A mount interface between two rotating gas turbine engine components includes a rigid ring to provide radial deflection restraint. In one example, the rigid ring is comprised of a metal matrix composite material.
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1. A mount interface for a gas turbine engine component comprising: a first rotating engine component having a first mount structure;a second rotating engine component having a second mount structure facing said first mount structure;a rigid ring surrounding said first and said second mount structur
1. A mount interface for a gas turbine engine component comprising: a first rotating engine component having a first mount structure;a second rotating engine component having a second mount structure facing said first mount structure;a rigid ring surrounding said first and said second mount structures to provide radial deflection restraint; andan axial retaining feature that prevents said rigid ring from moving axially relative to said first and second rotating engine components in a direction along a rotational axis, said axial retaining feature comprising a slot formed in an outer or inner peripheral surface of said first and second rotating engine components, and said slot including a first wall portion that abuts directly against one edge of said rigid ring and a second wall portion that abuts directly against an opposite edge of said rigid ring. 2. The mount interface according to claim 1 wherein said rigid ring comprises a continuous ring-shaped body made from one of a metal matrix composite, a polymer matrix composite, or a ceramic matrix composite. 3. The mount interface according to claim 1 wherein said first mount structure comprises a first flange defined by a first outer peripheral surface and said second mount structure comprises a second flange defined by a second outer peripheral surface, said first and said second flanges abutting against each other with said rigid ring completely surrounding said first and said second flanges at said first and said second outer peripheral surfaces. 4. The mount interface according to claim 3 wherein said rigid ring is received in a close fitting arrangement on said first and said second outer peripheral surfaces. 5. The mount interface according to claim 3 wherein said first and said second flanges and said rigid ring rotate together about an axis, and wherein at least one of said first and said second flanges includes an axial retaining slot that receives said rigid ring, said axial retaining slot being formed at a corresponding one of said first and said second outer peripheral surfaces to prevent said rigid ring from moving relative to said first and said second flanges in an axial direction along said axis. 6. A mount interface for a gas turbine engine component comprising: a first rotating engine component having a first mount structure, said first mount structure comprises a first flange defined by a first outer peripheral surface;a second rotating engine component having a second mount structure facing said first mount structure, said second mount structure comprises a second flange defined by a second outer peripheral surface;a rigid ring surrounding said first and said second mount structures to provide radial deflection restraint, said first and said second flanges abutting against each other with said rigid ring completely surrounding said first and said second flanges at said first and said second outer peripheral surfaces, and wherein at least one of said first and said second flanges includes radial cooling slots, and wherein said rigid ring includes a plurality of secondary cooling holes formed about an outer periphery of said rigid ring with at least one secondary cooling hole being radially aligned with a corresponding one of said radial cooling slots. 7. The mount interface according to claim 6 wherein said rigid ring includes at least one anti-rotation feature to prevent said rigid ring from rotating relative to said first and said second flanges. 8. The mount interface according to claim 7 wherein said at least one anti-rotation feature comprises one of a male and female member that cooperates with the other of said male and said female member that is associated with one of said first and said second flanges. 9. The mount interface according to claim 3 wherein said first and said second flanges comprise first and second rotor flanges associated with respective first and second rotor stages each supporting a plurality of blades for rotation about an axis. 10. The mount interface according to claim 3 wherein said first and said second flanges and said rigid ring rotate together about an axis, and wherein said first flange includes a first plurality of fastener holes spaced circumferentially apart from each other about said axis and said second flange includes a second plurality of fastener holes spaced circumferentially apart from each other about said axis, said first and second plurality of fastener holes being aligned with each other, and including a plurality of fasteners received within said first and said second pluralities of fastener holes to secure said first and said second flanges together. 