초록 ▼

A gas turbine engine component is disclosed having a cooling fluid passageway that provides relatively cool fluid to a surface of the gas turbine engine component. The cooling fluid passageway can be shaped in cross section to reduce a stress present in the gas turbine engine component. One form of

A gas turbine engine component is disclosed having a cooling fluid passageway that provides relatively cool fluid to a surface of the gas turbine engine component. The cooling fluid passageway can be shaped in cross section to reduce a stress present in the gas turbine engine component. One form of the shape is non-circular. The gas turbine engine component can be formed such that an overhanging material otherwise formed by the intersection of a cooling fluid passageway and a surface of the gas turbine engine component is absent. The gas turbine engine component can also have a depression formed near the surface of the gas turbine engine component such that the cooling fluid passageway exits into an upstream portion and a downstream portion of the depression.

대표청구항 ▼

1. An apparatus comprising: a film cooled gas turbine engine component having a passage defined by a passage surface for flowing a cooling air to a hot side, the passage extending at an acute angle to the hot side surface and the passage surface having a hot side surface side; andan edge break forme

1. An apparatus comprising: a film cooled gas turbine engine component having a passage defined by a passage surface for flowing a cooling air to a hot side, the passage extending at an acute angle to the hot side surface and the passage surface having a hot side surface side; andan edge break formed in the gas turbine engine component and having an edge break surface extending from the hot side surface to the hot side surface side of the passage, the side of the passage opposite the hot side surface side continuing to the hot side, the edge break representing an overhanging material absent from the gas turbine engine component when an edge break surface is formed; andwherein the passage includes a non-circular cross section defined by (xa)n+(yma)n=1, where x and y are variables and a, m, and n selected as constants to define the shape of the non-circular cross section; and wherein in the pair {m,n}, n does not equal 2 and m does not equal 1. 2. The apparatus of claim 1, wherein the edge break surface forms an angle of 45 degrees relative to the hot side surface. 3. The apparatus of claim 1, wherein the edge break surface extends to lateral edges of the passage. 4. The apparatus of claim 1, which further includes a ramp formed between a bottom edge of the edge break surface relative to the hot side surface and extending to the hot side surface at an angle less than the acute angle of the passage. 5. The apparatus of claim 4, wherein the passage exit is defined by the edge break surface and a surface of the ramp. 6. The apparatus of claim 1, wherein the edge break is part of a monolithic construction that includes a portion of the film cooled gas turbine engine component defining the passage. 7. The apparatus of claim 1, wherein the passage includes sides located between rounded corners and symmetric about two axes. 8. The apparatus of claim 7, wherein the sides are curved between the rounded corners. 9. The apparatus of claim 1, wherein the edge break surface forms an angle of between 60 degrees and 120 degrees relative to the hot side surface. 10. An apparatus comprising: a gas turbine engine turbine component having film cooling and a passage for conveying a cooling air to a surface of the gas turbine engine component, the passage having a non-circular cross sectional shape that produces a first stress under a loading condition that is relatively lower than a second stress produced by a passage that includes a circular cross sectional shape; andwhich further includes a diffuser between the surface and the passage; andwherein the diffuser includes a valley positioned between an upstream edge break and a downstream ramp, wherein the upstream edge break represents material missing from the gas turbine engine component by the failure of the passage to extend intact to the surface of the gas turbine engine component;wherein the passage takes the form of a cross sectional shape defined by a mathematical equation, the cross sectional shape representing the cross section that corresponds to the flow area of the passage;wherein the shape is defined by (xa)n+(yma)n=1, where x and y are variables and a, m, and n selected as constants to define the shape; and wherein the values of m and n are not {1,2}. 11. The apparatus of claim 10, wherein the passage includes sides located between rounded corners and symmetric about two axes. 12. The apparatus of claim 11, wherein the sides are curved between the rounded corners. 13. The apparatus of claim 10, which further includes an upright surface formed between the passage for conveying a cooling air and the surface of the gas turbine engine component. 14. The apparatus of claim 10, wherein the passage extends at an acute angle to a hot side of the gas turbine engine turbine component. 15. The apparatus of claim 10, wherein the edge break is part of a monolithic construction that includes a portion of the gas turbine engine component defining the passage. 16. An apparatus comprising: a coolable gas turbine engine component having a hot side and a film cooling opening operable to discharge a cooling fluid to create a film cooling for the hot side; anda depression formed in part by an edge break of a cooling hole and having an upstream portion that descends from the hot side to a valley, a downstream portion that ascends from the valley toward the hot side, the film cooling opening having a portion that discharges through the upstream portion and a portion that discharges through the downstream portion of the depression, wherein the edge break is defined as a surface formed in the coolable gas turbine engine component between the hot side and a passage that provides the film cooling opening, wherein the edge break is part of a monolithic construction that includes a portion of the coolable gas turbine engine component defining the cooling hole;wherein the valley extends in a line from one lateral side of the film cooling opening to another side of the film cooling opening. 17. The apparatus of claim 16, which further includes opposing sidewalls on each end of the downstream and upstream portion, wherein the downstream portion is substantially planar. 18. The apparatus of claim 16, wherein the upstream portion is substantially planar. 19. The apparatus of claim 16, wherein the passage includes a non-circular cross section. 20. The apparatus of claim 16, wherein a cross sectional shape corresponding to the flow area of the passage is defined by (xa)n+(yma)n=1, where x and y are variables and a, m, and n selected as constants to define the shape. 21. The apparatus of claim 16, wherein the passage extends at an acute angle to the hot side. 22. The apparatus of claim 16, wherein the passage includes sides located between rounded corners and symmetric about two axes. 23. The apparatus of claim 22, wherein the sides are curved between the rounded corners.