Rolls-royce Corporation

Jonathan F Carrotte

Anthony John Moran

Alastair Duncan Walker

Christopher L Ford

Ashley Gavin Barker

Michael Stephen Krautheim

Michael Whiteman

Michael A Macquisten

Anthony J Rae

Stephen Harding

Richard Northall

Ian Mariah

Martin S Goodwin

Mark Brend

Mark Cassell

Maxwell Williams

Anthony Moran

Michael S Krautheim

Ashley Barker

A direct injection fuel system is shown for injecting hydrogen fuel into a gas turbine combustor. The fuel injection system includes a plurality of fuel injector blocks. Each fuel injector block includes a fuel admission duct having an inlet for receiving hydrogen fuel from a fuel supply, an outlet for delivering hydrogen fuel into the combustor and a central axis extending from said inlet to said outlet. Each fuel injector block also includes an air admission duct located around the periphery of the fuel admission duct, having an inlet for receiving air from a diffuser and an outlet for delivering air into the combustor for mixing with the hydrogen fuel.

Fuel injection

An annular array of turning vanesis provided in a ductof a gas turbine engine. The annular array of turning vanescomprises aerodynamic vanesand strut-vanes. The strut-vaneshave greater chord length and extend further axially downstream than the aerodynamic vanes. The leading edge of the strut-vanesis upstream of the trailing edge of the aerodynamic vanes. The strut-vanes provide flow turning. The arrangement allows the ductto be axially short.

Gas turbine engine vanes

An annular array of turning vanesis provided in a ductof a gas turbine engine. The annular array of turning vanescomprises aerodynamic vanesand strut-vanes. The strut-vaneshave greater chord length and extend further axially downstream than the aerodynamic vanes. The leading edge of the strut-vanesis upstream of the trailing edge of the aerodynamic vanes. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the ductto be axially short.

A fuel injector includes a central member arranged on axis of fuel injector and a first member arranged around central member. A first swirler is arranged between central member and first member. A pilot fuel injector is arranged to supply fuel onto inner surface of first member. A second member is arranged between downstream end of first member and downstream end of shroud. A second swirler is arranged between upstream end of first member and upstream end of shroud and between downstream end of first member and upstream end of second member. A third swirler is arranged between downstream end of shroud and second member. A main fuel injector is arranged to supply fuel into an annular passage between first member and second member and a fourth swirler extends through first member.

Fuel injector for a gas turbine engine combustion chamber

An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough. The swirling air flow is used by the injector to produce an atomized fuel spray. The air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the air passage. Viewed on a longitudinal section through the injector, the air passage has a bend downstream of the swirler, the bend changing the direction of the air passage. The vanes are configured to introduce a radial component to the air flow exiting the swirler, the radial component guiding the air flow around the bend.

Airblast fuel injector

A gas turbine engine lean burn fuel injector includes a fuel injector head which has a first air swirler, a second air swirler arranged around the first air swirler, a pilot fuel injector arranged radially between the first air swirler and the second air swirler. A third air swirler arranged around the second air swirler, a fourth air swirler arranged around the third air swirler and a main fuel injector arranged radially between the third air swirler and the fourth air swirler. A shroud is arranged around the fourth air swirler. A downstream end of the shroud is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head and an upstream end of the shroud is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head.

Elliptical air opening at an upstream end of a fuel injector shroud and a gas turbine engine combustion chamber

A combustion chamber for a gas turbine engine comprising at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the interior of the combustion chamber. The cavity extends around at least part of the neck and is spaced apart therefrom to define a cooling chamber therebetween. The cooling chamber allows the neck and the cavity to be cooled with a flow of cooling air. The sunken neck allows the resonator to be located within enclosures with minimal volume without compromising on the damping properties afforded.

Combustion chamber for a gas turbine engine

A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extending through its wall for improved damping and cooling, at least one of the holes is directed towards the resonator cavity.

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Leicester, United Kingdom

Jonathan F Carrotte