|국가/구분||United States(US) Patent 등록|
|§371/§102 date||20070531 (20070531)|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 0 인용 특허 : 71|
A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inwardly from the rear case. The exhaust mixer extends in a flow path of a combustor to mix a high energy gas stream from the combustor with bypass air from a bypass fan. The engine mounts are located on the periphery of the rear case for mounting the engine to an aircraft. The rear case, exit guide vanes, exhaust mixer, and en...
1. A tip turbine engine case assembly comprising: an engine support structure unitarily installable into an engine aft of a fan-turbine rotor assembly in the tip turbine engine, said engine support structure including an engine case disposed about an engine centerline, an engine mount aft of the fan-turbine rotor assembly, and an exit guide vane fixed to said engine case, said exit guide vane extending radially inwardly from said engine case. 2. The assembly as recited in claim 1, wherein said exit guide vane is fixed to said engine case with a welded jo...