Diffuser case heat shields
A gas turbine engine includes a high pressure compressor disposed about a central longitudinal axis, a combustor, and a diffuser case. The diffuser case includes an outer ring providing a first platform and an inner ring providing a second platform. The first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis. A plurality of circumferentially spaced struts extend radially from the first platform to the second platform and each include first and second circumferential sides. A plurality of heat shields are disposed on a leading edge defined at a forward end of a respective one of the plurality of struts.
1. A gas turbine engine, comprising:
a high pressure compressor disposed about a central longitudinal axis;
a combustor; and
a diffuser case including
an outer ring providing a first platform,
an inner ring providing a second platform, wherein the first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis,
a plurality of circumferentially spaced struts extending radially from the first platform to the second platform and each including first and second circumferential sides, and
a plurality of heat shields, each disposed on a leading edge defined at a forward end of a respective one of the plurality of struts, wherein a radial distance at the leading edge from the first platform to the second platform defines a first radial height, and a radial distance from the first platform to the radially outermost point of the heat shield is a second radial height, and the second radial height is 5-80% of the first radial height.
2. The gas turbine engine as recited in claim 1 , wherein each of the plurality of heat shields includes a first extension portion and a second extension portion, wherein the first extension portion extends aft to a first end, the second extension portion extends aft to a second end, and the first and second end are spaced axially forward from a trailing edge of the strut.
3. The gas turbine engine as recited in claim 1 , wherein the first platform and the second platform bound a portion of a core flow path of the gas turbine engine.
4. The gas turbine engine as recited in claim 3 , wherein the high pressure compressor includes an exit guide vane including a first vane platform and a second vane platform, wherein the first platform contacts the first vane platform, and the second platform contacts the second vane platform.
5. The gas turbine engine as recited in claim 1 , wherein each of the plurality of struts includes an internal cavity.
6. The gas turbine engine as recited in claim 5 , wherein at least one of the plurality of heat shields and the plurality of struts includes at least one pedestal to provide at least one passageway between each of the plurality of heat shields and the plurality of struts.
7. The gas turbine engine as recited in claim 6 , wherein the internal cavities and a respective one of the at least one passageway are in fluid communication through cooling holes in the plurality of struts.
8. The gas turbine engine as recited in claim 1 , wherein a lip extends radially inward from the second platform and provides a first flange and a second flange, and each of the plurality of heat shields is disposed on the first flange and second flange.
9. The gas turbine engine as recited in claim 1 , wherein each of the plurality of heat shields is formed of a nickel alloy.
10. The gas turbine engine as recited in claim 1 , wherein each of the plurality of heat shields is received in a recess of the respective one of the plurality of struts.
11. The gas turbine engine as recited in claim 1 , wherein the radially outermost point of the heat shield is radially inward of the first platform at the leading edge.
12. A gas turbine engine, comprising:
a high pressure compressor disposed about a central longitudinal axis;
a combustor; and
a diffuser case including
an outer ring providing a first platform,
an inner ring providing a second platform, wherein the first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis,
a plurality of circumferentially spaced struts extending radially from the first platform to the second platform and each including first and second circumferential sides, and
a plurality of heat shields, each disposed on a leading edge defined at a forward end of a respective one of the plurality of struts, wherein each of the plurality of heat shields includes a radially inner portion that extends to cover a lip extending radially inward from the second platform, a radial distance at the leading edge from the first platform to the second platform defines a first radial height, and a radial distance from the first platform to the radially outermost point of the heat shield is a second radial height, and the second radial height is 5-80% of the first radial height.
13. The gas turbine engine as recited in claim 12 , wherein the radially inner portion is received in a pocket in the lip.
14. The gas turbine engine as recited in claim 12 , wherein each of the plurality of heat shields includes a radially outer portion providing a curved outer surface.
15. The gas turbine engine as recited in claim 14 , wherein the curved surface is a concave surface that curves inward as it extends radially outward and axially aft.
16. The gas turbine engine as recited in claim 12 , wherein the radially inner portion provides first and second flanges, and a radially inwardly extending portion radially inward of the first and second flanges.
17. The gas turbine engine as recited in claim 16 , wherein the radially inwardly extending portion provides one or more openings to accommodate one or more fasteners.
18. A gas turbine engine, comprising:
a high pressure compressor disposed about a central longitudinal axis;
a combustor; and
a diffuser case including
an outer ring providing a first platform,
an inner ring providing a second platform, wherein the first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis, wherein the first platform and the second platform bound a portion of a core flow path of the gas turbine engine, wherein the high pressure compressor includes an exit guide vane including a first vane platform and a second vane platform, wherein the first platform contacts the first vane platform, and the second platform contacts the second vane platform,
a plurality of circumferentially spaced struts extending radially from the first platform to the second platform and each including first and second circumferential sides, wherein each of the plurality of struts includes an internal cavity, and
a plurality of heat shields, each disposed on a leading edge of a respective one of the plurality of struts, wherein each of the plurality of heat shields includes a first extension portion and a second extension portion, wherein the first extension portion extends aft to a first end, the second extension portion extends aft to a second end, and the first and second end are spaced axially forward from a trailing edge of the strut,
each of the plurality of heat shields includes
a radially inner portion that extends to cover a lip extending radially inward from the second platform, and the radially inner portion is received in a pocket in the lip,
a radially outer portion providing a curved outer surface, the curved surface is a concave surface that curves inward as it extends radially outward and axially aft
wherein a radial distance at the leading edge from the first platform to the second platform defines a first radial height, and a radial distance from the first platform to the radially outermost point of the heat shield is a second radial height, and the second radial height is 5-80% of the first radial height.