Rolls-royce Corporation

Charles Bryce Graves

William G Cummings, Iii

Jun Shi

Russell N Bennett

Donald M Wicksall

Jack D Petty, Sr

Randall E Yount

Stuart M Bloom

Mindi D Moore

Thomas F Richardson, Jr

Jacob E Determan

Afework Woubshet

David E B Stone

A cartridge for attachment to the inner surface of a single-walled combustion liner of an annular combustor is provided. The cartridge includes at least one chute projecting into the combustion chamber for a counter swirl effect for improved fuel/air mixing in the combustion chamber and at least two studs projecting through associated stud holes in the liner. A method for attaching a cartridge to the inner surface of a single-walled combustion liner is also provided.

Tile attachment scheme for counter swirl doublet

A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.

Shell and tiled liner arrangement for a combustor

An improved system, apparatus and method may comprise an inner liner and an outer liner extending circumferentially around an engine centerline axis thereby forming a combustion chamber therebetween. The system, apparatus, and method may include a front end extending between the inner and outer liners and having a plurality of fuel nozzle ports configured to each receive a fuel nozzle. First and second outer plunged inlet holes may be formed in the outer liner and extending in a first radial direction toward the engine centerline axis and into at least a portion of the combustion chamber. First and second inner plunged inlet holes may be formed in the inner liner and extending in a second radial direction away from the engine centerline axis and into at least a portion of the combustion chamber.

Counter-swirl doublet combustor with plunged holes

An improved combustor for a gas turbine is operable to provide high combustion efficiency in a compact combustion chamber. The combustor includes a counter swirl doublet for improved fuel/air mixing. The enhanced combustor assembly and method of operation improves operation of the turbine.

Counter swirl doublet combustor

A combustor for use in a gas turbine engine includes a liner with a plurality of tiles coupled to a shell via a plurality of fasteners. Each of the plurality of fasteners extends through at least one of the tiles.

An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path. Upon heating, the bi-metal sealing member 'uncoils' contacting the second perpendicular surface, thus blocking the flowpath between the two surfaces. Various metals may be provided to provide predetermined sealing characteristics.

Bi-metal strip-seal

A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream that reduces a thickness of boundary layer formed on an opposing wall. The re-start in boundary layer can be used in a way that allows an upstream portion of the diffuser to be sized approaching a separation limit and a downstream portion of the diffuser to also be sized approaching a separation limit. In some forms the passages split by the blunt forebody can be sized relative to each other to balance flow between the branches.

Multi-passage diffuser with reactivated boundary layer

An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments.

Bi-metal fastener for thermal growth compensation

A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The combustor further includes a fuel inlet and swirler operatively connected to the forward end and at least one air inlet. The air inlet is equipped with a chute that extends into the interior of said combustor. The combustor is secured to a fixed structure proximate the forward end of the combustor.

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Avon, IN, United States of America

Charles Bryce Graves