Gearbox efficiency rating for turbomachine engines
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, 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. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-11.0, and a gearbox oil flow rate at an inlet of the gearbox within a range of 5-25 gallons per minute at a max takeoff condition.
1. A turbomachine engine comprising:
a fan assembly disposed radially within a fan case, wherein the fan assembly comprises a plurality of fan blades, and wherein a diameter of the fan blades is 72-216 inches;
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 are coupled to the core engine and the fan case; and
a gearbox coupled to the low-pressure turbine and the fan assembly, wherein the gearbox comprises a gear ratio within a range of 4.1-11.0 and a gearbox oil flow rate at an inlet of the gearbox within a range of 5-25 gallons per minute at a max takeoff condition.
2. The turbomachine engine of claim 1 , further comprising a gearbox efficiency rating within a range of 0.10-1.24 at the max takeoff condition.
3. The turbomachine engine of claim 2 , wherein the gearbox efficiency rating is within a range of 0.25-1.15 at the max takeoff condition.
4. The turbomachine engine of claim 2 , wherein the gearbox efficiency rating is within a range of 0.10-1.01 at the max takeoff condition.
5. The turbomachine engine of claim 2 , wherein the gearbox efficiency rating is within a range of 0.19-1.24 at the max takeoff condition.
6. The turbomachine engine of claim 1 , wherein the gear ratio of the gearbox is within a range of 4.5-11.0.
7. The turbomachine engine of claim 1 , wherein the gear ratio of the gearbox is within a range of 6-11.
8. The turbomachine engine of claim 1 , wherein the gearbox oil flow rate at the inlet of the gearbox is within a range of 10-20 gallons per minute at the max takeoff condition.
9. The turbomachine engine of claim 1 , wherein a net thrust of the turbomachine engine is within a range of 12,500-25,500 pounds force at the max takeoff condition.
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, and wherein the ring gear is coupled to the fan assembly.
11. 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 fixedly coupled to the low-pressure turbine, wherein the planet gears are rotatably coupled to a planet carrier, and wherein the planet carrier is fixedly coupled to the fan assembly.
12. The turbomachine engine of claim 1 , wherein the gearbox is a multi-stage gearbox.
13. The turbomachine engine of claim 1 , wherein the gearbox comprises one or more compound gears, wherein each compound gear includes a first portion having a first diameter and a second portion having a second diameter, the second diameter being less than the first diameter.
14. A turbomachine engine comprising:
a fan case;
a fan assembly housed within the fan case and comprising 16-20 fan blades;
a vane assembly housed within the fan case aft of the fan assembly and comprising a plurality of vanes;
a core engine comprising a low-pressure compressor comprising 2-4 stages, a high-pressure compressor comprising 8-10 stages, a high-pressure turbine comprising two stages, and a low-pressure turbine comprising 3-4 stages; and
an epicyclic gearbox coupled to the low-pressure turbine and the fan assembly and comprising a gear ratio of 4.1-10 configured such that the fan assembly rotates slower than one or more stages of the low-pressure turbine, wherein the epicyclic gearbox comprises a gearbox oil flow rate at an inlet of the epicyclic gearbox is 5-20 gallons per minute at a max takeoff condition.
15. The turbomachine engine of claim 14 , further comprising a gearbox efficiency rating of 0.10-1.1 at the max takeoff condition.
16. The turbomachine engine of claim 15 , wherein the gearbox efficiency rating is 0.25-0.55 at the max takeoff condition.
17. The turbomachine engine of claim 14 , wherein a diameter of the fan blades is 72-120 inches.
18. A turbomachine engine comprising:
a fan assembly disposed radially within a fan case, wherein the fan assembly comprises a plurality of 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 are coupled to the core engine and the fan case; and
a gearbox coupled to the low-pressure turbine and the fan assembly, wherein the gearbox comprises a gear ratio within a range of 4.1-11.0 and a gearbox oil flow rate at an inlet of the gearbox within a range of 5-25 gallons per minute at a max takeoff condition,
wherein a net thrust of the turbomachine engine is within a range of 12,500-25,500 pounds force at the max takeoff condition.
19. The turbomachine engine of claim 18 , further comprising a gearbox efficiency rating within a range of 0.10-1.24 at the max takeoff condition.
20. The turbomachine engine of claim 19 , wherein the gearbox efficiency rating is within a range of 0.25-1.15 at the max takeoff condition.