초록 ▼

Fuel conduit systems for internal installation in a gas turbine engine are provided which are low cost and easy to manufacture. First and second members co-operate to provide a channel to define a discrete fuel carrying conduit. The direction of fuel flow can be adapted to provide desired cooling ef

Fuel conduit systems for internal installation in a gas turbine engine are provided which are low cost and easy to manufacture. First and second members co-operate to provide a channel to define a discrete fuel carrying conduit. The direction of fuel flow can be adapted to provide desired cooling effect.

대표청구항 ▼

The invention claimed is: 1. A fuel manifold for providing fuel to a gas turbine engine fuel nozzle system, the manifold comprising: a first fuel conduit defined in the manifold, the conduit extending from a first inlet to a first end and communicating with a plurality of fuel nozzles about the man

The invention claimed is: 1. A fuel manifold for providing fuel to a gas turbine engine fuel nozzle system, the manifold comprising: a first fuel conduit defined in the manifold, the conduit extending from a first inlet to a first end and communicating with a plurality of fuel nozzles about the manifold; a second fuel conduit defined in the manifold adjacent the first conduit, the conduit extending from a second inlet to a second end and independently communicating with the plurality of fuel nozzles; and wherein the conduits are arranged such that fuel flowing in the first conduit travels relative to the manifold in a direction which is different than a fuel flow direction in the second conduit, and at least one of the conduits includes at least one flow rate maintenance member adapted to maintain a desired fuel flow rate in the conduit as fuel volume decreases along the conduit length. 2. The fuel manifold of claim 1 wherein the flow rate maintenance member comprises a portion of the manifold defining the conduit. 3. The fuel manifold of claim 1 wherein at least one of the conduits has a cross-sectional area that varies along a length of the conduit. 4. The fuel manifold of claim 3 wherein the cross-sectional area decreases along the length of the conduit. 5. The fuel manifold of claim 4 wherein the cross-sectional area continuously decreases along the length of the conduit. 6. The fuel manifold of claim 1, wherein the manifold has a ring shape, and wherein fuel in one of the first and second conduits travels clockwise around the manifold and fuel in the other conduit travels counter-clockwise around the manifold. 7. The fuel manifold of claim 6, wherein a cross-sectional area of each conduit is reduced along their respective lengths to thereby maintain a substantially constant fuel flow rate in each conduit. 8. The fuel manifold of claim 1, wherein the flow rate maintenance member includes a sealing member which encloses at least one of the conduits. 9. The fuel manifold of claim 1, wherein a heat shield assembly surrounds the manifold and encloses an air space disposed between the heat shield assembly and the manifold, the air space being sized to provide a predetermined thermal insulation to the manifold. 10. An internal fuel manifold for providing fuel to a gas turbine engine fuel nozzle system, the manifold comprising: a first fuel conduit defined in the manifold, the conduit extending from a first inlet to a first end and communicating with a plurality of fuel nozzles about the manifold; a second fuel conduit defined in the manifold adjacent the first conduit, the conduit extending from a second inlet to a second end and independently communicating with the plurality of fuel nozzles; and wherein the conduits are arranged such that fuel flowing in the first conduit travels relative to the manifold in a direction which is different than a fuel flow direction in the second conduit to thereby improve fuel cooling of the manifold, and a sealing member encloses at least one of the conduits, the sealing member maintaining a desired fuel flow rate in the conduit as fuel volume decreases along the conduit length. 11. The internal fuel manifold of claim 10, wherein a heat shield assembly surrounds the manifold and encloses an air space disposed between the heat shield assembly and the manifold, the air space being sized to provide a predetermined thermal insulation to the manifold. 12. A fuel manifold for providing fuel to a gas turbine engine fuel nozzle system, the manifold comprising: a first fuel conduit defined in the manifold, the conduit extending from a first inlet to a first end and communicating with a plurality of fuel nozzles about the manifold; a second fuel conduit defined in the manifold adjacent the first conduit, the conduit extending from a second inlet to a second end and independently communicating with the plurality of fuel nozzles; and wherein the conduits are arranged such that fuel flowing in the first conduit travels relative to the manifold in a direction which is opposite than a fuel flow direction in the second conduit, and a cross-sectional area of each conduit is reduced along their respective lengths to thereby maintain a substantially constant fuel flow rate in each conduit as fuel volume decreases along each respective length. 13. The fuel manifold of claim 12, wherein the cross-sectional area continuously decreases along the length of each said conduit. 14. The fuel manifold of claim 12, wherein the fuel manifold is an internal fuel manifold having a ring shape, and wherein fuel in one of the first and second conduits travels clockwise around the manifold and fuel in the other conduit travels counter-clockwise around the manifold. 15. The fuel manifold of claim 12, wherein a sealing member encloses at least one of the conduits, the sealing member maintaining the fuel flow rate in the conduit. 16. The fuel manifold of claim 12, wherein a heat shield assembly surrounds the manifold and encloses an air space disposed between the heat shield assembly and the manifold, the air space being sized to provide a predetermined thermal insulation to the manifold.