Thrust efficient turbofan engine
A disclosed turbofan engine includes a gas generator section for generating a gas stream flow. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than about fifty (50) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.30 at a take-off condition.
1. A turbofan engine comprising:
a gas generator section;
a power turbine rotatable at a first rotational speed, wherein the power turbine drives a speed reduction device; and
a propulsor section including a bypass flow path and a fan, wherein the power turbine drives the fan through the speed reduction device at a second rotational speed lower than the first rotational speed, the power turbine includes a number of rotors from three to six and a ratio between a number of fan blades and the number of rotors of the power turbine is between 3.3 and 8.6,
wherein the fan includes a tip diameter between fifty (50) and one-hundred sixty (160) inches, net engine thrust is between 16,000 lbf and 120,000 lbf, a mass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec, a first rotational speed of the power turbine is between 6,200 rpm and 12,500 rpm and an Engine Unit Thrust Parameter (“EUTP”) defined as the net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, the tip diameter of the fan and the first rotational speed of the power turbine, is less than 0.08 at a takeoff power condition.
2. The turbofan engine as recited in claim 1 , wherein the EUTP at a cruise condition is less than 0.08.
3. A turbofan engine comprising:
a gas generator section;
a power turbine rotatable at a first rotational speed, wherein the power turbine operates at a temperature less than 1800° F. at a sea level takeoff power condition, wherein the power turbine drives a speed reduction device; and
a propulsor section including a fan disposed within an enclosure defining a bypass flow path, wherein the power turbine drives the fan through the speed reduction device at a second rotational speed lower than the first rotational speed, the power turbine includes a number of rotors from three to six and a ratio between a number of fan blades and the number of rotors of the power turbine is between 3.3 and 8.6, wherein the fan includes a fan tip diameter between fifty (50) and one-hundred sixty (160) inches, a mass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec, a first rotational speed of the power turbine is between 6,200 rpm and 12,500 rpm and an Engine Unit Thrust Parameter (“EUTP”) defined as a net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, the fan tip diameter and the first rotational speed of the power turbine is less than 0.08 at a takeoff power condition.
4. The turbofan engine as recited in claim 3 , wherein the EUTP is less than 0.08 at a climb condition.
5. The turbofan engine as recited in claim 2 , wherein the speed reduction device includes a geared architecture between the power turbine and the fan with a gear ratio of greater than 2.3.
6. The turbofan engine as recited in claim 5 , wherein the fan operates at a fan pressure ratio across a fan blade alone that is less than 1.45.
7. The turbofan engine as recited in claim 6 , wherein the gas generator includes a two stage high pressure turbine and the fan includes less than 20 fan blades.
8. The turbofan engine as recited in claim 7 , wherein the EUTP at a climb condition is less than 0.08.
9. The turbofan engine as recited in claim 8 , wherein the speed reduction device comprises a planetary gear system, a mid-turbine frame is disposed between the high pressure turbine and the power turbine and the fan rotates at corrected fan tip speed that is less than 1150 ft/second.
10. The turbofan engine as recited in claim 9 , wherein the fan is of the propulsor section and is a single stage fan.
11. The turbofan engine as recited in claim 10 , wherein the power turbine is rotatable at the first rotational speed and operates a temperature less than 1800° F. at the takeoff power condition.
12. The turbofan engine as recited in claim 11 , wherein the gas generator defines an overall pressure ratio of between 40 and 80.
13. The turbofan engine as recited in claim 12 , wherein the EUTP at the cruise condition is greater than or equal to 0.05.
14. The turbofan engine as recited in claim 6 , wherein the EUTP at a climb condition is less than 0.08.
15. The turbofan engine as recited in claim 1 , wherein the speed reduction device includes a geared architecture between the power turbine and the fan with a gear ratio of greater than 2.3.
16. The turbofan engine as recited in claim 15 , wherein the fan includes less than 20 fan blades.
17. The turbofan engine as recited in claim 16 , wherein the EUTP at a cruise condition is less than 0.08.
18. The turbofan engine as recited in claim 17 , including a two stage high pressure turbine.
19. The turbofan engine as recited in claim 18 , wherein the fan includes less than 20 fan blades, a fan pressure ratio across a fan blade alone is less than 1.45, the speed reduction device includes a geared architecture between the power turbine and the fan with a gear ratio of greater than 2.3 and the EUTP at a climb condition is less than 0.08.
20. The turbofan engine as recited in claim 19 , wherein the gas generator defines an overall pressure ratio of between 40 and 80.
21. The turbofan engine as recited in claim 17 , wherein the EUTP at a climb condition is less than 0.08.
22. The turbofan engine as recited in claim 4 , wherein the speed reduction device includes a geared architecture between the power turbine and the fan with a gear ratio of greater than 2.3.
23. The turbofan engine as recited in claim 22 , wherein the gas generator includes a two stage high pressure turbine.
24. The turbofan engine as recited in claim 23 , wherein the fan includes less than 20 fan blades.
25. The turbofan engine as recited in claim 24 , wherein the gas generator defines an overall pressure ratio of between 40 and 80.
26. The turbofan engine as recited in claim 23 , wherein the fan includes less than 20 fan blades and the net engine thrust is between 16,000 lbf and 120,000 lbf.
27. The turbofan engine as recited in claim 22 , wherein the EUTP at a cruise condition is less than 0.08.
28. The turbofan engine as recited in claim 27 , wherein the gas generator defines an overall pressure ratio of between 40 and 80.
29. The turbofan engine as recited in claim 4 , wherein the fan operates at a fan pressure ratio across a fan blade alone that is less than 1.45.
30. The turbofan engine as recited in claim 29 , wherein the EUTP at a cruise condition is less than 0.08 and the net engine thrust is between 16,000 lbf and 120,000 lbf.
31. The turbofan engine as recited in claim 30 , wherein the fan includes less than 20 fan blades and the speed reduction device includes a geared architecture between the power turbine and the fan with a gear ratio that is greater than 2.3.
32. The turbofan engine as recited in claim 31 , wherein the gas generator includes a two stage high pressure turbine and the EUTP at the climb condition less than 0.08.