Low noise turbine for geared gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsBruce L. Morin, David A. Topol, Detlef Korte
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Abstract
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.
Claims30
A turbofan engine comprising:
- a fan section including a fan having a fan rotor and a plurality of fan blades, and including an outer housing surrounding the fan to define a bypass duct;
- a geared architecture;
- a high spool including a high pressure compressor driven by a high pressure turbine;
- a low spool including a low pressure compressor and a fan drive turbine, wherein the fan drive turbine drives the fan via the geared architecture;
- and
- wherein at least one stage of the fan drive turbine includes an array of rotatable blades and an array of vanes, the array of vanes of the at least one stage are immediately upstream or downstream from the array of blades, a ratio of the number of vanes to the number of blades of the at least one stage is greater than or equal to 1.55, and a mechanical tip rotational Mach number of the array of blades is greater than or equal to 0.5 at an approach speed, the approach speed taken at an approach certification point as defined in Part 36 of the Federal Airworthiness Regulations.
Dependencies are inferred from the claim text.