct to the spray ring, and the other of which seals the duct to the front bulkhead.

Claim 6

A duct within an inlet cowl of a turbo-fan engine of an aircraft, the duct serving to convey hot air to a selected area on the inside surface of the skin of the leading edge of the inlet cowl for preventing the accumulation of ice on the external surface of the skin in the selected area, wherein the duct is double-walled, in that it comprises an inner duct through which the hot air flows and an outer duct which contains the inner duct and which is connected to the periphery of an opening in the skin, thereby to contain such hot air as escapes from the inner duct, upon a rupture of the inner duct, and channel the said hot air so that it issues from the opening and thereby provides an indication of said rupture, and wherein the duct runs lengthwise of the inlet cowl and spans the space between a rear bulkhead and a front bulkhead for delivery of hot air to a spray ring in a cavity forward of the front bulkhead, the duct including at its forward end a pair of slidable sealing rings, one of which seals the duct to the spray ring, and the other of which seals the duct to the front bulkhead.

Claim 7

A duct as claimed in claim 4 including a seal carrier in which the sealing rings are mounted, which carrier itself seals the annular gap, between the inner duct and the outer duct, at the forward end of the duct.

Claim 8

A duct as claimed in claim 4, including an offtake duct with which the outer duct communicates and which branches laterally from the outer duct, and an outlet duct which is connected to the periphery of the said opening and to the offtake duct.