Airfoils having tapered tip flag cavity and cores for forming the same
Core assemblies for manufacturing airfoils and airfoils for gas turbine engines are described. The core assemblies include a tip flag cavity core having an upstream portion, a tapering portion, and a downstream portion, with the tapering portion located between the upstream portion and the downstream portion and the downstream portion defines an exit in a formed airfoil. The upstream portion has a first radial height H 1 , the downstream portion has a second radial height H 2 that is less than the first radial height H 1 , the tapering portion transitions from the first radial height H 1 at an upstream end to the second radial height H 2 at a downstream end, and at least one metering pedestal aperture is located within the tapering portion.
1. A core assembly for manufacturing an airfoil for a gas turbine engine, the core assembly comprising:
a tip flag cavity core having an upstream portion, a tapering portion, and a downstream portion, with the tapering portion located between the upstream portion and the downstream portion and the downstream portion defines an exit in a formed airfoil, wherein:
the upstream portion has a first radial height H 1 ,
the downstream portion has a second radial height H 2 that is less than the first radial height H 1 ,
the tapering portion transitions from the first radial height H 1 at an upstream end to the second radial height H 2 at a downstream end, and
at least one metering pedestal aperture is located within the tapering portion,
wherein the tapering portion has a first circumferential thickness T 1 and the downstream portion has a second circumferential thickness T 2 , wherein the first circumferential thickness T 1 is greater than the second circumferential thickness T 2 .
2. The core assembly of claim 1 , further comprising:
a leading edge cavity core arranged in connection with the tip flag cavity core, wherein the leading edge cavity core is configured to form a leading edge cavity that is fluidly connected to a tip flag cavity formed by the tip flag cavity core.
3. The core assembly of claim 1 , further comprising one or more cavity cores configured to form a serpentine cavity in the formed airfoil.
4. The core assembly of claim 1 , further comprising a trailing edge cavity core configured to form a trailing edge cavity in the formed airfoil.
5. The core assembly of claim 1 , wherein the first circumferential thickness T 1 has a relationship to the second circumferential thickness T 2 of between 1.25:1 to 4:1.
6. The core assembly of claim 1 , wherein the at least one metering pedestal aperture is positioned at an axial location L a within the tapering portion, with the axial location L a based on a point of transition from the upstream portion to the tapering portion.
7. The core assembly of claim 1 , wherein the at least one metering pedestal aperture is two metering pedestal apertures.
8. The core assembly of claim 1 , further comprising at least one structure to form a cooling feature fluidically connected to a formed gas path located within the downstream portion.
9. The core assembly of claim 1 , wherein the first radial height H 1 has a relationship to the second radial height H 2 of between 1.25:1 to 4:1.
10. An airfoil for a gas turbine engine, the airfoil comprising:
a tip flag cavity arranged proximate a tip of an airfoil body, the tip flag cavity having an upstream portion, a tapering portion, and a downstream portion, with the tapering portion located between the upstream portion and the downstream portion and the downstream portion defines an exit in the airfoil body, wherein:
the upstream portion has a first radial height H 1 ,
the downstream portion has a second radial height H 2 that is less than the first radial height H 1 ,
the tapering portion transitions from the first radial height H 1 at an upstream end to the second radial height H 2 at a downstream end, and
at least one metering pedestal is located within the tapering portion,
wherein the tapering portion has a first circumferential thickness T 1 and the downstream portion has a second circumferential thickness T 2 , wherein the first circumferential thickness T 1 is greater than the second circumferential thickness T 2 .
11. The airfoil of claim 10 , further comprising a leading edge cavity arranged in fluid connection with the tip flag cavity.
12. The airfoil of claim 10 , further comprising a serpentine cavity.
13. The airfoil of claim 10 , further comprising a trailing edge cavity.
14. The airfoil of claim 10 , wherein the first circumferential thickness T 1 has a relationship to the second circumferential thickness T 2 of between 1.25:1 to 4:1.
15. The airfoil of claim 10 , wherein the at least one metering pedestal is positioned at an axial location L a within the tapering portion, with the axial location L a based on a point of transition from the upstream portion to the tapering portion.
16. The airfoil of claim 10 , wherein the at least one metering pedestal is two metering pedestals.
17. The airfoil of claim 10 , further comprising at least one cooling feature fluidically connected to the gas path located within the downstream portion.
18. The airfoil of claim 10 , wherein the first radial height H 1 has a relationship to the second radial height H 2 of between 1.25:1 to 4:1.