Gas turbine engine fan
AssigneeGeneral Electric Company
InventorRollin George Giffin, III
Life of this patent
Estimating the term…
Abstract
An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide vanes, a first stage of first fan rotor blades, a stage of first variable angle stator vanes, and a fan bleed. The inlet guide vanes are angled to block the linear line of sight of the rotating fan blades through the inlet and include a RAM treatment which preferably is a coating of a radar absorbing material on the surface of the inlet guide vanes. The exemplary embodiment has a multi-stage fan section with the mid-stage fan bleed disposed between the first and second stages of fan rotor blades.
Claims9
A fan section for an aircraft gas turbine engine, said fan section comprising:
- in direct serial flow relationship;
- an inlet having fixed angle high swirl angle inlet guide vanes,
- a first stage of first fan rotor blades,
- a stage of first variable angle stator vanes, and
- said inlet guide vanes are angled to block the linear line of sight of said fan blades through the inlet and have a radar absorbing material treatment.
A gas turbine engine comprising:
- a multi-stage fan section having in direct serial flow relationship;
- an inlet having fixed angle high swirl angle inlet guide vanes,
- a first stage of first fan rotor blades,
- a stage of first variable angle stator vanes, and
- wherein said inlet guide vanes are angled to block the linear line of sight of said fan blades through the inlet and have a radar absorbing material treatment.
Dependencies are inferred from the claim text.