11. The mount interface according to claim 1 said first mount structure comprises a first rotor rim portion defined by a first outer peripheral surface and a first inner peripheral surface, and said second mount structure comprises a second rotor rim portion defined by a second outer peripheral surface and a second inner peripheral surface, said first and said second rotor rim portions being spaced apart from each other such that said rigid ring engages one of said first and said second outer peripheral surfaces or said first and said second inner peripheral surfaces. 12. A gas turbine engine comprising: a fan; a combustor section positioned aft of the fan; a turbine section positioned aft of the combustor section; and a compressor section wherein air compressed in the compressor section is mixed with fuel and burned in the combustor section to produce gases that are expanded in the turbine section, the compressor section including a plurality of rotors that rotate about an engine axis, said plurality of rotors including a first rotating component with a first mount structure and a second rotating component having a second mount structure to be associated with said first mount structure, wherein at least one of said first and said second rotating components includes cooling slots formed in a fore or aft end face of said one of said first and second rotating components and extending radially outwardly away from said engine axis; and a rigid ring cooperating with said first and said second mount structures to provide radial restraint, wherein said rigid ring includes a plurality of secondary cooling holes formed about an outer peripheral surface of said rigid ring and being spaced radially outwardly of said cooling slots, and with at least one secondary cooling hole being radially aligned with a corresponding one of said cooling slots. 13. The gas turbine engine according to claim 12 wherein said first rotating component comprises a first rotor flange and said second rotating component comprises a second rotor flange facing said first rotor flange, and wherein said rigid ring surrounds outer peripheral surfaces of said first and said second rotor flanges to provide radial deflection restraint. 14. The gas turbine engine according to claim 13 wherein said rigid ring comprises a continuous ring-shaped body comprised of a metal matrix material, said ring-shaped body being received on said first and said second rotor flanges in an interference fit. 15. The gas turbine engine according to claim 13 wherein at least one of said first and said second rotor flanges includes an axial retaining slot that receives said rigid ring, said axial retaining slot being formed in a corresponding one of said outer peripheral surfaces to prevent said rigid ring from moving relative to said first and said second rotor flanges in an axial direction along said engine axis. 16. A gas turbine engine comprising: a fan;a combustor section positioned aft of the fan;a turbine section positioned aft of the combustor section; anda compressor section wherein air compressed in the compressor section is mixed with fuel and burned in the combustor section to produce gases that are expanded in the turbine section, the compressor section including a plurality of rotors that rotate about an engine axis, said plurality of rotors including a first rotating component with a first mount structure and a second rotating component having a second mount structure to be associated with said first mount structure, and wherein said first rotating component comprises a first rotor flange and said second rotating component comprises a second rotor flange facing said first rotor flange; anda rigid ring cooperating with said first and said second mount structures to provide radial restraint, wherein said rigid ring surrounds outer peripheral surfaces of said first and said second rotor flanges to provide radial deflection restraint, and wherein at least one of said first and said second rotor flanges includes radial cooling slots extending in a direction radially away from said engine axis, and wherein said rigid ring includes a plurality of secondary cooling holes formed about an outer periphery of said rigid ring with at least one secondary cooling hole being radially aligned with a corresponding one of said radial cooling slots. 17. The gas turbine engine according to claim 13 wherein said rigid ring includes at least one anti-rotation feature that prevents said rigid ring from rotating relative to said first and said second rotor flanges, and wherein said at least one anti-rotation feature comprises one of a male and female member that cooperates with the other of said male and said female member that is associated with one of said first and said second rotor flanges. 18. The gas turbine engine according to claim 12 wherein said first rotating component comprises a first rotor rim portion and said second rotating component comprises a second rotor rim portion to be coupled to said first rotor rim portion, and wherein said rigid ring engages one of outer peripheral surfaces of said first and said second rotor rim portions or inner peripheral surfaces of said first and said second rotor rim portions. 19. The gas turbine engine according to claim 12 wherein said rigid ring comprises a continuous ring-shaped body made from one of a metal matrix composite, a polymer matrix composite, or a ceramic matrix composite. 