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US 2014/0174055 A1Published application
Turbine section of high bypass turbofan
AssigneeUnited Technologies Corporation
InventorsPaul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz
Life of this patent
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Abstract
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.
Claims20
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
- a speed reduction mechanism coupled to the fan and rotatable by the turbine.
3 more elements
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
- a speed reduction mechanism coupled to the fan and rotatable by the turbine.
3 more elements
Dependencies are inferred from the claim text.