Engine with chevron pin bank
AssigneeGeneral Electric Company
InventorsEmily Clark Clark, Julienne LaChance
Life of this patent
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Abstract
An apparatus for a turbine engine, such as a gas turbine engine, can include an engine component such as an airfoil. The airfoil includes an outer wall with a pressure side and a suction side confronting a hot gas flow exterior of the airfoil. A cooling circuit can provide a flow of cooling fluid through the interior of the airfoil to cool the airfoil operating within the hot gas flow. The cooling circuit can include a pin bank to induce turbulence on the cooling fluid to improve cooling of the airfoil.
Claims21
An airfoil for a turbine engine, the airfoil comprising:
- an outer wall defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction;
- a cooling circuit located within the airfoil and with a cooling passage including opposing sidewalls, and at least partially defining the cooling circuit;
- and
- a pin bank provided in the cooling passage comprising multiple chevron pins with at least one chevron pin of the multiple chevron pins including a pair of linear legs joined at a junction, where the multiple chevron pins are arranged in rows where the chevron pins in each row are separated by an intervening gap, where the rows are offset such that one intervening gap of one row is aligned in the span-wise direction with a chevron pin of an adjacent row;
- and
- at least one cooling fluid flow path extending in the span-wise direction through the one intervening gap of the one row and intersecting the chevron pin of the adjacent row.
A component for a turbine engine, the component comprising:
- a wall separating a cooling airflow from a hot airflow having a first surface facing the cooling airflow and a second surface facing the hot airflow;
- a cooling circuit at least partially defined by the wall and including a cooling passage having opposing sidewalls and defining a passage axis along a longitudinal length of the cooling passage;
- and
- a pin bank provided in the cooling passage comprising multiple chevron pins with at least one chevron pin of the multiple chevron pins including a pair of linear legs joined at a junction, where the multiple chevron pins are arranged in rows where the chevron pins in each row are separated by an intervening gap, where the rows are offset such that one intervening gap of one row is aligned along the passage axis with a chevron pin of an adjacent row;
- and
- at least one cooling fluid flow path extending along the passage axis through the one intervening gap of the one row and intersecting the chevron pin of the adjacent row.
An airfoil for a turbine engine, the airfoil comprising:
- an outer wall defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction;
- a cooling circuit located within the airfoil and with a cooling passage including opposing sidewalls, and at least partially defining the cooling circuit;
- and
- a pin bank provided in the cooling passage comprising a set of chevron pins arranged in rows, with the chevrons in each row separated by an intervening gap, and the rows being offset, such that the chevron pins of one row are aligned with the gap of an adjacent row, and the chevron pins of the one row have an effective width confronting the gap that is wider than the gap of the adjacent row;
- and
- at least one cooling fluid flow path through the rows is at least partially defined by the gaps in sequential rows.
Dependencies are inferred from the claim text.