초록 ▼

A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a seco

A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.

대표청구항 ▼

1. A turbofan engine comprising: a fan;a compressor in communication with the fan section, wherein the fan is configured to communicate a portion of air into a bypass path defining a bypass area outwardly of the compressor and a portion into the compressor and a ratio of air communicated through the

1. A turbofan engine comprising: a fan;a compressor in communication with the fan section, wherein the fan is configured to communicate a portion of air into a bypass path defining a bypass area outwardly of the compressor and a portion into the compressor and a ratio of air communicated through the bypass path relative to air communicated to the compressor is greater than about 6.0;a combustor in fluid communication with the compressor;a turbine in communication with the combustor, the turbine having a first turbine section that includes two or more stages and a second turbine section that includes at least two stages, wherein a ratio of airfoils in the first turbine section to the bypass ratio is less than about 170 and the first turbine section includes a maximum gas path radius and a ratio of the maximum gas path radius to a maximum radius of the fan is less than about 0.50;anda speed reduction mechanism coupled to the fan and rotatable by the turbine. 2. The turbofan engine as recited in claim 1, wherein the compressor includes a first compressor section and a second compressor section, wherein the second compressor section operates at a pressure higher than the first compressor section. 3. The turbofan engine as recited in claim 2, wherein the first compressor section includes at least four stages. 4. The turbofan engine as recited in claim 3, wherein the second compressor section includes at least eight stages. 5. The turbofan as recited in claim 4, wherein the second turbine section comprises a high pressure turbine and the first turbine section comprises a low pressure turbine that operates at a pressure lower than the high pressure turbine section and the low pressure turbine includes an airfoil count below about 1600. 6. The turbofan as recited in claim 5, wherein a hub-to-tip ratio (Ri:Ro) of the low pressure turbine section is between about 0.4 and about 0.5 measured at a maximum Ro axial location within the low pressure turbine. 7. The turbofan as recited in claim 6, wherein the low pressure turbine includes more than four stages. 8. The turbofan as recited in claim 6, wherein the speed reduction mechanism comprises an epicyclic gearbox. 9. The turbofan as recited in claim 8, wherein the epicyclic gearbox provides a speed reduction ratio is between about 2:1 and about 5:1. 10. A turbofan engine comprising: a fan;a compressor in communication with the fan section wherein the compressor includes a first compressor section including at least two stages and a second compressor section including at least five stages, wherein the second compressor section is configured to operate at a higher pressure than the first compressor section, wherein the fan is configured to communicate a portion of air into a bypass path defining a bypass area outwardly of the compressor and a portion into the compressor and a ratio of air communicated through the bypass path relative to air communicated to the compressor is greater than about 6.0;a combustor in fluid communication with the compressor;a turbine in communication with the combustor, the turbine having a first turbine section and a second turbine section, wherein a ratio of airfoils in the first turbine section to the bypass ratio is less than about 170 and the first turbine section includes a maximum gas path radius and a ratio of the maximum gas path radius to a maximum radius of the fan is less than about 0.50; anda speed reduction mechanism coupled to the fan and rotatable by the turbine. 11. The turbofan engine as recited in claim 10, wherein the first turbine section includes three or more stages. 12. The turbofan engine as recited in claim 11, wherein the first turbine section includes four or more stages. 13. The turbofan as recited in claim 12, wherein the second turbine section comprises a high pressure turbine and the first turbine section comprises a low pressure turbine that operates at a pressure lower than the high pressure turbine section and the low pressure turbine includes an airfoil count below about 1600. 14. The turbofan as recited in claim 13, wherein a hub-to-tip ratio (Ri:Ro) of the low pressure turbine section is between about 0.4 and about 0.5 measured at a maximum Ro axial location within the low pressure turbine. 15. The turbofan as recited in claim 14, wherein the bypass ratio is greater than about 8.0. 16. The turbofan as recited in claim 15, wherein a fan pressure ratio across the fan is less than about 1.45. 17. The turbofan as recited in claim 16, wherein the speed reduction mechanism comprises an epicyclic gearbox. 18. The turbofan as recited in claim 17, wherein the epicyclic gearbox provides a speed reduction ratio between about 2:1 and about 5:1.