A seal assembly (90;130;140;150;160) for a gas turbine engine , comprising: a first engine component including a flange , the first engine component disposed between a secondary cooling airflow path (S) and a core airflow path (C), wherein the secondary cooling airflow path (S) is at a pressure greater than a pressure of the core airflow path (C); a second engine component disposed between the secondary cooling airflow path (S) and the core airflow path (C), wherein a leakage airflow path (L) is disposed between the first engine component and the second engine component ; a first seal disposed between the secondary cooling airflow path (S) and the flange , wherein the first seal comprises at least one of a first "W" seal or a first brush seal; and a second seal disposed between the first seal and the core airflow path (C); characterised in that the first seal and the second seal are disposed in the leakage airflow path (L) between the secondary cooling airflow path (S) and the core airflow path (C), the second seal is disposed radially inward and in a series arrangement with the first seal such that leakage airflow path (L) is configured to contact first seal prior to reaching second seal ; the first seal is configured to withstand higher pressures than the second seal while maintaining an effective seal and the second seal is configured to withstand higher temperatures than first seal , such that the second seal protects the first seal from conditions in the core airflow path (C) and the first seal protects the second seal from conditions in the secondary cooling airflow path (S); and in that the second seal comprises at least one of a second "W" seal or a second brush seal. a first engine component including a flange , the first engine component disposed between a secondary cooling airflow path (S) and a core airflow path (C), wherein the secondary cooling airflow path (S) is at a pressure greater than a pressure of the core airflow path (C); a second engine component disposed between the secondary cooling airflow path (S) and the core airflow path (C), wherein a leakage airflow path (L) is disposed between the first engine component and the second engine component ; a first seal disposed between the secondary cooling airflow path (S) and the flange , wherein the first seal comprises at least one of a first "W" seal or a first brush seal; and a second seal disposed between the first seal and the core airflow path (C); characterised in that the first seal and the second seal are disposed in the leakage airflow path (L) between the secondary cooling airflow path (S) and the core airflow path (C), the second seal is disposed radially inward and in a series arrangement with the first seal such that leakage airflow path (L) is configured to contact first seal prior to reaching second seal ; the first seal is configured to withstand higher pressures than the second seal while maintaining an effective seal and the second seal is configured to withstand higher temperatures than first seal , such that the second seal protects the first seal from conditions in the core airflow path (C) and the first seal protects the second seal from conditions in the secondary cooling airflow path (S); and in that the second seal comprises at least one of a second "W" seal or a second brush seal. <EOS>