Abstract: The present invention is a unique splitter of a core engine compressor in a double bypass, variable cycle engine. The splitter is extended forward to a second fan section. The extended splitter may divide the rotor blades into outer and inner portions to allow the flow past these portions to act essentially aerodynamically independent of each other in a single or double bypass mode of operation of the variable cycle engine.

Abstract: A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly from at least one of the first and second airfoil sides. Adjacent ones of second ends of the first and second ribs are staggered apart longitudinally and overlap chordally for defining a gap therebetween facing transversely for turning cooling air upon flow through the gap. The gap increases convective heat transfer enhancement for reducing cooling air requirements and improving blade creep life.

Abstract: An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities.

Abstract: A turbine nozzle assembly includes an outer casing having first and second spaced apart support flanges for supporting a nozzle segment including a plurality of nozzle vanes extending between inner and outer bands. The outer band includes first and second spaced apart retention hooks, with the first hook being configured to axially engage the first support flange. And, the second support flange is sized for axially receiving the second hook without tilting of the nozzle segment. An annular retainer radially engages the second support flange and axially abuts the second hook for axially retaining the second hook. And, a clip axially engages the second hook and support flange around the retainer for radially supporting the nozzle segment to the outer casing.

Abstract: A multiple annular combustor for a gas turbine engine is disclosed having a plurality of concentrically disposed annular combustion zones about a centerline axis. The multiple annular combustor includes a first annular combustion zone, a second annular combustion zone, and a centerbody disposed between the first and second annular combustion zones. The centerbody has a first wall extending axially from an upstream end to a downstream end and a second wall radially spaced from the first wall extending axially from an upstream end to a downstream end, where the downstream ends of the first and second walls are connected by an aft wall and a pair of side walls to form a passage therebetween. The centerbody is geometrically configured to cause a thermoelastic neutral axis to be positioned radially with respect to the first and second walls thereof so that thermal stress imposed on the first and second walls is minimized.

Abstract: A turbine nozzle includes a circumferentially continuous annular outer band, and a plurality of circumferentially spaced apart vanes extending radially inwardly therefrom. A circumferentially segmented inner band is joined to the vanes and is disposed coaxially with the outer band. The inner band includes a plurality of circumferentially adjoining arcuate segments, adjacent ones of which have circumferentially facing end faces spaced apart to define a gap therebetween. In an exemplary embodiment, strip seals are inserted in corresponding slots formed in the end faces to seal leakage therebetween.

Abstract: A shroud panel for a turbine shroud includes forward and aft hooks which are used to support the panel radially above a plurality of turbine rotor blades. The panel forward hook has radially outer and inner lands, with the outer land being defined by a plurality of pads circumferentially spaced apart from each other by a respective recess. The panel forward hook is sized to engage the complementary forward slot of the turbine shroud substantially concentrically therein. The pads and recess restrict flow leakage around the panel forward hook for maintaining backflow margin and improving clearance control.

Abstract: An air fuel mixer is disclosed having a mixing duct, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited. In addition, the mixing duct of the mixer includes slots, preferably with flares associated therewith, at its downstream end which modify the shape and direction of mixing eddies emanating therefrom.

Abstract: A compressor includes an axially split casing surrounding stages of rotor blades and stator vanes. The vanes include a shroud joined to radially inner ends thereof and disposed in a cavity adjoining a rotor disk. An annular cavity seal abuts the vane shroud and adjoins the rotor disk for sealing the cavity therebetween. The seal is axially retained to the shroud in both casing halves, and is radially inwardly retained in only the casing lower half for allowing assembly and removal of the casing upper half relative to the casing lower half without radial interference between the shroud and the seal.

Abstract: A turbine frame includes annular outer and inner bands with circumferentially spaced apart struts extending therebetween. Annular outer and inner liners adjoin the outer and inner bands, and a plurality of fairings surround respective ones of the struts and are joined to the liners. A plurality of circumferentially spaced apart telescopic outer and inner joints support the liners to the bands, and allow unrestrained differential thermal radial movement therebetween.

Abstract: A reinforced rotor disk assembly includes a rotor disk having a rim, hub, and web therebetween. The web includes at least one annular extension spaced radially inwardly of the rim. A plurality of rotor blades extend outwardly from the rim. And, a reinforcing ring is disposed radially around the extension for restraining radial outward growth thereof to react centrifugal load in the disk. The reinforcing ring preferably includes a plurality of circumferentially extending structural fibers in a corresponding matrix for carrying hoop loads therein.

Abstract: A turbine nozzle includes outer and inner bands having respective mounting holes therein. A plurality of vanes extends through respective pairs of outer and inner holes in the bands. The vane outer and inner ends are resiliently supported to the bands to allow differential thermal movement therebetween so that the individual vanes float relative to the outer and inner bands to prevent thermal stress failure thereof.

