Cooling hole with shaped meter
A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.
1. A gas turbine engine component having a cooling passage, the component comprising:
a wall comprising:
a first wall surface defining an inlet of the cooling passage;
a second wall surface opposite the first wall surface and defining an outlet of the cooling passage;
a metering section extending downstream from the inlet, the metering section comprising:
an upstream side; and
a downstream side opposite the upstream side, wherein the downstream side comprises a first passage wall and a second passage wall, and wherein the upstream side comprises a third passage wall and a fourth passage wall, the first passage wall, the second passage wall, the third passage wall, and the fourth passage wall each being located in a common plane transverse to a longitudinal axis of the metering section;
a diffusing section extending from the metering section to the outlet, wherein the diffusing section comprises multiple lobes and a ridge located between two lobes of the multiple lobes;
wherein
the first and second passage walls are straight within the common plane and extend towards the downstream side to form a first V-shape in the common plane at the ridge; and
the third and fourth passage walls are straight within the common plane and extend towards the downstream side to form a second V-shape in the common plane.
2. The gas turbine engine component of claim 1 , wherein the first passage wall and the second passage wall intersect to form an angle that is greater than 90 degrees.
3. The gas turbine engine component of claim 1 , wherein the first passage wall and the third passage wall are parallel, and wherein the second passage wall and the fourth passage wall are parallel.
4. The gas turbine engine component of claim 1 , wherein the first V-shape has a first angle and the second V-shape has a second angle, wherein the first angle and the second angle are non-equivalent.
5. The gas turbine engine component of claim 4 , wherein the first and second V-shapes form a chevron shape having a center and two opposite ends, wherein the chevron shape has a height at the center that is greater than a height at either of the two opposite ends.
6. The gas turbine engine component of claim 1 , wherein the first V-shape and the second V-shape together define a chevron exit of the metering section, and wherein the multiple lobes each increase in lateral width and depth in a direction along the ridge, the ridge being inclined relative to the second wall surface and having a decreasing depth to the chevron exit of the metering section.
7. The gas turbine engine component of claim 1 , wherein the component is selected from the group consisting of a blade airfoil, a vane airfoil, a blade platform, a vane platform, a combustor liner, a blade outer air seal, a blade shroud, an augmentor, and an endwall.
8. A method of forming the gas turbine engine component of claim 1 , wherein the diffusing section is formed by electrical discharge machining first and the metering section is formed by electrical discharge machining second.
9. A method of forming the gas turbine engine component of claim 1 , wherein the gas turbine engine component is additively manufactured.