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A secondary flow system provides a compact injector cooling structure for turbine blades which includes an Angled On-board Injector (AOBI) that locates a metering throat at an inward angle relative to an engine centerline. The AOBI positions the metering throat at the inward angle relative to an eng

A secondary flow system provides a compact injector cooling structure for turbine blades which includes an Angled On-board Injector (AOBI) that locates a metering throat at an inward angle relative to an engine centerline. The AOBI positions the metering throat at the inward angle relative to an engine centerline to communicate cooling airflow to an angled annular section of a turbine rotor disk coverplate.

대표청구항 ▼

1. A cooling structure for a gas turbine engine comprising: an upstream wall defined transverse to an engine axis;a downstream wall transverse to said engine axis;an annular body which interconnects said upstream wall and said downstream wall; andan angled on-board injector extending from said body,

1. A cooling structure for a gas turbine engine comprising: an upstream wall defined transverse to an engine axis;a downstream wall transverse to said engine axis;an annular body which interconnects said upstream wall and said downstream wall; andan angled on-board injector extending from said body, said injector including a radial nozzle section and an angled nozzle section angled relative said engine axis, said angled nozzle section extends at least partially into an angled on-board injector cavity defined in part by an angled annular section of a rotor coverplate having a multiple of apertures located therethrough such that an airflow from said angled on-board injector is directed toward said multiple of apertures. 2. The cooling structure as recited in claim 1, wherein said angled nozzle section is angled between approximately 0 degrees and 90 degrees relative said engine axis. 3. The cooling structure as recited in claim 1, wherein said angled nozzle section defines a metering throat. 4. The cooling structure as recited in claim 1, wherein said angled annular section is transverse to said angled nozzle section. 5. A cooling structure for a gas turbine engine comprising: a turbine stator assembly defined about an engine axis;an angled on-board injector in fluid communication with said turbine stator assembly, said angled on-board injector including an angled nozzle section angled relative said engine axis; anda turbine blade assembly adjacent said turbine stator assembly, said turbine blade assembly having a rotor coverplate mounted upstream of a rotor disk to rotate therewith, said rotor coverplate having a multiple of apertures through an angled annular section said rotor coverplate, said angled nozzle section extends at least partially into an angled on-board injector cavity defined in part by said angled annular section such that an airflow from said angled on-board injector is directed toward said multiple of apertures. 6. The cooling structure as recited in claim 5, wherein said angled on-board injector is radially inboard of said stator assembly. 7. The cooling structure as recited in claim 5 wherein said angled nozzle section is transverse to said angled on-board injector. 8. The cooling structure as recited in claim 5, wherein said angled nozzle section is angled toward said turbine blade assembly. 9. The cooling structure as recited in claim 5, wherein said angled nozzle section is angled radially inboard and toward said turbine blade assembly. 10. The cooling structure as recited in claim 5, wherein said angled nozzle section is angled between approximately 0 degrees and 90 degrees. 11. A cooling structure for a gas turbine engine comprising: a turbine stator assembly defined about an engine axis;an angled on-board injector in fluid communication with said turbine stator assembly, said angled on-board injector including an angled nozzle section angled relative said engine axis; anda turbine blade assembly adjacent said turbine stator assembly, said turbine blade assembly having a rotor coverplate mounted upstream of a rotor disk to rotate therewith, said rotor coverplate having a multiple of apertures through an angled annular section of said rotor coverplate, said angled nozzle section extends at least partially into an angled on-board injector cavity defined in part by said angled annular section of said rotor coverplate such that said angled nozzle section is generally transverse to said angled annular section and an airflow from said angled on-board injector is directed toward said multiple of apertures. 12. The cooling structure as recited in claim 11, wherein said angled annular section is generally perpendicular to said angled nozzle section. 13. The cooling structure as recited in claim 1, wherein said angled annular section of said rotor coverplate is defined between an upper flange and a lower flange which extend generally parallel to said engine centerline. 14. The cooling structure as recited in claim 13, further comprising an upper seal and a lower seal which respectively engage said upper flange and said lower flange to define said angled on-board injector cavity. 15. The cooling structure as recited in claim 13, wherein said angled on-board injector cavity is annular. 16. The cooling structure as recited in claim 1, wherein said angled nozzle section is transverse to said angled annular section. 17. The cooling structure as recited in claim 16, wherein said radial nozzle section is generally perpendicular to said engine axis.