Abstract: A seating spring is provided for a gas turbine engine compressor stator having a casing with a circumferential casing slot for mounting a plurality of vane sectors at outer bands thereof. The seating spring has at least one reaction tab configured to abut the casing at one side of the casing slot and a spring arm connected to the reaction tab and configured to abut a respective one of the outer bands to bias the outer band against the casing at a second side of the casing slot. A retention arm is connected to the reaction tab and engages the casing so as to be prevented from moving radially outward. The spring arm is thereby retained in contact with the outer band.

Abstract: An exemplary embodiment of the invention is an engine diagnostic system including a plurality of sensors. One of the plurality of sensors includes a speed sensor generating a speed value indicative of aircraft speed. A processor is coupled to the sensors and stores prior mission data and current mission data in a data memory when the speed value is within a predetermined velocity range. A fault indicator is provided which is visible from the exterior of the aircraft. The processor detects a presence or absence of a fault in response to the prior mission data and current mission data and activates the fault indicator in response to the presence of a fault. Another exemplary embodiment of the invention is a method for detecting faults in an aircraft. The method includes determining when aircraft speed is within a predetermined velocity range and obtaining current mission data in response to the aircraft speed being within the velocity range.

Abstract: A coolable gas turbine engine airfoil for a gas turbine engine suitable for a blade or vane includes an outer airfoil wall with pressure and suction sides extending chordwise between leading and trailing edges of the airfoil, a leading edge cooling plenum formed between a forward most span rib and the outer wall along the leading edge of the airfoil, and a cooling air channel within the airfoil bounded in part by the forward most rib. A slotted cooling air impingement element is disposed in the span rib for impinging cooling air from the channel on an interior surface of the outer airfoil wall along the leading edge of the airfoil. One embodiment of the slotted cooling air impingement element is a single longitudinally extending slot extending along almost an entire length of the forward most rib and the longitudinally slot preferably includes longitudinally spaced apart rounded ends.

Abstract: Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.

Abstract: A turbine airfoil includes a leading edge, a trailing edge, and a root and tip spaced apart along a span axis. First and second airfoil sides extend therebetween. A cooling circuit is disposed between the sides for channeling a cooling fluid. A plurality of diffusion fan holes are spaced apart along the span axis in the airfoil first side, with each fan hole increasing in flow area between an inlet at the cooling circuit and an outlet on the airfoil first side disposed coaxially about a centerline fan axis. The fan axis is inclined at an acute span angle, with the outlet being greater in span height than the inlet, and substantially equal in width for increasing coverage of the outlets and film cooling air therefrom along the span axis.

Abstract: A liner for a gas turbine engine combustor, including an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget joining the upstream and downstream liner sections for providing mechanical stiffness at a junction of the upstream and downstream liner sections. The cooling nugget further includes a first portion connected to the upstream liner section, a second portion connected to the downstream liner section, and a third portion joining the first and second cooling nugget portions at a first end, the third cooling nugget portion extending radially from the first end, wherein the cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section.

Abstract: A combustor includes outer and inner liners joined at one end to an annular dome. A swirl cup is mounted to the dome and includes a flare cone extending therethrough. The flare cone has an obtuse flare angle for discharging fuel in a wide spray from an outlet of the cone. A flared beat shield surrounds the cone, and extends in part aft from the cone outlet, and is offset in part forwardly from the cone outlet to define a radially outwardly facing step.

Abstract: An air-cooled airfoil whose surfaces adjacent its trailing edge are not equally cooled in order to compensate for unequal heating of the pressure and suction walls near the trailing edge. The airfoil is formed to have a cooling passage defined by and between the pressure and suction walls at the airfoil trailing edge. The interior surface of the suction wall is formed to be substantially smooth and uninterrupted, while the interior surface of the pressure wall is formed to include surface features that project into the cooling passage to cause preferential convective cooling of the pressure wall as compared to the suction wall when air flows through the cooling passage.

Abstract: An article having a design external aerodynamic shape includes a body with a body external surface and an outer portion external surface of an outer portion bonded with a part of but less than substantially all of the body surface. The external surfaces of the body and outer portion each define less than the design external aerodynamic shape. However, together they define such shape. The article is made by selecting the design external aerodynamic shape from an existing article having a first body and a first outer portion. A replacement outer portion is selected in an amount less than the first outer portion and bonded with a region less than substantially all of a replacement body external surface. The replacement body has a replacement body external surface and replacement body external shape different from the first body substantially by that amount. The replacement body is made with the replacement body external shape.

