초록 ▼

A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel is formed in a surface of a gas turbine engine component, and the channel is adapted for conveying a fluid flow from an inlet to an outlet. At least a

A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel is formed in a surface of a gas turbine engine component, and the channel is adapted for conveying a fluid flow from an inlet to an outlet. At least a first sealing member is disposed within the channel and divides the channel into at least a first discrete conduit and a second discrete conduit. A second sealing member encloses the channel to define the second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.

대표청구항 ▼

What is claimed is: 1. A gas turbine engine fuel nozzle system having a spray tip assembly in flow communication with a fuel source, the fuel nozzle system comprising; a fuel-convoying member comprising a channel formed therein for providing fuel flow to the spray tip assembly, the channel having a

What is claimed is: 1. A gas turbine engine fuel nozzle system having a spray tip assembly in flow communication with a fuel source, the fuel nozzle system comprising; a fuel-convoying member comprising a channel formed therein for providing fuel flow to the spray tip assembly, the channel having a length and defining at least one shoulder therein along the length, the shoulder corresponding to a change in width of the channel; at least a first inner sealing member disposed within the channel and mounted to the shoulder substantially along said length, the first inner sealing member dividing the channel into at least a primary discrete conduit and a secondary discrete conduit; and an outer sealing member for enclosing the channel substantially along its length to define the secondary discrete conduit; whereby each discrete conduit is adapted for directing an independent fuel flow from the fuel source to the spray tip assembly. 2. The fuel nozzle system as defined in claim 1, wherein the fuel-conveying member is an annular fuel manifold ring and the channel is defined therearound. 3. The fuel nozzle system as defined in claim 2, wherein the annular fuel manifold ring feeds a plurality of the spray tip assemblies directly engaged thereto. 4. The fuel nozzle system as defined in claim 1, wherein the channel is stepped by reason of the presence of the shoulder, and wherein the first inner sealing member abuts the shoulder. 5. The fuel nozzle system as defined in claim 1, wherein the outer sealing member is engaged to an outer surface of the fuel-conveying member in which the channel is formed. 6. The fuel nozzle system as defined in claim 1, wherein the secondary discrete conduit has a larger cross-sectional area than the primary discrete conduit. 7. The fuel nozzle system as defined in claim 1, wherein the fuel-conveying member includes a third discrete conduit in the channel. 8. The fuel nozzle system as defined in claim 7, wherein the third discrete conduit is nested with the primary and secondary discrete conduits within the channel, and is sealing divided from the secondary discrete conduit by a second inner sealing member disposed within the channel. 9. The fuel nozzle system as defined in claim 7, wherein the third discrete conduit is defined by at least an auxiliary channel formed in the fuel-conveying member separately from the channel, and covered by at least an auxiliary outer sealing member. 10. The fuel nozzle system as defined in claim 7, wherein two opposing auxiliary channels are formed in the fuel-conveying member parallel to but outside said channel. 11. The fuel nozzle system as defined in claim 1, wherein the fuel-conveying member is provided in a single solid piece of material. 12. The fuel nozzle system as defined in claim 1, wherein the first inner sealing member and the outer sealing member are brazed to the fuel-conveying member. 13. The fuel nozzle system as defined in claim 1, wherein the fuel-conveying member is a fuel nozzle stem. 14. The fuel nozzle system as defined in claim 13, wherein the channel extends linearly along a portion of an axial length of the fuel stem member. 15. A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets, the system comprising: a channel formed in a surface of a gas turbine engine component, the channel having a length and defining at least one shoulder therein along the length, the shoulder corresponding to a change in width of the channel, the channel being adapted for conveying a fluid flow from an inlet to an outlet; at least a first sealing member disposed within the channel and mounted to the shoulder substantially along said length, the first sealing member dividing the channel into at least a first discrete conduit and a second discrete conduit; and a second sealing member enclosing the channel substantially alone its length to define the second discrete conduit; whereby the first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets. 16. The multiple conduit system of claim 15, wherein the channel is stepped by reasons of the presence of the shoulder, and wherein the first sealing member abuts the shoulder. 17. The multiple conduit system of claim 15, wherein the second sealing member engages the surface of the gas turbine engine component. 18. A method of manufacturing a gas turbine engine fuel nozzle having multiple discrete fuel conduits for directing independent fuel flows from a fuel source to a spray tip assembly, the method comprising: providing a fuel-conveying member; providing a channel in a surface of the fuel-conveying member; providing a shoulder in the channel along a length of the channel, the shoulder corresponding to a change in width of the channel; fixing at least a first sealing member into the channel against the shoulder substantially along said length to divide the channel into a first discrete fuel conduit and a second discrete fuel conduit; and fixing a second sealing member to the fuel-conveying member substantially along said length to enclose the channel and thereby define the second discrete fuel conduit. 19. The method as defined in claim 18, further comprising providing the fuel-conveying member from a solid piece of material. 20. A gas turbine engine fuel nozzle system having a spray tip assembly in flow communication with a fuel source, the fuel nozzle system comprising: a fuel-conveying member comprising a channel formed in a peripheral surface thereof and-defining an opening in the peripheral surface; at least a first inner sealing member receivable within the channel, the first inner sealing member being mounted therewithin substantially along the channel to sealingly divide the channel into nested primary and secondary discrete conduits, the primary discrete conduit being defined between a bottom of the channel and the inner sealing member and being narrower than the secondary conduit; an outer sealing member fastenable to the fuel-conveying member for enclosing the channel; and whereby each discrete conduit is adapted for directing fuel flow from the fuel source to the spray tip assembly. 21. The fuel nozzle system as defined in claim 20, wherein the secondary discrete conduit is defined between the inner sealing member and the outer sealing member. 22. The fuel nozzle system as defined in claim 20, wherein the first inner sealing member is insertable into the channel through said opening. 23. A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets, the system comprising: a channel formed in a peripheral surface of a gas turbine engine fluid-conveying component, the channel defining an opening in the peripheral surface; at least a first inner sealing member receivable within the channel, the first inner sealing member being mounted therewithin substantially along the channel to sealingly divide the channel into nested first and second discrete conduits, the first discrete conduit being defined between a bottom of the channel and the first inner sealing member and being narrower than the second conduit; an outer sealing member fastenable to the fluid-conveying component for enclosing the channel; and the first and second discrete conduits each providing independent fluid flow communication from the respective inlets to the respective outlets. 24. The multiple conduit system as defined in claim 23, wherein the second discrete conduit is defined between the first inner sealing member and the outer sealing member. 25. The multiple conduit system as defined in claim 23, wherein the first inner sealing member is insertable into the channel through the opening. 26. A method of manufacturing a gas turbine engine fuel assembly having multiple discrete fuel conduits for directing independent fuel flows from a fuel source to a spray tip assembly, the method comprising: providing a fuel-conveying member; forming a channel in a peripheral surface of the fuel-conveying member, the channel defining an opening in a peripheral surface; inserting at least a first inner sealing member into the channel through the opening, and mounting the inner sealing member within the channel substantially alone a length of the channel to sealingly divide the channel into nested first and second discrete fuel conduits; and mounting an outer sealing member to the fuel-conveying member to enclose the channel substantially along a length of the channel, the first discrete fuel conduit being defined between a bottom of the channel and the inner sealing member.