Collins Engine Nozzles

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A torch igniter for a combustor of a gas turbine engine includes an igniter body (20) and an igniter head. The igniter body is disposed within a high-pressure case (18) of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head (22) is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector (34).

A filter assembly comprising: a manifold (1) having a fluid inlet (2) and a fluid outlet (3), a filter housing (4) having a filter medium (6) provided therein, the filter medium defining an inner filter chamber (7) and defining an outer filter chamber (8) between the filter medium and the filter housing, the filter housing being removably attached to the manifold so as to provide a fluid flow path from the inlet into the inner filter chamber via a supply channel (11), through the filter medium into the outer chamber and out of the outlet; characterised by the filter assembly further comprising a bypass valve assembly forming a bypass channel (13) from the supply channel (11) that bypasses flow through the filter medium, the bypass valve assembly comprising one or more openings (200) in a wall of the supply chamber and a corresponding one or more flaps (202) associated with respective openings (200), the one or more flaps (202) being configured to move from a default closed position over the respective opening (200) to close the opening, to an open position relative to the respective opening in which fluid can flow from the supply channel (11) via the opening (200), the flaps moveable from the closed to the open position in response to a pressure differential across the flap exceeding a predetermined value, the flaps further configured to return from the open to the closed position when the pressure differential is below the predetermined value.

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A fuel injection system (100) for a gas turbine engine (102) includes a first plurality of fuel nozzles (110) arrayed in a circular pattern. Each of the nozzles in the first plurality of fuel nozzles (110) includes a first airflow area defined therethrough. A second plurality of fuel nozzles (112) radially inward from the first plurality of fuel nozzles (110). Each of the nozzles in the second plurality of fuel nozzles (112) includes a second airflow area defined therethrough. The first airflow area is larger than the second airflow area. A third plurality of fuel nozzles (114) can be radially inward from the second plurality of fuel nozzles (112). Each of the nozzles in the third plurality of fuel nozzles (114) can include a third airflow area defined therethrough. The second airflow area can be larger than the third airflow area.

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