Patent ID: 7966823

Claim:
A gas turbine engine assembly having a core gas turbine engine and an augmentor assembly configured to be disposed axially aft of the core gas turbine engine, said augmentor assembly including a flow splitter apparatus comprising: an augmentor outer casing; an augmentor liner configured to be disposed radially within and radially spaced apart from said augmentor outer casing to define an augmentor liner cooling flow path between said augmentor casing and said annular augmentor liner; and an axially extending augmentor flow splitter duct disposed at the upstream end of said augmentor liner and radially between said augmentor outer casing and said annular augmentor liner within the augmentor liner cooling flow path and defining a splitter portion of the augmentor liner cooling flow path, wherein the splitter portion includes an axially forward open end and an axially aft open end such that air is permitted to flow axially through a screech suppression zone from the axially forward open end through the axially aft open end between said augmentor liner and said augmentor flow splitter duct.