One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of
One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
대표청구항▼
1. A rotating machine, comprising: a first component having a first component surface subject to radial displacement during operation of said rotating machine, said first component surface being defined by a first diameter;a second component having a second component surface spaced apart from said f
1. A rotating machine, comprising: a first component having a first component surface subject to radial displacement during operation of said rotating machine, said first component surface being defined by a first diameter;a second component having a second component surface spaced apart from said first component surface, said second component surface being defined by a second diameter different from said first diameter;a squeeze film damper disposed in a cavity defined between said first component surface and said second component surface, said squeeze film damper being structured to provide damping based on said radial displacement; anda seal disposed adjacent to said squeeze film damper, said seal having a first sealing surface and a second sealing surface, wherein said first sealing surface is structured to seal against said first component surface at said first diameter, and wherein said second sealing surface is structured to seal against said second component surface at said second diameter. 2. The rotating machine of claim 1, wherein said squeeze film damper is structured as an annular squeeze film damper ring. 3. The rotating machine of claim 1, wherein said seal is a self-charging seal. 4. The rotating machine of claim 3, wherein said seal is structured to receive a charging pressure from damping fluid in said cavity. 5. The rotating machine of claim 1, wherein said seal is a bifurcated seal having a first leg and a second leg; wherein said first sealing surface is disposed on said first leg; and wherein said second sealing surface is disposed on said second leg. 6. The rotating machine of claim 5, wherein said seal includes a hollow defined between said first leg and said second leg, and wherein said hollow is open to said cavity. 7. The rotating machine of claim 1, wherein said first component is a portion of a rolling element bearing; and wherein said second component is a static bearing support structure of said rotating machine. 8. The rotating machine of claim 7, wherein said first component is one of an inner race and an outer race of said rolling element bearing, and wherein said first diameter is said one of a corresponding inner race pilot diameter and outer race pilot diameter of said rolling element bearing. 9. The rotating machine of claim 1, wherein said squeeze film damper is a dual sided damper ring structured to perform damping on both sides of said dual sided damper ring. 10. The rotating machine of claim 1, wherein said cavity is charged with a fluid that is employed in conjunction with said squeeze film damper to provide said damping. 11. A gas turbine engine, comprising: a rotating engine structure;a static engine structure having a static structure pilot diameter;a rolling element bearing structured to transmit a load from said rotating engine structure to said static engine structure, said rolling element bearing having an inner race and an outer race, said inner race having an inner race pilot diameter and said outer race having an outer race pilot diameter, wherein said static structure pilot diameter and one of said inner race pilot diameter and said outer race pilot diameter form a cavity therebetween; anda damping system for damping said load, said damping system including: a squeeze film damper disposed in said cavity, said cavity also containing a viscous damping fluid, wherein said squeeze film damper is operative to provide viscous damping of said load using said viscous damping fluid based on clearances between said static engine structure at said static structure pilot diameter and said rolling element bearing at said one of said inner race pilot diameter and said outer race pilot diameter; anda seal disposed at least partially in said cavity, said seal having a first sealing surface and a second sealing surface, wherein said first sealing surface is structured to seal against said static engine structure at said static structure pilot diameter, and wherein said second sealing surface is structured to seal against said rolling element bearing at said one of said inner race pilot diameter and said outer race pilot diameter. 12. The gas turbine engine of claim 11, further comprising an isolator spring disposed in said cavity and piloted by said static engine structure at said static structure pilot diameter and said rolling element bearing at said one of said inner race pilot diameter and said outer race pilot diameter, wherein said isolator spring is structured to absorb radial displacement between said rolling element bearing and said static engine structure. 13. The gas turbine engine of claim 12, wherein said isolator spring is an annular spring having alternating contact between said static engine structure at said static structure pilot diameter and said rolling element bearing at said one of said inner race pilot diameter and said outer race pilot diameter. 14. The gas turbine engine of claim 11, wherein said seal is a self-charging seal. 15. The gas turbine engine of claim 14, wherein said seal is structured to receive a charging pressure from said viscous damping fluid in said cavity. 16. The gas turbine engine of claim 11, wherein said seal is a bifurcated seal having a first leg and a second leg; wherein said first sealing surface is disposed on said first leg; and wherein said second sealing surface is disposed on said second leg. 17. The gas turbine engine of claim 16, wherein said seal includes a hollow defined between said first leg and said second leg, and wherein said hollow is open to said cavity. 18. The gas turbine engine of claim 11, wherein said squeeze film damper is operative to provide viscous damping of said load using said viscous damping fluid based on clearances between said static engine structure at said static structure pilot diameter and said rolling element bearing at said outer race pilot diameter. 19. A rotating machine, comprising: a rotating structure;a static structure having a static structure pilot diameter;a rolling element bearing structured to transmit a variable load from said rotating structure to said static structure, said rolling element bearing having an inner race and an outer race, said inner race having an inner race pilot diameter and said outer race having an outer race pilot diameter, wherein said static structure pilot diameter and one of said inner race pilot diameter and said outer race pilot diameter form a cavity therebetween;means for damping said variable load; andmeans for sealing said means for damping, said means for sealing being operative to seal between said static structure pilot diameter and said one of said inner race pilot diameter and said outer race pilot diameter. 20. The rotating machine of claim 19, further comprising means for absorbing radial displacement between said static structure pilot diameter and said one of said inner race pilot diameter and said outer race pilot diameter. 21. A damper system for rotating machinery, comprising: a squeeze film damper disposed in a cavity defined between a diameter of a static structure of said rotating machinery and one of an inner race diameter and an outer race diameter of a rolling element bearing of said rotating machinery, said cavity also containing a viscous damping fluid, wherein said squeeze film damper is operative to provide viscous damping of a load using said viscous damping fluid based on clearances between said static structure diameter and said one of said inner race diameter and said outer race diameter; anda seal disposed at least partially in said cavity, said seal having a first sealing surface and a second sealing surface, wherein said first sealing surface is structured to seal against said static structure at said diameter of said static structure, and wherein said second sealing surface is structured to seal against said rolling element bearing at said one of said inner race diameter and said outer race diameter.
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이 특허에 인용된 특허 (9)
Pettinato, Brian C.; De Choudhury, Pranabesh, Bearing assembly and centering support structure therefor.
Wiley ; III Walter H. (Palm Beach Gardens FL) Aaron ; Jr. Charles D. (Palm Beach Gardens FL) Carlson Russell L. (North Palm Beach FL) Davis ; III Charles L. (Palm Beach Gardens FL) Marmol Ronald A. (, Fluid damper for thrust bearing.
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