Back to results
US 9,790,861 B2Granted
Gas turbine engine having support structure with swept leading edge
AssigneeUnited Technologies Corporation
InventorBrent Veiga
Life of this patent
Estimating the term…
Abstract
A gas turbine engine nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core casing defined about an axis; a fan nacelle mounted at least partially around the core nacelle; and a support structure extending radially from the core nacelle to the fan nacelle, wherein the support structure has a leading edge that is swept.
Claims12
A nacelle assembly for a gas turbine engine comprising:
- a core casing defined about an axis;
- a fan nacelle mounted at least partially around the core nacelle;
- a guide vane extending between the core casing and the fan nacelle;
- and
- a support structure extending radially from the core casing to the fan nacelle, wherein the support structure has a leading edge that is swept and the support structure is aft of the guide vane relative to the axis,
- wherein the leading edge has an angle relative to a radial axis of the gas turbine engine, the angle is from 10 degrees to 20 degrees, and
- wherein the support structure comprises an upper bifurcation and a lower bifurcation each defining a respective one of the leading edge, the angle of the leading edge corresponding to the upper bifurcation being different from the angle of the leading edge corresponding to the lower bifurcation.
4 more elements
A gas turbine engine comprising:
- a fan, a compressor section, a combustor section, and a turbine section, the turbine section configured to drive a shaft to rotatably drive the fan and the compressor;
- a geared architecture rotatably coupling the shaft and the fan;
- and
- a nacelle having an inner wall providing a bypass duct configured to receive bypass air from the fan, a support structure extending radially from a core of the gas turbine engine to the inner wall, the support structure having at least one leading-edge that is swept, and the support structure being downstream of a plurality of guide vanes in the bypass duct,
- wherein the at least one leading edge has an angle relative to a radial axis of the gas turbine engine, the angle is from 10 degrees to 20 degrees, and
- wherein the support structure comprises an upper bifurcation and a lower bifurcation each defining a respective one of the at least one leading edge, the angle of the at least one leading edge corresponding to the upper bifurcation being different from the angle of the at least one leading edge corresponding to the lower bifurcation.
3 more elements
A method of influencing flow within a gas turbine engine, comprising:
- providing a support structure within a bypass flowpath, the support structure having a swept leading edge downstream of a guide vane in the bypass flowpath,
- wherein the swept leading edge has an angle relative to a radial axis of the gas turbine engine, the angle is from 10 degrees to 20 degrees, and
- wherein the support structure comprises an upper bifurcation and a lower bifurcation each defining a respective one of the swept leading edge, the angle of the swept leading edge corresponding to the upper bifurcation being different from the angle of the swept leading edge corresponding to the lower bifurcation.
Dependencies are inferred from the claim text.