US 2020/0346779 A1Published application

Aero engine flow rate

AssigneeROLLS-ROYCE plc

InventorsRichard G. Stretton, Michael C. Willmot

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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 is: the   turbine   diameter   at   an   axial   location of   the   lowest   pressure   rotor   stage ground   plane   to   wing   distance and a quasi-non-dimensional mass flow rate Q defined as: Q = W  T  0 P   0 · A flow where: W is mass flow rate through the fan in Kg/s; T0 is average stagnation temperature of the air at the fan face in Kelvin; P0 is average stagnation pressure of the air at the fan face in Pa; and Aflow is the flow area of the fan face in m2, and wherein a Q ratio of: the downstream blockage ratio×Q is in a range from 0.005 to 0.01.

Claims19

Dependent claims

A gas turbine engine for an aircraft and arranged to be mounted beneath a wing of the aircraft, the engine having an engine length and 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, the hub and fan blades of the fan together defining a fan face having a fan tip radius;
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 is defined as:
the


turbine


diameter


at


an


axial


location
of


the


lowest


pressure


rotor


stage
ground


plane


to


wing


distance
and wherein an engine blockage ratio of:
(
2
×
the


fan


tip


radius

/

the


engine


length
)
the


downstream


blockage


ratio
is in the range from 2.5 to 4.

86 more elements

Dependencies are inferred from the claim text.

Facts

Application: 16/934,767Filed 21 Jul 2020
Priority: GB 1820930.421 Dec 2018
Published: 5 Nov 2020
Term ends: Not estimatedThe source records don’t support an estimate.

Classification15 codes

B64D 33/02
Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for: of combustion air intakes
B64D 27/12
Of gas-turbine type: within, or attached to, wings
F02C 7/04
Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for…:…
F02K 1/52
Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto: nozzles specially constructed…

Family

Application16/398,909Continuation · filed 30 Apr 2019
Application16/741,005Continuation · filed 13 Jan 2020
Application16/934,767Continuation
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From the US filing history. Foreign family members aren’t listed.