A cooling structure for a gas turbine engine comprising: a gas turbine engine structure defining a cooling cavity , wherein the gas turbine engine structure includes an opening to define a portion of a cooling flow path; a swirler tube configured to direct cooling flow in a desired direction into the cooling cavity ; a bracket assembly supporting the swirler tube and having first and second attachment interfaces to fix the bracket assembly to the gas turbine engine structure, and wherein the bracket assembly comprises a forward bracket positioned on one side of the gas turbine engine structure and an aft bracket positioned on an opposite side of the gas turbine engine structure; and wherein the swirler tube is associated with the aft bracket and the forward bracket includes a mounting flange portion that includes the first attachment interface and has a center boss portion that defines a portion of the cooling flow path, and wherein the aft bracket includes a mounting flange portion that includes the second attachment interface and has a center boss portion that receives cooling flow from the opening and is associated with the swirler tube , further comprising an inlet tube associated with the center boss portion of the forward bracket to direct cooling flow through the opening and into the swirler tube ; the forward and aft brackets each including a first orientation feature ; and a second orientation feature associated with the gas turbine engine structure, the first and second orientation features cooperating with each other to ensure that the swirler tube is only installed in one orientation relative to the gas turbine engine structure; wherein the first orientation feature comprises a male feature and the second orientation feature comprises a female feature that is received within the male feature; characterised in that the male feature comprises a tab and the female feature comprises a slot , and wherein the tab portion of the forward bracket extends outwardly from a peripheral edge of the mounting flange portion and the tab portion of the aft bracket extends outwardly from a peripheral edge of the mounting flange portion . a gas turbine engine structure defining a cooling cavity , wherein the gas turbine engine structure includes an opening to define a portion of a cooling flow path; a swirler tube configured to direct cooling flow in a desired direction into the cooling cavity ; a bracket assembly supporting the swirler tube and having first and second attachment interfaces to fix the bracket assembly to the gas turbine engine structure, and wherein the bracket assembly comprises a forward bracket positioned on one side of the gas turbine engine structure and an aft bracket positioned on an opposite side of the gas turbine engine structure; and wherein the swirler tube is associated with the aft bracket and the forward bracket includes a mounting flange portion that includes the first attachment interface and has a center boss portion that defines a portion of the cooling flow path, and wherein the aft bracket includes a mounting flange portion that includes the second attachment interface and has a center boss portion that receives cooling flow from the opening and is associated with the swirler tube , further comprising an inlet tube associated with the center boss portion of the forward bracket to direct cooling flow through the opening and into the swirler tube ; the forward and aft brackets each including a first orientation feature ; and a second orientation feature associated with the gas turbine engine structure, the first and second orientation features cooperating with each other to ensure that the swirler tube is only installed in one orientation relative to the gas turbine engine structure; wherein the first orientation feature comprises a male feature and the second orientation feature comprises a female feature that is received within the male feature; <EOS>