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US 2023/0323836 A1Published application
Turbine section of a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsPaul R. Adams, Frederick M. Schwarz, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Gabriel L. Suciu
Life of this patent
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Abstract
A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
Claims20
A gas turbine engine comprising:
- a propulsor including a circumferential array of blades;
- a compressor in fluid communication with the propulsor;
- a combustor in fluid communication with the compressor;
- a turbine section in fluid communication with the combustor, the turbine section having a two-stage high pressure turbine section coupled to drive a portion of the compressor and a low pressure turbine section;
- and
- a speed reduction mechanism coupling the low pressure turbine section to the propulsor, wherein the speed reduction mechanism comprises gearbox coupled to the propulsor and rotatable by the low pressure turbine section such that the low pressure turbine section rotates faster than the propulsor, the gear box having a speed reduction ratio between 2:1 and 13:1, wherein:
- a maximum gaspath radius along the low pressure turbine section to a maximum radius of the blades of the propulsor is greater than 0.35 and less than 0.55.
4 more elements
A gas turbine engine comprising:
- a core engine case;
- a gaspath through the core engine case, the gas path having a maximum gas path radius;
- a propulsor section fan having array of blades, wherein the array of blades have a maximum blade radius;
- a compressor in fluid communication with the propulsor;
- a combustor in fluid communication with the compressor;
- a turbine in fluid communication with the combustor, the turbine having a low pressure turbine section, wherein a ratio of a maximum gaspath radius along the low pressure turbine section to the maximum blade radius is greater than 0.35 and less than 0.55;
- and
- a speed reduction mechanism coupling the low pressure turbine section to the fan.
5 more elements
Dependencies are inferred from the claim text.