Patent ID: 9341075
Filing Date: 2016-05-17
CPC Classification: F01D,F02C,F02K,Y02T

Claim Text:
1. A device for use with a gas turbine engine having a turbine exhaust case and a low pressure turbine case upstream from the turbine exhaust case, the device comprising: a variable area mixing plane device located upstream of the turbine exhaust case and downstream from the low pressure turbine case configured to selectively mix a core flow and a fan flow; a swirl inducing vane in the path of the fan flow for inducing swirl in the fan flow, the swirl inducing vane directing fan flow to a mixing cavity upstream of the turbine exhaust case; a core flow source for introducing the core flow into the mixing cavity to mix the core and fan flows and direct the mixed flow to the turbine exhaust case; an augmentor downstream of the turbine exhaust case, wherein the augmentor injects fuel into the mixed flow downstream from the turbine exhaust case; a duct having a substantially annular cross-section formed by a radially outward surface of a core engine case and a radially inward surface of an outer fan case concentric with the core engine case and the turbine exhaust case, wherein a portion of the duct is downstream from the augmentor; and a splitter mounted proximate the swirl inducing vane that divides the fan flow between the duct and an inlet to the variable area mixing plane device, wherein the flow within the duct cools the core engine case during operation of the augmentor.