Low noise turbine for geared gas turbine engine
AssigneesUnited Technologies Corporation, MTU Aero Engines AG
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 compressor section driven by the turbine section, 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.
Claims28
A gas turbine engine, comprising:
- a turbine section including a fan drive turbine;
- a compressor section driven by the turbine section;
- a geared architecture driven by the fan drive turbine;
- and
- a fan driven by the fan drive turbine via the geared architecture;
- wherein at least one stage of the turbine section includes an array of rotatable blades and an array of vanes, and
- wherein 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
- wherein a mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.
A turbine section of a geared gas turbine engine, comprising:
- at least one stage having a ratio of vanes to blades that is greater than or equal to 1.55, wherein the blades are configured to operate at a mechanical tip rotational Mach number that is greater than or equal to 0.5 at an approach speed.
A method of providing a portion of a gas turbine engine comprising:
- providing at least one stage of a turbine section of a geared gas turbine engine, the at least one stage having a ratio of vanes to blades that is greater than or equal to 1.55, wherein a mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.
A gas turbine engine, comprising:
- a turbine section including a fan drive turbine;
- a compressor section driven by the turbine section;
- a geared architecture driven by the fan drive turbine;
- and
- a fan driven by the fan drive turbine via the geared architecture;
- wherein at least one stage of the turbine section includes an array of rotatable blades and an array of vanes, and
- wherein a ratio of the number of vanes to the number of blades is greater than or equal to 1.55, and
- wherein a mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed, and
- wherein the vanes of the at least one stage are immediately upstream or downstream from the blades, and
- wherein the gas turbine engine is rated to produce 15,000 pounds of thrust or more.
Dependencies are inferred from the claim text.