Abstract: A cooling system for use in a rotor assembly of a gas turbine engine, the rotor assembly including an annular disk rotatable about a centerline axis of the engine and a plurality of blades mounted on the disk. The disk includes alternating posts and slots, with each slot receiving a blade dovetail. The cooling system comprises an axially extending plenum disposed inward of each blade dovetail and a thermal isolation chamber, formed by a seal body, disposed over the outer surface of each disk post. An annular forward blade retainer is attached to the disk and sealed with adjacent structures via inner and outer seals. Alternative structures are disclosed for diverting the cooling air from the plenums, past the inner and outer seals, and into the isolation chambers during operation of the engine so as to cool each disk point, without compromising the structural integrity of the forward blade retainer.

Abstract: A dome assembly for a multiple annular combustor is disclosed as including an annular dome plate having at least two radial domes, wherein each of the radial domes include a plurality of circumferentially spaced openings therein. A heat shield is positioned within each of the openings, with a threaded forward end located upstream of the dome plate and an aft end located downstream of the dome plate. A retainer nut with threads formed on an annular surface thereof is matingly engagable with the forward end of each heat shield. When the retainer nut is tightened onto the heat shield forward end, the heat shield is mechanically attached to the dome plate. Preferably, at least one centerbody extends axially downstream from either the radially outer or inner side of the aft end. The dome assembly includes a ferrule within each of the dome plate openings for receiving an air/fuel mixer therein, the ferrule having an annular sealing flange extending radially therefrom.

Abstract: A compressor rotor includes a rim having airfoils extending radially outwardly therefrom, and a corresponding web and hub extending radially inwardly. A row of curvic coupling teeth extends axially away from one end of the rim. An imperforate support ring extends radially inwardly from the rim end for carrying hoop loads. And, a balance ring extends radially inwardly from the support ring, and includes a balance notch circumferentially splitting the balance ring.

Abstract: A variable stator vane assembly which substantially eliminates leakage paths by utilizing a cantilevered finger spring seal and an o-ring is described. In one form, the stator vane assembly includes a spacer configured to form, with an upper, or outer, surface of the vane trunnion bushing, an annulus. The ring shaped cantilevered finger spring seal is positioned in the annulus and forms a seal between the spacer and trunnion bushing. The stator vane assembly also includes, in one form, an o-ring located at an interface between the stator case and the stator vane metal jacket.

Abstract: A turbine rotor assembly includes a rotor disk, rotor blades joined thereto, and a blade retention plate for axially retaining the blades on the disk. The disk includes an outer rim, an inner hub, and an annular web extending therebetween. An axial extension extends from the web and is spaced radially below a corner of the rim. The blades have dovetails axially disposed in respective dovetail slots in the disk rim. The retention plate includes an outer rim which abuts the disk rim and blade dovetails, an inner hub, and a web extending therebetween. The plate hub has an outer rabbet disposed in abutting contact with the rim corner, and an inner rabbet radially adjoining the axial extension for maintaining abutting contact therewith upon differential radial contraction between the retention plate and the disk which separates the outer rabbet from the rim corner.

Abstract: A fuel injector includes outer and inner coaxial shells spaced radially apart to define a flow channel therebetween having an inlet and an outlet. A strut extends radially outwardly from the inner and outer shells at leading edges thereof and is fixedly joined thereto. An annular lobed mixer is disposed coaxially in the channel and includes a leading edge, a trailing edge spaced from the channel outlet to define a mixing nozzle, and a plurality of circumferentially spaced apart lobes increasing in radial height from the leading to trailing edges of the mixer. The lobes defines with the outer and inner shells corresponding pluralities of outer and inner chutes for separately channeling respective portions of inlet air. The fuel is injected into the lobed mixer forming a fuel and air mixture in the mixing nozzle for discharge through the channel outlet into a combustor.

Abstract: An air fuel mixer having a mixing duct, a set of inner and outer counter-rotating swirlers at the upstream end of the mixing duct, and means for injecting fuel into the mixing duct is provided, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the fuel nozzle by means of a plurality of fuel spokes so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.

Abstract: A modular oil monitor for a gas turbine engine includes a mounting pad having a seat with a plurality of oil inner ports disposed therein and joined in flow communication with an oil tank and an oil sump of the engine. A module having a base is removably fixedly joined to the seat, with the base having a plurality of oil outer ports disposed therein and joined in flow communication with respective ones of the inner ports. The module also includes a filter circuit disposed in flow communication between first and second ones of the outer ports, with the filter circuit including an oil filter removably joined to the module for filtering supply oil channeled therethrough. A first sensor is removably joined to the module for measuring the oil temperature or pressure. The module provides at one location various lubricating system components which may be individually inspected or replaced. Or, the entire module may be replaced in one operation.