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Walt Disney was no Mickey Mouse inventor. He devised a serious animation camera which he patented. With the device, his company created "Snow White".
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| Number | Title | Issue Date |
| 4183210 | Gas turbine engine powerplants A ducted fan gas turbine powerplant consists of a core gas generator, which may be a single or two-shaft gas generator, and which drives a fan at the downstream end of the powerplant. The exhaust from the gas generator is mixed with flow in the fan duct a... | 01/15/1980 |
| 4170110 | Combustion process A combustion process derived from boundary layer stream containment and manipulation of all the combustion phases in auto-pro-progression, within a unitary-continuous sequence, in a supersonic and/or high subsonic velocity mainstream employs no auxiliary ... | 10/09/1979 |
| 4170109 | Thrust augmentor having swirled flows for combustion stabilization A thrust augmentor for a turbofan, gas turbine engine is disclosed. Techniques for mixing and burning dissimilar density gases in a thrust augmentor are developed. In accordance with one specific teaching the flame front in a swirl augmentor is stabilized... | 10/09/1979 |
| 4159625 | Control for gas turbine engine Increased thrust during the transonic flight mode of an aircraft powered by a gas turbine engine is realized by a closed loop control that closes the loop on the pressure ratio across the fan by adjusting fuel flow and/or exhaust nozzle area in a turbofan... | 07/03/1979 |
| 4142365 | Hybrid mixer for a high bypass ratio gas turbofan engine A high bypass ratio gas turbofan engine provided with a hybrid mixer for mixing that portion of the bypass stream equivalent to a bypass ratio of substantially two with the core engine hot gas stream. The mixture is passed through a common exhaust nozzle.... | 03/06/1979 |
| 4137708 | Jet propulsion A jet propulsion engine and a method of operating a jet propulsion engine for propulsion of an aircraft over a wide range of speed from zero to supersonic. The engine is a turbofan type with a duct burner and with separate variable exhausts from the duct ... | 02/06/1979 |
| 4137709 | Turbomachinery and method of operation Axial flow turbomachinery having an impeller with a plurality of contoured blades mounted within a diffuser throat and about a central rotatable hub. This blade shape is defined by the ratio of the blade root and tip chords to the minimum midsection blade... | 02/06/1979 |
| 4133173 | Ducted rockets The overall efficiency of a reaction engine having primary and secondary combustion chambers is greatly improved by reducing the primary exhaust velocity to subsonic speed. This is accomplished in a preferred embodiment by using an exhaust tube downstream... | 01/09/1979 |
| 4132067 | Accoustic propulsion system The system comprises exerting thrust on an object within a particulate medium, such as air, by creating an oscillatory field, such as sound waves, in the medium and by mounting on the object a control apparatus for controlling the movement of the particul... | 01/02/1979 |
| 4128995 | Method and apparatus for stabilizing an augmenter system A turbine is stabilized in high speed, high altitude flight conditions by reducing the maximum augmenter fuel/air ratio in response to certain pressure and temperature conditions. Temperatures and pressures indicative of those at the combustor are sensed ... | 12/12/1978 |
| 4124976 | Method for reducing the critical injection parameter in a solid fuel ramjet A method and system for reducing the critical injection parameter (h/D.su) in a solid fuel ramjet (SFRJ) by using a low h/Dp fuel within the recirculation region of the grain and a higher h/Dp fuel for the majority of the grain to r... | 11/14/1978 |
| 4123196 | Supersonic compressor with off-design performance improvement A turbomachine such as a compressor having one or more rows of blades designed to operate at a supersonic inlet relative Mach number is provided with a manifold surrounding the blade tips for extracting air from the passages between adjacent blades by an ... | 10/31/1978 |
| 4109460 | Liquid fuel rocket engine having adjustable nozzle throat section A liquid fuel rocket engine comprises a housing having an outer annular wall and an inner annular wall which define therebetween a combustion chamber of substantially uniform cross section and leading to a converging wall section and a nozzle throat of na... | 08/29/1978 |
| 4095420 | Augmentor outer segment lockout and fan upmatch A thrust augmented twin spool turbofan engine system to control instability at high altitude, low Mach number conditions wherein an engine electronic control monitors engine inlet temperature, engine burner pressure and Mach number, and inhibits fuel flow... | 06/20/1978 |
| 4085583 | Method for selectively switching motive fluid supply to an aft turbine of a multicycle engine Air breathing gas turbine engine design concepts, and methods and apparatus for providing variable engine cycles are disclosed. The preferred engine embodiments involve two flow control valve systems for internal management of air, each of which have the ... | 04/25/1978 |
