# US 12,180,896 B2 · Gearbox efficiency rating for turbomachine engines

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- Number: US 12,180,896 B2
- Document ID: US12180896B2
- Status: Granted
- Kind: B2
- Application number: 18/419,892
- Filed: 2024-01-23
- Published: 2024-07-18
- Granted: 2024-12-31
- Earliest claimed: 2020-08-04
- Assignees: GE Avio S.r.l.
- Applicants: GE Avio S.r.l.
- Inventors: Pietro Molesini; Andrea Piazza; Fabio De Bellis
- Web page: https://patentgrep.com/patent/US12180896B2

## CPC

- F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H)
- F16H 57/08: of gearings with members having orbital motion
- F01D 25/18: Lubricating arrangements (of machines or engines in general F01M)
- F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M)
- F02K 3/06: with front fan
- F05D 2220/32: in gas turbines
- F05D 2260/4031: as in toothed gearing
- F05D 2260/40311: of the epicyclical, planetary or differential type
- F05D 2260/98: Lubrication
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F16H: GEARING
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can 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. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0.

## Claims

### Claim 1

A turbomachine engine comprising:
a fan assembly including a plurality of fan blades arranged in a single row, wherein the fan blades comprise a diameter (D);
a vane assembly including a plurality of vanes, wherein the vane assembly is disposed aft of the fan assembly and configured to receive bypass airflow from the fan assembly;
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 (GR) of the first rotational speed to the second rotational speed is within a range of 4.1-14.0; and
a net thrust (T) of the turbomachine engine measured in pounds force at the max takeoff condition is within a range of 12,000-30,000 pounds force,
wherein
0
.
0
⁢
3
⁢
4
⁢
(
G
⁢
R
1.5
)
(
D
1.56
T
)
1
.
5
⁢
3
>
5
,
and
wherein
0
.
0
⁢
1
⁢
5
⁢
(
G
⁢
R
1.4
)
(
D
1
.
5
⁢
6
T
)
1.53
<
5
⁢
5
.

### Claim 2 (depends on 1)

The turbomachine engine of claim 1, wherein
0
.
0
⁢
1
⁢
5
⁢
(
G
⁢
R
1.4
)
(
D
1.56
T
)
1.53
<
2
⁢
4
.

### Claim 3 (depends on 1)

The turbomachine engine of claim 1, wherein
0
.
0
⁢
1
⁢
5
⁢
(
GR
1.4
)
(
D
1.56
T
)
1
.
5
⁢
3
<
2
⁢
0
.

### Claim 4 (depends on 3)

The turbomachine engine of claim 3, wherein
0
.
0
⁢
3
⁢
4
⁢
(
GR
1
.
5
)
(
D
1.56
T
)
1
.
5
⁢
3
>
1
⁢
0
.

### Claim 5 (depends on 1)

The turbomachine engine of claim 1, further comprising a gearbox efficiency rating within a range of 0.19-1.8, wherein the gearbox efficiency rating is greater than 0.023 (GR1.5) and less than 0.034 (GR1.5).

### Claim 6 (depends on 5)

The turbomachine engine of claim 5, wherein the gear ratio is within a range of 4.1-6.9, and wherein the gearbox efficiency rating is within a range of 0.19-0.62.

### Claim 7 (depends on 5)

The turbomachine engine of claim 5, wherein the gear ratio is within a range of 7.0-9.9, and wherein the gearbox efficiency rating is within a range of 0.43-1.06.

### Claim 8 (depends on 5)

The turbomachine engine of claim 5, wherein the gear ratio is within a range of 10.0-12.9, and wherein the gearbox efficiency rating is within a range of 0.73-1.58.

### Claim 9 (depends on 5)

The turbomachine engine of claim 5, wherein the gear ratio is within a range of 13.0-14.0, and wherein the gearbox efficiency rating is within a range of 1.08-1.8.

### Claim 10 (depends on 1)

The turbomachine engine of claim 1, wherein the fan blades comprise a diameter within a range of 120-216 inches.

