FIELD OF THE INVENTION

The present subject matter relates generally to an aircraft propulsion device, or more particularly to an aircraft propulsion device having variable pitch guide vanes.

BACKGROUND OF THE INVENTION

A gas turbine engine generally includes a core having, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. During operation, an engine airflow is provided to an inlet of the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with the compressed air and burned within the combustion section to provide combustion gases. The combustion gases are routed from the combustion section to the turbine section. The flow of combustion gasses through the combustion section drives the compressor section and is then routed through the exhaust section, e.g., to atmosphere.

In particular configurations, the gas turbine engine additionally includes a fan mechanically coupled to the core and a plurality of outlet guide vanes. For example, the fan of such a gas turbine engine typically includes a plurality of rotatable blades driven by a shaft of the core. Rotation of the plurality of blades generates thrust for the gas turbine engine. Additionally, the plurality outlet guide vanes can direct an airflow from the blades to, e.g., reduce an amount of noise generated by the gas turbine engine and enhance a performance of the gas turbine engine.

In certain configurations, the gas turbine engine may define an outer nacelle enclosing the plurality of fan blades of the fan and the plurality of outlet guide vanes. Such a configuration allows for the outlet guide vanes to be rotated about respective pitch axes at radially outer ends where the outlet guide vanes attach to the outer nacelle.

However, certain gas turbine engines may not include the outer nacelle enclosing the plurality of fan blades and the plurality of outlet guide vanes. Accordingly, known means for actuating the outlet guide vanes may not be included with such gas turbine engines. Therefore, a gas turbine engine capable of actuating a plurality of outlet guide vanes without requiring an outer nacelle enclosing the plurality of outlet guide vanes would be useful.

BRIEF DESCRIPTION OF THE INVENTION

Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.

In one exemplary embodiment of the present disclosure, an aeronautical propulsion device defining a radial direction is provided. The propulsion device includes a fan having a plurality of fan blades for providing a flow of air in a flowpath, as well as a plurality of variable guide vanes for directing air to or from the fan in a desired direction. The plurality of guide vanes each define an inner end and an outer end along the radial direction. The plurality of guide vanes are each attached to a housing of the propulsion device at the inner end in a rotatable manner the aeronautical propulsion device additionally includes a pitch change mechanism positioned within the housing of the propulsion device and mechanically coupled to at least one of the plurality of guide vanes for changing a pitch of the at least one of the plurality of guide vanes.

In another exemplary embodiment of the present disclosure, a gas turbine engine defining a radial direction is provided. The gas turbine engine includes a fan including a plurality of fan blades for providing a flow of air in a flowpath, and a plurality of variable outlet guide vanes for directing air from the plurality of fan blades of the fan in a desired direction. The plurality of variable outlet guide vanes each define an inner end and an outer end along the radial direction. The plurality of variable outlet guide vanes are each attached to a core of the gas turbine engine at the inner end in a rotatable manner. The gas turbine engine additionally includes a pitch change mechanism positioned within the core of the gas turbine engine and mechanically coupled to at least one of the plurality of variable outlet guide vanes for changing a pitch of the at least one of the plurality of variable outlet guide vanes.

These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.

