Patent ID: 7553130

Claim:
A compressor nozzle ring for an aircraft engine, said nozzle ring comprising: an inner shroud; an outer shroud; and a multiplicity of blades arranged circumferentially and extending radially from the inner shroud to the outer shroud, each of the blades passing through a corresponding aperture formed in the inner shroud and being attached to the inner shroud with sealing cement containing an organic polymer adhesive, wherein said adhesive is polyimide based; wherein end regions of the blades project radially inward beyond the inner shroud; wherein an insert disposed inside the inner shroud and in proximity to the inner shroud surrounds, in conjunction with the inner shroud and the blades, a continuous space along the inside of the inner shroud that is filled with said cement, and the continuous space filled with the cement continues without a gap between adjacent blades of the blades and around the end regions of the adjacent blades; and wherein said insert surrounds the end regions of the adjacent blades including a radially innermost area of the adjacent blades.