Abstract: A combustor for a gas turbine engine having a porous outer metallic shell and a thin-walled, nonporous ceramic liner whose backside is impingement cooled, with only primary and secondary openings in the ceramic liner for delivering pressurized primary air and dilution air to the combustion zone.

Abstract: A butterfly valve for controlling the flow of high temperature fluids includes a valve body defining a flow path and having opposed portals. Cover plates are mounted over each of the portals and have a conical shaped wall extending inward to a bearing support member. A flow modulator is disposed between the cover plates and is mounted to the bearing support members by ceramic bearings. The modulator has a plate disposed in said flow path which is bounded by a leading edge, a trailing edge, and two disk flanges. Each of the disk flanges has a labyrinth seal in sealing engagement with an inner wall of said valve body. Nozzles are mounted to said cover plate to deliver cooling air flow to the bearings. A constant cooling flow rate is maintained by appropriately sized circumferential chambers adjacent each of the labyrinth seals.

Abstract: A gas turbine engine having a compressor rotor and turbine rotor in back-to-back relation and annular groove therebetween. A nonrotating seal is disposed in the groove. A dual pilot ring is disposed at the radial inner end of the groove. The dual pilot ring includes an inner annular ring and an outer annular ring radially spaced apart to define a clearance gap. The inner ring is mounted to radially facing piloting surfaces on both the compressor and turbine rotors and maintains concentricity between the two rotors as they grow at different thermal rates. The outer annular ring transfers axial loads between the rotors.

Abstract: Disclosed is an oil film cooled face seal that is comprised of an annular stator having a flat surface in rubbing contact with the flat sealing surface of a rotor. The rotor has a flange portion extending radially from a base portion. The base portion has a plurality of holes extending radially therethrough in fluid communication with a source of cooling oil. One side of the flange portion comprises the flat sealing surface. The opposite side, or backface, has a plurality of external radially spaced apart annular grooves criss-crossing a plurality of external circumferentially spaced apart substantially radial grooves. Each of the radial grooves is aligned with and in fluid communication with a corresponding hole in the base portion, and extends fully across the backface.

Abstract: An improved oil seal is provided for sealing passage of rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a slinger rotor mounted on the shaft for rotation therewith. The slinger rotor has an inner surface with an annular cavity and axially extending lands separated from each other by axially extending slots. The cavity and slots define a low velocity zone in which oil is centrifuged out. The slots and cavity so the centrifuged oil flows away from the end wall of the bearing housing. A labyrinth, air seal is disposed between the shaft and end wall.

Abstract: A transition assembly for directing the gas flow from a combustor to an axial turbine includes a transition liner having a shroud disposed about its outer surface and abutting thereto at a plurality of points to defining a plurality of cooling air passages therebetween. The downstream end of the assembly is circumscribed by the first stage stator and extends axially to just upstream of the first stage turbine rotor. At this end a plurality of circumferentially spaced struts are mounted between the liner and the shroud to define a plurality of axially facing nozzles which are angled to impart a pre-swirl to the cooling air exiting therefrom.

Abstract: A face seal comprising an annular carbon stator having a flat sealing surface in rubbing contact with a flat sealing surface of an annular metallic rotor. The rotor has a head portion connected to a base portion by a neck portion, that is disposed on the same side of the rotor as the rotor's flat sealing surface. The neck portion has two straight radial surfaces, and is disposed on the same side of the rotor as the rotor's flat sealing surface. The formation of adverse thermal gradients within the rotor can be avoided by adjusting the axial thickness of the neck portion, thereby preventing coning of the rotor.

Abstract: A thermal barrier coating for superalloy turbine engine vanes and blades that are exposed to high temperature gas is disclosed. The coating includes a ceramic layer applied to an aluminide or MCrAlY bond coat by electron beam physical vapor deposition. The ceramic layer has a first portion having unstabilized porosity, a second portion, overlying the first portion, with stabilized porosity, and an outer portion wherein the pores are coated with a noble metal. The stabilized porosity portion along with the noble metal coating reduce the thermal conductivity of the ceramic layer. Stabilizing the porosity renders it more resistant to sintering densification at high temperatures.

Abstract: To contain high energy fragments generated by a hub burst, a compressor containment assembly in a gas turbine engine includes a diffuser housing having an arcuate portion that defines a channel which traps the high energy fragments and an axial facing U-shaped which imparts flexibility. The assembly also includes a concave back shroud having a series of grooves that create resistance for the fragments as they slide along its surface. At its radial outer end the back shroud has an annular rim that absorbs some of the energy and delays the shearing of bolts. A bumper is disposed between the back shroud and a turbine wheel to limit the deflection of the back shroud during a hub burst.

Abstract: To contain high energy fragments generated by a hub burst, a compressor containment assembly in a gas turbine engine includes a diffuser housing having an arcuate portion that defines a channel which traps the high energy fragments and an axial facing U-shaped which imparts flexibility. The assembly also includes a concave back shroud having a series of grooves that create resistance for the fragments as they slide along its surface. At its radial outer end the back shroud has an annular rim that absorbs some of the energy and delays the shearing of bolts. A bumper is disposed between the back shroud and a turbine wheel to limit the deflection of the back shroud during a hub burst.

