Turbine engine assembly with a component having a leading edge trough
AssigneeGeneral Electric Company
InventorsVictor Hugo Silva Correia, Robert Francis Manning, George Joe-Kueng Chan, James Earl Kopriva
Life of this patent
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Abstract
An assembly for a turbine engine comprises a circumferential band defining an air flow path, a component having a leading edge and extending from the band into the flow path, and a trough located in a surface of the band along the leading edge.
Claims24
An assembly fora turbine engine having a combustion section emanating a combustion airflow, comprising:
- radially spaced inner and outer bands defining a flow path between the inner and outer bands, wherein the inner and outer bands each have an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge;
- an airfoil extending from one of the inner or outer bands into the flow path and defining a leading edge confronting the flow path, the airfoil having a pressure side and a suction side, and extending from the leading edge to a trailing edge to define a chord-wise direction, and extending from a root to a tip to define a span-wise direction, where the root is proximate one of the inner or outer bands and the tip is proximate the other of the inner or outer bands;
- and
- an imperforate trough extending into the surface of one of the inner or outer bands along the leading edge;
- whereby the imperforate trough generates a vortex in the combustion airflow.
An assembly for a turbine engine having a combustion section emanating a combustion airflow, comprising:
- at least one circumferential band at least partially defining an air flow path along which the combustion airflow moves and having an upstream edge and a downstream edge relative to the air flow path, with a surface extending between the upstream edge and the downstream edge;
- a component extending from the at least one circumferential band into the airflow path and defining a leading edge confronting the air flow path;
- an imperforate trough extending into the surface of the at least one circumferential band along the leading edge;
- and
- a flow enhancer located within the imperforate trough, wherein the flow enhancer comprises at least one of a turbulator, fastback turbulator, pin fins, pin bank, vortex generator, or chevron;
- whereby the imperforate trough generates a vortex in the combustion airflow.
An assembly for a turbine engine having a combustion section emanating a combustion airflow, comprising:
- at least one circumferential band at least partially defining an air flow path along which the combustion airflow moves and having an upstream edge and a downstream edge relative to the air flow path, with a surface extending between the upstream edge and the downstream edge;
- a component extending from the at least one circumferential band into the air flow path and defining a leading edge confronting the air flow path;
- and
- an imperforate trough extending into the surface of the at least one circumferential band along the leading edge;
- and
- a cove located at least along an intersection of the leading edge and the imperforate trough;
- whereby the imperforate trough generates a vortex in the combustion airflow.
Dependencies are inferred from the claim text.