A turbine comprising: a stator section (401; 501) having a plurality of vanes (402a; 502a); a rotating section (403; 503) having a plurality of blades (402b; 502b) attached to a disc (426;526), the rotating section (403; 503) being axially adjacent the stator section (401; 501) along an axis of the turbine, the stator section being aftward of the rotating section along the axis of the turbine; and a primary tangential onboard injector (428; 528) located radially inward from the stator section (401; 501) and attached to the stator section and configured to direct a cooling airflow (410; 510) from the stator section in a forward direction toward the rotating section (403; 503), the primary tangential onboard injector (428; 528) turning the airflow (410; 510) in a direction of rotation (D R) of the rotating section (403; 503); wherein a rim cavity (442; 542) is defined between the stator section (401; 501) and the rotating section (403; 503), the rim cavity (442; 452) arranged to turn a leakage flow (410a; 510a) leaking from the cooling airflow which passed through the primary tangential onboard injector in a direction of a gaspath flowing from the blades (402b; 502b) toward the vanes (402a; 502a); and wherein a secondary tangential onboard injector (430; 530) having a first wall and a second wall is attached to the stator section and is positioned between a portion of the vanes (402a; 502a) and a portion of the disc (426, 526) along a path of the leakage flow, whereby the first wall is fixed to a part of an inner diameter platform of a vane and the second wall is fitted with a seal (438; 538) that seals relative to a rotating surface that is part of the disc (426; 526), wherein the secondary tangential onboard injector (430; 530) turns the leakage flow (410a; 510a) such that when the leakage flow enters the gaspath, the direction of leakage flow is in the flow direction of the gaspath flow. a stator section (401; 501) having a plurality of vanes (402a; 502a); a rotating section (403; 503) having a plurality of blades (402b; 502b) attached to a disc (426;526), the rotating section (403; 503) being axially adjacent the stator section (401; 501) along an axis of the turbine, the stator section being aftward of the rotating section along the axis of the turbine; and a primary tangential onboard injector (428; 528) located radially inward from the stator section (401; 501) and attached to the stator section and configured to direct a cooling airflow (410; 510) from the stator section in a forward direction toward the rotating section (403; 503), the primary tangential onboard injector (428; 528) turning the airflow (410; 510) in a direction of rotation (D R) of the rotating section (403; 503); wherein a rim cavity (442; 542) is defined between the stator section (401; 501) and the rotating section (403; 503), the rim cavity (442; 452) arranged to turn a leakage flow (410a; 510a) leaking from the cooling airflow which passed through the primary tangential onboard injector in a direction of a gaspath flowing from the blades (402b; 502b) toward the vanes (402a; 502a); and wherein a secondary tangential onboard injector (430; 530) having a first wall and a second wall is attached to the stator section and is positioned between a portion of the vanes (402a; 502a) and a portion of the disc (426, 526) along a path of the leakage flow, whereby the first wall is fixed to a part of an inner diameter platform of a vane and the second wall is fitted with a seal (438; 538) that seals relative to a rotating surface that is part of the disc (426; 526), wherein the secondary tangential onboard injector (430; 530) turns the leakage flow (410a; 510a) such that when the leakage flow enters the gaspath, the direction of leakage flow is in the flow direction of the gaspath flow.