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A turbofan engine includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in the ambient air and a power turbine that converts the gas stream flow into shaft power. The turbofan engine further includes a propulsor section including

A turbofan engine includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in the ambient air and a power turbine that converts the gas stream flow into shaft power. The turbofan engine further includes a propulsor section including a fan driven by the power turbine through a geared architecture 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. An Engine Unit Thrust Parameter 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 a take-off condition.

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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 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 a take-off condition. 2. 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. 3. 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. 4. The turbofan engine as recited in claim 1, wherein the tip diameter of the fan is between about 50 inches and about 160 inches. 5. 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. 6. 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. 7. The turbofan engine as recited in claim 1, wherein the propulsive thrust generated by the turbofan engine is between about 16,000 lbf and about 120,000 lbf. 8. The turbofan engine as recited in claim 7, wherein the gas generator defines an overall pressure ratio of between about 40 and about 80. 9. 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 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 0.10 at one of a climb condition and a cruise condition. 10. The turbofan engine as recited in claim 9, wherein the EUTP at one of the climb condition and the cruise condition is less than about 0.08. 11. The turbofan engine as recited in claim 9, wherein the EUTP at a take-off condition is less than about 0.15. 12. The turbofan engine as recited in claim 9, wherein the tip diameter of the fan is between about 50 inches and about 160 inches. 13. The turbofan engine as recited in claim 9, wherein the mass flow generated by the propulsor section is between about 625 lbm/hour and about 80,000 lbm/hour. 14. 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. 15. The turbofan engine as recited in claim 9, wherein the propulsive thrust generated by the turbofan engine is between about 16,000 lbf and about 120,000 lbf. 16. The turbofan engine as recited in claim 9, wherein the gas generator defines an overall pressure ratio of between about 40 and about 80. 17. 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 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 0.15 at a take-off condition. 18. The turbofan engine as recited in claim 17, wherein the EUTP at one of a climb condition and a cruise condition is less than about 0.10. 19. The turbofan engine as recited in claim 17, wherein the EUTP at the take-off condition is less than about 0.08. 20. The gas turbofan engine as recited in claim 17, wherein the fan section defines a bypass airflow having a bypass ratio greater than about ten (10). 21. The turbofan engine as recited in claim 17, wherein the tip diameter of the fan is between about 50 inches and about 160 inches. 22. The turbofan engine as recited in claim 17, wherein the mass flow generated by the propulsor section is between about 625 lbm/hour and about 80,000 lbm/hour. 23. The turbofan engine as recited in claim 17, wherein the first speed of the second turbine is between about 6200 rpm and about 12,500 rpm. 24. The turbofan engine as recited in claim 17, wherein the second turbine comprises a low pressure turbine with 3 to 6 stages.