Bifurcated air inlet housing for a miniature gas turbine engine
A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.
1. A gas turbine engine comprising:
a nose cone including a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of said nose cone upstream end, said inlet housing including a mixing portion downstream of the housing upstream end which mixes airflow from separate flow paths; and
a rotor and a turbine driving a shaft to drive the rotor, said shaft including a bearing mounted at a location downstream of said nose cone upstream end;
wherein the airflow in the mixing portion generally surrounds 360 degrees of a rotational axis of the gas turbine engine; and
wherein said gas turbine engine is a miniature gas turbine engine.
2. The gas turbine engine as set forth in claim 1 , wherein said gas turbine engine delivers less than or equal to 180 lbf. of thrust.
3. The gas turbine engine as set forth in claim 1 , wherein said gas turbine engine is of an axial length less than 15 inches (38.1 centimeters) in length from said upstream end to a downstream end.
4. The gas turbine engine as set forth in claim 1 , wherein there are two of said plurality of separate flow paths.
5. The gas turbine engine as set forth in claim 4 , wherein said inlet housing defines two spaced flow areas to separate said separate flow paths, with said flow areas having semi-cylindrical radially inner boundaries and generally rectangular radially outer boundaries, and said two spaced flow areas separated by webs, which support said bearing within an outer housing portion, and said mixing portion is downstream of said webs.
6. An aircraft comprising:
a fuselage including at least two scoop inlets for delivering inlet air to an included gas turbine engine;
said gas turbine engine including a nose cone including a nose cone upstream end, and an inlet housing including at least two separate flow paths at a housing upstream end which is downstream of said nose cone upstream end, said inlet housing including a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths; and
a rotor and a turbine driving a shaft to drive the rotor, with said shaft including a bearing mounted at a location downstream of said nose cone upstream end;
wherein the airflow in the mixing portion generally surrounds 360 degrees of a rotational axis of the gas turbine engine; and
wherein said gas turbine engine is a miniature gas turbine engine.
7. The aircraft as set forth in claim 6 , wherein said gas turbine engine delivering less than or equal to 180 lbf. of thrust.
8. The aircraft as set forth in claim 6 , wherein said gas turbine engine is of an axial length less than 15 inches (38.1 centimeters) in length from said upstream end to a downstream end.
9. The aircraft as set forth in claim 6 , wherein there are two of said plurality of separate flow paths.
10. The aircraft as set forth in claim 9 , wherein said inlet housing defines two spaced flow areas to separate said separate flow paths, with said flow areas having semi-cylindrical radially inner boundaries and generally rectangular radially outer boundaries, and said two spaced flow areas separated by webs which support said bearing within said outer housing portion and said mixing portion is downstream of said webs.