Compressor bleed port with cavity intake wire

A gas turbine engine, comprising:

• a compressor assembly, including:
• a case surrounding a core;
• a row of stator blades within the case, wherein the row of stator blades has first shrouds;
• a row of rotor blades within the case and adjacent to the row of stator blades, wherein the row of rotor blades has second shrouds,
• wherein the first shrouds define first mate faces that axially face the second shrouds, and the second shrouds define second mate faces that axially face the first shrouds;
• a bleed port groove defined between the first mate faces and the second mate faces, wherein the bleed port groove is annular;
• a bleed port defined along the bleed port groove;
• a bleed cavity defined in the case, exterior to the first shrouds and the second shrouds, and fluidly coupled to the core via the bleed port;
• and
• the bleed port groove includes:
• one wire that is a circumferentially extending first wire secured within the bleed port groove to one of the first and second mate faces, wherein the first wire is configured as a continuous annular ring;
• or
• two wires that include:
• the circumferentially extending first wire secured within the bleed port groove to the one of the first and second mate faces;
• and a circumferentially extending second wire secured within the bleed port groove to another one of the first and second mate faces, wherein the first wire and the second wire are configured as continuous annular rings,
• whereby the bleed port is configured to control vibrational frequences induced by a core flow through the bleed port.

A method of controlling flow in a gas turbine engine, the method comprising:

• directing a core flow through a compressor, past a row of stator blades having first shrouds and toward a row of rotor blades having second shrouds;
• and
• diverting a portion of the flow towards a bleed cavity via a bleed port, of a bleed port groove, defined between the first shrouds and the second shrouds, over one or more circumferentially extending wires in the bleed port groove,
• wherein the bleed port groove is annular, and
• the bleed port groove includes:
• one wire that is a circumferentially extending first wire secured within the bleed port groove to one of the first and second mate faces, wherein the first wire is configured as a continuous annular ring;
• or
• two wires that include:
• the circumferentially extending first wire secured within the bleed port groove to the one of the first and second mate faces;
• and a circumferentially extending second wire secured within the bleed port groove to another one of the first and second mate faces, wherein the first wire and the second wire are configured as continuous annular rings,
• whereby the bleed port is configured to control vibrational frequences induced by the core flow through the bleed port.