A gas turbine module comprises a frame, a bearing support ring, a service line, and a scupper channel system. A service line is disposed through a radial passage of the frame and a service line port of the bearing support ring. The scupper line is disposed radially through a radial passage of the fr
A gas turbine module comprises a frame, a bearing support ring, a service line, and a scupper channel system. A service line is disposed through a radial passage of the frame and a service line port of the bearing support ring. The scupper line is disposed radially through a radial passage of the frame and is open to the scupper drain port. The scupper channel system is formed into a radially inner surface of the bearing support ring, and includes a collection portion in fluid communication with the scupper drain port.
대표청구항▼
1. A gas turbine module comprising: a frame including a strut radially interconnecting an inner hub and an outer case, and a passage extending radially through the inner hub, the strut, and the outer case;a bearing support ring mounted to the frame radially inward of the frame inner hub, the bearing
1. A gas turbine module comprising: a frame including a strut radially interconnecting an inner hub and an outer case, and a passage extending radially through the inner hub, the strut, and the outer case;a bearing support ring mounted to the frame radially inward of the frame inner hub, the bearing support ring including a scupper drain port and a service line port disposed proximate to the scupper drain port;a service line disposed radially through the radial passage of the frame and the service line port of the bearing support ring;a scupper line disposed radially through the radial passage of the frame and open to the scupper drain port; anda scupper channel system formed into a radially inner surface of the bearing support ring, the scupper channel system including a collection portion in fluid communication with the scupper drain port. 2. The gas turbine module of claim 1, further comprising a bearing compartment secured to a bearing compartment mounting flange, wherein the service line also extends into the bearing compartment. 3. The gas turbine module of claim 2, wherein the bearing compartment is supported around an aft end of the frame inner hub via the bearing support ring. 4. The gas turbine module of claim 1, wherein the scupper line, and the scupper drain port are located proximate a bottom dead center (BDC) position of the bearing support ring. 5. The gas turbine engine module of claim 1, wherein the collection portion is formed proximate the service line port. 6. The gas turbine engine module of claim 5, wherein the collection portion is formed concentrically around the service line port. 7. The gas turbine engine module of claim 1, wherein the scupper channel system also includes a separate transport trench in fluid communication with the collection portion and the scupper drain port. 8. The gas turbine engine module of claim 1, wherein the bearing support ring comprises a bearing support ring section and a flow divider ring section. 9. A turbine exhaust case (TEC) assembly comprising: a frame including a circumferentially distributed plurality of struts each extending radially between an inner hub, and an outer case;a passage formed radially through one of the plurality of struts;a bearing support ring mounted to the frame inner hub, the bearing support ring including a scupper drain port circumferentially aligned with the passage; anda scupper channel system formed into a radially inner surface of the bearing support ring, the scupper channel system including a liquid collection portion in fluid communication with the scupper drain port. 10. The TEC assembly of claim 9, further comprising: a scupper line disposed radially through the radial passage of the frame and open to the scupper drain port. 11. The TEC assembly of claim 9, further comprising: a service line port disposed radially through the bearing support ring, wherein the scupper line, and the scupper drain port are located proximate a bottom dead center (BDC) position of the bearing support ring. 12. The TEC assembly of claim 9, wherein the collection portion is formed proximate the service line port. 13. The TEC assembly of claim 12, wherein the collection portion is formed concentrically around the service line port. 14. The TEC assembly of claim 9, wherein the scupper channel system also includes a separate transport trench in fluid communication with the collection portion and the scupper drain port. 15. The TEC assembly of claim 9, wherein the bearing support ring comprises a bearing support ring section and a flow divider ring section. 16. A gas turbine engine component comprising: a generally cylindrical section including a radially inner surface and a radially outer surface;a generally frustoconical ring section contiguous with a forward end of the cylindrical section, the frustoconical ring section and the cylindrical ring section being a single piece;a scupper drain port formed through the generally cylindrical section of the component; anda scupper channel system formed into a portion of the radially inner surface of the component, the scupper channel system including a collection portion in fluid communication with the scupper drain port. 17. The gas turbine engine component of claim 16, wherein the scupper drain port is located proximate a bottom dead center (BDC) position of the cylindrical section. 18. The gas turbine engine component of claim 16, further comprising a service line port, wherein the scupper collection portion is disposed proximate the service line port. 19. The gas turbine engine component of claim 18, wherein the collection portion is formed concentrically around the service line port. 20. The gas turbine engine component of claim 18, wherein the scupper channel system further comprises a separate transport trench in fluid communication with the collection portion and the scupper drain port. 21. The gas turbine engine component of claim 16, wherein the gas turbine engine component comprises a bearing support ring.
