Abstract: A combustor floatwall panel includes a stack of layers of a sintered material forming in the aggregate a panel, an attachment stud, and a cooling flow passageway. The panel has a first surface and a second surface parallel to the first surface. The attachment stud projects from the second surface. The cooling flow passageway includes a feeder hole extending through the attachment stud, and at least one effusion cooling hole extending to the first surface. The effusion cooling hole is fluidly connected to the feeder hole. The effusion cooling hole extends along a first axis where the effusion cooling hole meets the first surface. The feeder hole extends along a second axis. The first axis is at a first angle relative to the first surface. The second axis is at a second angle relative to the first surface. The second angle is greater than the first angle.

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract: A combustor floatwall panel includes a stack of layers of a sintered material forming in the aggregate a panel, an attachment stud, and a cooling flow passageway. The panel has a first surface and a second surface parallel to the first surface. The attachment stud projects from the second surface. The cooling flow passageway includes a feeder hole extending through the attachment stud, and at least one effusion cooling hole extending to the first surface. The effusion cooling hole is fluidly connected to the feeder hole. The effusion cooling hole extends along a first axis where the effusion cooling hole meets the first surface. The feeder hole extends along a second axis. The first axis is at a first angle relative to the first surface. The second axis is at a second angle relative to the first surface. The second angle is greater than the first angle.

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract: An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.

Abstract: An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract: A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of impingement film floatwall panels for a combustion chamber, wherein the knowledge base comprises at least one data value signal for each one of the plurality of design rule signals. The steps also include entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the impingement film floatwall panels and comparing the entered desired data value signal for the selected one of the plurality of parameters with the corresponding at least one data value signal in the knowledge base for the corresponding one of the plurality of design rule signals.

Abstract: A fuel nozzle guide and method of assembly/disassembly is disclosed with the nozzle guide having a frusto-conical hub section, an annular base, a pair of retaining tabs for securing the guide to the outer wall of a combustor bulkhead for limited movement relative to the bulkhead, and a radial inflow swirler. The method of assembly/disassembly comprises assembling/disassembling the nozzle guide in the bulkhead from the outer wall (cold) side of the bulkhead and mechanically connecting/disconnecting the nozzle guide to/from the outer wall of the bulkhead with mechanical fasteners.

Abstract: This invention relates to a combustor liner for a gas turbine engine with means for loosely mounting one of the two spaced liner walls relative to the other to support it so that it "floats". The floating wall is made up of a plurality of segments to permit relatively minimal stress during thermal expansion, and the movement of each segment is restricted by at least one washer, and removal of the washer(s) permits the segment to be individually removed without removal of adjacent segments.

Abstract: A spillage oil drain from the volume between a conical hub and a disk is comprised of a radial slot in the edge of the hub flange where it abuts the disk.