Outlet guide vane assembly for a turbofan engine

Patent metadata

Field	Value
Publication number	US-12018592-B1
Application number	US-202218086112-A
Country	US
Kind code	B1
Filing date	Dec 21, 2022
Priority date	Dec 21, 2022
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

A turbofan engine defining a circumferential direction is provided. The turbofan engine includes: a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including N OGV number of outlet guide vanes, the plurality of outlet guide vanes including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane, the first and second outlet guide vanes defining a gap spacing greater than 360 degrees divided by N OGV , and the pylon attachment location positioned outside of between the first and second outlet guide vanes along the circumferential direction.

First claim

We claim:

1. A turbofan engine defining a circumferential direction, the turbofan engine comprising:
a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction;
an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades;
an N OGV plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane;
wherein the plurality of unducted rotor blades includes N B number of unducted rotor blades, wherein N B is greater than N OGV ;
wherein the plurality of outlet guide vanes includes a cluster of outlet guide vanes defining a cluster spacing less than 360/N OGV and greater than or equal to 360/(N B +2); and

a circumferential gap extending from the first outlet guide vane to the second outlet guide vane wherein the circumferential gap is greater than 360 degrees divided by N OGV , and the pylon attachment location is located outside of the circumferential gap.

2. The turbofan engine of claim 1 , wherein the turbofan engine defines an acoustically sensitive location along the circumferential direction, wherein the acoustically sensitive location is positioned between the first and second outlet guide vanes, and wherein the acoustically sensitive location is positioned between a three o'clock position and a nine o'clock position.

3. The turbofan engine of claim 1 , wherein the turbofan engine defines an acoustically sensitive location along the circumferential direction, wherein the acoustically sensitive location is positioned between the first and second outlet guide vanes, and wherein the acoustically sensitive location is positioned between a five o'clock position and a seven o'clock position.

4. The turbofan engine of claim 1 , wherein the turbofan engine defines an acoustically sensitive location along the circumferential direction, wherein the acoustically sensitive location is positioned between the first and second outlet guide vanes, and wherein the acoustically sensitive location is positioned between a three o'clock position and a five o'clock position or between a seven o'clock position and a nine o'clock position.

5. The turbofan engine of claim 1 , wherein the cluster includes the first outlet guide vane.

6. The turbofan engine of claim 5 , wherein the cluster is a first cluster, wherein the plurality of outlet guide vanes includes a second cluster of outlet guide vanes defining a second cluster spacing less than 360/N OGV and greater than or equal to 360/(N B +2), and wherein the second cluster includes the second outlet guide vane.

7. The turbofan engine of claim 1 , wherein the gap spacing is at least 25% greater than the cluster spacing and up to 200% of the cluster spacing.

8. The turbofan engine of claim 1 , wherein the pylon attachment location is positioned at a 12 o'clock position.

9. The turbofan engine of claim 1 , wherein the plurality of outlet guide vanes are unshrouded outlet guide vanes.

10. A turbofan engine defining an axial direction, the turbofan engine comprising:
a turbomachine, the turbomachine defining a pylon attachment location along the axial direction;
an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades, the plurality of unducted rotor blades including N B number of unducted rotor blades; and
a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including N OGV number of outlet guide vanes which is less than N B , the plurality of outlet guide vanes including a first pair of outlet guide vanes defining a spacing less than 360/N OGV and greater than or equal to 360/(N B +2), wherein the pylon attachment location is aft of the plurality of outlet guide vanes.

11. The turbofan engine of claim 10 , wherein the spacing is greater than or equal to 360/(N B +1).

12. The turbofan engine of claim 10 , wherein the spacing is greater than or equal to 360/N B .

13. An aircraft comprising:
a fuselage;
a first wing extending from a first side of the fuselage and a second wing extending from a second side of the fuselage; and
a propulsion system comprising:
a first turbofan engine mounted to the first wing or the fuselage on the first side of the fuselage, the first turbofan engine defining a first circumferential direction and comprising a first unducted rotor assembly and a first plurality of outlet guide vanes positioned downstream of the first unducted rotor assembly, the first unducted rotor assembly including a first plurality of unducted rotor blades, wherein the first plurality of unducted rotor blades includes N B number of unducted rotor blades, wherein N B is greater than N OGV , wherein the first plurality of outlet guide vanes includes a first cluster of outlet guide vanes defining a first cluster spacing less than 360/N OGV and greater than or equal to 360/(N B +2):

a first gap spacing defined by the first plurality of outlet guide vanes and extending along the first circumferential direction, wherein the first gap spacing location is between a 2 o'clock position and a 7 o'clock position, the first gap spacing being greater than an average gap spacing of the first plurality of outlet guide vanes; and
a second turbofan engine mounted to the second wing or the fuselage on the second side of the fuselage, the second turbofan engine defining a second circumferential direction and comprising a second unducted rotor assembly and a second plurality of outlet guide vanes positioned downstream of the second unducted rotor assembly, the second unducted rotor assembly including a second plurality of unducted rotor blades, wherein the second plurality of unducted rotor blades includes N B number of unducted rotor blades, wherein N B is greater than N OGV , wherein the second plurality of outlet guide vanes includes a second cluster of outlet guide vanes defining a second cluster spacing less than 360/N OGV and greater than or equal to 360/(N B +2); and
a second gap spacing defined by the second plurality of outlet guide vanes and extending along the first circumferential direction, wherein the second gap spacing location is between a five o'clock position and a 10 o'clock position, the second gap spacing being greater than an average gap spacing of the second plurality of outlet guide vanes.

14. The aircraft of claim 13 , wherein the first gap location is between a three o'clock position and a six o'clock position, and wherein the second gap location is between a six o'clock position and a nine o'clock position.

15. The aircraft of claim 13 , wherein the first side of the fuselage is a port side of the fuselage, and wherein the second side of the fuselage is a starboard side of the fuselage.

16. The aircraft of claim 13 , wherein the first turbofan engine defines a first acoustically sensitive location along the first circumferential direction positioned at the first gap location, and wherein the second turbofan engine defines a second acoustically sensitive location along the first circumferential direction positioned at the second gap location.

17. The aircraft of claim 13 , wherein the first plurality of outlet guide vanes includes N OGV1 number of outlet guide vanes, wherein the first plurality of outlet guide vanes further includes a first outlet guide vane and a second outlet guide vane adjacent the first out

Assignees

• Gen Electric

Inventors

• Ramakrishnan Kishore
• Karve Ravish
• Carle Sara Elizabeth
• Wood Trevor Howard

Classifications

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2220/323

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

• F05D2250/37

  circumferential · CPC title