Patent ID: 8647057

Claim:
An exhaust diffuser for a turbine engine comprising: an inner boundary; an outer boundary defined by a diffuser shell, the outer boundary being radially spaced from the inner boundary so that a flow path for guiding an exhaust flow is defined therebetween, the outer boundary having a radially inwardly extending region in which the outer boundary extends radially inwardly toward the inner boundary; and at least one gas jet including a jet exit located on the inner boundary, upstream from a downstream end of the inner boundary, the downstream end of the inner boundary extending radially inwardly in a downstream direction from the jet exit, the jet exit discharging a flow of gas downstream substantially parallel to an outer surface of the inner boundary, wherein the flow of gas exits the gas jet in the downstream direction tangential to the inner boundary at a velocity greater than a local exhaust flow velocity in the diffuser at the jet exit to produce a Coanda effect and to direct a portion of the exhaust flow in the diffuser toward the inner boundary.