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US 9,957,808 B2Granted
Airfoil leading edge film array
AssigneeUnited Technologies Corporation
InventorsThomas N. Slavens, Matthew A. Devore
Life of this patent
Estimating the term…
Abstract
An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a first cooling hole with a first cooling passage arranged at a first angle relative to a chordwise axis and a second cooling hole with a second cooling passage arranged at a second different angle relative to the chordwise axis. A radial projection of the first cooling passage intersects a radial projection of the second cooling passage.
Claims22
An airfoil for a gas turbine engine, comprising:
- a first cooling hole, having a first cooling passage arranged at a first angle relative to a chordwise axis;
- a second cooling hole, having a second cooling passage arranged at a second, different angle relative to said chordwise axis, wherein a radial projection of said first cooling passage intersects a radial projection of said second cooling passage, said chordwise axis being defined as an axis perpendicular to a spanwise axis, and extending from a leading edge in a direction towards a trailing edge of said airfoil;
- and
- wherein said first cooling passage has a first inlet and a first outlet, and said second cooling passage has a second inlet and a second outlet, and said second inlet is closer to said chordwise axis than said first inlet, and said first outlet is closer to said chordwise axis than said second outlet.
1 more element
A section for a gas turbine engine, comprising:
- a rotor;
- a variable vane positioned downstream of said rotor;
- wherein at least one of said rotor and said variable vane includes an airfoil having a plurality of first cooling passages and a plurality of second cooling passages, each of said first cooling passages having a first cooling passage arranged at a first angle relative to a chordwise axis, each of said second cooling passages having a second cooling passage arranged at a second, different angle relative to said chordwise axis, and a radial projection of one of said first cooling passages intersects a radial projection of one of said second cooling passages, said chordwise axis being defined as an axis perpendicular to a spanwise axis, and extending from a leading edge in a direction towards a trailing edge of said airfoil;
- and
- wherein each of said first cooling passages has a first inlet and a first outlet, and each of said second cooling passages has a second inlet and a second outlet, said second inlet being closer to said chordwise axis than said first inlet and said first outlet being closer to said chordwise axis than said second outlet.
2 more elements
Dependencies are inferred from the claim text.