Abstract: A method of accessing a nozzle tip assembly of a gas turbine engine fuel nozzle is disclosed. The fuel nozzle has a stem and a heat shield enclosing at least part of the stem. The nozzle tip assembly is disposed within an inner cavity of the stem. The method includes forming an opening in at least the heat shield of the fuel nozzle, the opening providing access to the inner cavity of the stem via a first end thereof. The first end of the cavity is positioned opposite to a fuel nozzle exit from which fuel is conveyed from the fuel nozzle. The method includes accessing the nozzle tip assembly in the inner cavity via the opening. The method includes closing the opening after accessing the nozzle tip assembly.

Abstract: A method of providing a floating collar for a gas turbine engine combustor is provided, and comprises providing an annular sheet metal blank and bending the blank to provide the floating collar with an axial extending annular collar portion, an annular flange portion extending radially from the collar portion and a smooth transition portion between the collar and flange portions. The arrangement offers reduced cost, and simplicity, and therefore facilitates manufacturing.

Abstract: An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor, the dome including a plurality of effusion cooling holes provided non-perpendicularly to an entry surface of the holes, the dome being substantially planar.

Abstract: A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral pattern around an axis along which fuel is injected into the combustor by the fuel nozzles.

Abstract: A simplified floating collar mounting arrangement for receiving a fuel nozzle swirler body of a gas turbine engine combustor is provided. The assembly comprises a floating collar mounted between a spaced-apart mounting flange and cap, and slidably trapped therebetween such that relative radial movement is permitted. The arrangement offers reduced part count and simplicity, and therefore improves reliability.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.