Cooling features for a component of a gas turbine engine
A component for a gas turbine engine, including: at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity; a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features are formed in accordance with at least one of the following groups: i) a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity and a plurality of wedge shaped features each having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the surface than the downstream portion; ii) a plurality features having a curved or “J” shaped base that extends upwardly from the surface, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface, and a plurality features having a base that extends upwardly from the surface with a curved portion that defines an opening therethrough; iii) a first plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the first plurality of pins and a second plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the second plurality of pins the plurality of grooves formed in the peripheral surface of each of the second plurality of pins are configured such that “V” shapes or inverted “V” shapes are formed in the peripheral surface of each of the second plurality of pins; and iv) a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.
1. A component for a gas turbine engine, comprising:
at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity;
a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features comprising:
a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity each of the plurality of airfoil shaped features includes a base portion that extends upwardly away from the surface and the base portion also extends horizontally with respect to the surface such that a tail portion is formed, the tail portion creates an undercut portion located underneath the tail portion and a first portion of the plurality of airfoil shaped features are oriented such that the tail portion comprises an upstream end of the first portion of the plurality of airfoil shaped features and a second portion of the plurality of airfoil shaped features are oriented such that the tail portion comprises a downstream end of the second portion of the plurality of airfoil shaped features.
2. The component according to claim 1 , wherein a third portion of the plurality of airfoil shaped features has a tail portion that is shifted and/or rotated with respect to a base portion of the third portion of the plurality of airfoil shaped features.
3. The component according to claim 1 , further comprising a plurality of cooling features comprising a plurality features having a curved or “J” shaped base that extends upwardly from the surface of the at least one internal cavity, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface of the at least one internal cavity, and a plurality features having a base that extends upwardly from the surface of the at least one internal cavity with a curved portion that defines an opening therethrough, wherein the plurality features having the curved or “J” shaped base have an undercut portion located below a distal end of the curved or “J” shaped base.
4. The component according to claim 3 , wherein the plurality features having the double curved or symmetrically “J” shaped base have an undercut portion located below a distal end of the curved or “J” shaped base.
5. The component according to claim 3 , wherein each of the plurality features having the curved portion have surfaces that are angled inwardly toward each other as they extend from either an upstream end or a downstream end such that a narrow cross section of the base is provided at the opening.
6. The component according to claim 5 , wherein each of the plurality features having the curved portion have a gap provided at a top of the curved portion.
7. The component according to claim 3 , wherein each of the plurality features having the curved portion have a width that varies.
8. The component according to claim 1 , wherein a plurality of cooling features are located on an upper surface spaced from the surface, the plurality of cooling features located on the upper surface are rounded or circular protrusions that extend from the upper surface.
9. The component according to claim 1 , wherein the component is one of a blade outer air seal, a turbine blade, and vane.
10. The component according to claim 1 , further comprising a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip of the plurality of chevron shaped trip strips has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.
11. A gas turbine engine, comprising the component of claim 1 , wherein the component is configured to receive a cooling air flow.
12. A component for a gas turbine engine, comprising:
at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity;
a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features comprising:
a plurality of wedge shaped features that extend upwardly from the surface of the at least one internal cavity each of the plurality of wedge shaped features having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the surface than the downstream portion, wherein each of the plurality of wedge shaped features have a pair of channels located in side walls of each of the plurality of wedge shaped features and the pair of channels taper downwardly towards the downstream portion.
13. The component according to claim 12 , wherein each of the plurality of wedge shaped features each have an undercut portion located at the upstream portion.
14. The component according to claim 12 , wherein the component is one of a blade outer air seal, a turbine blade, and vane.
15. The component according to claim 12 , further comprising a plurality of cooling features comprising a plurality features having a curved or “J” shaped base that extends upwardly from the surface of the at least one internal cavity, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface of the at least one internal cavity, and a plurality features having a base that extends upwardly from the surface of the at least one internal cavity with a curved portion that defines an opening therethrough, wherein the plurality features having the curved or “J” shaped base have an undercut portion located below a distal end of the curved or “J” shaped base.
16. The component according to claim 12 , further comprising a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip of the plurality of chevron shaped trip strips has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.
17. A component for a gas turbine engine, comprising:
at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity;
a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features comprising:
a first plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the first plurality of pins and a second plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the second plurality of pins, the plurality of grooves formed in the peripheral surface of each of the second plurality of pins are configured such that “V” shapes or inverted “V” shapes are formed in the peripheral surface of each of the second plurality of pins, wherein the plurality of grooves that are formed into the peripheral surface of each of the first plurality of pins are curved so that they twist either clockwise or counter clockwise with respect to a top surface of the first plurality of pins.
18. The component according to claim 17 , wherein the component is one of a blade outer air seal, a turbine blade, and vane.
19. The component according to claim 17 , further comprising a plurality of cooling features comprising a plurality features having a curved or “J” shaped base that extends upwardly from the surface of the at least one internal cavity, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface of the at least one internal cavity, and a plurality features having a base that extends upwardly from the surface of the at least one internal cavity with a curved portion that defines an opening therethrough, wherein the plurality features having the curved or “J” shaped base have an undercut portion located below a distal end of the curved or “J” shaped base.
20. The component according to claim 17 , further comprising a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip of the plurality of chevron shaped trip strips has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.
21. A component for a gas turbine engine, comprising:
a plurality of cooling features extending from an exterior surface of the component, the plurality of cooling features are formed in accordance with at least one of the following groups:
i) a plurality of wedge shaped features that extend upwardly from the exterior surface, each of the plurality of wedge shaped features having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the exterior surface than the downstream portion wherein each of the plurality of wedge shaped features have a pair of channels located in side walls of each of the plurality of wedge shaped features and the pair of channels taper downwardly towards the downstream portion;
ii) a first plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the first plurality of pins and a second plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the second plurality of pins the plurality of grooves formed into the peripheral surface of each of the second plurality of pins are configured such that “V” shapes or inverted “V” shapes are formed in the peripheral surface of each of the second plurality of pins, wherein the plurality of grooves that are formed into the peripheral surface of each of the first plurality of pins are curved so that they twist either clockwise or counter clockwise with respect to a top surface of the first plurality of pins; and
iii) a plurality of airfoil shaped features that extend upwardly from the exterior surface of the of the component each of the plurality of airfoil shaped features includes a base portion that extends upwardly away from the exterior surface of the component and the base portion also extends horizontally with respect to the exterior surface of the component such that a tail portion is formed, the tail portion creates an undercut portion located underneath the tail portion and a first portion of the plurality of airfoil shaped features are oriented such that the tail portion comprises an upstream end of the first portion of the plurality of airfoil shaped features and a second portion of the plurality of airfoil shaped features are oriented such that the tail portion comprises a downstream end of the second portion of the plurality of airfoil shaped features.