Gearbox efficiency rating for turbomachine engines
View Patent ↗A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. 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.
1. A turbomachine engine comprising:
a fan case;
a fan assembly disposed radially within the fan case and comprising a plurality of fan blades;
a pitch change mechanism coupled to the fan assembly and configured to adjust a pitch of the fan blades;
a core engine including a low-pressure turbine;
a vane assembly including a plurality of vanes, wherein the vanes are disposed aft of the fan blades and extend radially outwardly from the core engine to the fan case;
a gearbox coupled to the low-pressure turbine and the fan assembly, wherein the gearbox is configured such that a ratio of a first rotational speed of the low-pressure turbine to a second rotational speed of the fan assembly 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 pitch change mechanism is a first pitch change mechanism, and wherein the turbomachine engine further comprises a second pitch change mechanism coupled to the vane assembly and configured to adjust a pitch of the vanes.
3. The turbomachine engine of claim 1 , wherein the gearbox efficiency rating is 0.25-1.5.
4. The turbomachine engine of claim 1 , wherein the ratio of the first rotational speed of the low-pressure turbine to the second rotational speed of the fan assembly is within a range of 4.5-12.0.
5. The turbomachine engine of claim 1 , wherein the ratio of the first rotational speed of the low-pressure turbine to the second rotational speed of the fan assembly 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 D is 120-216 inches.
8. The turbomachine engine of claim 1 , wherein T is within a range of 10,000-100,000 pounds force.
9. 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 coupled to the low-pressure turbine, and wherein the ring gear is coupled to the fan assembly.
10. 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 coupled to the low-pressure turbine, wherein the planet gears are coupled to a planet carrier, and wherein the planet carrier is coupled to the fan assembly.
11. The turbomachine engine of claim 1 , wherein the gearbox is a multi-stage gearbox.
12. The turbomachine engine of claim 1 , wherein the gearbox is a compound gearbox.
13. A turbomachine engine comprising:
a fan case;
a fan assembly housed within the fan case and comprising a plurality of fan blades;
a pitch change mechanism coupled to the fan assembly;
a vane assembly housed within the fan case and comprising a plurality of vanes configured to receive bypass airflow from the fan blades;
a core engine comprising a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine;
a gearbox coupled to the low-pressure turbine and the fan assembly, wherein the gearbox comprises a gear ratio of 4.1-14.0 and is configured such that the fan assembly rotates slower than one or more stages of the low-pressure turbine; 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.
14. The turbomachine engine of claim 13 , wherein the gearbox efficiency rating is 0.10-1.01.
15. The turbomachine engine of claim 13 , wherein the gearbox efficiency rating is 0.19-1.8.
16. The turbomachine engine of claim 13 , wherein Q is within a range of 6-36 gallons per minute.
17. The turbomachine engine of claim 13 , wherein D is 140-192 inches.
18. The turbomachine engine of claim 13 , wherein T is within a range of 10,000-40,000 pounds force, wherein the fan assembly comprises 8-14 fan blades, wherein the low-pressure compressor comprises 1-2 stages, wherein the high-pressure compressor comprises 10-11 stages, wherein the high-pressure turbine comprises two stages, wherein the low-pressure turbine comprises 6-7 stages.
19. A turbomachine engine comprising:
a fan case;
a fan assembly comprising a plurality of fan blades disposed within the fan case;
a pitch change mechanism coupled to the fan assembly;
a core engine comprising a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine;
a vane assembly comprising a plurality of vanes disposed radially outwardly of the core engine and radially aligned with the fan assembly;
a gearbox coupled to the low-pressure turbine and the fan assembly, wherein the gearbox comprises a gear ratio of 6.0-12.0 and is configured such that a first rotational speed of the fan assembly is less than a second rotational speed of the low-pressure turbine; and
a gearbox efficiency rating of 0.18-1.41.
20. The turbomachine engine of claim 19 , wherein a gearbox oil flow rate at an inlet of the gearbox is within a range of 5-40 gallons per minute at a max takeoff condition, wherein a diameter of the fan blades is 140-192 inches, and wherein a net thrust of the turbomachine engine is within a range of 12,000-30,000 pounds force at the max takeoff condition.