Patent ID: 7765808

Claim:
A fuel manifold assembly for a gas turbine engine comprising an annular fuel manifold having at least one circumferential fuel conveying passage in fluid flow communication with a fuel inlet to the fuel manifold, the fuel conveying passage defining at least one slow fuel flowing location disposed diametrically opposite to said inlet, a heat shield at least partly enclosing the fuel manifold, the heat shield comprising a front segment and a rear segment axially aft of the front segment, the front and rear heat shield segments being independently attached to the fuel manifold by front segment joints and rear segment joints respectively, the front segment joints and the rear segment joints being disposed in alternating relation about a circumference of the fuel manifold, the fuel manifold defining four equal quadrants with a center point coincident with a center of the annular fuel manifold, the slow fuel flowing location being located between a first two of the quadrants and the fuel inlet being located between a remaining two of the quadrants, and wherein one or more of the front segment joints and one or more of the rear segment joints are disposed in each of said four quadrants at circumferentially adjacent locations furthest from said slow fuel flowing location within each said quadrant.