Abstract: In one exemplary embodiment, the present invention is directed to a method that comprises providing a reaction substrate having a plurality of substrate reservoirs adapted to receive a reactant system at least partially embodied in a liquid. A thermal unit maintains the reactant system at a first temperature. A head plate is disposed adjacent to the reaction substrate to form a sealed and pressurized headspace above the substrate reservoirs. The head plate is maintained at a second temperature higher than the first temperature. A second reactant may be introduced as a gas into the headspace above the plurality of substrate reservoirs.

Abstract: A coated article is prepared by furnishing an article substrate having a free sulfur content of less than about 1 part per million. The low-sulfur article may be made of a material selected to have a low sulfur content, provided with a scavenging element that reacts with free sulfur to produce a sulfur compound, or desulfurized by contact with a reducing gas such as hydrogen. A platinum-group metal layer is deposited over the article substrate, and a ceramic coating is applied over the platinum-group metal layer.

Abstract: A combustor for a gas turbine engine having a longitudinal axis therethrough, including an outer liner having a forward end and an aft end, an inner liner having a forward end and an aft end, a first dome formed upstream of the outer liner forward end so as to define a first combustion zone radially oriented to the longitudinal axis, and a dome plate having an outer portion connected to an upstream end of the first dome and an inner portion connected to the inner liner forward end, wherein a second combustion zone is defined by the dome plate, the outer liner, and the inner liner substantially perpendicular to the first combustion zone.

Abstract: A mixer for use in a combustion chamber of a gas turbine engine. The mixer includes an annular housing having an upstream end, a downstream end, a mount for attaching the housing to an upstream end of the combustion chamber, and an interior surface defining a hollow interior. The mixer also has a first swirler mounted inside the annular housing including a plurality of vanes extending inward from the housing for swirling air traveling through the housing. In addition, the mixer includes an annular fuel injector having a plurality of fuel injection ports arranged in a generally circular pattern mounted inside the first swirler for releasing droplets of fuel into swirling air downstream from the fuel injector. Further, the mixer has a second swirler mounted inside the fuel injector including a plurality of vanes extending inward from the injector for swirling air traveling through the housing downstream from the fuel injector.

Abstract: A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube sub-system includes a plurality of shock tubes which mix air and fuel introduced to the pulse detonation augmentor and detonate the mixture. The detonation creates hot combustion gases which are directed from the engine to produce thrust for the engine. Alternatively, the system includes a pulse detonation augmentation system that replaces a core engine of a turbo-fan engine.

Abstract: A method of fabricating an annular liner for a combustion chamber of a gas turbine engine. The combustion chamber has a dome including a fuel nozzle for delivering fuel to the combustion chamber. A metal piece is formed into an annular section constituting at least a portion of the liner and having at least one seam extending generally axially with respect to an axial centerline of the liner. An upstream end of the liner is machined to have a registration feature for connecting the liner to the combustion chamber dome in at least one predetermined orientation with respect to the dome. Further, the method includes ensuring the registration feature and the seam are located relative to each other on the liner so the seam is at a preselected position with respect to the combustion chamber dome when the liner is connected to the combustion chamber dome in the predetermined orientation.

Abstract: A gas turbine engine nozzle includes outer and inner bands. Each of the bands includes segments circumferentially adjoining at corresponding splits. The splits of the inner band are circumferentially spaced from the splits of the outer band. A plurality of vanes are fixedly joined to the outer and inner segments which collectively define an accordion loadpath therethrough.

Abstract: An airfoil for use in a gas turbine engine includes a pressure side and a suction side joined at a trailing edge wall that defines a trailing edge. The airfoil includes at least one cooling hole extending through the trailing edge wall so as to pass cooling fluid from the pressure side of the airfoil to the suction side.

Abstract: Apparatus and method to facilitate vapor phase coating of turbine airfoils. A dovetail receptacle receives the dovetails of a plurality of airfoils. The airfoils are separated by spacers with the airfoil dovetails sealed in a chamber of the receptacle to facilitate vapor phase coating of airfoil flowpath surfaces and platform upper surfaces of several airfoils simultaneously while masking the dovetail sections.

Abstract: A gas turbine engine includes a combustor system to reduce an amount of nitrogen oxide emissions formed by the gas turbine engine. The combustor system includes a combustor including a first annular dome. A centerbody is secured within the dome and includes at least one orifice for supplying fuel to the dome. An inner swirler is attached to the centerbody and an outer swirler is attached radially outward from the inner swirler such that a leading edge of the inner swirler and a leading edge of the centerbody are disposed upstream from a leading edge of the outer swirler.

