Abstract: The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead (34) an inner support ring (70) and an outer support ring (84) at end upstream end thereof. The bulkhead (34) has an inner surface (40), when in use is provided on an internal surface of a combustor (16) and exposed to combustion products and an outer surface (41) provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (70); and an outer mating feature to cooperate with the outer support ring (84). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner (70) and outer (84) support rings.

Abstract: The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead (34) an inner support ring (70) and an outer support ring (84) at end upstream end thereof. The bulkhead (34) has an inner surface (40), when in use is provided on an internal surface of a combustor (16) and exposed to combustion products and an outer surface (41) provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (70); and an outer mating feature to cooperate with the outer support ring (84). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner (70) and outer (84) support rings.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.