A gas turbine engine comprising: a bearing support ring, wherein the bearing support ring comprising: a first annular body; a second annular body disposed radially inward of the first annular body relative a center axis of the gas turbine engine; and a radial spring connected to the first annular body and the second annular body, wherein the radial spring extends circumferentially about the center axis and extends radially between the first annular body and the second annular body; a frame comprising: a case extending circumferentially around the first annular body of the bearing support ring; an annular member connected to the case and positioned radially between the radial spring and the second annular body of the bearing support ring, wherein the annular member extends circumferentially around the second annular body; and a fluid port extending radially through the annular member; a seal disposed around the annular member of the frame, disposed axially forward of the fluid port, and extending radially between the annular member and the radial spring of the bearing support ring; a first fluid passage extending through the case and positioned axially over the first annular body; a second fluid passage formed between the bearing support ring and the case and the annular member of the frame, wherein the second fluid passage extends from the first fluid passage to the fluid port; and a bearing outer race disposed radially inward of the second annular body of the bearing support ring. a bearing support ring, wherein the bearing support ring comprising: a first annular body; a second annular body disposed radially inward of the first annular body relative a center axis of the gas turbine engine; and a radial spring connected to the first annular body and the second annular body, wherein the radial spring extends circumferentially about the center axis and extends radially between the first annular body and the second annular body; a first annular body; a second annular body disposed radially inward of the first annular body relative a center axis of the gas turbine engine; and a radial spring connected to the first annular body and the second annular body, wherein the radial spring extends circumferentially about the center axis and extends radially between the first annular body and the second annular body; a frame comprising: a case extending circumferentially around the first annular body of the bearing support ring; an annular member connected to the case and positioned radially between the radial spring and the second annular body of the bearing support ring, wherein the annular member extends circumferentially around the second annular body; and a fluid port extending radially through the annular member; a case extending circumferentially around the first annular body of the bearing support ring; an annular member connected to the case and positioned radially between the radial spring and the second annular body of the bearing support ring, wherein the annular member extends circumferentially around the second annular body; and a fluid port extending radially through the annular member; a seal disposed around the annular member of the frame, disposed axially forward of the fluid port, and extending radially between the annular member and the radial spring of the bearing support ring; a first fluid passage extending through the case and positioned axially over the first annular body; a second fluid passage formed between the bearing support ring and the case and the annular member of the frame, wherein the second fluid passage extends from the first fluid passage to the fluid port; and a bearing outer race disposed radially inward of the second annular body of the bearing support ring.