Abstract: A coupling assembly includes a first coupling member, a second coupling member, and a coupling nut disposed over a portion of the second coupling member and threadingly engaging the first coupling member to retain the first and second coupling members together. An insulation blanket encloses the coupling nut, and a retention strip having a first end attached to an inner surface of the insulation blanket and a second end attached to the coupling nut is provided to prevent loosening of the coupling nut.

Abstract: Disengagement of C-clips in turbine shroud assemblies is prevented by providing each C-clip with at least one anti-rocking pad. The anti-rocking pad is disposed on a radially inner surface of the C-clip so as to make snug contact with a portion of the shroud adjacent to the C-clip. The snug contact limits rocking motion of the C-clip, thereby preventing C-clip disengagernent.

Abstract: A method of adjusting airflow through a plurality of cooling holes by depositing a thermal barrier coating on an exterior surface and/or an interior surface of the component by a physical vapor deposition process. The cooling holes are not masked. Thus, a portion of the thermal barrier coating partially obstructs airflow through the cooling holes and reduces airflow through the cooling holes. A predetermined pressure drop is developed across the cooling holes and airflow through the cooling holes is measured. The measured airflow is compared to a preselected range of desired cooling hole airflows and the steps of depositing the thermal barrier coating, developing the predetermined pressure drop, calculating airflow and comparing the measured airflow to the preselected range are repeated until the measured airflow is within the preselected range of desired cooling hole airflows.

Abstract: A turbine airfoil includes at least one spar arrangement having a length less than an associated turbine airfoil length. During operation, the turbine airfoil has an outer skin surface which operates at a substantially higher temperature than that of an internal supporting parted spar arrangement. The parted spar arrangement permits the turbine airfoil outer skin surface to thermally expand between spar arrangements, thus preventing self-constraining thermal stresses from forming within the spar arrangement or the airfoil skin surfaces.

Abstract: A combustor liner has a stepped combustor liner surface and an overhang portion forming an air cooling slot. A contoured rear facing edge of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions increase engine performance and extend a working life of the combustor assembly.

Abstract: A nickel-base superalloy substrate has an overlying protective coating including a modified aluminum-containing protective layer. The modified aluminum-containing protective layer is formed of nickel, aluminum, calcium in an amount of from about 50 to about 300 parts per million by weight, and, optionally, elements interdiffused into the modified aluminum-containing protective layer from the substrate. Magnesium or barium may be used instead of or in addition to the calcium. A ceramic layer may overlie the modified aluminum-containing protective layer.

Abstract: An impingement baffle for a turbine nozzle vane includes a perforate sleeve for discharging impingement air therethrough. A cap closes the sleeve at a top end, and includes an inlet hole. A spoolie cup includes a flange at the bottom thereof which is disposed atop the cap around the inlet hole for channeling air therein. A retainer is joined to the cap to loosely trap the cup flange thereatop for permitting limited lateral sliding movement thereof.

Abstract: A method for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine by channeling a substrate to provide cooling channels through the substrate having a diameter of about 0.005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source through the cooling channels. A bond coat of about 0.0005″ to about 0.005″ in thickness is applied to the substrate such that the bond coat partially fills the cooling channels. A porous TBC of at least about 0.003″ to about 0.01″ thick is applied over the bond coat, such that the TBC completely fills the cooling channels. Cooling fluid from a cooling fluid source is passed through the cooling channels and porous TBC. Because the channel exit is filled with TBC, the cooling fluid is transmitted through the porous passageways of the TBC. The porous passageways provide a plurality of tortuous routes to the TBC surface.

Abstract: A coated article is provided with a coating stabilizing portion in a coating combination on a substrate of the article. The coating combination includes a coating diffusion portion on the substrate and an outer coating portion outwardly from the coating diffusion portion. The coating stabilizing portion is provided between the coating diffusion portion and the outer coating portion to inhibit diffusion of undesirable elements to an interface with the outer coating portion and to enhance mechanical properties.

Abstract: A fan outlet guide vane includes integral outer and inner platforms conforming to arcuate sides thereof, and multiple mounting bosses on the platforms. The platform sides are arcuate to conform with the vane sides for improving aerodynamic efficiency. The multiple mounting bosses improve mounting of the vanes to corresponding supporting rings.