Airfoil with cooling hole having a flared section
Abstract
An airfoil is provided for a gas turbine engine. The airfoil may comprise a main body comprising a leading edge having a leading edge outer surface, a trailing edge having a trailing edge outer surface, a suction side having a suction side outer surface and a pressure side having a pressure side outer surface. The main body may further comprise at least one interior cooling passage and a plurality of cooling holes extending from the cooling passage to at least one of the leading edge outer surface, the trailing edge outer surface, the suction side outer surface and the pressure side outer surface. Preferably, at least one of the cooling holes includes a proximal metering section having a first dimension extending transverse to an axis extending in a flow direction of a cooling fluid passing through the one cooling hole, a flared section and an exit opening having a second dimension transverse to the axis which is larger than the first dimension. The flared section is preferably curvilinear as it extends from the proximal metering section towards the exit opening.
Claims
exact text as granted — not AI-modified1 . An airfoil for a gas turbine engine comprising:
a main body comprising a leading edge having a leading edge outer surface, a trailing edge having a trailing edge outer surface, a suction side having a suction side outer surface and a pressure side having a pressure side outer surface, said main body further comprising at least one interior cooling passage and a plurality of cooling holes extending from said cooling passage to at least one of said leading edge outer surface, said trailing edge outer surface, said suction side outer surface and said pressure side outer surface; at least one of said cooling holes including a proximal metering section having a first dimension extending transverse to an axis extending in a flow direction of a cooling fluid passing through said one cooling hole, a flared section and an exit opening having a second dimension transverse to the axis which is larger than said first dimension, wherein said flared section is curvilinear as it extends from said proximal metering section towards said exit opening.
2 . An airfoil as set out in claim 1 , wherein said one cooling hole further comprises a distal section extending from at least a portion of said flared section to at least a portion of said exit opening.
3 . An airfoil as set out in claim 2 , wherein said one cooling hole further comprises a concave interface section located between said flared section and said distal section.
4 . An airfoil as set out in claim 2 , wherein said flared section meets directly with said distal section.
5 . An airfoil as set out in claim 1 , wherein said proximal metering section has a diameter D and a length between about 1.0D and about 5.0D.
6 . An airfoil as set out in claim 5 , wherein said one cooling hole extends at an angle θ of from about 20 degrees to about 90 degrees to said one outer surface.
7 . An airfoil as set out in claim 6 , wherein said one outer surface has a thickness T and said one cooling hole has an overall length L determined from the following equation:
length L =thickness T /Sin θ
8 . An airfoil as set out in claim 5 , wherein said diameter D of said proximal metering section is from about 0.5 mm to about 5.0 mm.
9 . An airfoil as set out in claim 1 , wherein the shape of said flared section is defined by the following equation:
y
=
y
1
4
×
1
+
[
(
y
1
/
y
0
)
4
-
1
]
·
[
1
-
x
1
d
]
wherein:
y 1 =an exit radius or dimension for a largest portion of said flared section;
y 0 =a radius of said proximal metering section;
I d =a length of a longest portion of said flared section;
x=independent coordinate extending along the axis with an origin at a beginning of said flared section; and
y=dependent coordinate perpendicular to the axis with an origin at a central axis of said one cooling hole.
10 . An airfoil as set out in claim 9 , wherein said exit opening is square or circular in shape as viewed along the axis of said one cooling hole.
11 . An airfoil as set out in claim 1 , wherein the shape of said flared section is defined by the following equation:
y
=
y
1
1
+
[
(
y
1
/
y
0
)
2
-
1
]
·
[
1
-
x
1
d
]
wherein:
y 1 =an exit radius or dimension for a curvilinear portion of said flared section;
y 0 =a radius of said proximal metering section;
I d =a length of a longest portion of said flared section;
x=independent coordinate extending along the axis with an origin at a beginning of said flared section; and
y=dependent coordinate perpendicular to the axis with an origin at a central axis of said one cooling hole.Join the waitlist — get patent alerts
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