Rolls-royce Corporation

Paul Allan Hucker

Stephen Charles Harding

Alan P Geary

Iain Morgan

Giuseppe Rallo

Anthony John Moran

Jonathan Mark Gregory

Nicholas Alexander Worth

Eliot Burrows

Steven Ballantyne

Stephen C Harding

Nicholas Worth

Anthony Moran

The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead () an inner support ring () and an outer support ring () at end upstream end thereof. The bulkhead () has an inner surface (), when in use is provided on an internal surface of a combustor () and exposed to combustion products and an outer surface () provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (); and an outer mating feature to cooperate with the outer support ring (). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner () and outer () support rings.

Gas turbine engine combustor apparatus

An igniter seal arrangement for a combustion chamber. The combustion chamber has a wall having first surface and second surfaces. A boss projects from the first surface, and has a platform on its remote end. The platform has an inner surface spaced from the first surface of the wall to define a chamber between the first surface of the wall and the inner surface of the platform. The platform has an outer surface facing away from the first surface of the wall and an aperture extends through the wall from the outer surface of the platform of the boss to the second surface. First and second L-shape rails extend from the platform and a sealing member has a first edge and a second edge locatable between the outer surface of the platform and the first and second L-shape rails and the sealing member has an aperture to receive an igniter.

Igniter seal arrangement for a combustion chamber

A gas turbine engine combustion chamber includes upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. A frame structure at the downstream end of each segment has multiple spaced radially extending holes. The downstream end of each segment has an axially upstream extending groove and the downstream ring structure has an annular axially upstream extending hook which locates in the groove of each segment. A portion of the downstream ring structure abuts the frame structure of each segment. The downstream ring structure has multiple holes through the portion abutting the frame structure and segment is removably secured to the downstream ring structure by multiple fasteners locating in the holes in the segments and the downstream ring structure.

Combustion chamber having a hook and groove connection

A gas turbine engine combustion chamber includes upstream and downstream ring structures and a plurality of circumferentially arranged combustion chamber segments. Each segment extends the full length of the combustion chamber and each segment is secured to the upstream ring structure and is mounted on the downstream ring structure. The upstream end of each combustion chamber segment includes a surface having a plurality of circumferentially spaced radially extending holes and the upstream ring structure having a plurality of circumferentially spaced holes extending radially through a portion abutting the surface of the upstream end of each combustion chamber segment. Each combustion chamber segment being removably secured to the upstream ring structure by a plurality of fasteners locatable in the holes in the combustion chamber segment and corresponding holes in the upstream ring structure.

Combustion chamber

A combustion chamber includes at least one annular wall which includes at least one box like structure and each box like structure includes an inner wall, outer wall, upstream end wall and downstream end wall. The inner wall is spaced radially from the outer wall and the outer wall has a plurality of apertures for the supply of coolant into the box like structure. The inner wall, the outer wall, the upstream end wall and the downstream end wall are integral. The upstream end of the annular wall has features to secure the annular wall to an upstream ring structure and a downstream end of the annular wall has features to mount the annular wall on a downstream ring structure. The inner wall has at least one slot extending through the full thickness of the inner wall to accommodate differential thermal expansion between the inner wall and the outer wall.

Combustion chamber and a combustion chamber segment

A combustion chamber comprises an upstream ring structure, a downstream ring structure and a plurality of circumferentially arranged combustion chamber segments. Each combustion chamber segment extends the full length of the combustion chamber. Each combustion chamber segment comprises a frame structure and at least an inner wall and the frame structure and the inner wall are integral. An upstream end of each combustion chamber segment is secured to the upstream ring structure and a downstream end of each combustion chamber segment is mounted on the downstream ring structure. The combustion chamber segments are manufactured by additive layer manufacture. The combustion chamber segments have a stiff frame structure which carries the structural loads, the thermal loads, surge loads and flameout loads and the frame structure distributes loads into adjacent components.

A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture has a metering portion and a diffusing portion arranged in flow series and each metering portion is elongate and the width is greater than the length of the metering portion. The metering portion of each aperture has a U-shaped bend. The diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a rectangular shape in the second surface of the wall. Each inlet has an elongate shape in the first surface of the wall and the inlet in the wall is arranged substantially diagonally with respect to the outlet in the wall.

Cooled component

A method of assembling an annular combustion chamber assembly comprises positioning a plurality of first combustion chamber segments circumferentially side by side to form an annulus and removably securing the downstream end of each first combustion chamber segment to a first ring to form a first assembly. The method comprises positioning a plurality of second combustion chamber segments circumferentially side by side to form an annulus, removably securing the downstream end of each second combustion chamber segment to a second ring to form a second assembly. The method comprises removably securing the upstream end of each second combustion chamber segment of the second assembly to an annular upstream end wall. The method comprises inserting the second assembly into the first assembly and then removably securing the upstream end of each first combustion chamber segment of the first assembly to the annular upstream end wall to form the annular combustion chamber assembly.

Method of assembling an annular combustion chamber assembly

A cooled gas turbine engine component comprises a wall having first and second surfaces. The second surface has a plurality of recesses and each recess has a planar upstream end surface arranged so that it hangs over the upstream end of the recess. Each recess has a depth equal to the required depth plus the thickness of the thermal barrier coating to be deposited. The wall has a plurality of angled effusion cooling apertures extending from the first surface towards the second surface. Each effusion cooling aperture has an inlet in the first surface and an outlet in the end surface of a corresponding one of the recesses in the second surface. Each recess has smoothly curved transitions from the end surface and side surfaces to the second surface. Blocking of the effusion cooling apertures by thermal barrier coating is reduced.

A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure.

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Bristol, United Kingdom

Paul Allan Hucker