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Burdgick Steven S. (Clifton Park NY) Hess John R. (Clifton Park NY) Mercer Gary D. (Ballston Lake NY) Crum Gregory A. (Greenville SC) Cencula James E. (Ballston Lake NY) Eastman John A. (Clifton Park, Casing distortion control for rotating machinery.
Guimbard, Jean-Michel Bernard; Pabion, Philippe Jean-Pierre; Prestel, Sebastien Jean Laurent; Soupizon, Jean-Luc, Inter-turbine casing with cooling circuit, and turbofan comprising it.
Halchak Kenneth L. (Wilmington NC) Schwarz Daniel C. (Hamilton OH) Birmingham Martin L. (West Chester OH), Method for assembling a turbine frame assembly.
Nguyen, Ly D.; Cruse, Louis; Fowkes, Ivar Gene; Salas, Silvestre; North, William; Kadambi, Vadanth, Method of forming a thermally isolated gas turbine engine housing.
Arraitz Anne-Marie,FRX ; Bil Eric Stephan,FRX ; Hacault Michel Gerard Paul,FRX ; Leray Laurent Philippe Yves,FRX ; Loubet Michel Jean,FRX ; Marchi Marc Roger,FRX ; Morcillo Jean Manuel,FRX ; Mortgat , Method of reducing the gap between a liner and a turbine distributor of a turbojet engine.
McNickle Alan D. (Sellersville PA) Hwang Mingfong (Lansdale PA) Pope Adam N. (Cincinnati OH), Seal for sealing an incompressible fluid between a relatively stationary seal and a movable member.
Lescure, Xavier Firmin Camille Jean; Massot, Aurelien Rene-Pierre; Prestel, Sebastien Jean Laurent; Schnell, Christian Rene, Sealing a hub cavity of an exhaust casing in a turbomachine.
Coign,Robert Walter; Humanchuk,David John; Foster,Gregory Thomas; Worley,Kevin Lee, System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor.
Grateau Roland M. E. (Viry Chatillon FRX) Guibert Alain J. E. (Savigny le Temple FRX) Henu Alain J. C. (Le Mee sur Seine FRX) Kapala Patrick (Claye FRX) Mareix Jean-Pierre L. (Avon FRX) Monchois Flor, Turbine casing delimiting an annular gas flow stream divided by radial arms.
Meade Robert J. (West Chester OH) Albrecht Richard W. (Fairfield OH) Weisgerber Robert H. (Loveland OH), Turbine disk interstage seal axial retaining ring.
Weisgerber Robert H. (Loveland OH) Albrecht Richard W. (Fairfield OH) Glynn Christopher C. (Hamilton OH) Kutney ; Jr. John T. (Cincinnati OH) Meade Robert J. (West Chester OH), Turbine disk interstage seal system.
Vdoviak John W. (Marblehead MA) Moyer Roy E. (Cincinnati OH) Evans Dennis C. (Topsfield MA), Turbine engine assembly with aft mounted outlet guide vanes.
Fledderjohn Steve R. (Cincinnati OH) Przytulski James C. (Fairfield OH) Elston ; III Sidney B. (Cincinnati OH) Gilchrist Alan R. (Fairfield OH) Hauser Ambrose A. (Wyoming OH), Turbine support assembly including turbine heat shield and bolt retainer assembly.
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