FLEXIBLE HOSE

Abstract

The present invention provides a flexible hose for connecting a fuel manifold to a burner of a gas turbine engine. The flexible hose includes a metal convolute tube, an elongate member or members located in grooves formed in the inner surface of the convolute tube, and a pressure-containing sheath outside the convolute tube. The flexible tube has end connectors fluidly-tightly joined to respective ends of the hose for connection at one end of the hose to the fuel manifold of the gas turbine engine, and at the other end of the hose to the burner of the gas turbine engine.

Claims

1. A flexible hose for connecting a fuel manifold to a burner of a gas turbine engine, the hose having: a metal convolute tube; an elongate member or members located in grooves formed in the inner surface of the convolute tube; a pressure-containing sheath outside the convolute tube; and end connectors fluidly-tightly joined to respective ends of the hose for connection at one end of the hose to the fuel manifold, and at the other end of the hose to the burner.

2. The flexible hose of claim 1 wherein the inner surface of the metal convolute tube is spirally grooved.

3. The flexible hose of claim 1 wherein the, or each, elongate member has a helical shape.

4. The flexible hose of claim 1 wherein the, or each, elongate member is formed of metal.

5. The flexible hose of claim 1 wherein the end connectors are welded or brazed to the metal convolute tube at the ends of the hose.

6. The flexible hose of claim 1 wherein the pressure-containing sheath is a braided sheath.

7. The flexible hose of claim 1 wherein the hose is a concentric double layer hose.

8. Gas turbine engine combustion equipment having a fuel manifold and a plurality of burners which receive fuel from the fuel manifold and direct the received fuel into one or more combustors, the burners being connected to the manifold by respective flexible hoses of claim 1.

9. A gas turbine engine having the combustion equipment of claim 8.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:

[0028] FIG. 1 shows a longitudinal cross-section through a ducted fan gas turbine engine;

[0029] FIG. 2 shows a schematic longitudinal cross-section through a flexible hose; and

[0030] FIGS. 3(a) and 3(b) show schematic longitudinal cross-sections through (a) a concentric double layer hose in which the elongate members have circular cross-sections, and (b) a concentric double layer hose in which the elongate members have semi-circular cross-sections.

DETAILED DESCRIPTION AND FURTHER OPTIONAL FEATURES

[0031] With reference to FIG. 1, a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X. The engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19. A nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.

[0032] During operation, air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate-pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate-pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high-pressure compressor 14 where further compression takes place.

[0033] The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high and intermediate-pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.

[0034] FIG. 2 shows a schematic longitudinal cross-section through a flexible hose 100 for connecting a rigid fuel manifold of the combustion equipment 15 to a burner. End connecters (not shown) are welded to respective ends of the hose for connection at one end to the fuel manifold, and at the other end of the hose to the burner. The hose has a metal convolute tube 25, which has spiral grooves formed in an inner surface thereof. An elongate member 27, in the form of a helical metal spring is located within the grooves. A braided metal, pressure-containing sheath 29 covers substantially all of the external surface of the convolute tube 25.

[0035] In use, as fuel flows through the flexible hose 100 from the manifold to the burner, general engine vibrations cause the elongate member 27 to vibrate within the tube 25. This prevents build-up of coke within the convolute tube 25, the vibration helping to dislodge any particulate matter that has accumulated.

[0036] The welding of the end connectors to respective ends of the metal convolute tube 25 creates reliable fluid-tight joints between the manifold and the flexible hose, and the flexible hose and the burner respectively.

[0037] FIG. 3(a) shows a schematic longitudinal cross-section through a concentric double layer hose 200. The hose has an inner 25a and an outer 25b metal convolute tube, each with just inner grooves. Inner 27a and outer 27b elongate members, both in the form of helical springs, are respectively located within the grooves of the inner and outer metal convolute tubes. Two separate fuel flows are transported by the concentric double layer hose 200: the inner metal convolute tube 25a carries a mains fuel flow M in its central bore, and the outer metal convolute tube 25b carries a pilot fuel flow P in the annular passage formed between the inner and outer convolute tubes. A braided metal, pressure-containing sheath 29 covers substantially all of the external surface of the outer convolute tube 25b. End connecters (not shown) are welded to respective ends of the hose for connection at one end of the hose to the respective fuel manifolds which provide the separate fuel flows, and at the other end of the hose to respective fuel passages of the burner.

[0038] Again, vibration of the elongate members 27a, b can prevent build-up of coke within the tubes 25a, b, and welding of the end connectors creates reliable fluid-tight joints.

[0039] FIG. 3(b) shows a schematic longitudinal cross-section through a concentric double layer hose 200 similar to that shown in FIG. 3(a), but wherein each of the elongate members 27a, b is a half-moon spring with a semi-circular cross section. The semi-circular cross-section allows the elongate members 27a, b to locate securely in the grooves of their respective metal convolute tubes 25a, b whilst presenting a relatively smooth surface to the fluid flows to reduce turbulence. Elongate members having such cross-sections can equally be adopted in flexible hoses of the type shown in FIG. 2.

[0040] While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. For example, the convolute tubes may have (e.g. spiral) grooves on their outer surfaces as well as their inner surfaces. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.