Rolls-royce Corporation

Industrial Turbine Company Limited

Ian James Toon

Jeffrey D Willis

Allan J Salt

Andrew Charles Graham

Gary Eadon

Robert Anthony Hicks

Bernard W Boyce

Norman E Deacon

John H Currin

Stephen J O'Dell

Samantha Hayes-Bradley

Richard E Pollard

Allan John Salt

Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage. The inner surface profile of the second-splitter wall has a divergent section downstream of its convergent section.

Fuel spray nozzle having a splitter with by-pass ducts

A gas turbine engine fuel system including a combustor with at least one fuel injector, a fuel manifold that supplies fuel to each injector, a drain tank in fluid communication with the fuel manifold, and a vacuum generator that selectively provides below atmospheric pressure to the drain tank and includes first and second chambers separated by a flexible diaphragm. The fuel system also includes a first check valve that allows one-way flow from the fuel manifold into the fuel injector, and a second check valve that allows one-way flow from the fuel injector to the fuel manifold. The vacuum generator reduces a pressure within the second chamber causing the diaphragm to increase a volume of the first chamber and reduce a volume of the second chamber, such that expanding the first chamber causes below atmospheric pressure in the drain tank and fuel manifold, and the second check valve opens.

Fuel system with vacuum generator to purge fuel from fuel nozzles

An igniter assembly for a combustion system of a gas turbine engine is provided. The igniter assembly includes an igniter plug having a tip which, in use, is located at an aperture in a wall of a flame-tube of the combustion system such that the tip can provide an electrical discharge to ignite an air-fuel mixture within the flame-tube. The igniter assembly further includes a substantially annular igniter boss which locates on the wall of the flame-tube at the aperture to encircle the tip. The igniter boss has a slot formed therein at one side of the tip. An entrance of the slot receives air from outside the flame-tube and an exit of the slot delivers the air as a sheet-shaped flow over the tip. The slot is tapered such that the thickness of the slot narrows from its entrance to its exit.

Igniter assembly

An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

Airblast fuel injector

Fuel spray nozzle for a gas turbine engine

A fuel injector for a fuel spray nozzle of a gas turbine engine combustor is provided. The fuel injector has an annular flow passage which conveys fuel to a prefilming lip at an end of the flow passage. The fuel injector also has plurality of fuel distributor slots which are circumferentially spaced around and in fluid communication with the other end of the flow passage to deliver respective fuel streams into the flow passage. The slots are configured so that the fuel streams enter the flow passage at a swirl angle of at least 80&#xb0; relative to the axis of the flow passage.

Fuel injector

An improved fuel spray nozzle for a gas turbine engine is proposed, in order to address problems associated with the nozzles being wetted with fuel purged from fuel lines upon engine shutdown. The nozzle has a heat shield provided around a fuel discharge orifice, the heat shield incorporating a sliding expansion joint and having a drip collar arranged to cover the expansion joint so as to protect it from being wetted by fuel ejected through the fuel discharge orifice and falling on the heat shield. The fuel spray nozzle is particularly suited to marine or industrial gas turbine engines having a plurality of radially oriented combustion chambers with respective fuel spray nozzles.

Fuel injector for a gas turbine engine

A fuel injector head for a gas turbine engine the head having a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric splitter separates the pilot injector from the main injector and has a toroid chamber which is supplied with air in use to generate a toroidal flow which delays mixing of the pilot and main air flows.

In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements including liquid fuel jets are arranged to such that through high angle incidents by the airflow appropriate vaporization and droplet formation is achieved for a fuel/air mixture combustible in a combustor of a turbine engine. At low liquid fuel flow rates below a pre-determined level the liquid fuel is atomised and entrained by the airflow. At high liquid fuel flow rates the fuel splash impinges upon a wash surface to develop a wash film which is again vaporised and atomised about an edge for a fuel/air mixture capable of combustion.

Fuel injection

A joint for a gas turbine fuel injector, the joint comprises a housing for supporting a fuel injector, a first tube terminating within the housing and a second tube. The housing at least partially encloses an adaptor having a bore, with one end of the first tube and one end of the second tube being located within opposing ends of the bore. First sealing means are provided between the outside of the first tube and the adaptor bore, second sealing means are provided between the outside of the second tube and the adaptor bore and third sealing means are provided between the outside of the adaptor and the housing. The joint is particularly suitable for conduits carrying a relatively cold fluid mounted in a relatively hot housing.

Component for fuel supply

In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements including liquid fuel jets are arranged to such that through high angle incidents by the airflow appropriate vaporization and droplet formation is achieved for a fuel/air mixture combustible in a combustor of a turbine engine. At low liquid fuel flow rates below a pre-determined level the liquid fuel is atomized and entrained by the airflow. At high liquid fuel flow rates the fuel splash impinges upon a wash surface to develop a wash film which is again vaporized and atomized about an edge for a fuel/air mixture capable of combustion.

Gas turbine engine combustion chamber

A gas turbine engine combustion chamber which has primary, secondary and tertiary combustion zones in flow series has a secondary fuel and air mixing duct and a tertiary fuel and air mixing duct. The secondary mixing duct has a secondary air intake at its upstream end and the tertiary mixing duct has a tertiary air intake at its upstream end. The tertiary air intake is arranged adjacent to the secondary air intake. A combined secondary and tertiary fuel system is provided to supply fuel to the secondary and tertiary mixing ducts. The fuel system comprises a manifold arranged adjacent to the secondary mixing duct but is spaced from the tertiary mixing duct by the secondary mixing duct. The manifold has apertures to direct fuel towards the tertiary air intake across the secondary air intake. Variations in fuel pressure cause the fuel to flow into the secondary air intake or the tertiary air intake.

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Leicester, United Kingdom

Ian James Toon