Aero engine flow rate
AssigneeROLLS-ROYCE plc
InventorsRichard G. Stretton, Michael C. Willmot
Life of this patent
Estimating the term…
Abstract
A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio of: the turbine diameter at an axial location of the lowest pressure rotor stage a distance from a ground plane to the wing is in the range from 0.2 to 0.3.
Claims18
A gas turbine engine for an aircraft mounted beneath a wing of the aircraft, the engine comprising:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the turbine comprising a lowest pressure rotor stage, the turbine having a turbine diameter;
- a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub;
- and
- a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft,
- wherein a downstream blockage ratio of:
- the
-
-
- turbine
-
-
- diameter
-
-
- at
-
-
- an
-
-
- axial
- location
-
-
- of
-
-
- the
-
-
- lowest
-
-
- pressure
-
-
- rotor
-
-
- stage
- a
-
-
- distance
-
-
- from
-
-
- a
-
-
- ground
-
-
- plane
-
-
- to
-
-
- the
-
-
- wing
- is in a range from 0.2 to 0.3.
An aircraft comprising a wing and a gas turbine engine mounted beneath the wing of the aircraft, the engine comprising:
- an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the turbine comprising a plurality of rotor stages including a lowest pressure rotor stage located furthest downstream, the turbine having a turbine diameter;
- a fan located upstream of the engine core, the fan comprising a plurality of fan blades;
- and
- a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft,
- wherein a downstream blockage ratio of:
- the
-
-
- turbine
-
-
- diameter
-
-
- at
-
-
- an
-
-
- axial
-
-
- location
-
-
- of
-
-
- the
-
- lowest
-
-
- pressure
-
-
- rotor
-
-
- stage
-
- a
-
-
- distance
-
-
- from
-
-
- a
-
-
- ground
-
-
- plane
-
-
- to
-
-
- the
-
-
- wing
- is in a range from 0.2 to 0.3.
Dependencies are inferred from the claim text.