Abstract: A push-lock device for connecting a tile to a gas turbine engine wall includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including portions of both a push-down pop-up mechanism and a locking-bracket mechanism, the locking-bracket mechanism moveable to a locked position such that the locking-bracket mechanism limits movement of a tile away from a gas turbine engine wall; and a biasing member to be positioned closer to the tile than the locking-bracket mechanism.

Abstract: A combustion chamber of a gas turbine, including an external combustion chamber wall as well as an internal combustion chamber wall, wherein the internal combustion chamber wall, at its frontal end area as it appears with respect to the flow direction of the combustion chamber, is supported in a longitudinally slidable manner inside a groove of a base plate that is arranged in the area of a combustion chamber head, and is fixedly attached at the external combustion chamber wall at its back end area.

Abstract: A combustor for a gas turbine including a casing, a flow sleeve at least partially disposed within the casing, a combustion liner at least partially disposed within the flow sleeve, a liner stop feature extending from the combustion liner, and a liner guide stop including a first end separated from a second end, the second end configured to be at least partially engaged with the liner stop feature, wherein the liner guide stop extends through the casing and the flow sleeve.

Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.

Abstract: An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments.

Abstract: The present invention relates to a gas-turbine combustion chamber with mixing air orifices, with a combustion chamber wall, with tiles arranged on the inside of the combustion chamber wall at a certain distance from said combustion chamber wall as well as with mixing air orifices passing through the combustion chamber wall and the tiles, characterized in that the mixing air orifices are formed by chutes which are designed tube-like and pass through the tiles, and that several chutes are formed on a mixing air wall element extending at least around part of the circumference of the combustion chamber.

Abstract: A turbomachine is provided and includes a combustor in which fuel and air are combusted, a turbine disposed for reception of products of combustion from the combustor, a transition piece fluidly interposed between the combustor and the turbine and including a body formed to define dilution holes configured to allow air to enter the combustor and for enabling steam injection toward a main flow of the products of the combustion proceeding from the combustor to the turbine and a fuel injection system supportively coupled to the transition piece and configured to inject fuel toward the main flow of the products of the combustion to thereby restore a flame temperature of the main flow of the products of the combustion reduced by steam injection enabled by the dilution holes.

Abstract: An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.

Abstract: A heat shield for a combustor liner includes first linear film cooling slots through the heat shield and second linear film cooling slots through the heat shield. The first linear film cooling slots are run in a row and each of the first linear film cooling slots is angled from the row in a first direction. The second linear film cooling slots also run in the row and each of the second linear film cooling slots is angled from the row in a second direction opposite the first direction. The second linear film cooling slots alternate with the first linear film cooling slots in the row. The first and second linear film cooling slots are connected to form a single, multi-cornered film cooling slot.

Abstract: Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NOx emissions of gas turbine combustors. The gas turbine combustion burner includes a plurality of swirling vanes (20) for ejecting fuel from fuel ejection holes (23, 24) into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow and a nozzle (21) having the swirling vanes (20) arranged radially on an outer circumferential surface thereof and having a first fuel passage (26), through which the fuel is guided to the fuel ejection holes (23, 24), provided therein, a cavity (25) communicating with the fuel ejection holes (23, 24) is provided in each swirling vane (20), and at least two second fuel passages (27) are provided between the cavity (25) and the first fuel passage (26) along an axial direction.

Abstract: A combustor component of a gas turbine engine includes a substrate with a cold side, a central core section and a hot side, the cold side and the hot side have a porosity different than the central core section.

Abstract: A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure.

Abstract: A gas turbine combustor including a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions which are corner portions of the transition piece flow sleeve in a sectional direction thereof.

Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.

Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.

Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.

Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.

Abstract: A combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture.

Abstract: A highly durable, high-strength thermal shield element is provided for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal shield element comprises a base produced from a solidified cast ceramic material into which a plurality of reinforcing elements are integrated, to increase the tensile strength of the thermal shield element.

Abstract: A gas turbine combustor comprising a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions which are corner portions of the transition piece flow sleeve in a sectional direction thereof.

Abstract: An annular combustor includes an annular outer shell that includes a first flange that defines an inner diameter IDOS and an annular inner shell that includes a second flange that defines an outer diameter ODIS. An annular hood includes a radially outer hood flange and a radially inner hood flange. A bulkhead includes a radially outer bulkhead flange that defines an outer diameter ODB and a radially inner bulkhead flange that defines an inner diameter IDB. The first flange is secured at a radially outer joint between the radially outer hood flange and the radially outer bulkhead flange. The second flange is secured at a radially inner joint between the radially inner hood flange and the radially inner bulkhead flange. The IDOS and the ODB define a ratio R1 of IDOS/ODB that is 0.998622-1.001129, and the IDB and the ODIS define a ratio R2 of IDB/ODIS that is 0.998812-1.001388.

