Blade outer air seal cooling fin
A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.
1. A blade outer air seal (BOAS) for a gas turbine engine, comprising:
a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion, wherein the seal body forms a contiguous full ring hoop; and
a multitude of cooling fins attached around the radially outer face of the seal body, each of the multitude of cooling fins extend between the leading edge portion and the trailing edge portion, each of the multitude of cooling fins having at least one aperture transverse to the engine central longitudinal axis, the multitude of cooling fins arranged around the seal body such that each of the multitude of cooling fins are arranged generally parallel to an engine central longitudinal axis.
2. The blade outer air seal (BOAS) as recited in claim 1 , wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins have at least one aperture which defines a second area different than the first area.
3. The blade outer air seal (BOAS) as recited in claim 1 , further comprising a seal secured to the radially inner face of the seal body.
4. The blade outer air seal (BOAS) as recited in claim 3 , wherein the seal is a honeycomb seal.
5. The blade outer air seal (BOAS) as recited in claim 1 , wherein the multitude of cooling fins extends outboard of a radially outermost surface of at least one of the leading edge portion and the trailing edge portion.
6. The blade outer air seal (BOAS) as recited in claim 1 , wherein each of the multitude of cooling fins forms a triangular shape in cross-section.
7. The blade outer air seal (BOAS) as recited in claim 1 , wherein the multitude of cooling fins is manufactured of a nickel-chromium-iron-molybdenum alloy brazed to the radially outer face.
8. The blade outer air seal (BOAS) as recited in claim 7 , wherein the multitude of cooling fins is manufactured as a single component that is wrapped around the seal body, each of the multitude of cooling fins form a triangular shape in cross-section.
9. A gas turbine engine, comprising:
an engine casing;
a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion, the radially outer face adjacent to the engine casing, wherein the seal body forms a contiguous full ring hoop;
a honeycomb seal secured to the radially inner face of the full ring hoop seal body;
a multitude of cooling fins disposed around the radially outer face and spaced from the engine casing, each of the multitude of cooling fins extend between the leading edge portion and the trailing edge portion, each of the multitude of cooling fins having at least one aperture, the multitude of cooling fins manufactured as a single component that is wrapped around the seal body such that each of the multitude of cooling fins are arranged parallel to an engine central longitudinal axis, a first set of the multitude of cooling fins have at least one aperture transverse to the engine central longitudinal axis which defines a first area, and a second set of the multitude of cooling fins have at least one aperture transverse to the engine central longitudinal axis which defines a second area less than the first area, the second set of the multitude of cooling fins are circumferentially offset from the first set of the multitude of cooling fins to be adjacent to a cooling airflow injection port which injects cooling airflow parallel to the engine central longitudinal axis; and
a seal member mounted radially inward from the engine casing to the BOAS to limit the amount of cooling airflow injected into an annular cavity formed by the engine case and the BOAS.
10. The gas turbine engine as recited in claim 9 , wherein a BOAS is positioned radially outward from a blade tip of a blade of at least one of a compressor section and a turbine section.
11. The gas turbine engine as recited in claim 9 , wherein the first area is associated with a quantity of airflow to an annular cavity formed by the casing and a BOAS to provide a desired coefficient of thermal expansion for a blade outer air seal (BOAS).
12. A method of controlling a specific rate of thermal expansion that will match a corresponding blade design by using a cooling fin arrangement attached to a blade outer air seal (BOAS) for a gas turbine engine, comprising:
determining a desired coefficient of thermal expansion for a blade outer air seal (BOAS), wherein the blade outer air seal (BOAS) forms a full ring hoop;
manufacturing a configuration of cooling fins in accords with the desired coefficient of thermal expansion, an area of at least one aperture in each of a multitude of cooling fins disposed around a radially outer face of a seal body, a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins have at least one aperture which defines a second area different than the first area;
wrapping the configuration of cooling fins around the seal body such that each of the multitude of cooling fins are arranged parallel to an engine central longitudinal axis and the at least one aperture is transverse to the engine central longitudinal axis and the second set of the multitude of cooling fins are circumferentially offset from the first set of the multitude of cooling fins to be adjacent to a cooling airflow injection port; and
brazing the configuration of cooling fins as a corrugated full hoop to a radially outer face of the seal body.
13. The blade outer air seal (BOAS) as recited in claim 2 , further comprising a cooling airflow injection port which injects cooling airflow parallel to the engine axis.
14. The blade outer air seal (BOAS) as recited in claim 13 , wherein the second set of the multitude of cooling fins are circumferentially located adjacent to the cooling airflow injection port.
15. The blade outer air seal (BOAS) as recited in claim 7 , wherein the multitude of cooling fins are a corrugated full hoop.
16. The gas turbine engine as recited in claim 9 , wherein the multitude of cooling fins are manufactured of a nickel-chromium-iron-molybdenum alloy brazed to the radially outer face.
17. The gas turbine engine as recited in claim 16 , wherein the multitude of cooling fins are a corrugated full hoop.
18. The blade outer air seal (BOAS) as recited in claim 1 , wherein each of the multitude of cooling fins are arranged parallel to the engine axis.
19. The blade outer air seal (BOAS) as recited in claim 1 , wherein the multitude of cooling fins have a circumferentially spacing which forms an outer profile that is triangular.
20. The blade outer air seal (BOAS) as recited in claim 1 , wherein the multitude of cooling fins have a circumferentially spacing which forms an outer profile that is sinusoidal.
21. The blade outer air seal (BOAS) as recited in claim 1 , wherein the multitude of cooling fins have a circumferentially spacing which forms an outer profile that is an upside down “T” shape.
22. The blade outer air seal (BOAS) as recited in claim 1 , wherein the multitude of cooling fins have a circumferentially spacing which forms an outer profile that is an upside down “L” shape.
23. The blade outer air seal (BOAS) as recited in claim 1 , further comprising a multiple apertures within each of the multitude of cooling fins.
24. The blade outer air seal (BOAS) as recited in claim 23 , wherein the multitude of cooling fins extend across the entire length between the leading edge portion and the trailing edge portion.