Abstract: An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction.

Abstract: A turbine nozzle baffle includes a plurality of apertures inclined through a shell for discharging a coolant tangentially therefrom. The baffle is disposed inside a nozzle vane and the tangentially discharged coolant flows generally parallel along the inner surface of the vane for convection cooling thereof.

Abstract: A gas turbine engine outlet guide vane assembly has annular inner and outer end walls, a flowpath between the inner and outer end walls, outlet guide vanes radially disposed between the inner and outer end walls, and boundary layer energizing means for energizing boundary layers using secondary flow to mix free stream flow into the boundary layers along the inner and outer end walls and suction and pressure sides of the vanes. The boundary layer energizing means includes having the vanes circumferentially leaned in a direction that the suction sides face. The boundary layer energizing means also includes swept leading and/or trailing edges of the vanes that extend radially between the inner and outer end walls. The swept leading and/or trailing edges may be curved inwardly into the vanes from the outer end walls to leading and/or trailing edge points respectively between the end walls.

Abstract: A gas turbine frame has inner and outer annular bands, respectively, joined together by generally radially extending struts therebetween. A radially outer conical support arm extends radially outwardly from the outer band and a radially inner conical support arm extends radially inwardly from the inner band. Circumferentially spaced apart inner and outer openings are disposed in the inner and outer conical support arms, respectively. Each of the struts has at least one radially extending hollow passage which extends through the inner and outer bands. The frame is a single piece integral casting. The inner and outer conical support arms have an equal number of the inner and outer circumferentially spaced apart openings. The inner circumferentially spaced apart openings are equi-angularly spaced apart and the outer circumferentially spaced apart openings are equi-angularly spaced apart.

Abstract: An engine tracking filter system that obtains information from two or more operating conditions to estimate health parameters P, performance parameters Yp, and sensor estimates Ys, is described. Such multipoint estimation of engine health enables estimation of all engine health parameters rather than only a few engine health parameters for use in engine component diagnostics, trending, and fault detection and isolation. In addition, such estimation is believed to provide improved estimates of sensed parameters for use in sensor redundancy management and sensor elimination, and also is believed to provide improved estimates of performance parameters for use in model based control to reduce required temperature, stall, and other margins.

Abstract: Brush seal lifetime and sealing efficiency are increased by providing a brush seal with a holder and a carrier moveably suspended from the holder by a plurality of flexible support wires. A plurality of bristles is secured to the carrier. Preferably, the holder is attached to a stationary member, and the bristles sealingly engage a rotating member.

Abstract: A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.

Abstract: Drainage is enhanced in an orifice formed inside the internal passage of a pneumatic line by providing the orifice with first and second portions. The first portion defines a diameter that is smaller than the diameter of the internal passage, and the second portion defines a progressively increasing diameter. Generally, a first end of the second portion has a diameter that is equal to the first portion diameter, and a second end of the second portion has a diameter that is equal to the internal passage diameter.

Abstract: A nozzle lock for circumferentially securing a nozzle segment relative to the engine casing of a gas turbine engine. The nozzle lock includes a thickener pad joined to an outer surface of the engine casing and a locking member disposed in a notch located in the outer band of the nozzle segment. A pin formed on the locking member is press-fit into the casing and the thickener pad.

Abstract: An exhaust nozzle includes an annular exhaust duct for discharging exhaust from an aft end thereof. Circumferentially adjoining chevrons extend from the duct aft end around only an arcuate portion thereof leaving a plain arcuate shelf between terminal ones of the chevrons. Each of the chevrons has a triangular configuration and a compound arcuate contour both circumferentially and axially.

Abstract: A method is provided for making, from a plurality of members brazed together, an article including an environmental resistant surface coating and a wear resistant surface portion. Prior to brazing, the members are assembled with at least one preform including the wear resistant material in a matrix including a first brazing alloy having a brazing temperature in a brazing temperature range. The assembly of members includes a second brazing alloy having a brazing temperature in the brazing temperature range. The assembly of members and wear resistant preform is heated in the brazing temperature range to provide a brazed article preform. Then the article preform is machined to a selected geometry and can be coated with the environmental coating.

Abstract: A rotor assembly for a gas turbine engine operates with reduced circumferential rim stress. The rotor assembly includes a rotor including a plurality of rotor blades and a radially outer platform. The rotor blades extend radially outward from the platform. A root fillet extends circumferentially around each blade between the blades and platforms. The platforms include an outer surface including a plurality of indentations extending between adjacent rotor blades. Each indentation extends from a leading edge of the platform to a trailing edge of the platform with a depth that tapers to an approximate zero depth at the trailing edge.

Abstract: A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart dovetail slots are disposed through the rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of the rim, and extending radially inwardly from a disk outer surface of the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. In the exemplary embodiment of the disk illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang is located radially outwardly on each of the disk posts and a chamfer is on a radially outer corner of the each of the disk posts on a portion of the overhangs.

Abstract: A heat shield for a gas turbine engine hub which facilitates reducing thermal stress in an exhaust frame of a gas turbine engine. The exhaust frame includes the hub mounted within the engine with a plurality of supports. The supports extend radially outward from the hub through a primary flow cavity and facilitate flow to a secondary flow cavity. The heat shield defines the secondary flow cavity such that the secondary flow cavity is radially inward and axially adjacent the hub. The heat shield includes a plurality of thermal stress relieving corrugations.

Abstract: A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.

Abstract: An electrical connector including a wire clamp that restricts wire movement within an electrical connector assembly to facilitate reducing wire chafing and arcing is described. The electrical connector assembly couples to at least one wire and also includes a backshell. The wire extends from an overbraid through the connector assembly to electrical pins. The backshell includes an overbraid clamping portion that includes exterior and interior surfaces, and an opening extending therebetween. The wire clamp includes two body portions that define at least one opening sized to receive the wire. A plurality of ribs extend into each wire clamp opening.

Abstract: A rotor assembly for a gas turbine engine includes a bearing assembly that reduces dynamic loads to a support frame and static bending to the rotor assembly during periods of rotor unbalance. The rotor assembly includes a rotor shaft coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race, a rolling element, and a mounting race. The mounting race includes a spherical face and is secured to the bearing assembly with a retainer that plastically fails at a pre-determined moment load.

Abstract: A fuel system for a gas turbine engine having a fuel conduit carried within an outer containment member for receiving and containing leakage from the fluid conduit. The fuel conduit includes an end that carries an elongated ferrule that has a first, enlarged head end to receive a connecting nut and a second end for receiving an end of the fuel conduit and for spacing the end of the fuel conduit from the head end of the ferrule. The ferrule has a body portion intermediate the first and second ends that has a tapered outer surface so that the body portion has thicker side wall adjacent the head end than that adjacent the second end.

Abstract: The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust performance measured at manufacture or overhaul. In one embodiment, the invention provides an analog speed signal to flight control apparatus. The invention may also be configured to provide a digital speed signal to engine power management control apparatus.

Abstract: A gas turbine engine blade spacer has an axially extending backbone, spaced apart forward, mid and aft dovetail lands, respectively, disposed along the backbone, the backbone and the forward, mid, and aft dovetail lands having bottom curved backbone surfaces. Each of the forward, mid and aft dovetail lands has a riser that extends above the backbone and has a riser flat top. In the exemplary embodiment disclosed herein, a spacer tab extends generally axially forward of the forward land and includes intersecting axially and radially extending tab apertures. A void extends around the backbone and between the forward and aft dovetail lands and the void is filled with an elastomeric material. The spacer has a constant shape and size cross-section between the forward and aft dovetail lands.