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| Number | Title | Issue Date |
| 5413871 | Thermal barrier coating system for titanium aluminides An article of manufacture has as its basic structure a piece of a titanium aluminide, such as gamma (TiAl) or alpha-2 (Ti3Al), desirably in the shape of an aircraft gas turbine component. A thermal barrier coating system overlies at least a portion of the... | 05/09/1995 |
| 5320307 | Aircraft engine thrust mount An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart... | 06/14/1994 |
| 5320487 | Spring clip made of a directionally solidified material for use in a gas turbine engine The present invention discloses a spring clip made of a directionally solidified nickel-base superalloy for use in a high pressure compressor stator sub-assembly of a gas turbine engine. The spring clip includes a body section and a pair of arms integrall... | 06/14/1994 |
| 5318309 | Brush seal An improved brush seal for reducing swirl, recirculation and turbulence of an approaching gas stream to reduce irregular bristle wear and operating costs. The brush real may include a baffle of the honeycomb type or circumferentially stacked plates type, ... | 06/07/1994 |
| 5318402 | Compressor liner spacing device A spacer band for maintaining uniform spacing between adjacent compressor liner segments comprising two segments having a plurality of locking fingers extending from the band for engaging the casing at both ends of the liner segments and in the middle of ... | 06/07/1994 |
| 5310317 | Quadra-tang dovetail blade A gas turbine engine rotor blade includes an airfoil joined to a dovetail. The dovetail includes a shank from which extends two pairs of dovetail tangs being defined by a bifurcating slot disposed therebetween. The dovetail is configured for retention in ... | 05/10/1994 |
| 5307637 | Angled multi-hole film cooled single wall combustor dome plate A gas turbine engine combustor is provided with a combustor dome plate film cooling means having an annular slotted ring to provide a film starting means upstream of a multi-hole film cooled single wall metal dome plate which is annular in shape. One part... | 05/03/1994 |
| 5301901 | Telescoping centerbody wedge for a supersonic inlet An aircraft engine two-dimensional inlet system of the present invention provides a telescoping two-dimensional centerbody that is referred to as a wedge. The telescoping wedge may be of a fixed wedge angle design or a variable wedge angle design. The pre... | 04/12/1994 |
| 5299910 | Full-round compressor casing assembly in a gas turbine engine A full-round compressor casing assembly is employed in a gas turbine engine which includes alternating axially-arranged stages of movable blades and stationary vanes, with each stage of movable blades having a row of rotor blades attached to and extending... | 04/05/1994 |
| 5287694 | Fluid channeling system A fluid channeling system includes a fluid ejector, a heat exchanger, and a fluid pump disposed in series flow communication The ejector includes a primary inlet for receiving a primary fluid, and a secondary inlet for receiving a secondary fluid which is... | 02/22/1994 |
| 5288210 | Turbine disk attachment system A disk attachment system for a high pressure turbine section of a gas turbine engine, the high pressure turbine section including a first stage disk and a second stage disk. The first stage disk includes a first conical aft shaft extending rearwardly from... | 02/22/1994 |
| 5285632 | Low NOx combustor A combustor includes a dome assembly having radially outer and inner liners joined thereto and defining therebetween a combustion zone. The dome assembly includes at least one annular dome having a pair of axially extending first flanges between which are... | 02/15/1994 |
| 5286071 | Bellows sealed ball joint A bellows sealed ball joint comprising an inner spherical shell, a bellows and an outer spherical shell. The inner spherical shell comprises a plurality of elongated non-spherical areas or indentations which receive a plurality of locking surfaces on the ... | 02/15/1994 |
| 5282720 | Fan blade retainer A rotor blade retention assembly includes a rotor blade having a dovetail mounted in a complementary axial dovetail groove in a rotor disk. A primary blade retainer retains the blade in the groove against axial movement in a first direction. A secondary b... | 02/01/1994 |
| 5282358 | Gas turbine engine dual inner central drive shaft A dual inner central drive shaft in a gas turbine engine includes rearward and forward shaft portions which overlap and interengage with one another. The rearward shaft portion includes an elongated cylindrical inner middle portion and a rear conical end ... | 02/01/1994 |
| 5281096 | Fan assembly having lightweight platforms A fan assembly includes a plurality of discrete platforms disposed between adjacent rotor blades extending radially outwardly from a rotor disk. Each platform includes forward and aft axially spaced apart ends, and radially upper and lower spaced apart su... | 01/25/1994 |
| 5281097 | Thermal control damper for turbine rotors Sheet Metal thermal control dampers are disposed in the cavities between turbine blades to bear against the undersides of opposed blade platforms portions of angularly adjacent blades under centrifugal loading to dampen blade vibrations and to seal the ga... | 01/25/1994 |
| 5281098 | Single ring blade retaining assembly The present invention provides an axial blade to disk retaining assembly having a plurality of circumferentially disposed lugs arranged in a ring around an axial facing surface of the blade and disk assembly and a plurality of circumferentially disposed h... | 01/25/1994 |
| 5280705 | Fuel injection system for scramjet engines To promote fuel and air mixing combustor of a scramjet engine, fuel is injected as a succession of pulses into the airstream flowing through the combustor. By controlling the duty cycle and flow rate of the fuel pulses, increased fuel penetration and mixi... | 01/25/1994 |
| 5279130 | Auxiliary refrigerated air system with anti-icing To prevent icing in an auxiliary refrigerated air system utilized in jet aircraft for environmental control purposes, wherein high pressure, high temperature input air bleed from the engine compressor is boosted in pressure and temperature, cooled in a he... | 01/18/1994 |