### Claim 11 (depends on 1)

The turbomachine engine of claim 1, wherein the fan blades comprise a diameter within a range of 120-192 inches.

### Claim 12 (depends on 1)

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.

### Claim 13 (depends on 1)

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.

### Claim 14

A turbomachine engine comprising:
a fan assembly including a plurality of fan blades arranged in a single row, wherein the fan blades comprise a diameter (D) within a range of 72-120 inches;
a vane assembly including a plurality of vanes, wherein the vane assembly is disposed aft of the fan assembly and configured to receive bypass airflow from the fan assembly;
a core engine including a low-pressure compressor comprising 1-8 stages, a high-pressure compressor comprising 8-15 stages, a combustor, a high-pressure turbine comprising 1-2 stages, and a low-pressure turbine comprising 3-7 stages;
a gearbox including an input and an output, wherein the input is coupled to the low-pressure turbine 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 (GR) of the first rotational speed to the second rotational speed is within a range of 4.1-14.0; and
a net thrust (T) of the turbomachine engine measured in pounds force at the max takeoff condition,
wherein
0
.
0
⁢
3
⁢
4
⁢
(
GR
1
.
5
)
(
D
1.56
T
)
1
.
5
⁢
3
>
5
,
and
⁢
wherein
0
.
0
⁢
1
⁢
5
⁢
(
GR
1.4
)
(
D
1.56
T
)
1
.
5
⁢
3
<
5
⁢
5
.

### Claim 15 (depends on 14)

The turbomachine engine of claim 14, wherein
0
.
0
⁢
1
⁢
5
⁢
(
GR
1.4
)
(
D
1.56
T
)
1
.
5
⁢
3
<
2
⁢
4
.

### Claim 16 (depends on 14)

The turbomachine engine of claim 14, wherein
0
.
0
⁢
1
⁢
5
⁢
(
GR
1.4
)
(
D
1.56
T
)
1
.
5
⁢
3
<
2
⁢
0
.

### Claim 17 (depends on 16)

The turbomachine engine of claim 16, wherein
0
.
0
⁢
3
⁢
4
⁢
(
GR
1
.
5
)
(
D
1.56
T
)
1
.
5
⁢
3
>
1
⁢
0
.

### Claim 18 (depends on 14)

The turbomachine engine of claim 14, wherein the gear ratio is within a range of 4.1-6.9, and further comprising a gearbox efficiency rating within a range of 0.19-0.62, wherein the gearbox efficiency rating is greater than 0.023 (GR1.5) and less than 0.034 (GR1.5).

### Claim 19 (depends on 14)

The turbomachine engine of claim 14, wherein the net thrust is within a range of 12,000-30,000 pounds force.

### Claim 20

A turbomachine engine comprising:
a fan assembly including a plurality of fan blades arranged in a single row, wherein the fan blades comprise a diameter (D) within a range of 72-120 inches;
a vane assembly including a plurality of vanes, wherein the vane assembly is disposed aft of the fan assembly and configured to receive bypass airflow from the fan assembly;
a core engine including a low-pressure compressor comprising exactly 3 stages, a high-pressure compressor comprising exactly 9 stages, a combustor, a high-pressure turbine comprising exactly 2 stages, and a low-pressure turbine comprising exactly 4 stages;
a gearbox including an input and an output, wherein the input is coupled to the low-pressure turbine 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 (GR) of the first rotational speed to the second rotational speed is within a range of 4.1-6.9; and
a net thrust (T) of the turbomachine engine measured in pounds force at the max takeoff condition,
wherein
0
.
0
⁢
3
⁢
4
⁢
(
G
⁢
R
1.5
)
(
D
1.56
T
)
1
.
5
⁢
3
>
5
,
and
wherein
0
.
0
⁢
1
⁢
5
⁢
(
G
⁢
R
1.4
)
(
D
1
.
5
⁢
6
T
)
1.53
<
5
⁢
5
.