Aircraft turbofan engine having variable pitch fan and method of over-pitching the variable pitch fan in an engine out condition to reduce drag

Patent metadata

Field	Value
Publication number	US-10954805-B2
Application number	US-201816022670-A
Country	US
Kind code	B2
Filing date	Jun 28, 2018
Priority date	Jun 28, 2018
Publication date	Mar 23, 2021
Grant date	Mar 23, 2021

Abstract

There is provided a turbofan engine for an aircraft. The turbofan engine has a core with a fan cowl and a variable pitch fan (VPF) configured to only rotate in a first rotation direction. The VPF has a plurality of fan blades each configured to over-pitch to an over-pitch position relative to a feathered position. The turbofan engine has outer guide vanes (OGVs) axially disposed downstream of the VPF, and has a rotation control device to prevent the VPF from rotating in a second rotation direction opposite the first rotation direction, during an engine out (EO) condition of the turbofan engine. When the VPF is prevented from rotating during the EO condition, the fan blades are over-pitched to the over-pitch position relative to the feathered position, to achieve no or minimal air flow separation about the OGVs, and to reduce drag of the turbofan engine during the EO condition.

First claim

What is claimed is:

1. A turbofan engine for an aircraft, the turbofan engine comprising:
a core with a fan cowl surrounding a portion of the core, the core having a first end and a second end;
a variable pitch fan (VPF) coupled to the first end of the core and configured to only rotate in a first rotation direction, the variable pitch fan having a plurality of fan blades extending radially outward from the core to the fan cowl, the plurality of fan blades each configured to over-pitch to an over-pitch position relative to a feathered position of the variable pitch fan;
a plurality of outer guide vanes (OGVs) axially disposed downstream of the variable pitch fan, each of the plurality of outer guide vanes (OGVs) being nonrotatable and extending radially outward from the core to the fan cowl; and
a rotation control device comprising a ratchet device, the rotation control device coupled to a portion of a central shaft aligned along a longitudinal center axis of the turbofan engine, and the central shaft, in turn, coupled to the variable pitch fan, the rotation control device preventing the variable pitch fan from rotating in a second rotation direction opposite the first rotation direction, during an engine out (EO) condition of the turbofan engine for the aircraft,
wherein when the variable pitch fan is prevented from rotating in the second rotation direction during the engine out (EO) condition, the plurality of fan blades are over-pitched to the over-pitch position relative to the feathered position, to achieve no or minimal air flow separation about the plurality of outer guide vanes (OGVs), and to reduce drag of the turbofan engine during the engine out (EO) condition.

2. The turbofan engine of claim 1 , wherein the turbofan engine comprises a very-high-bypass-ratio engine having a fan pressure ratio in a range of from 1.10 to 1.30.

3. The turbofan engine of claim 1 , wherein the turbofan engine comprises a low-fan-pressure-ratio engine having a length to diameter (L/D) ratio of the fan cowl of the turbofan engine in a range of from 0.6 to 1.0.

4. The turbofan engine of claim 1 , wherein each of the plurality of fan blades is configured to be over-pitched to the over-pitch position relative to the feathered position of the variable pitch fan, by an over-pitch in a range of from 1 degree over-pitch to 10 degrees over-pitch.

5. The turbofan engine of claim 1 , wherein the plurality of outer guide vanes (OGVs) comprise a total number of OGVs in a range of from 3 OGVs to 24 OGVs.

6. The turbofan engine of claim 1 , wherein the plurality of outer guide vanes (OGVs) each has a thickness to chord (t/c) ratio in a range of from 3% to 9%.

7. The turbofan engine of claim 1 , wherein the core is tapered at the second end, such that there is an annular bypass area reduction between a leading edge and a trailing edge of each of the plurality of outer guide vanes (OGVs).

8. The turbofan engine of claim 1 , wherein the plurality of outer guide vanes (OGVs) each has a root end coupled to the core and a tip end coupled to the fan cowl.

