Mistuned concentric airfoil assembly and method of mistuning same

An airfoil assembly for a gas turbine engine, comprising:

• an annular shroud having a radially inner face and a radially outer face opposing the radially inner face;
• a radially inner array of airfoils extending from the radially inner face;
• a radially outer array of airfoils extending from the radially outer face, wherein at least one airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and at least one airfoil of the radially inner array of airfoils is circumferentially misaligned with the airfoils of the radially outer array of airfoils;
• wherein the radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section;
• and
• wherein each of the radially inner array of airfoils at or above a horizontal midline of the assembly is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils when is in an installed position.

An airfoil assembly for a gas turbine engine, comprising:

• a shroud having a radially inner face and a radially outer face opposing the inner face;
• a radially inner array of airfoils extending from the radially inner face;
• and
• a radially outer array of airfoils extending from the radially outer face, wherein a distance between circumferentially adjacent airfoils of the radially inner array of airfoils or circumferentially adjacent airfoils in the radially outer array of airfoils varies;
• wherein a total number of airfoils in the radially inner array of airfoils is greater than a total number of airfoils in the radially outer array of airfoils;
• and
• wherein one airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils at a twelve o'clock position, and the remaining airfoils of the radially inner array of airfoils are circumferentially misaligned with all airfoils in the radially outer array of airfoils.

A method of reducing a vibratory response of airfoils that support a shroud for a gas turbine engine, comprising:

• circumferentially aligning an airfoil of a radially inner array of airfoils and an airfoil of a radially outer array of airfoils at a twelve o'clock position;
• and circumferentially misaligning the remaining airfoils of the radially inner array of airfoils with all the airfoils of the radially outer array;
• and
• guiding flow through a radially inner bypass flow passage using the radially inner array of airfoils, the radially inner bypass flow passage bypassing and being radially outward of a core flow passage.

An airfoil assembly for a gas turbine engine, comprising:

• an annular shroud having a radially inner face and a radially outer face opposing the radially inner face;
• a radially inner array of airfoils extending from the radially inner face;
• a radially outer array of airfoils extending from the radially outer face, wherein at least one airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and at least on airfoil of the radially inner array of airfoils is circumferentially misaligned with the airfoils of the radially outer array of airfoils;
• wherein the radially inner array of the airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section;
• wherein the radially outer array of airfoils are configured to guide flow within a radially outer bypass flow passage;
• wherein the radially inner bypass flow passage and the radially outer bypass flow passage are both radially outside a core flow passage;
• wherein a distance between circumferentially adjacent airfoils of the radially inner array of airfoils or circumferentially adjacent airfoils in the radially outer array of airfoils varies;
• wherein the core flow passage extends through the compressor section, a combustor section and a turbine section;
• wherein each of the radially inner array of airfoils at or above a horizontal midline of the assembly is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils when is in an installed position, the horizontal midline extending through an opposed pair of the radially inner array of airfoils and extending through an opposed pair of the radially outer array of airfoils;
• and
• wherein each of the radially inner and radially outer bypass flow passages is free of any rotatable airfoils downstream of the radially inner array of airfoils and downstream of the radially outer array of airfoils.