Abstract: A tile is provided for lining the hot side of a wall of a combustor. The tile has a tile body with one or more bosses protruding from the cold side thereof. The or each boss extends, in use, through the wall of the combustor and has a threaded recess formed therein for threadingly connecting with a bolt which is inserted into the recess from the cold side of the combustor wall. The bolt fastens the tile to the combustor wall.

Abstract: Floatwall panel assemblies and related systems are provided. A floatwall panel assembly includes a panel formed of porous ceramic material, the porous ceramic material exhibiting a porosity gradient along at least one of a length, a width and a depth of the panel, the panel lacking a substrate, formed of a material other than porous ceramic material, for supporting the porous ceramic material.

Abstract: A heat shield element arrangement including a heat shield element for a heat shield arranged on a supporting structure is provided. On each of the two opposing sides running parallel to the installation grooves the heat shield element includes a continuous screw head opening which penetrates the cold side and the hot side of the heat shield element substantially vertically and through which the screw head of the respective screw is arranged to be accessible to the supporting structure, and a spring element may be arranged under the respective screw, which spring element may be extended along the hot side of the heat shield element and the parallel installation groove of the supporting structure. An outer end of the spring element is embodied as a clamping retaining hook which is provided for the purpose of engaging in the laterally recessed retaining groove of the heat shield element.

Abstract: A process for producing refractory ceramics (K) for use as heat shield in the hot gas path of gas turbine plants: introducing a casting composition into a component casing mold for the refractory ceramic (K), closing the casting mold so that the casting composition is under a defined static pressure after closure; orienting vibration of the casting mold in the direction (V) of a normal (N) to a surface of the refractory ceramic (K) to be produced, and subsequently removing the casting from the mold and firing the cast component.

Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.

Abstract: A first member is retained to a second member to resist separation in a first direction. A joint comprises a first recess in the first member. The first member comprises at least a ceramic matrix composite (CMC) substrate. The joint comprises at least one ceramic key partially accommodated in the first recess and engaging the second member. The second member comprises at least a metallic substrate.

Abstract: The present invention relates to a tile fastening arrangement of a gas-turbine combustion chamber having a combustion chamber wall with tiles fastened to said combustion chamber wall at a distance from the latter, characterized in that the tile is provided with an annular flange arranged on its side assigned to the combustion chamber wall, said flange being dimensioned to match a recess of the combustion chamber wall and fastened to the combustion chamber wall by means of a fastening element which engages in the combustion chamber wall.

Abstract: A gas turbine includes a liner, a casing surrounding the liner, a hula seal flexibly connected to an aft end of the liner and a liner aft support mechanism. The liner is configured to receive compressed gas and fuel at an upstream end, the mixture of the compressed gas and the fuel being burned in a combustion core area of the liner to yield hot exhaust gasses. The liner aft end support mechanism is located downstream from an area where a highest temperature on an outer surface of the liner is attained, and upstream to a portion where the hula seal is connected to the liner, and is configured to movably support the liner inside the casing. The liner aft end support mechanism includes at least three individual support elements configured to allow a part of the individual support elements to move in the flow direction relative to at least one of the liner or the casing.

Abstract: A push-lock pin for connecting a plate to surface includes a cylindrical pin housing and a shaft within the housing. The shaft has a ball-lock mechanism and a push-down pop-up mechanism.

Abstract: An annular seal for use between coupled combustor components includes a segmented annular solid edge portion and a plurality of alternating spring fingers and slots extending from the solid edge portion and arranged about a circumference of the solid edge portion, wherein one or more of the plurality of spring fingers or one or more of the plurality of straight and angled slots have non-uniform width dimensions.

Abstract: Gas-turbine combustion chamber with a combustion chamber head made from a metallic material and mounting at least one burner, and with a combustion chamber wall made from a ceramic material, where at least one igniter plug or other combustion chamber attachment is arranged in a recess of the combustion chamber wall, and where in the area of the recess a seal is arranged that is mounted by a metallic holding mechanism from another component than the combustion chamber wall.

Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

Abstract: A coating material suitable for use in high temperature environments and capable of providing a damping effect to a component subjected to vibration-induced stresses. The coating material defines a damping coating layer of a coating system that lies on and contacts a substrate of a component and defines an outermost surface of the component. The coating system includes at least a second coating layer contacted by the damping coating layer. The damping coating layer contains a ferroelastic ceramic composition having a tetragonality ratio, c/a, of greater than 1 to 1.02, where “c” is a c axis of a unit cell of the ferroelastic ceramic composition and “a” is either of two orthogonal axes, a and b, of the ferroelastic ceramic composition.

