Abstract: An adjustable mask system (100) includes a cushion with a seal (130) having the ability to change size and/or shape. The seal is preferably a one-piece, continuous member without interruptions. To effect adjustment of the size and/or shape of the seal, an actuator may be provided, which may take the form of a dial (190).

Abstract: A cooling arrangement for a surface of a wall in a gas turbine engine, the wall having a plurality of effusion holes each with an outlet onto the surface for supplying an effusion flow to the surface and an inlet, the inlets of the effusion holes being arranged at the peripheries of groups tessellated on an opposing surface of the wall, each inlet being located on the peripheries of three groups. The arrangement comprises a second wall spaced apart from the opposing surface having impingement orifices each for directing a flow of air in use to a respective impingement location on the opposing surface, each group having a centrally positioned impingement location.

Abstract: A patient interface for delivering breathable gas to a patient includes a foam interfacing portion adapted to provide a nasal interface to contact under and around the patient's nose in use and including an orifice adapted to surround both the patient's nares in use, and a positioning and stabilizing structure to support the foam interfacing portion in an operative position on the patient's face. The positioning and stabilizing structure is structured to provide a range of rotational, axial, and/or lateral movement to the foam interfacing portion while maintaining a sufficient interface and resisting the application of tube drag and/or headgear tension to the foam interfacing portion.

Abstract: A fuel distributor valve (19) of a type suitable for use in the fuel supply system of a gas turbine engine is disclosed. The valve comprises: a valve body (22) through which a bore (24) extends between a fuel inlet (22) and a fuel outlet (23); a first valve seat (28) and associated valve member (30) provided across the bore (24), the first valve seat (28) defining at least one fuel-flow-port (26) and the valve member (30) being moveable between a closed position in which it substantially seals against the first valve seat (28) to close the or each fuel-flow-port (26) and an open position in which it is spaced from the first valve seat (28) to permit the flow of fuel through the or each fuel-flow-port (26) in a direction flowing from the fuel inlet (22) towards the fuel outlet (23).

Abstract: Headgear for a respiratory mask includes a strap arrangement including front strap portions adapted to be disposed over a patient's cheeks and having front ends adapted for attachment to an airway interfacing portion, top strap portions connected to respective front strap portions and adapted to be disposed over the top of a patient's head and to connect to each other, and a back strap extending rearwardly from and connecting respective junctions of the front strap portions and top strap portions or regions adjacent these junctions and adapted to locate underneath a patient's occiput. In use with a patient having long hair, the back strap is adapted to extend under the patient's hair and urge upwardly on the patient's hair and against the patient's head beneath the occiput. In use with a patient having short hair, the back strap is adapted to urge against the patient's head beneath the occiput. In an embodiment, front strap portions of the headgear may be provided with a sleeve or cover (e.g.

Abstract: A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.

Abstract: A patient interface for delivering breathable gas to a patient includes a nasal prong assembly including a pair of nasal prongs structured to sealingly communicate with nasal passages of a patient's nose in use and headgear to maintain the nasal prong assembly in a desired position on the patient's face. The headgear includes side straps and rigidizers provided to respective side straps. Each rigidizer includes a first end portion that provides a connector structured to engage a respective end of the nasal prong assembly and an inwardly curved protrusion in the form of a cheek support that curves inwardly of the connector. The cheek support is adapted to follow the contour of the patient's cheek and guide a respective end portion of the side strap into engagement with the patient's cheek to provide a stable cheek support.

Abstract: A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member 46 which forces air flowing through the pre-diffuser 40 to separate, initially to be directed away from the midline 48 before subsequently being allowed to diffuse back towards the midline 48. The majority of the diffusion takes place on the walls of the central member and is thus in an inner region of the annulus of air ejected from the pre-diffuser to pass to the combustor. Any boundary losses therefore do not significantly effect air at the extremities of this annulus, this air being destined for the annuli of the combustor and requiring relatively high energy levels.

Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.

Abstract: A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (38) and a downstream region (40). Distribution means (41) is arranged between the downstream region (40) and the outlet (28) to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region (40) to the cross-sectional area of the upstream region (38) is greater than 1.5 to 1.

Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.

Abstract: A seal arrangement for a combustor is disclosed. The seal arrangement comprises a seal defining a first aperture, an inner combustor wall defining a second aperture, and an outer combustor wall defining a third aperture. The first and second apertures are arranged in line with each other to receive an article therethrough. The seal is arranged between the inner and outer combustor walls.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A double wall structure (22) for a combustor (15) of a gas turbine engine (10) comprising an inner wall (28) and an outer wall (27), the inner wall (28) comprising a plurality of main tiles (50), the main tiles (50) are secured to the outer wall (27) by a securing means (35), wherein the inner wall (28) further comprises a plurality of edge tiles (52) which are secured to the outer wall (27) by securing means (35), each edge tile (52) overlapping at least one edge (30, 31, 54, 61) of a main tile (50) thereby further securing the main tiles (50) to the outer wall (27).

Abstract: A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (38) and a downstream region (40). Distribution means (41) is arranged between the downstream region (40) and the outlet (28) to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region (40) to the cross-sectional area of the upstream region (38) is greater than 1.5 to 1.