| 4070827 | Method and apparatus for limiting ingestion of debris into the inlet of a gas turbine engine A method and apparatus are disclosed for limiting ingestion of debris into the inlet of a gas turbine engine. The invention includes providing first means in communication with a source of fluid under pressure for introducing at least one jet of fluid at ... | 01/31/1978 |
| 4069661 | Variable mixer propulsion cycle A design technique, method and apparatus for controlling the bypass gas stream pressure and varying the bypass ratio of a mixed flow gas turbine engine in order to achieve improved performance. The disclosed preferred embodiments each include a unique mix... | 01/24/1978 |
| 4068469 | Variable thrust nozzle for quiet turbofan engine and method of operating same An improved method of operating a gas turbine engine is presented wherein engine-generated noise is maintained at a reduced level during reduced thrust operation. Fan speed is maintained at a constant level while fan nozzle area is increased. This maintai... | 01/17/1978 |
| 4062185 | Method and apparatus for windmill starts in gas turbine engines A hydraulic pump and drive system is interconnected between the fan and compressor rotor of a turbofan engine such that the windmill speed of the core rotor can be boosted to a speed sufficient to allow a significantly increased in-flight start envelope b... | 12/13/1977 |
| 4055946 | Twin-spool gas turbine power plant with means to spill compressor interstage airflow In order to take advantage of the efficient utilization of fuel occasioned by operating a turbine type power plant of the multiple spool design at very high overall pressure ratios, the high pressure spool is operated at substantially full speed and subst... | 11/01/1977 |
| 4050242 | Multiple bypass-duct turbofan with annular flow plug nozzle and method of operating same A propulsion nozzle having a substantially cylindrical translatable shroud partially defining an outer flow duct and an articulated plug mounted within the shroud to partially define an inner coannular flow duct. A variable position valve comprises the do... | 09/27/1977 |
| 4043121 | Two-spool variable cycle engine An auxiliary fan is disposed upon the periphery of at least a portion of the fan of a conventional gas turbofan engine. Flow modulating components such as variable vanes and nozzles are utilized in conjunction therewith to produce a wide range of operatin... | 08/23/1977 |
| 4038817 | Fuel jettison system Fuel is selectively jettisoned through the engine of an aircraft by way of a normally closed, solenoid-operated jettison valve which is fed from the boost pump in the engine fuel system. The jettison valve is servo activated by the main fuel flow so that ... | 08/02/1977 |
| 4007587 | Apparatus for and method of suppressing infrared radiation emitted from gas turbine engine An apparatus for and method of suppressing infrared radiation emitted from hot metal parts at the aft end of a gas turbine engine and from the exhaust gas plume thereof is provided and such apparatus comprises a dual purpose ejector vane assembly operativ... | 02/15/1977 |
| 3999379 | Reduction of depressurization thrust termination jolt Thrust termination of a solid propellant rocket motor is obtained by connecting the nozzle to the combustion chamber pressure vessel by means of explosive and extrusable bolts. When it is desired to obtain thrust termination, the explosive bolts are blown... | 12/28/1976 |
| 3988888 | Filter/cooler A filter-cooler is provided for use with a rocket motor to cool and filter ighly aluminized hot gases from around 5800° F to around 2000° F. The cooled and filtered gases are then usable, for example, in thrust vector control mechanisms. A decomposable c... | 11/02/1976 |
| 3987621 | Method for reducing jet exhaust takeoff noise from a turbofan engine In a turbofan engine for jet aircraft the inner stream includes no noise suppression apparatus and the jet exhaust noise generated at takeoff is reduced by mechanically suppressing the jet exhaust noise of the outer stream and operating the engine at a by... | 10/26/1976 |
| 3974648 | Variable geometry ramjet engine A variable-geometry ramjet engine, capable of operation over the Mach 3 to 12 speed range, is provided by disposing a movable cowl around a centerbody. The engine is axisymmetric and features a translatable cowl which slides relative to the centerbody on ... | 08/17/1976 |
| 3946554 | Variable pitch turbofan engine and a method for operating same Variable geometry guide vanes are provided in a variable pitch turbofan assembly. A method is disclosed for reducing aerodynamically induced stresses in the variable pitch fan blades as the blades are changed between the forward and reverse pitch modes. T... | 03/30/1976 |
| 3943706 | Ignition system for rocket engine combustion chambers operated by non-hypergolic propellant components An ignition system for rocket engine combustion chambers which are operated by non-hypergolic propellant components and particularly for the pre-combustion chambers of main stream engines of this type, comprises a main combustion chamber having injector m... | 03/16/1976 |
