Rolls-royce Corporation

Rolls-royce Deutschland Ltd & Co. Kg

Alan P Geary

Paul Allan Hucker

Miklos Gerendas

Stephen Charles Harding

Anthony John Moran

Jonathan Mark Gregory

Volker Herzog

Iain Morgan

Keith Bell

Kenneth James Young

Klaus Stefan Steinbach

Iain David Jeffrey Dupere

Stephen C Harding

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

A fuel injector system with a fuel feed arm extending inwardly from an outer casing of combustion equipment of a gas turbine engine to a flame tube of the equipment, which ends in an injection nozzle which penetrates a head of the tube to deliver fuel. The system has a swirler arranged coaxially with the nozzle at the head of the tube, including one or more circuits which produce flows of swirling air around the fuel. A seal ring seals the nozzle to the swirler, the nozzle being removably inserted into the ring. The ring has a flange portion, and the swirler has a pair of spaced retention grooves at a front face thereof. Opposite edges of the flange portion slidingly locate in the grooves so it sealingly engages to the front face. The swirler has a spring mechanism which retains the flange portion in the grooves.

Fuel injector system

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.

Cooled component

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.

Component for attaching to a wall

A combustor system is provided for a gas turbine engine. The combustor system includes an annular combustion chamber, and outer and inner casings housing the combustion chamber. The outer casing is outwardly radially spaced from the combustion chamber and the inner casing being inwardly radially spaced from the combustion chamber. The combustor system further includes an attachment arrangement at the rearward end of the combustion chamber for attaching the combustion chamber to the engine. The attachment arrangement axially restrains the rearward end of the combustion chamber relative to the casings. The combustor system further includes a first stop surface formed at the forward end of the combustion chamber adjacent a selected one of the outer and inner casings, and a corresponding first baulking surface axially forward of the first stop surface formed by the selected casing. The first stop surface and the first baulking surface are spaced from each other to allow forward axial movement of the combustion chamber relative to the selected casing. However, the amount of relative forward axial movement is limited by engagement of the first stop surface with the first baulking surface.

Combustor system

An arrangement for sealing an opening formed in a wall for receiving a member. The arrangement comprises a sealing member with a passage, and the sealing member is moveably mounted on the wall adjacent to the opening such that the sealing member passage is substantially co-axial with the opening in the wall. Biasing means for biasing the sealing member towards the wall are also provided.

Sealing arrangement

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

Combustion chamber for gas turbine engine

A device is provided for passing a fluid flow across a static or rotating barrier wherein there is relative rotation between the flow and the barrier and wherein it is necessary to pass the maximum of flow through the device while keeping the diameter of the device as small as possible. One embodiment of the invention shown in FIG. 2 is a device for use in a gas turbine engine for supplying cooling air across a bolted joint to a space behind a cover plate 6 for cooling an engine disc. The device comprises a cylindrical receiver 11 having helical slots 13 running through it from one axial end face to the other, the helix angle being the same as the angle of the relative velocity vector between the flow and the slots. The helical shape of the slots ensures that the radius of the axis of each slot is constant along the length of the slots and allows greater slot height and hence greater flow area.

Device for passing a fluid flow through a barrier

A device is provided for passing a fluid flow across a static or rotating barrier wherein there is relative rotation between the flow and the barrier and wherein it is necessary to pass the maximum of flow through the device while keeping the diameter of the device as small as possible. One embodiment of the invention shown in FIG. 2 is a device for use in a gas turbine engine for supplying cooling air across a bolted joint 19 to a space behind a cover plate 6 for cooling an engine disc. The device comprises a cylindrical receiver 11 having helical slots 13 running through it from one axial end face to the other the helix angle being the same as the angle of the relative velocity vector between the flow and the slots. The helical shape of the slots ensures that the radius of the axis of each slot is constant along the length of the slots and allow greater slot height and hence greater flow area.

Growing community of inventors

Bristol, United Kingdom

Alan P Geary