Nacelle for gas turbine engine and aircraft comprising the same

Patent metadata

Field	Value
Publication number	US-11408306-B2
Application number	US-202117152075-A
Country	US
Kind code	B2
Filing date	Jan 19, 2021
Priority date	Feb 13, 2020
Publication date	Aug 9, 2022
Grant date	Aug 9, 2022

Abstract

A nacelle for housing a fan within a gas turbine engine having a longitudinal centre line includes a leading edge and a trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. An azimuthal angle (θ) is defined about the longitudinal centre line. The nacelle length (Lnac) varies azimuthally. The nacelle length (Lnac) decreases azimuthally from an inboard end of the nacelle to an outboard end of the nacelle.

First claim

We claim:

1. A nacelle for a housing a fan within a gas turbine engine, the nacelle having a longitudinal centre line and comprising:
a leading edge and a trailing edge; and
a nacelle length (L nac ) defined as an axial distance between the leading edge and the trailing edge;
wherein an azimuthal angle (θ) is defined about the longitudinal centre line, and wherein the nacelle length (L nac ) varies azimuthally; and
wherein the nacelle length (L nac ) decreases azimuthally from an inboard end of the nacelle to an outboard end of the nacelle.

2. The nacelle of claim 1 , wherein the nacelle length (L nac ) varies as a function of the azimuthal angle (θ).

3. The nacelle of claim 2 , wherein the nacelle length (L nac ) has a maximum value (L 1 ) at the inboard end of the nacelle.

4. The nacelle of claim 2 , wherein the nacelle length (L nac ) has a minimum value (L 2 ) at the outboard end of the nacelle.

5. The nacelle of claim 1 , further comprising:
an intermediate plane defined between the leading edge and the trailing edge, wherein the intermediate plane is substantially normal to the longitudinal centre line and includes a maximum radius (r max ) of an outer surface of the nacelle with respect to the longitudinal centre line; and
wherein the radius of the outer surface in the intermediate plane varies azimuthally.

6. The nacelle of claim 5 , wherein the radius of the outer surface in the intermediate plane varies azimuthally as a function of the azimuthal angle (θ).

7. The nacelle of claim 5 , further comprising a fan casing disposed downstream of the leading edge, wherein the intermediate plane axially bisects the fan casing.

8. The nacelle of claim 1 , wherein a highlight radius (r hi ) is defined at the leading edge of the nacelle, and wherein a ratio of the nacelle length (L nac ) to the highlight radius (r hi ) is greater than 2.4 and less than 3.6.

9. A gas turbine engine for an aircraft, the gas turbine engine comprising:
the nacelle of claim 1 ;
a fan received within the nacelle; and
an engine core received within the nacelle.

10. An aircraft comprising the gas turbine engine of claim 9 , the aircraft further comprising:
a fuselage; and
at least one wing extending from the fuselage;
wherein the nacelle is attached to the at least one wing.

Assignees

• Rolls Royce Plc

Inventors

• Tejero Embuena Fernando L
• Macmanus David G
• Sheaf Christopher T J

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B64D27/12

  within, or attached to, wings · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• B64D33/02

  of combustion air intakes · CPC title