20. A gas turbine engine comprising: a fan;a combustor section positioned aft of the fan;a turbine section positioned aft of the combustor section; anda compressor section wherein air compressed in the compressor section is mixed with fuel and burned in the combustor section to produce gases that are expanded in the turbine section, the compressor section including a plurality of rotors that rotate about an engine axis, said plurality of rotors including a first rotating component with a first mount structure and a second rotating component having a second mount structure to be associated with said first mount structure;a rigid ring cooperating with said first and said second mount structures to provide radial restraint; andan axial retaining feature that prevents said rigid ring from moving axially relative to said first and second rotating components in a direction along said engine axis, said axial retaining feature comprising a slot formed in an outer or inner peripheral surface of said first and second rotating components, and said slot including a first wall portion that abuts directly against one edge of said rigid ring and a second wall portion that abuts directly against an opposite edge of said rigid ring. 21. A mount interface for a gas turbine engine component comprising: a first rotating engine component having a first mount structure;a second rotating engine component having a second mount structure facing said first mount structure, wherein said first and second rotating engine components rotate about an engine axis, and wherein at least one of said first and said second rotating engine components includes cooling slots formed in a fore or aft end face of said one of said first and second rotating engine components and extending radially outwardly away from said engine axis anda rigid ring surrounding said first and said second mount structures to provide radial deflection restraint, wherein said rigid ring comprises a continuous ring-shaped body made from one of a metal matrix composite, a polymer matrix composite, or a ceramic matrix composite, and wherein said rigid ring includes a plurality of secondary cooling holes formed about an outer peripheral surface of said rigid ring and being spaced radially outwardly of said cooling slots, and with at least one secondary cooling hole being radially aligned with a corresponding one of said cooling slots. 22. A mount interface for a gas turbine engine component comprising: a first rotating engine component having a first mount structure that comprises a first flange defined by a first outer peripheral surface;a second rotating engine component having a second mount structure facing said first mount structure, and wherein said second mount structure comprises a second flange defined bya second outer peripheral surface;a rigid ring surrounding said first and said second mount structures to provide radial deflection restraint, said first and said second flanges abutting against each other with said rigid ring completely surrounding said first and said second flanges at said first and said second outer peripheral surfaces, and wherein at least one of said first and said second flanges includes radial cooling slots, and wherein said rigid ring includes a plurality of secondary cooling holes formed about an outer periphery of said rigid ring with at least one secondary cooling hole being radially aligned with a corresponding one of said radial cooling slots, and wherein said first and said second pluralities of fastener holes are circumferentially spaced apart from each other and are located between adjacent radial cooling slots; andwherein said first and said second flanges and said rigid ring rotate together about an axis, and wherein said first flange includes a first plurality of fastener holes spaced circumferentially apart from each other about said axis and said second flange includes a second plurality of fastener holes spaced circumferentially apart from each other about said axis, said first and second plurality of fastener holes being aligned with each other, and including a plurality of fasteners received within said first and said second pluralities of fastener holes to secure said first and said second flanges together. 23. The gas turbine engine according to claim 16 wherein said first and said second rotor flanges and said rigid ring rotate together about an axis, and wherein said rigid ring fits against the outer peripheral surface of said first and said second rotor flanges, and wherein said first rotor flange includes a first plurality of fastener holes spaced circumferentially apart from each other about said axis and said second rotor flange includes a second plurality of fastener holes spaced circumferentially apart from each other about said axis, said first and second plurality of fastener holes being aligned with each other, and including a plurality of fasteners received within said first and said second pluralities of fastener holes to secure said first and said second rotor flanges together, and wherein said first and said second pluralities of fastener holes are circumferentially spaced apart from each other and are located between adjacent radial cooling slots.
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이 특허에 인용된 특허 (17)
Schneider Raymond P. (North Palm Beach FL) Marshall James F. (Lake Park FL) Crowell Maclean (Jupiter FL), Compressor construction.
Dziech Aaron M. ; Reisenauer Daniel E. ; Bolt William Z. ; Albrecht ; Jr. Richard W. ; Ward Steven D., Cooling air supply through bolted flange assembly.
Lenahan Dean T. (Cincinnati OH) Riedmiller Charles F. (Loveland OH) Elovic Andrew P. (Rishon Lezion ILX), Integral turbine nozzle support and discourager seal.
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