Abstract: A self piloting balance arbor for use in the dynamic balancing of gas turbine engine components having shafts extending therefrom. The arbor includes a cylindrical sleeve for receiving the shaft, and an annular flange at one end. A conical compliant member extends axially and radially inward from the flange to an end portion having two flat surfaces perpendicular to each other. Upon the application of a load to the arbor the two flat surfaces come into contact with the component, thereby correctly positioning the arbor relative to the component.

Abstract: A gas turbine vane or blade having a novel internal structure that allows for cooling under low pressure ratios. The vane has an air inlet passage that communicates with an inner cooling cavity positioned between the air passage and the vane's trailing edge. Disposed within this cavity are deflectors, turning members, ribs, and deflecting pins arranged so as to direct the cooling air through the cavity in a manner that minimizes pressure loss. Thus maintaining the velocity and flow of the cooling air.

Abstract: To contain high energy fragments generated by a hub burst, a compressor containment assembly in a gas turbine engine includes a diffuser housing having an arch portion that defines a channel which traps the high energy fragments and an axial facing U-shaped which imparts flexibility. The assembly also includes a concave back shroud having a series of grooves that create resistance for the fragments as they slide along its surface. At its radial outer end the back shroud has an annular rim that absorbs some of the energy and delays the shearing of bolts. A bumper is disposed between the back shroud and a turbine wheel to limit the deflection of the back shroud during a hub burst.

Abstract: An apparatus for reducing ripple in the flow of a fluid through a positive displacement pump comprises an inlet tube in fluid communication with an inlet of the pump and an outlet tube in fluid communication with an outlet of the pump. A first annulus is in fluid communication with the inlet tube and a second annulus is in fluid communication with the outlet tube. A drive shaft is connected to a main drive shaft of the pump and first and second cams are connected to the drive shaft. The first cam is associated with the first annulus and the second cam is associated with the second annulus. A plurality of pins are provided and each has a portion located within one of the annuluses and an end opposite that portion in contact with the cam associated with the respective annulus.

Abstract: An underwater vehicle such as a torpedo has a jet pump propulsion system. A high speed pump is located inside a rigid cylindrical housing of the torpedo near an end thereof. A water inlet communicates with the pump as does a water outlet provided at the aft end of the rigid housing via a water passage. A high speed electrical motor, on the order of 10,000 rpm, is provided inside an inner cylindrical housing disposed within the outer cylindrical housing. The electric motor is provided aft of the pump and the electric motor shaft is directly coupled to the pump rotor. Only one bearing and one water seal is provided between the electric motor and pump rotor. A water exit passage is provided between the inner cylindrical housing containing the high speed motor and the rigid outer cylindrical housing. Water passing through the exit passage cools the electric motor by dissipating heat therefrom.

Abstract: Non-destructive evaluation of a ceramic nozzle is accomplished by generating a thermal gradient across the nozzle while it is mounted in a test rig. The thermal gradient is then measured and compared to a preselected gradient that is representative of the harshest condition to which the nozzle will be exposed during its operating life. The thermal gradient is adjusted until it approximates the preselected gradient. The nozzle is then observed for any cracks which reveal a weakness in the ceramic.

Abstract: A thermal barrier coating for superalloy turbine engine vanes and blades that are exposed to high temperature gas is disclosed. The coating includes an Aluminide or MCrAlY layer, an alumina layer, and a ceramic top layer. The ceramic layer has a columnar grain microstructure. A bond inhibitor is disposed in the gaps between the columnar grains. This inhibitor is either unstabilized zirconia, unstabilized hafnia, or a mixture thereof.

Abstract: A rotor assembly for a gas turbine engine has a disc with dovetail grooves and a plurality of blades with dovetail roots contoured to be received within the grooves. The inner surface of a flexible, high temperature, low compression set seal is bonded to the inner surface of each root portion. The outer surface of the seal has two portions inclined at an angle and spaced apart to define a surface portion for sealingly contacting the base of the groove. The longitudinal edges of the outer surface are curved to facilitate assembly.

Abstract: A face seal includes an annular carbon stator having a flat surface in rubbing contact with the flat surface of a composite annular rotor. The annular rotor has a head portion and a base portion. Embedded in the head portion are high thermal conductivity graphite fibers that are oriented to maximize heat dissipation. Incorporation of graphite fibers makes the rotor resistant to time-dependent creep deformation, thus preserving sealing integrity.

Abstract: An improved oil seal is provided for sealing passage of rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a slinger rotor mounted on the shaft for rotation therewith. The slinger rotor includes a radially outwardly extending slinger ring with radially open slinger ports formed therein, in combination with an axially projecting centrifuge sleeve defining an internal tapered centrifuge surface disposed in close running clearance with an axially projecting cylindrical wall segment on the end wall. During shaft rotation, the centrifuge surface pumps oil in a direction away from the end wall to the slinger ring for discharge through the slinger ports to the interior of the bearing housing.