A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft p
A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft power. The power turbine rotates at a first rotational speed. 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.
대표청구항▼
1. A turbofan engine comprising: a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air;a power turbine converting the gas stream flow into shaft power, the power turbine rotating at a first rotational speed;a speed reduction
1. A turbofan engine comprising: a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air;a power turbine converting the gas stream flow into shaft power, the power turbine rotating at a first rotational speed;a speed reduction device driven by the power turbine; anda propulsor section including 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, wherein 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. 2. The turbofan engine as recited in claim 1, wherein the EUTP is less than about 0.25 at the take-take off condition. 3. The turbofan engine as recited in claim 1, wherein the EUTP is less than about 0.20 at the take-off condition. 4. The turbofan engine as recited in claim 1, wherein the EUTP at one of a climb condition and a cruise condition is less than about 0.10. 5. The turbofan engine as recited in claim 1, wherein the EUTP at one of a climb condition and a cruise condition is less than about 0.08. 6. The turbofan engine as recited in claim 1, wherein the tip diameter of the fan is greater than about 50 inches and less than about 160 inches. 7. The turbofan engine as recited in claim 1, wherein the mass flow generated by the propulsor section is between about 625 lbm/hour and about 80,000 lbm/hour. 8. The turbofan engine as recited in claim 1, wherein the first speed of the power turbine is between about 6200 rpm and about 12,500 rpm. 9. The turbofan engine as recited in claim 1, wherein the propulsive thrust generated by the turbofan engine is between about 16,000lbf and about 120,000 lbf. 10. The turbofan engine as recited in claim 1, wherein the gas generator defines an overall pressure ratio of between about 40 and about 80. 11. A turbofan engine comprising: a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air;a power turbine converting the gas stream flow into shaft power, the power turbine rotating at a first rotational speed;a speed reduction device driven by the power turbine; anda propulsor section including 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, wherein the fan includes a fan 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 0.15 at one of a climb condition and a cruise condition. 12. The turbofan engine as recited in claim 11, wherein the EUTP is less than about 0.125 for at least one of the climb condition and the cruise condition. 13. The turbofan engine as recited in claim 11, wherein the EUTP at one of the climb condition and the cruise condition is less than about 0.08. 14. The turbofan engine as recited in claim 11, wherein the EUTP at a take-off condition is less than about 0.15. 15. The turbofan engine as recited in claim 11, wherein the tip diameter of the fan is between about 50 inches and about 160 inches. 16. The turbofan engine as recited in claim 11, wherein the mass flow generated by the propulsor section is between about 625 lbm/hour and about 80,000 lbm/hour. 17. The turbofan engine as recited in claim 11, wherein the first speed of the power turbine is between about 6200 rpm and about 12,500 rpm. 18. The turbofan engine as recited in claim 11, wherein the propulsive thrust generated by the turbofan engine is between about 16,000 lbf and about 120,000 lbf. 19. The turbofan engine as recited in claim 11, wherein the gas generator defines an overall pressure ratio of between about 40 and about 80. 20. A turbofan engine comprising: a gas generator section for generating a high energy gas stream, the gas generating section including a compressor section, combustor section and a first turbine;a second turbine converting the high energy gas stream flow into shaft power, the second turbine rotating at a first speed and including less than or equal to about six (6) stages;a geared architecture driven by the second turbine; anda propulsor section driven by the second turbine through the geared architecture at a second speed lower than the first speed, the propulsor section including a fan with a pressure ratio across the fan section less than about 1.45, the propulsor section generating propulsive thrust as a mass flow rate of air through a bypass flow path from the shaft power, wherein 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 a mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the second turbine is less than about 0.30 at a take-off condition. 21. The turbofan engine as recited in claim 20, wherein the EUTP is less than about 0.25 at the take-off condition. 22. The turbofan engine as recited in claim 20, wherein the EUTP is less than about 0.20 at the take-off condition. 23. The turbofan engine as recited in claim 20, wherein the EUTP at one of a climb condition and a cruise condition is less than about 0.10. 24. The turbofan engine as recited in claim 20, wherein the EUTP at the take-off condition is less than about 0.08. 25. The gas turbofan engine as recited in claim 20, wherein the fan section defines a bypass airflow having a bypass ratio greater than about ten (10). 26. The turbofan engine as recited in claim 20, wherein the tip diameter of the fan is between about 50 inches and about 160 inches. 27. The turbofan engine as recited in claim 20, wherein the mass flow generated by the propulsor section is between about 625 lbm/hour and about 80,000 lbm/hour. 28. The turbofan engine as recited in claim 20, wherein the first speed of the second turbine is between about 6200 rpm and about 12,500 rpm. 29. The turbofan engine as recited in claim 20, wherein the second turbine comprises a low pressure turbine with 3 to 6 stages. 30. The turbofan engine as recited in claim 20, wherein a ratio between the number of fan blades and the number of rotors in the second turbine is between about 3.3 and about 8.6.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (30)
Seda, Jorge F., Aircraft engine with inter-turbine engine frame.
Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E., Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor.
Moniz, Thomas Ory; Schilling, Jan Christopher; Orlando, Robert Joseph; Patt, Raymond Felix, Power take-off system and gas turbine engine assembly including same.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.