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US 10,590,778 B2Granted
Engine component with non-uniform chevron pins
AssigneeGeneral Electric Company
InventorsEmily Rosette Clark, Weston Nolan Dooley, Kirk D. Gallier
Life of this patent
Estimating the term…
Abstract
An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.
Claims26
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 comprising a passage wall defining a cooling passage;
- and
- at least one pin spanning the cooling passage and having two legs each defining a leg axis and joined at a junction defining a pin centerline, where the pin is asymmetrical relative to the pin centerline;
- wherein the at least one pin includes an internal passage extending at least partially through the at least one pin.
2 more elements
A component for a turbine engine, component comprising:
- an outer 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 located within the component and comprising a passage wall with opposing sidewalls defining a cooling passage therebetween, and defining a passage centerline equidistant from the passage sidewalls;
- and
- at least one pin spanning the cooling passage and having two legs each defining a leg axis and joined at a junction defining a pin centerline, and the at least one pin being asymmetrical relative to the pin centerline and having the pin centerline arranged along the passage centerline.
1 more element
A method of cooling an engine component, the method comprising:
- generating an asymmetrical turbulent flow by flowing a cooling fluid over at least one pin having two legs each defining a leg axis and joined at a junction defining a pin centerline, and the at least one pin being asymmetrical relative to the pin centerline;
- and
- passing at least a portion of the cooling fluid through an interior passage within the at least one pin.
Dependencies are inferred from the claim text.