초록 ▼

A fan containment system for a gas turbine engine, and a method of making the same, is disclosed that in one embodiment includes casing that surrounds at least a portion of a plurality of fan blades. In one form, a pair of standoff rings is formed in an outer surface of the casing that are spaced ap

A fan containment system for a gas turbine engine, and a method of making the same, is disclosed that in one embodiment includes casing that surrounds at least a portion of a plurality of fan blades. In one form, a pair of standoff rings is formed in an outer surface of the casing that are spaced apart from one another a predetermined distance running circumferentially about the inner nacelle ring. A containment ring is positioned around a radially outer surface of the standoff rings to form an interference fit between the two.

대표청구항 ▼

1. A containment system for rotating turbomachinery, comprising: a gas turbine engine flow path structure having an annular shape;an outer ring located radially outward of the gas turbine engine flow path structure, the outer ring operable to be at least partially radially in-line with a rotating bl

1. A containment system for rotating turbomachinery, comprising: a gas turbine engine flow path structure having an annular shape;an outer ring located radially outward of the gas turbine engine flow path structure, the outer ring operable to be at least partially radially in-line with a rotating blade of a gas turbine engine, wherein the outer ring includes first and second protrusions extending radially inward from a surface to form an inner space of the outer ring; andan abutment structure coupling the outer ring to the gas turbine engine flow path structure in an interference fit;wherein the gas turbine engine flow path structure includes first and second standoffs extending from the same base, wherein the standoffs and base form a monolithic structure, the first and second standoffs forming a portion of the abutment structure coupling the outer ring to the gas turbine engine flow path structure;wherein the first and second standoffs are located between the first and second protrusions. 2. The containment system of claim 1 wherein the outer ring is an integral structure, and wherein outer ring contacts the gas turbine engine flow path structure. 3. The containment system of claim 1 wherein the standoffs are circumferential standoff rings formed along an annular surface of the gas turbine engine flow path structure. 4. The containment system of claim 1 wherein the protrusions and the standoffs form at least part of the abutment structure coupling the outer ring to the gas turbine engine flow path structure. 5. The containment system of claim 4 wherein at least one of the protrusions is coupled to at least one of the standoffs with a mechanical fastener. 6. The containment system of claim 5 wherein the mechanical fastener is one of a rivet, a bolt, or a screw. 7. The containment system of claim 4 which further includes a containment cavity formed between the gas turbine engine flow path structure and the outer ring. 8. A rotating component safety device comprising: a gas turbine engine containment ring having first and second radial press fit locating features that extend radially inwardly from opposite sides of the containment ring, anda gas turbine engine fan casing having an annular shape base portion and first and second radial press fit locating features that both extend from the base portion;the containment ring having a radially inner open interior operable to be coupled to the gas turbine engine fan casing received into the radially inner open interior via an interference;wherein the first and second radial press fit locating features of the fan casing extend radially outwardly toward the gas turbine engine containment ring, and the radial press fit locating features of the gas turbine engine fan casing are located axially inwardly of the radial press fit locating features of the gas turbine engine containment ring. 9. The device of claim 8 wherein the gas turbine engine containment ring includes a ribbed surface. 10. The device of claim 8 wherein the radial press fit locating features are formed in an inner diameter side of the gas turbine engine containment ring. 11. The device of claim 10 wherein the radial press fit locating features are formed as protrusions that extend from the inner diameter side of the gas turbine engine containment ring. 12. The device of claim 8 wherein the radial press fit locating features of the fan casing are complementary to the radial press fit locating features of the gas turbine engine containment ring. 13. The device of claim 8 wherein the fan casing may be formed from a material selected from the group consisting of aluminum and a light weight composite material, and the gas turbine engine containment ring may be formed from a material selected from the group consisting of steel, titanium, or a heavy-duty composite material. 14. An apparatus comprising: a fan casing arrangement for a gas turbine engine including radially outwardly projecting means, wherein the radially outwardly projecting means includes a base portion and radially outwardly projecting first and second standoffs both extending from the base portion, wherein the base portion and radially outwardly projecting first and second standoffs form a monolithic structure;a containment ring including radially inwardly projecting means, the radially inwardly projecting means including first and second protrusions extending radially inwardly; andthe radially outwardly projecting first and second standoffs of the radially outwardly projecting means and the radially inwardly projecting means being configured for interference fit coupling the fan casing to the containment ring;wherein the first and second standoffs are located between the first and second protrusions. 15. A method comprising: subjecting a containment ring and an annular flowpath structure to a heat transfer process, the heat transfer process resulting in a difference in temperature between the containment ring and the flowpath structure, the containment ring having a first engagement surface located upstream of a second engagement surface, the annular flowpath structure having a base portion and a first radially outwardly projecting receiving portion upstream of a second radially outwardly projecting receiving portion, wherein the first and second radially outwardly projecting receiving portions both extend from the base portion;placing the containment ring around the annular flowpath structure;locating the first engagement surface of the containment ring upstream of the first radially outwardly projecting receiving portion of the annular flowpath structure, and locating the second engagement surface of the containment ring downstream of the second radially outwardly projecting receiving portion of the annular flowpath structure; andcoupling the containment ring during assembly through the heat transfer process to the annular flowpath structure to form an interference fit between the first and second engagement surfaces and the respective first and second radially outwardly projecting receiving portions. 16. The method of claim 15 wherein the subjecting includes heating the containment ring to an elevated temperature relative to the flowpath structure. 17. The method of claim 16 wherein the subjecting includes cooling the flowpath structure to a depressed temperature relative to the containment ring. 18. The method of claim 15 wherein the placing includes aligning a central axis of the containment ring with a central axis of the annular flowpath structure and translatingly moving the containment ring along its central axis. 19. The method of claim 15 wherein the coupling includes alleviating the heat transfer process, wherein a difference in temperature during the coupling is less than the difference in temperature during the subjecting. 20. The method of claim 19 wherein the coupling includes engaging a locating feature of the containment ring with a locating feature of the annular flowpath structure.