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A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring

A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring such that the channel has a cross-sectional area that varies around a circumference of the ring.

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What is claimed is: 1. A method of manufacturing an internal manifold of a gas turbine engine, the method comprising: providing a solid ring; machining at least one annular channel in the ring using a turning process, including: rotating the ring about a central axis thereof; forming the annular ch

What is claimed is: 1. A method of manufacturing an internal manifold of a gas turbine engine, the method comprising: providing a solid ring; machining at least one annular channel in the ring using a turning process, including: rotating the ring about a central axis thereof; forming the annular channel with a cross-sectional area that varies around a circumference of the ring by engaging a tool bit with a peripheral surface of the rotating ring to remove material from said surface to provide said channel defined in said surface, and varying a position of the tool bit relative to the surface of the ring while said ring is rotated and the tool bit engaged with said surface in accordance with a predetermined channel area profile to thereby provide the channel with a varying cross-sectional area around the ring circumference; and sealingly fastening a sealing member to the ring to enclose the channel and define therewith at least one circumferential conduit having a cross-sectional area that varies around the circumference of the ring. 2. The method as defined in claim 1, wherein the peripheral surface is planar and substantially normal to the central axis of said ring, the step of varying a position of the tool bit includes varying a depth of the tool bit within the ring in a axial direction substantially parallel to said central axle, the predetermined profile being a depth profile, such that the channel has a depth that varies around the circumference of the ring. 3. The method as defined in claim 1, wherein the cross-sectional area of the channel is varied progressively between a maximum cross-sectional area defined in proximity of an inlet of the channel and a minimum cross-sectional area defined away from the inlet. 4. The method as defined in claim 1, wherein the step of varying a position of the tool bit includes varying a cutting depth of the tool bit within the ring during a first rotation of the ring relative to the tool bit differently than within the ring during a second rotation of the ring relative to the tool bit disposed at a different position, the predetermined profile being a width profile, such that the cross-sectional area of the channel is varied by varying a width of the channel around the circumference of the ring. 5. The method as defined in claim 1, wherein a plurality of such channels are machined. 6. The method as defined in claim 1, wherein the position of the tool bit is varied in a continuous manner. 7. The method as defined in claim 1, wherein the position of the tool bit is varied in a stepped manner. 8. The method as defined in claim 1, wherein the position of the tool bit is varied such as to have a channel with a cross-sectional area varying continuously between a maximum cross-sectional area defined in proximity of an inlet of the channel and a minimum cross-sectional area defined away from the inlet. 9. The method as defined in claim 3, wherein the maximum cross-sectional area and the minimum cross-sectional area are defined at substantially diametrically opposed locations on the ring. 10. The method as defined in claim 1, wherein the channel is machined around part of the circumference of the ring, and the method further includes the step of machining at least one additional channel around a remaining part of the circumference of the ring, the position of the tool bit relative to the ring being varied as a function of the relative circumferential location of the tool bit such that the additional channel also has a cross-sectional area that varies around the circumference of the ring. 11. An annular internal fuel manifold made in accordance with the method of claim 1. 12. A method of creating a channel having a varied cross-sectional area in an internal fuel manifold ring of a gas turbine engine, the method comprising: using a turning machine to rotate the ring about a central axis thereof and to machine an annular channel in a peripheral outer surface of the ring using a preselected tool bit by engaging the tool bit with the peripheral outer surface of the rotating ring to remove material from said surface, the machining including forming the channel with a cross-sectional area that varies around a circumference of the ring by varying a position of the tool bit while said ring is rotated in accordance with a predetermined profile. 13. The method of claim 12, wherein the peripheral outer surface is planar and substantially normal to said central axis about which the ring is rotated, the step of machining the annular channel further comprising displacing the tool bit in at least an axial direction substantially parallel to said central axis to remove material from the peripheral outer surface of the rotating ring, thereby forming the annular channel with a depth that varies around the circumference of the ring.