초록 ▼

An internal fuel manifold assembly for a gas turbine engine comprises a fuel manifold ring and a fuel inlet assembly fastened thereto. The fuel inlet assembly providing fluid flow communication with the fuel manifold ring and being joined to the fuel manifold ring at an inlet region thereon. The inl

An internal fuel manifold assembly for a gas turbine engine comprises a fuel manifold ring and a fuel inlet assembly fastened thereto. The fuel inlet assembly providing fluid flow communication with the fuel manifold ring and being joined to the fuel manifold ring at an inlet region thereon. The inlet region of the fuel manifold ring is reinforced relative to the remainder of the circumference of the fuel manifold ring.

대표청구항 ▼

The invention claimed is: 1. An internal fuel manifold assembly for a gas turbine engine comprising: a fuel manifold ring having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas t

The invention claimed is: 1. An internal fuel manifold assembly for a gas turbine engine comprising: a fuel manifold ring having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas turbine engine, the fuel manifold ring having an inlet region that is reinforced relative to a remainder of a circumference of the fuel manifold ring; and a fuel inlet assembly having a fuel inlet tube providing fluid flow communication with said at least one fuel conveying passage within the fuel manifold ring, the fuel inlet assembly being joined to the fuel manifold ring at said reinforced inlet region thereof, wherein said reinforced inlet region of the fuel manifold ring has a thickness in an axial direction greater than that of said remainder of the fuel manifold ring. 2. The internal fuel manifold assembly as defined in claim 1, wherein said reinforced inlet region of the fuel manifold ring is a discontinuous increase in cross-sectional thickness relative to said remainder of the circumference of the fuel manifold ring. 3. The internal fuel manifold assembly as defined in claim 1, wherein said fuel inlet assembly includes a tubular heat shield disposed outwardly from the fuel inlet tube and extending along at least a portion of a length thereof, the heat shield having an outer end fastened to the fuel manifold ring at said inlet region thereof, said reinforced inlet region having a maximum axial thickness at least greater than a diameter of the outer end of the heat shield. 4. The internal fuel manifold assembly as defined in claim 1, wherein said reinforced inlet region of the fuel manifold ring has an opening therein within which an outer end of the fuel inlet tube is sealingly received a given insertion distance, an outer wall of said reinforced inlet region surrounding said outer end of the fuel inlet tube having a substantially constant thickness along a majority of said insertion distance. 5. The internal fuel manifold assembly as defined in claim 1, wherein said fuel manifold ring defines a plane substantially perpendicular to a longitudinal main engine axis which is coincident with a center of the fuel manifold ring, said fuel inlet tube being disposed at an angle relative to said plane. 6. The internal fuel manifold assembly as defined in claim 5, wherein said fuel reinforced inlet region of the fuel manifold ring has an outer wall surface which is substantially parallel to said angle. 7. The internal fuel manifold assembly as defined in claim 1, wherein said reinforced inlet region of the fuel manifold ring has an outer wall surrounding an outer end of the fuel inlet assembly, the outer wall having a thickness sufficient to permit material removal prior to refinishing a joint between the fuel inlet assembly and the fuel manifold ring. 8. The internal fuel manifold assembly as defined in claim 1, wherein said fuel inlet assembly and said fuel manifold fastened together by a brazed joint. 9. A mounting system for an internal fuel manifold of a gas turbine engine comprising a series of supports spaced apart about the fuel manifold, the series of supports including a fuel inlet assembly connected to the fuel manifold and providing fuel flow thereto, the fuel inlet assembly having a heat shield surrounding an internal fuel inlet tube defining a fuel flow passage therein, the fuel inlet assembly being joined to the fuel manifold at a inlet region thereon, said inlet region being reinforced relative to a remainder of the fuel manifold, wherein said reinforced inlet region of the fuel manifold has a thickness in an axial direction greater than that of said remainder of the fuel manifold. 10. The mounting system as defined in claim 9, wherein said inlet region defines a stepped opening therein, the stepped opening receiving outer ends of the fuel inlet tube and the heat shield concentrically therein. 11. The mounting system as defined in claim 10, wherein said outer ends of the fuel inlet tube and the heat shield are fastened to said reinforced inlet region of said fuel manifold. 12. The mounting system as defined in claim 11, wherein said outer ends are brazed to said reinforced inlet region. 13. The mounting system as defined in claim 9, wherein said reinforced inlet region of the fuel manifold ring has an outer wall surrounding an outer end of the fuel inlet assembly which is received therein, the outer end of the fuel inlet assembly and the fuel manifold being fastened together by a joint, the outer wall of the reinforced inlet region having a thickness sufficient to permit material removal prior to refinishing said joint. 14. The mounting system as defined in claim 9, wherein said fuel manifold is an annular ring, said reinforced inlet region thereof being a discontinuous increase in cross-sectional thickness relative to said remainder of the fuel manifold about a circumference thereof. 15. A method of manufacturing an internal fuel manifold for a gas turbine engine comprising: forming an annular fuel manifold ring having at least one fuel conveying passage therein and having a nominal cross-sectional thickness in an axial direction about a majority of a circumference of the annular fuel manifold; and forming a reinforced inlet region of the annular fuel manifold, the reinforced inlet region being adapted to receive a fuel inlet therein for providing fuel flow to the at least one fuel conveying passage, the reinforced inlet region having a locally increased cross-sectional thickness relative to said nominal cross-sectional thickness. 16. The method of manufacturing as defined in claim 15, wherein the step of forming said reinforced inlet region further comprises forming an outer wall portion thereof surrounding an opening for receiving the fuel inlet, the outer wall portion having a thickness sufficient to permit material removal prior to refinishing a joint between the fuel inlet and the fuel manifold once fastened together. 17. The method of manufacturing as defined in claim 16, further comprising making said thickness of said outer wall substantially constant along a majority of a depth of said opening within said fuel inlet is receivable. 18. The method of manufacturing as defined in claim 15, further comprising fastening said fuel inlet to said reinforced fuel inlet region by a brazed joint.