A gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoi
A gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoins the first leg to a second leg, which is conical in shape. A seal is supported by the second leg.
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1. A gas turbine engine comprising: a seal assembly supported by a member at a joint, the seal assembly including a seal support having a radial flange secured to the joint, a first bend adjoins the radial flange and a first leg, which extends from the radial flange generally in a first axial direct
1. A gas turbine engine comprising: a seal assembly supported by a member at a joint, the seal assembly including a seal support having a radial flange secured to the joint, a first bend adjoins the radial flange and a first leg, which extends from the radial flange generally in a first axial direction, a second bend adjoins the first leg to a second leg, which is conical in shape, wherein the first and second legs are tangential to opposing ends of the second bend, the second leg extends from the second bend generally in a second axial direction that is opposite of the first axial direction to provide a fold, the first and second legs and first and second bends provided by an integral member, the second leg provides a channel at a portion not adjoining the second bend and the first leg; anda seal carried by the channel. 2. The gas turbine engine according to claim 1, wherein the seal is a piston ring. 3. The gas turbine engine according to claim 1, comprising a mid turbine case having a seal land, the seal engaging the seal land. 4. The gas turbine engine according to claim 3, wherein the member is arranged radially inward of the mid turbine frame. 5. The gas turbine engine according to claim 4, wherein the member is a first member, and comprising a second member secured to the first member at the joint, the second member includes an annular flange extending axially, the annular flange radially outward of the radial flange, the fold wrapping about the annular flange. 6. The gas turbine engine according to claim 3, wherein the seal assembly is integral with the member. 7. The gas turbine engine according to claim 1, wherein the member is arranged radially inward of a mid turbine frame, and a cooling cavity is provided between the member and the mid turbine frame, and the seal configured to seal the cooling cavity at one side. 8. The gas turbine engine according to claim 1, comprising: a fan;a compressor section fluidly connected to the fan, the compressor comprising a high pressure compressor and a low pressure compressor;a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor, the turbine section comprising: a high pressure turbine;a low pressure turbine coupled to the low pressure compressor via a shaft;a geared architecture interconnects between the shaft and the fan; andwherein the seal assembly is provided in at least one of the compressor and turbine sections. 9. The gas turbine engine according to claim 8, wherein the gas turbine engine includes a low Fan Pressure Ratio of less than 1.45. 10. The gas turbine engine according to claim 8, wherein the fan includes a low corrected fan tip speed of less than 1150 ft/s. 11. The gas turbine engine according to claim 1, wherein the portion is remote from the second bend and the first leg. 12. A gas turbine engine, comprising: a fan;a compressor section fluidly connected to the fan, the compressor comprising a high pressure compressor and a low pressure compressor;a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor, the turbine section comprising: a high pressure turbine;a low pressure turbine coupled to the low pressure compressor via a shaft;a geared architecture interconnects between the shaft and the fan;a seal assembly provided in at least one of the compressor and turbine sections, the seal assembly supported by a mid turbine frame at a joint, the mid turbine frame arranged between the high and low pressure turbines, the seal assembly including a seal support having a radial flange secured to the joint, a first bend adjoins the radial flange to a first leg, which extends from the radial flange generally in a first axial direction, a second bend adjoins the first leg to a second leg, which is conical in shape, wherein the first and second legs are tangential to opposing ends of the second bend, the second leg extends from the second bend generally in a second axial direction that is opposite of the first axial direction to provide a fold, the first and second legs and first and second bends provided by an integral member, the second leg provides a channel at a portion not adjoining the second bend and the first leg; anda seal carried by the channel. 13. The gas turbine engine according to claim 12, wherein the gas turbine engine includes a low Fan Pressure Ratio of less than 1.45. 14. The gas turbine engine according to claim 12, wherein the fan includes a low corrected fan tip speed of less than 1150 ft/s. 15. The gas turbine engine according to claim 12, wherein the mid turbine frame is a first member, and comprising a second member secured to the first member at the joint, the second member includes an annular flange extending axially, the annular flange radially outward of the radial flange, the fold wrapping about the annular flange. 16. The gas turbine engine according to claim 12, wherein the portion is remote from the second bend and the first leg.
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