Forward facing tangential onboard injectors for gas turbine engines

1. A turbine comprising:

a stator section having a plurality of vanes;

a rotating section having a plurality of blades, the rotating section being axially adjacent the stator section 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 located radially inward from the stator section and configured to direct an airflow from the stator section in a forward direction toward the rotating section, the primary tangential onboard injector turning the airflow in a direction of rotation of the rotating section,

wherein a leakage flow passes between the stator section and the rotating section and into a gaspath flowing from the blades toward the vanes, the turbine further comprising a secondary tangential onboard injector positioned in a flow path of the leakage flow,

wherein the secondary tangential onboard injector has a first wall and a second wall, wherein the first wall is fixed to a vane element surface that is part of the stator section and the second wall is fixed to the first wall by a fixed airfoil meant to turn the leakage air in the flow direction of the gaspath flow,

wherein the rotating section includes a rotating seal that forms a seal between a rotating surface of the rotating section and the second wall, and

a restrictive flow seal is arranged downstream from the secondary tangential onboard injector along the flow path of the leakage flow.

2. The turbine of claim 1 , further comprising a rim cavity defined between the stator section and the rotating section, the rim cavity arranged to turn a leakage flow in a direction of a gaspath flowing from the blades toward the vanes.

3. The turbine of claim 1 , wherein the secondary tangential onboard injector turns the leakage flow such that when the leakage flow enters the gaspath, the direction of leakage flow is in a flow direction of a gaspath flow.

4. The turbine of claim 1 , wherein the rotating seal is a brush seal, knife edge seal, or axial non-contact seal.

5. The turbine of claim 1 , wherein the restrictive flow seal is a brush seal, knife edge seal, or axial non-contact seal.

6. A gas turbine engine comprising:

a compressor section;

a combustor section arranged downstream of the compressor section; and

a turbine section arranged downstream of the combustor section, the turbine section comprising:

a stator section having a plurality of vanes;

a rotating section having a plurality of blades, the rotating section being axially adjacent the stator section along an axis of the gas turbine engine, the stator section being aftward of the rotating section along the axis of the gas turbine engine; and

a primary tangential onboard injector located radially inward from the stator section and configured to direct an airflow from the stator section in a forward direction toward the rotating section, the primary tangential onboard injector turning the airflow in a direction of rotation of the rotating section,

wherein a leakage flow passes between the stator section and the rotating section and into a gaspath flowing from the blades toward the vanes, the turbine further comprising a secondary tangential onboard injector positioned in a flow path of the leakage flow,

wherein the secondary tangential onboard injector has a first wall and a second wall, wherein the first wall is fixed to a vane element surface that is part of the stator section and the second wall is fixed to the first wall by a fixed airfoil meant to turn the leakage air in the flow direction of the gaspath flow,

wherein the rotating section includes a rotating seal that forms a seal between a rotating surface of the rotating section and the second wall, and

a restrictive flow seal is arranged downstream from the secondary tangential onboard injector along the flow path of the leakage flow.

7. The gas turbine engine of claim 6 , further comprising a rim cavity defined between the stator section and the rotating section, the rim cavity arranged to turn a leakage flow in a direction of a gaspath flowing from the blades toward the vanes.

8. The gas turbine engine of claim 6 , wherein the secondary tangential onboard injector turns the leakage flow such that when the leakage flow enters the gaspath, the direction of leakage flow is in a flow direction of a gaspath flow.

9. The gas turbine engine of claim 6 , wherein the rotating seal is a brush seal, knife edge seal, or axial non-contact seal.

10. The gas turbine engine of claim 6 , wherein the restrictive flow seal is a brush seal, knife edge seal, or axial non-contact seal.

11. The gas turbine engine of claim 6 , further comprising:

a second stator section having a plurality of vanes;

a second rotating section having a plurality of blades, the second rotating section being axially adjacent the second stator section along an axis of the gas turbine engine and aftward of the first stator section, the second stator section being aftward of the second rotating section along the axis of the gas turbine engine; and

a second primary tangential onboard injector located radially inward from the second stator section and configured to direct an airflow from the second stator section in a forward direction toward the second rotating section, the second primary tangential onboard injector turning the airflow in a direction of rotation of the second rotating section.

12. The gas turbine engine of claim 11 , wherein a leakage flow passes between the second stator section and the second rotating section and into the gaspath, the gas turbine engine further comprising an additional secondary tangential onboard injector positioned in a flow path of the leakage flow between the second stator section and the second rotating section.