FLUID COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE AND METHOD

摘要

A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.

主权项

1. A fluid cooling arrangement of a gas turbine engine for aerospace propulsion, the fluid cooling arrangement comprising:
an inner structure; an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path; at least one strut operatively coupling the inner structure to the outer structure; and at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.