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 defined in the end wall of the impingement insert , the bypass aperture fluidly coupling an interior of the impingement insert and an end section of the cavity ; and an ejection channel defined in an aft section of the gas turbine component, the ejection channel 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 and the ejection channel 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 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 defined in the end wall of the impingement insert , the bypass aperture fluidly coupling an interior of the impingement insert and an end section of the cavity ; and an ejection channel defined in an aft section of the gas turbine component, the ejection channel 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 defined in the end wall of the impingement insert , the bypass aperture fluidly coupling an interior of the impingement insert and an end section of the cavity ; and an ejection channel defined in an aft section of the gas turbine component, the ejection channel 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 and the ejection channel 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 defined in the end wall of the impingement insert is positioned adjacent the trailing edge wall. <EOS>