| 5279109 | Gas turbine engine variable bleed pivotal flow splitter The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine e... | 01/18/1994 |
| 5279112 | Fuel line fitting To connect an external fuel line to an internal fuel line feeding an internal fuel manifold in a combustor of a gas turbine engine, a fitting includes a first joint half terminating the internal fuel line and a second joint half terminating the external f... | 01/18/1994 |
| 5277382 | Aircraft engine forward mount An aircraft engine mount includes an annular casing fixedly disposed in the engine, a mounting platform spaced radially outwardly from the casing and fixedly joinable to an aircraft pylon, and a pair of circumferentially spaced apart links pivotally joine... | 01/11/1994 |
| 5275536 | Positioning system and impact indicator for gas turbine engine fan blades A fan blade and rotor disk assembly for a gas turbine engine has a projection attached to a shank region of a fan blade. The projection makes contact with a surface region of a disk post when the fan blade is assembled to the rotor disk. In one form, a sp... | 01/04/1994 |
| 5275529 | Sandwich panel joint A fastener extends through a bushing in a panel for joining the panel to a stationary frame. The bushing includes a tubular plug extending through the panel which includes a head, a shank, and a distal end. The bushing also includes a tubular sleeve exten... | 01/04/1994 |
| 5275357 | Aircraft engine mount An aircraft engine mount includes a frame fixedly joined in a gas turbine engine and a platform fixedly joined to an aircraft wing or tail pylon. A first beam is pivotally joined to the frame and the platform at first and second joints, respectively. The ... | 01/04/1994 |
| 5275000 | Reducing thermal deposits in endothermic fuel reactors of propulsion systems An endothermic hydrocarbon fuel system to avoid thermally induced coking on the catalytic surfaces of an heat exchanger used as a reactor to dehydrogenate the fuel so that it provides a heat sink for the heat exchanger for cooling parts of high speed airc... | 01/04/1994 |
| 5275534 | Turbine disk forward seal assembly A forward seal assembly located in a turbine section of a turbine engine, the turbine section having a disk including a web, a bore, and a forward shaft integral with the web, wherein the forward seal assembly includes a face plate extending from the forw... | 01/04/1994 |
| 5273397 | Turbine casing and radiation shield A thermal radiation shield is joined to an annular casing through which combustion gases are axially flowable. The shield is spaced at least in part radially inwardly from the casing inner surface and includes axially spaced apart forward and aft edges an... | 12/28/1993 |
| 5272868 | Gas turbine engine lubrication system A lubrication system for a gas turbine engine includes first and second coaxially rotor shafts having at least one differential bearing disposed in outer and inner seats thereof. An annular first scoop extends axially from a first portion of the first sha... | 12/28/1993 |
| 5273396 | Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud A high pressure turbine in a gas turbine engine contains an arrangement of channels, holes and windows through components controlling the operating clearance between tips of turbine blades and casing shroud segments wherein the arrangement defines a seria... | 12/28/1993 |
| 5271714 | Turbine nozzle support arrangement In a gas turbine engine having an annular casing with a stationary support structure, a high pressure turbine, and an annular high pressure turbine nozzle having at least one stage which includes a plurality of circumferentially aligned nozzle segments an... | 12/21/1993 |
| 5271711 | Compressor bore cooling manifold To control disc temperature, provide blade tip clearance control, and purge the rotor bore of a high pressure compressor in a gas turbine engine, an axially elongated manifold is disposed coaxially in the rotor bore to distribute cooling air bleed from th... | 12/21/1993 |
| 5271588 | Multi-piece tube clamp A clamp for mounting a tube to a support plate in a gas turbine engine includes a base plate and a capture plate for capturing the tube therebetween, with a fastener positionable through the base and capture plates for clamping them together and mounting ... | 12/21/1993 |
| 5271718 | Lightweight platform blade A rotor blade for a gas turbine engine includes an airfoil, platform and dovetail. The platform has top and bottom surfaces, with a plurality of pockets disposed in the bottom surface for reducing weight of the platform, with the pockets defining a plural... | 12/21/1993 |
| 5269135 | Gas turbine engine fan cooled heat exchanger A fan-jet gas turbine engine heat exchanger is cooled by fan air taken from the fan duct at a relatively high pressure region of the fan nozzle upstream of the fan nozzle's throat and exhausted into a relatively low pressure region of the fan nozzle upstr... | 12/14/1993 |
| 5267608 | Heat exchanger and reactor for aircraft and propulsion systems A heat exchanger for use in high speed aircraft propulsion engines provides a plurality of heat pipes wherein the evaporator sections of the heat pipes are disposed in a hot fluid flow conduit and the condenser sections are disposed in a cold fluid flow c... | 12/07/1993 |
| 5267828 | Removable fan shroud panel A shroud panel is removably joinable inwardly of a fan casing and outwardly of a fan blade in a turbofan gas turbine engine. The panel includes an arcuate backing plate having a plurality of screws disposed therethrough for mounting the panel to the casin... | 12/07/1993 |
| 5263312 | Tube fitting for a gas turbine engine A tube fitting for use with a flammable fluid is disposed in an auto-ignition zone of a gas turbine engine. The tube fitting has a pair of separable casings defining a passage to accommodate flow therethrough of the flammable fluid, and the casings have a... | 11/23/1993 |
| 5261229 | Noise-suppressed exhaust nozzles for jet engines An array of chutes is permanently mounted within the flowpath of an exhaust nozzle of an aircraft jet engine for entraining and mixing ambient air with the exhaust gas so as to reduce the noise level of aircraft, particularly during take-off. In order to ... | 11/16/1993 |