9. The turbofan engine of claim 1 , wherein the drag is reduced, and the turbofan engine has a reduced drag coefficient.

10. An aircraft comprising:
a fuselage;
a first wing and a second wing, each attached to the fuselage;
a first turbofan engine attached to the first wing and a second turbofan engine attached to the second wing, each turbofan engine comprising:
a core with a fan cowl surrounding a portion of the core, the core having a first end and a second end; and,
a drag reduction system comprising:
a variable pitch fan (VPF) coupled to the first end of the core and configured to only rotate in a first rotation direction, the variable pitch fan having a plurality of fan blades extending radially outward from the core to the fan cowl, the plurality of fan blades each configured to over-pitch to an over-pitch position relative to a feathered position of the variable pitch fan;
a plurality of outer guide vanes (OGVs) axially disposed downstream of the variable pitch fan, each of the plurality of outer guide vanes (OGVs) being nonrotatable and extending radially outward from the core to the fan cowl, and each of the plurality of outer guide vanes (OGVs) having a thickness to chord (t/c) ratio in a range of from 3% to 9%.; and
a rotation control device comprising a ratchet device, the rotation control device coupled to a portion of a central shaft aligned along a longitudinal center axis of the turbofan engine, and the central shaft, in turn, coupled to the variable pitch fan, the rotation control device preventing the variable pitch fan from rotating in a second rotation direction opposite the first rotation direction, during an engine out (EO) condition of one of, the first turbofan engine or the second turbofan engine, of the aircraft,

wherein when the variable pitch fan is prevented from rotating in the second rotation direction during the engine out (EO) condition, the plurality of fan blades are over- pitched to the over-pitch position relative to a feathered position, to achieve no or minimal air flow separation about the plurality of outer guide vanes (OGVs), and to reduce an engine out (EO) drag.

11. The aircraft of claim 10 , wherein the first turbofan engine and the second turbofan engine each comprises a very-high-bypass-ratio engine having a fan pressure ratio in a range of from 1.10 to 1.30.

12. The aircraft of claim 10 , wherein the first turbofan engine and the second turbofan engine each comprises a low-fan-pressure-ratio engine having a length to diameter (L/D) ratio of the fan cowl of each of the first turbofan engine and the second turbofan engine, in a range of from 0.6 to 1.0.

13. The aircraft of claim 10 , wherein the plurality of outer guide vanes (OGVs) comprise a total number of OGVs in a range of from 3 OGVs to 24 OGVs.

14. The aircraft of claim 10 , wherein each of the plurality of fan blades is configured to be over-pitched to the over-pitch position relative to the feathered position of the variable pitch fan, by an over-pitch in a range of from 1 degree over-pitch to 10 degrees over-pitch.

15. A method of over-pitching a variable pitch fan (VPF) of a turbofan engine of an aircraft in an engine out (EO) condition to reduce drag, the method comprising the steps of:
installing two or more turbofan engines on the aircraft, each turbofan engine comprising:
a core with a fan cowl surrounding a portion of the core, the core having a first end and a second end;
the variable pitch fan coupled to the first end of the core and configured to only rotate in a first rotation direction, the variable pitch fan having a plurality of fan blades extending radially outward from the core to the fan cowl, the plurality of fan blades each configured to over-pitch to an over-pitch position relative to a feathered position of the variable pitch fan;
a plurality of outer guide vanes (OGVs) axially disposed downstream of the variable pitch fan, each of the plurality of outer guide vanes (OGVs) being nonrotatable and extending radially outward from the core to the fan cowl; and
a rotation control device comprising a ratchet device, the rotation control device coupled to a portion of a central shaft aligned along a longitudinal center axis of the turbofan engine, and the central shaft, in turn, coupled to the variable pitch fan, the rotation control device preventing the variable pitch fan from rotating in a second rotation direction opposite the first rotation direction, in an engine out (EO) condition of at least one turbofan engine of the two or more turbofan engines of the aircraft,

Assignees

• Boeing Co

Inventors

• Vassberg John C
• Dehaan Mark
• Roman Dino L

Classifications

• F05D2220/323

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D7/00 Primary

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title

• F01D21/00 Primary

  Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for · CPC title