A gas turbine component with an ejection circuit for removing debris from cooling air flowing through the gas turbine component of a gas turbine system, the gas turbine component comprising: an impingement insert disposed within a cavity in the gas turbine component, the impingement insert including an end wall and a plurality of distribution holes for directing cooling air against a wall of the cavity; and a debris ejection circuit, including: a bypass aperture (132, 232) defined in the end wall of the impingement insert, the bypass aperture (132, 232) fluidly coupling an interior of the impingement insert and an end section of the cavity; and an ejection channel (138, 238) defined in an aft section of the gas turbine component, the ejection channel (138, 238) fluidly coupling the end section of the cavity and a wheelspace cavity cavity, the wheelspace cavity being radially inward of the gas turbine component; wherein the gas turbine component is configured to direct debris in the cooling air through the bypass aperture (132, 232) and the ejection channel (138, 238) to the wheelspace cavity due to a pressure differential between the interior of the gas turbine component and the wheelspace cavity, wherein the gas turbine component comprises a nozzle of the gas turbine system, characterized in that the plurality of distribution holes for directing cooling air against the wall of the cavity is formed in a trailing edge wall of the impingement insert, wherein the bypass aperture (132, 232) defined in the end wall of the impingement insert is positioned adjacent the trailing edge wall. an impingement insert disposed within a cavity in the gas turbine component, the impingement insert including an end wall and a plurality of distribution holes for directing cooling air against a wall of the cavity; and a debris ejection circuit, including: a bypass aperture (132, 232) defined in the end wall of the impingement insert, the bypass aperture (132, 232) fluidly coupling an interior of the impingement insert and an end section of the cavity; and an ejection channel (138, 238) defined in an aft section of the gas turbine component, the ejection channel (138, 238) fluidly coupling the end section of the cavity and a wheelspace cavity cavity, the wheelspace cavity being radially inward of the gas turbine component; a bypass aperture (132, 232) defined in the end wall of the impingement insert, the bypass aperture (132, 232) fluidly coupling an interior of the impingement insert and an end section of the cavity; and an ejection channel (138, 238) defined in an aft section of the gas turbine component, the ejection channel (138, 238) fluidly coupling the end section of the cavity and a wheelspace cavity cavity, the wheelspace cavity being radially inward of the gas turbine component; wherein the gas turbine component is configured to direct debris in the cooling air through the bypass aperture (132, 232) and the ejection channel (138, 238) to the wheelspace cavity due to a pressure differential between the interior of the gas turbine component and the wheelspace cavity, wherein the gas turbine component comprises a nozzle of the gas turbine system, characterized in that the plurality of distribution holes for directing cooling air against the wall of the cavity is formed in a trailing edge wall of the impingement insert, wherein the bypass aperture (132, 232) defined in the end wall of the impingement insert is positioned adjacent the trailing edge wall.