Abstract: There is described a method of operating a gas turbine engine having a rotor rotatable about a rotation axis, a core gas path defined annularly around the rotation axis, and a casing defining a wall to the core gas path. The method generally has: generating compressed air from a compressed air source, the compressed air source being external relative the gas turbine engine; and guiding the compressed air in sequence from the compressed air source, radially inwardly relative the rotation axis, through a bleed port and into the core gas path.

Abstract: Herein provided are systems and methods for operating an engine of an aircraft. The engine is operated at a first fuel flow rate. An indication of a measured humidity level within the engine is obtained from a humidity sensor coupled to the engine. A determination is made regarding whether the measured humidity level within the engine is indicative that a flameout risk for the engine is below a predetermined risk level. Responsive to determining that the flameout risk is below the predetermined risk level, the engine is operated at a second fuel flow rate lower than the first fuel flow rate.

Abstract: Systems and methods for mitigating flameout risk in an engine of an aircraft are provided. A humidity value is obtained from a humidity sensor associated with the engine. A flameout risk for the engine is determined based on the humidity value. The flameout risk is compared to a predetermined risk threshold. When the flameout risk is above the predetermined risk threshold, a rate of fuel flow to the engine is increased.

Abstract: A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.

Abstract: A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.

Abstract: A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.

Abstract: A combustor heat shield for a gas turbine engine has a heat shield panel adapted to be mounted to an inner surface of a combustor shell with a back face of the panel spaced-apart from the combustor shell to define an air gap therewith. Studs project from the back face of the panel for engagement in corresponding mounting holes defined in the combustor shell. Each stud has a threaded distal end portion for engagement with a nut outside of the combustor shell. At least one of the studs has a channel defined in a peripheral surface thereof. The channel extends longitudinally along the stud from an inlet end connectable to a source of cooling air outside of the combustor shell to an outlet end disposed within the air gap for locally providing cooling air at the base of the stud.

Abstract: A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.

Abstract: A combustor heat shield for a gas turbine engine has a heat shield panel adapted to be mounted to an inner surface of a combustor shell with a back face of the panel spaced-apart from the combustor shell to define an air gap therewith. Studs project from the back face of the panel for engagement in corresponding mounting holes defined in the combustor shell. Each stud has a threaded distal end portion for engagement with a nut outside of the combustor shell. At least one of the studs has a channel defined in a peripheral surface thereof. The channel extends longitudinally along the stud from an inlet end connectable to a source of cooling air outside of the combustor shell to an outlet end disposed within the air gap for locally providing cooling air at the base of the stud.

Abstract: A gas turbine engine combustor includes an exit duct having annular first and second exit duct walls radially spaced apart to define therebetween the combustor exit opening. The first and/or second exit duct walls has a double-skin wall section which includes an inner hot wall facing the combustor exit opening and an outer cold wall fastened to the inner hot wall and radially spaced away therefrom to define a radial gap therebetween. The outer cold wall has a coefficient of thermal expansion greater than that of the inner hot wall. This helps reduce thermal growth mismatch between the outer cold wall and the inner hot wall during operation of the combustor, and reduces thermal stress at the joint between the hot and cold walls.

Abstract: A bearing support ring includes a plurality of contact pads radially protruding from inner and outer circumferential surfaces of the ring. Flexible portions of the ring are defined between the contact pads and have a radial thickness less than that of the ring at the contact pads, such as to permit elastic deflection of the ring in a radial direction between the contact pads. Openings sized to permit unrestricted oil flow are provided, such as within the flexible portions of the ring.

Abstract: A bearing support ring includes a plurality of contact pads radially protruding from inner and outer circumferential surfaces of the ring. Flexible portions of the ring are defined between the contact pads and have a radial thickness less than that of the ring at the contact pads, such as to permit elastic deflection of the ring in a radial direction between the contact pads. Openings sized to permit unrestricted oil flow are provided, such as within the flexible portions of the ring.

Abstract: The strainer comprises an unitary body having a main section and a collar section located around the main section. The collar section has a substantially outwardly-projecting portion located around the main section and an upstream projecting portion located around the substantially outwardly-projecting portion.

Abstract: The strainer comprises an unitary body having a main section and a collar section located around the main section. The collar section has a substantially outwardly-projecting portion located around the main section and an upstream projecting portion located around the substantially outwardly-projecting portion.

Abstract: A method of insulating an article comprising: surrounding at least a portion of the article with an insulating layer, inserting the article portion surrounded by the insulating layer into an outer protective sleeve, and shrinking the outer protective sleeve around the insulating layer.