Aircraft engine
AssigneeROLLS-ROYCE plc
InventorsBenjamin Mohankumar, Mark J. Wilson, Cesare A. Hall
Life of this patent
Estimating the term…
Abstract
An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric S, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, and L/D is between 0.2 and 0.45.
Claims16
An aircraft engine comprising:
- a fan, the fan having a diameter D, the fan including a plurality of fan blades, each fan blade having a sweep metric S and a leading edge, a forward-most portion on the leading edge of each fan blade being in a first reference plane;
- and
- a nacelle, comprising an intake portion upstream of the fan, a forward-most edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane;
- wherein the aircraft engine has a relative Mach number at a cruise design point condition Mrel from from 0.4 to 0.93 and L/D is from 0.2 to 0.45, and
- wherein the sweep metric S of each fan blade is from 0.2 to 0.9.
An aircraft engine comprising:
- a fan, the fan having a diameter D, the fan including a plurality of fan blades, each fan blade having a sweep metric S and a leading edge, a forward-most portion on the leading edge of each fan blade being in a first reference plane;
- and
- a nacelle, comprising an intake portion upstream of the fan, a forward-most edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane;
- wherein the aircraft engine has a relative Mach number at a cruise design point condition Mrel from 0.4 to 0.93 and L/D is from 0.2 to 0.45, and
- wherein the sweep metric S of each fan blade is from 0.25 to 0.9.
An aircraft engine comprising:
- a fan, the fan having a diameter D, the fan including a plurality of fan blades, each fan blade having a sweep metric S and a leading edge, a forward-most portion on the leading edge of each fan blade being in a first reference plane;
- and
- a nacelle, comprising an intake portion upstream of the fan, a forward-most edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane;
- wherein the aircraft engine has a relative Mach number at a cruise design point condition Mrel from 0.4 to 0.93 and L/D is from 0.2 to 0.45, and
- wherein the sweep metric S of each fan blade is from 0.30 to 0.9.
Dependencies are inferred from the claim text.