Gearbox efficiency rating for turbomachine engines

Patent metadata

Field	Value
Publication number	US-2022042461-A1
Application number	US-202117344736-A
Country	US
Kind code	A1
Filing date	Jun 10, 2021
Priority date	Aug 4, 2020
Publication date	Feb 10, 2022
Grant date	—

Abstract

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

First claim

1 . A turbomachine engine comprising:
a fan assembly including a plurality of fan blades; a vane assembly including a plurality of vanes; a core engine including one or more compressor sections and one or more turbine sections; a gearbox including an input and an output, wherein the input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, wherein the output is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0; and a gearbox efficiency rating of 0.10-1.8, wherein the gearbox efficiency rating equals

Q
⁡

(

D
1.56

T

)

1.53

,

wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, and wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition.

2 . The turbomachine engine of claim 1 , wherein the gearbox efficiency rating is 0.10-1.01.

3 . The turbomachine engine of claim 1 , wherein the gearbox efficiency rating is 0.19-1.8.

4 . The turbomachine engine of claim 1 , wherein the gear ratio is within a range of 4.5-12.0.

5 . The turbomachine engine of claim 1 , wherein the gear ratio is within a range of 6.0-11.0.

6 . The turbomachine engine of claim 1 , wherein Q is within a range of 5-55 gallons per minute.

7 . The turbomachine engine of claim 1 , wherein Q is within a range of 6-36 gallons per minute.

8 . The turbomachine engine of claim 1 , wherein D is 120-216 inches.

9 . The turbomachine engine of claim 1 , wherein D is 120-192 inches.

10 . The turbomachine engine of claim 1 , wherein T is within a range of 10,000-100,000 pounds force.

11 . The turbomachine engine of claim 1 , wherein T is within a range of 12,000-30,000 pounds force.

12 . The turbomachine engine of claim 1 , wherein the gearbox is an epicyclic gearbox comprising a sun gear, a plurality of planet gears, and a ring gear, wherein the sun gear is the input, and wherein the ring gear is the output.

13 . The turbomachine engine of claim 1 , wherein the gearbox is an epicyclic gearbox comprising a sun gear, a plurality of planet gears, and a ring gear, wherein the sun gear is the input, wherein the planet gears are coupled to a planet carrier, and wherein the planet carrier is the output.

14 . The turbomachine engine of claim 1 , wherein the gearbox is a multi-stage gearbox.

15 . The turbomachine engine of claim 1 , wherein the gearbox is a two-stage gearbox.

16 . The turbomachine engine of claim 1 , wherein the gearbox is a compound gearbox.

17 . A turbomachine engine comprising:
a fan assembly including a plurality of fan blades; a vane assembly including a plurality of vanes; a core engine including a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine; a gearbox including an input and an output, wherein the input is coupled to the low-pressure turbine and comprises a first rotational speed, wherein the output is coupled to the fan assembly and has a second rotational speed, and wherein a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.5-14.0; and a gearbox efficiency rating of 0.12-1.8, wherein the gearbox efficiency rating equals Q(D{circumflex over ( )}1.56/T){circumflex over ( )}1.53, wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, and wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition.

18 . The turbomachine engine of claim 17 , wherein Q is within a range of 5-55 gallons per minute, wherein D is 120-216 inches, and wherein T is within a range of 10,000-100,000 pounds force.

19 . The turbomachine engine of claim 17 , wherein the gearbox is an epicyclic gearbox comprising a star gear configuration.

20 . The turbomachine engine of claim 17 , wherein the gearbox is an epicyclic gearbox comprising a planet gear configuration.

21 . The turbomachine engine of claim 17 , wherein the fan assembly comprises 8-20 fan blades, wherein the low-pressure compressor comprises 1-8 stages, wherein the high-pressure compressor comprises 8-15 stages, wherein the high-pressure turbine comprises 1-2 stages, and the low-pressure turbine comprises 3-7 stages.

22 . A turbomachine engine comprising:
a fan assembly including a plurality of fan blades; a vane assembly including a plurality of vanes; a core engine including a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine; and a gearbox comprising a gear ratio within a range of 6.0-12.0 and a gearbox efficiency rating of 0.18-1.41.

23 . The turbomachine engine of claim 22 , wherein a gearbox oil flow rate at an inlet of the gearbox is within a range of 5-55 gallons per minute at a max takeoff condition.

24 . The turbomachine engine of claim 22 , wherein a diameter of the fan blades is 120-216 inches.

25 . The turbomachine engine of claim 22 , wherein a net thrust of the turbomachine engine is within a range of 10,000-100,000 pounds force at a max takeoff condition.

26 . A turbomachine engine comprising:
a fan assembly including a plurality of fan blades; a vane assembly including a plurality of vanes; a core engine including one or more compressor sections and one or more turbine sections; a gearbox including an input and an output, wherein the input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, and wherein the output is coupled to the fan assembly and has a second rotational speed; and a gearbox efficiency rating of 0.10-1.8, wherein the gearbox efficiency rating equals

Q
⁡

(

D
1.56

T

)

1.53

,

wherein Q is a gearbox oil flow rate at an inlet of the gearbox measured in gallons per minute at a max takeoff condition, wherein D is a diameter of the fan blades measured in inches, and wherein T is a net thrust of the turbomachine engine measured in pounds force at the max takeoff condition.

27 . The turbomachine engine of claim 26 , wherein the gearbox is an epicyclic gearbox comprising a gear rat

Assignees

• Ge Avio Srl

Inventors

• Molesini Pietro
• Piazza Andrea
• De Bellis Fabio

Classifications

• F16H57/02

  Gearboxes; Mounting gearing therein · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2260/4031

  as in toothed gearing · CPC title