Abstract: Combustors of gas turbine engines having a combustor shell having a first end and a second end opposite the first end, a first securing element positioned at the first end of the combustor shell, a second securing element positioned at the second end of the combustor shell, a plurality of high temperature material panels fixedly secured by the first securing element at the first end and the second securing element at the second, wherein a panel gap is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels, and a seal divider extending from the first end to the second end and positioned on the combustor shell and arranged to seal the panel gap between adjacent first and second high temperature material panels.

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

Abstract: A gasket for installation within a cavity between a support shell and a liner panel of a combustor wall assembly, the support shell having a multiple of impingement holes, and the liner panel having a multiple of film holes, the gasket including a multiple of cells arranged with respect to the multiple of impingement holes and the multiple of film holes, wherein at least one of the multiple of cells segregate a respective subset of the multiple of impingement holes and a subset of the multiple of film holes.

Abstract: A turbine engine optical system includes a plurality of viewing ports in an engine case that are circumferentially spaced from one-another. At least one optical device is optically coupled to the ports for viewing an internal chamber defined by the engine case and for depicting at least spatial temperature distributions. The chamber may be an exhaust chamber and the controller may have the capability to correlate events in the exhaust chamber to events in an upstream combustor chamber and may thereby adjust operating parameters of a fuel system of the combustor.

Abstract: A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the first fuel injection stage and fluidly connected to a selective valve, and a second fuel reservoir fluidly connected to the selective valve. The selective valve connects one of the first fuel reservoir and the second fuel reservoir to the second fuel injection stage.

Abstract: A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.

Abstract: An actuation system according to various embodiments can include an actuation ring having a first end and a second end separated by a gap, the actuation ring being configured to be coupled to a blade outer air seal (BOAS). The actuation system can also include an actuator coupled to at least one of the first end or the second end and configured to adjust a size of the gap such that a tip clearance between the BOAS and a blade tip is reduced in response to the size of the gap being reduced.

Abstract: A gas turbine engine includes a combustor having a fuel nozzle assembly for delivering fuel to a combustion chamber. A sensor is at least partially housed within the fuel nozzle assembly for sensing a parameter associated with the delivery of fuel to the combustion chamber. In one example, the sensor is an optical sensor coupled to an optical decoder for ascertaining the parameter. A trim valve is in communication with the fuel nozzle assembly. A controller is in communication with the sensor and is programmed to actuate the trim valve to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor is arranged near a fuel exit of the fuel nozzle assembly. The controller actuates the trim valve for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system.

Abstract: An oxidation resistant coating system for a turbine engine component includes a cathodic arc coating applied to a surface of the engine component, a thin APS metallic coating applied to a surface of the cathodic arc coating, and a ceramic top coating applied to a surface of the thin APS metallic coating to improve lifetime of the engine components.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a disk and a rod. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The disk is slidably engaged with the bracket. The rod is for connecting to an exhaust duct of the gas turbine engine. The rod is pivotably connected to the disk.

Abstract: A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.

Abstract: A heat shield for a combustor includes a ring shaped body including a central opening defining a radially inner edge of the ring shaped body. The ring shaped body is at least partially made of a ceramic material. The heat shield includes a shaped portion designed to enhance an interference fit.

Abstract: A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.

Abstract: An aeration system for a fuel injector system of a gas turbine engine includes a air tank in communication with a fuel injector and method of operation thereof.

Abstract: A self-purge system for a fuel injector system of a gas turbine engine includes an accumulator in communication with a fuel passage to selectively purge the fuel passage.

Abstract: A fuel injector providing a flow of fuel having a variable swirl and/or variable effective area is disclosed. The fuel injector may have a nozzle defining a mixing chamber having an outlet proximate a centerline of the mixing chamber, a first fuel line in fluid communication with the mixing chamber and a second fuel line in fluid communication with the mixing chamber. The first fuel line may terminate in a tangential fuel inlet positioned tangential to the centerline of the nozzle, while the second fuel line may terminate in a radial fuel inlet positioned radial to the centerline of the nozzle.

Abstract: A turbine engine optical system includes a plurality of viewing ports in an engine case that are circumferentially spaced from one-another. At least one optical device is optically coupled to the ports for viewing an internal chamber defined by the engine case and for depicting at least spatial temperature distributions. The chamber may be an exhaust chamber and the controller may have the capability to correlate events in the exhaust chamber to events in an upstream combustor chamber and may thereby adjust operating parameters of a fuel system of the combustor.

Abstract: A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the first fuel injection stage and fluidly connected to a selective valve, and a second fuel reservoir fluidly connected to the selective valve. The selective valve connects one of the first fuel reservoir and the second fuel reservoir to the second fuel injection stage.

Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. Bluff body fuel injectors are along the bulkhead.

Abstract: A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a disk and a rod. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The disk is slidably engaged with the bracket. The rod is for connecting to an exhaust duct of the gas turbine engine. The rod is pivotably connected to the disk.