Abstract: A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.

Abstract: A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.

Abstract: The present disclosure relates to methods for coating gas turbine engine components, such as combustor panels. In one embodiment, a method includes forming a first layer to a substrate to form a bond coat, and forming a second layer over the first layer. The second layer may be formed by a material having a thermal conductivity within the range of 4.45 to 30 Kcal/(m hoC). According to one or more embodiments, the first layer may be formed by at least one of a high velocity oxy-fuel (HVOF) source, an electric-arc source and low pressure plasma spraying. According to one or more embodiments, the second layer, and as a result a thermal barrier coating, may be formed by at least one of air plasma spraying, suspension plasma spraying, and electronic beam physical vapor deposition.

Abstract: A vibration damper 38 for a fuel nozzle 24 having a central axis about which are disposed an inner 34 and outer 36 concentric fuel tubes. The damper includes a sleeve 40 and at least two legs 42, each leg having a radial portion extending from the sleeve and a resilient, longitudinally extending portion 46. The sleeve engages the inner tube while the longitudinally extending portions of the legs bear against the inner surface 37 of the outer tube to dampen vibrations between the concentric tubes. Besides damping objectionable vibratory forces experienced by the fuel tubes in the fuel nozzle, the present invention offers minimal fuel flow blockage in the concentric fuel tubes.

Abstract: A low NO.sub.x fuel nozzle assembly 10 includes a nozzle 24 with a tangential entry (TE) swirler 46 and centerbody element 48 each releasably mounted to an assembly support structure 26, such as to readily provide for operator access to the nozzle's major elements for the purpose of repair or replacement.

Abstract: A support structure for a low NO.sub.x industrial gas turbine engine fuel nozzle includes a pressure vessel which forms an interior cavity such that the exterior of the pressure vessel is exposed to the high pressure and temperature of the compressor outlet while the interior cavity of the pressure vessel is exposed to ambient conditions. The fuel lines to the nozzle run through the interior cavity of the pressure vessel, isolated from the high temperatures and pressures at the compressor outlet. The pressure vessel housing and the ambient air within the housing act as natural insulators which prevent the fuel lines from becoming too hot and coking. The support structure also facilitates maintenance of the combustor section of the engine since the low NO.sub.x fuel nozzle and the annular combustor assembly of the engine are easily accessible for maintenance.

Abstract: A seal support for a brush seal used between a turbine nozzle assembly and a rotor assembly includes a cover plate portion and a support arm. Various construction details are developed that provide a lightweight support for a brush seal and a windage cover. In a particular embodiment, the seal support includes a cover plate portion having circumferentially continuous surfaces to reduce windage losses and a support arm extending inward over a brush seal. In the installed condition, the seal support is positioned to engage the turbine nozzle assembly in an interference fit to dampen the seal support. In another particular embodiment, the support arm has scalloped corners that mate with corners of adjacent seal supports to define an opening. The opening is located to permit cooling fluid to flow through a metering hole and into a cavity to purge the cavity of gas path fluid.

Abstract: An improved fuel nozzle guide (100) for a gas turbine engine combustion chamber (65) includes an eccentric detent (150) which allows only a predetermined amount of limited pivotable movement of a retainer (125) and bushing (105) employed in the guide.

Abstract: When second shell section 18 diverges with respect to first shell section 16, the second liner panel 50 is located with a changing spacing from the shell. The liner is close to the shell at the upstream edge 68, and farther from the liner at the downstream end 57. The downstream end of the first liner panel 64 overlaps the second liner panel 50 on the gas side.