Abstract: A turbomachine including an annular combustion chamber, a sectorized turbine nozzle arranged at an outlet from the chamber, and a sealing mechanism interposed axially between the chamber and the nozzle, the sealing mechanism including an annular gasket that is axially resilient. The gasket includes a first axial bearing mechanism for bearing against a downstream end of the chamber and a downstream annular lip that is sectorized, each sector of the downstream lip being in alignment with a sector of the nozzle and including a second axial bearing mechanism for bearing against an upstream end of the nozzle sector.

Abstract: A coated turbine engine article having a first wall and a second wall, wherein the first wall has a shielding feature integral with the article and which inhibits entry of a coating material into an open passage extending between the first wall and the second wall when the coating material is directed towards the article using a line of sight process.

Abstract: A combustor liner is provided. The combustor liner may include an upstream portion and a downstream end portion. The upstream portion may have a radius and a length along a generally longitudinal axis. The downstream end portion may have a radius and a length along the generally longitudinal axis. The downstream end portion may define a plurality of channels. Each of the plurality of channels may extend helically through the length of the downstream end portion. Each of the plurality of channels may be configured to flow an air flow therethrough, cooling the downstream end portion.

Abstract: A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.

Abstract: There is described a heat shield element comprising a hot side which is turned towards the hot medium, a cold side which is turned away from the hot medium, peripheral sides which connect the hot side to the cold side and a material volume which is defined by the hot side, the cold side and the peripheral sides, wherein the material volume comprises at least two material areas which are made of different materials. The materials are different from each other at least in respect of their resistance and/or thermal expansion coefficient.

Abstract: A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion and a support that receives the cooled ceramic portion.

Abstract: An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection system. Heat protection deflectors are fastened to the chamber end wall. Holes are formed through the chamber end wall to pass cooling air onto an upstream face of each deflector. The inner or outer edge of a deflector presents a sealing rim engaging the respective inner or outer wall of the chamber.

Abstract: A system of integrating baffles for enhanced cooling of CMC liners is comprised of a combustor assembly having a dome mount assembly, outer liner and inner liner. Liners include those manufactured from and in a process for CMC (Ceramic Matrix Composite). One or more liner baffles such as outer baffle and inner baffle, are provided to reduce the pressure drop across the liner, allowing the addition of more cooling holes and thereby reducing the cooling hole spacing while not increasing the required amount of cooling air. CMC liners are incorporated, as desired, to take advantage of shapes and hole dispositions made possible by use of CMC over past designs.

Abstract: The present invention relates to combustors, and provides a combustion liner that may at least partially contain a combustion process. The combustion liner may include a support structure that supports a plurality of panels. The panels may be in the form of thermal barrier panels, e.g., that are attached to the support structure and/or other parts of the machine.

Abstract: A turbine system is disclosed. The turbine system includes a transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.

Abstract: A fluidized bed boiler plant and a method of combusting sulfurous fuel in the fluidized bed boiler plant, a furnace of which plant is provided with a fluidized bed of particles. Sulfurous fuel, CaCO3-containing sulphur-binding agent and combusting air are introduced to the bed of particles, whereby fuel burns and generates flue gases and the sulphur-binding agent calcinates to CaO and binds SO2 generated in the combustion. Energy is recovered to a heat exchange medium circulating in heat exchange tubes of a condensing heat exchanger arranged in a flue gas channel, and a water solution of acid condensing on outer surfaces is neutralized by mixing it in a mixing vessel to a CaO-containing ash from a plant, preferably, fly ash collected by a dust separator.

Abstract: A system comprises a plurality of components disposed to define a gas path. At least one component comprises a silicon-bearing substrate over which is disposed a coating, and the coating comprises a recession-resistant material exposed to the gas path. A silicon source is disposed in fluid communication with the gas path and is configured to be delivered to the gas path to maintain, in gas flowing in the gas path over the coating, a silicon mass concentration in the range from about 1.

Abstract: A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert adjacent to the support shell and the heat shield panel.

Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing in which a corner is formed between an aft portion of the housing and a bulkhead wall in which a corner recirculation zone is located to stabilize and anchor the flame of the pilot mixer. The pilot mixer can further include features to cool the annular housing, including in the area of the corner recirculation zone.

Abstract: A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.

Abstract: A wall element for a combustion space, the wall element comprising a ceramic body, a support within the body, and attachment means extending from the support and protruding from the body for securing the ceramic body to a combustion space wall.