A sealing structure for sealing a gap between a combustor liner having an outer surface and a surrounding structure surrounding the combustor liner, includes: an annular sealing member held on the surrounding structure so as to be in contact with the outer surface of the combustor liner. The sealing member includes a plurality of sealing segments arranged in an annular configuration. The sealing structure seals the gap around the combustor liner of the combustor and absorbs, the difference in thermal expansion between the combustor liner and the surrounding structure.

Sealing structure for combustor liner

An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length. Inherent with this swirl afterburner concept are design compactness, light weight, lower cost, smooth and efficient combustion, high thrust output, wide flammability limits, continuous operation at stoichiometric fuel/oxidizer mixture ratios, no combustion instabilities, and relatively low pressure losses.

Compact swirl augmented afterburners for gas turbine engines

The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination of the invention also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage a corresponding circumferentially-facing portion of the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination of the invention also includes a rolling assembly operably disposed between the free-standing ring and the plurality of projections to reduce binding during the relative radial displacement.

Combustor liner support and seal assembly

A gas turbine afterburner includes a gutter electrode that helps to hold an afterburner flame. A charge source applies a majority charge to be carried by a turbine exhaust gas. Electrical attraction between the majority charge and the gutter electrode helps to hold the afterburner flame.

Gas turbine and gas turbine afterburner

A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust ring is coaxially disposed within the turbine case. The splash plate extends axially along the turbine exhaust ring, radially spaced between the turbine exhaust ring and the turbine case. There are cooling fluid apertures in the turbine case to provide cooling fluid flow from the bypass duct onto the splash plate, and impingement holes in the splash plate to provide impingement flow onto the turbine exhaust ring.

Impingement cooling for turbofan exhaust assembly

An augmentor for a gas turbine engine with a nozzle is provided having an outer casing, a liner, a stiffening ring, a plurality of fingerseals, and apparatus for fastening the stiffening ring and the fingerseals to the liner. The liner includes a plurality of first cooling apertures. The stiffening ring includes a plurality of second cooling apertures. The finger seals are positioned between the liner and the stiffening ring. Each fingerseal includes a plurality of cooling slots having a lengthwise axis. The cooling slots, first apertures, and second apertures are relatively positioned such that cooling air passing through the second cooling holes must thereafter travel within one of the cooling slots in a direction substantially along the lengthwise axis of the slot, before entering the first apertures.

Cooled gas turbine engine augmentor fingerseal assembly

An afterburner 20 for a gas turbine engine 10 has a fuel spray ring 24a for injecting fuel into the afterburner, a flameholder gutter 34a for stabilizing combustion of a fuel-air mixture flowing through the afterburner, and an ignitor 35 for initiating combustion and includes an enclosure 50 attached to the gutter. The enclosure has radially inner and outer walls 52, 54 and circumferentially spaced apart webs 60, 62 extending between the walls to define a radially and circumferentially bounded chamber 64. Each web has a forward opening 72 and an aft opening 74 so that a portion of the spray ring and a portion of the gutter are embraced by the enclosure. The enclosure is ideally circumferentially aligned with the ignitor and regulates the fuel-air ratio within and in the vicinity of the chamber to ensure reliable lighting of the afterburner and flawless advancement to full afterburning operation.

Gas turbine engine afterburner

An augmentor 10 for a gas turbine engine with a nozzle is provided having an outer casing 22, a liner 20, a stiffening ring 26, a plurality of fingerseals 24, and apparatus 52 for fastening the stiffening ring and the fingerseals to the liner. The liner includes a plurality of first cooling apertures 32. The stiffening ring includes a plurality of second cooling apertures 34. The finger seals 24 are positioned between the liner 20 and the stiffening ring 20. Each fingerseal includes a plurality of cooling slots 46 having a lengthwise axis. The cooling slots 46, first apertures 32, and second apertures 34 are relatively positioned such that cooling air passing through the second cooling holes 34 must thereafter travel within one of the cooling slots 46 in a direction substantially along the lengthwise axis of the slot, before entering the first apertures 32.

Ronald T. Clawson

Papers

Cooled gas turbine engine augmentor fingerseal assembly

Gas turbine engine afterburner

Cooled gas turbine engine augmentor