Abstract: A turbine nozzle vane includes pressure and suction sidewalls extending between leading and trailing edges. The vane includes a pair of integral ribs defining three internal cooling channels between the leading and trailing edges. Rows of film cooling holes extend through the sidewalls, and three rows in the pressure side are inclined along the span of the airfoil at different slopes.

Abstract: A combustor liner for use in a gas turbine engine includes a first annular panel section having a first cooling nugget formed at one end thereof and a second annular panel section having a second cooling nugget formed at one end thereof. A first row of cooling holes is formed in the first cooling nugget, and a second row of cooling holes is formed in the second cooling nugget. The second row of cooling holes is arranged in a preferential cooling pattern including a plurality of arrays, each array has a first set of cooling holes having a first diameter and a second set of cooling holes having a second diameter that is smaller than the first diameter. The cooling hole arrays are preferably arranged to minimize tooling set-ups and thereby reduce cost. At least one igniter tower is formed in the first annular panel section and is circumferentially aligned with one of the second sets of cooling holes.

Abstract: A combustor liner includes a row of primary dilution holes disposed aft of a forward end thereof, and a row of secondary dilution holes disposed between the primary holes and an aft end of the liner. The secondary holes vary in size circumferentially to a maximum size offset circumferentially from the primary holes.

Abstract: An exhaust nozzle includes cascade vanes mounted in a duct for discharging exhaust. The vanes have a dolphin profile which is effective for turning subsonically the exhaust near leading edges of the vanes, and then diffusing supersonically the exhaust downstream therefrom. Thrust efficiency of the vanes is therefore shifted to lower pressure ratios during operation for improving performance of the nozzle.

Abstract: A stator coil winding arrangement comprises an inner layer and an outer layer, which define the two layers of the coil. A first turn of the inner layer is positioned directly over the outer layer. All subsequent turns of the inner layer return to the inner layer to be positioned over the inner layer. With this winding arrangement, total losses in the stator coil are reduced by approximately a factor of two.

Abstract: An infrared suppressor system for a gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine. The system features a unique arrangement of multiple baffles that are connected together as a single baffle module. The baffle arrangement permits mixing of hot and cool gas flows while eliminating line-of-sight infrared radiation in an axially compact suppressor. The baffles are additionally linked together into a single insertable baffle module that permits removal of the baffle module when infrared suppression is unnecessary.

Abstract: A gas turbine engine turbine blade shrouded tip has an airfoil tip with a cross-sectional airfoil shape, a blade tip shroud attached to the tip, and a shroud cooling circuit disposed within the blade tip shroud. The shroud cooling circuit is operable for cooling substantially all of the shroud and is in fluid communication with a hollow interior of the tip. One embodiment of the invention includes two circumferentially extending forward and aft seal teeth on a radially outer shroud surface of the shroud extending in a radial direction away from the hollow interior of the tip. The shroud cooling circuit includes circumferentially extending shroud cooling passages between clockwise and counter-clockwise shroud side edges of the shroud. Forward and aft pluralities of the shroud cooling passages within the tip shroud are in fluid communication with first and second cavities respectively in the hollow interior.

Abstract: A brush seal for sealing a leakage path located between a rotating member and a stationary member includes an intermediate plate attached to the stationary member and having at least one purge hole formed therein. The brush seal also includes a first end plate attached to the stationary member on one side of the intermediate plate and a second end plate attached to the stationary member on the other side of the intermediate plate. A first bristle pack is disposed between the first end plate and the intermediate plate, and a second bristle pack is disposed between the second end plate and the intermediate plate.

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 turbine airfoil includes pressure and suction sides extending between leading and trailing edges and defining an internal cooling air passage. A row of trailing edge holes is disposed in flow communication with the air passage behind the trailing edge. The airfoil is sized in conjunction with an adjacent airfoil for accelerating combustion gases along the pressure side at the trailing edge holes to a velocity at least as high as the velocity of the cooling air discharged from the holes.

Abstract: An impingement baffle in the form of a plate includes spaced apart impingement holes for directing cooling air in corresponding jets against a hot wall. Dimples are integrally formed in the plate adjacent corresponding ones of the impingement holes for shielding thereof.