| Patent Number |
Title Of Patent |
Date Issued |
| 5135185 |
Wing mounted unducted fan engine |
August 4, 1992 |
| An aircraft engine is mounted on an aircraft wing such that the wing wake sheds along a zone at a predetermined position on the engine disk thereby minimizing dynamic loads or resonance. For a prechosen or design set of engine conditions the strength of the dynamic load is a function of |
| 5010729 |
Geared counterrotating turbine/fan propulsion system |
April 30, 1991 |
| High by-pass fan jet engine includes counterrotating turbine blade sets for receiving hot combustion gases from a core engine portion and driving the fan blades through a planetary gear-type reduction gear assembly. Lightweight, highspeed, concentric, counterrotating shafts transmit powe |
| 4969325 |
Turbofan engine having a counterrotating partially geared fan drive turbine |
November 13, 1990 |
| A high bypass ratio turbofan engine having a fan section, a booster compressor disposed aft of the fan section relative to the flow of combustion gases through the engine, and a core section disposed aft of the booster compressor. A low pressure counterrotating turbine, disposed aft |
| 4948339 |
Propeller blade counterweight |
August 14, 1990 |
| The invention concerns a system for reducing the resisting torque which must be overcome in changing pitch of aircraft propeller blades. The resisting torque includes gas twisting moment and centrifugal twisting moment. The invention includes a bearing system which derives a torque f |
| 4936748 |
Auxiliary power source in an unducted fan gas turbine engine |
June 26, 1990 |
| A power takeoff for an unducted fan gas turbine engine having first and second counterrotating coaxial rotors coupled respectively to first and second propellers. The rotors and propellers are oriented for rotation about a longitudinal axis of the engine. A gear is coupled to each of the |
| 4916894 |
High bypass turbofan engine having a partially geared fan drive turbine |
April 17, 1990 |
| The present invention provides a high bypass turbofan engine configuration wherein a fan drive turbine is divided into first and second turbine sections mounted for independent rotation within the engine frame. The first, higher pressure, higher speed turbine section is coupled to the fa |
| 4913623 |
Propeller/fan-pitch feathering apparatus |
April 3, 1990 |
| A pitch feathering system for a gas turbine driven aircraft propeller having multiple variable pitch blades utilizes a counter-weight linked to the blades. The weight is constrained to move, when effecting a pitch change, only in a radial plane and about an axis which rotates about the |
| 4883240 |
Aircraft propeller noise reduction |
November 28, 1989 |
| In one form of the invention, a counterrotating pair of aircraft propellers produces noise in the form of a frequency-modulated carrier wave. The frequency modulation allows a designer to manipulate the energy spectrum of the noise in order to, for example, place much of the acoustic ene |
| 4825648 |
Turbofan engine having a split cowl |
May 2, 1989 |
| A turbofan engine having a power generating portion of the engine supporting a fan and surrounded by a cowl. The cowl is split with the two sections being arcuate and hinged so that they can pivotally open for access and removability of the power generating portion of the engine. The |
| 4296599 |
Turbine cooling air modulation apparatus |
October 27, 1981 |
| The cooling air flowpath for a turbomachine includes a plurality of valves placed in mutually parallel relationship to collectively provide for the modulation of the cooling airflow. Minimum flow requirements are assured while economizing on air to increase efficiency. Any single valve p |
| 4251987 |
Differential geared engine |
February 24, 1981 |
| A gas turbine engine comprising a fan, a compressor and a turbine, wherein the torque requirements of the fan or compressor can be modulated, is provided with differential gearing to transmit all of the fan and compressor power requirements from the turbine. The differential gearing |
| 4222235 |
Variable cycle engine |
September 16, 1980 |
| A variable cycle turboshaft engine includes a remote fan system and respective high and low pressure systems for selectively driving the fan system in such a manner as to provide VTOL takeoff capability and minimum specific fuel consumption (SFC) at cruise and loiter conditions. For |
| 4222234 |
Dual fan engine for VTOL pitch control |
September 16, 1980 |
| A core engine with a single shaft driving both a forward and a rear fan, with the fans discharging into separate nozzles which are variable to direct exhaust gases in either the downward or rearward direction or in any direction therebetween. Separate flow modulating means are provided |
| 4149824 |
Blade containment device |
April 17, 1979 |
| A device is provided for containing blades of rotating turbomachinery comprising a high-strength ring supported in radial spacial relationship over the blade tips by means of a stationary support structure. The ring is supported in such a manner that it is capable of spinning with respec |
| 4132069 |
Integrated gas turbine engine-nacelle |
January 2, 1979 |
| A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inne |
| 4083181 |
Gas turbine engine with recirculating bleed |
April 11, 1978 |
| A method of reducing carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet. As this hot inlet air is recycled, the |
| 4068470 |
Gas turbine engine with convertible accessories |
January 17, 1978 |
| Drive means for connecting a gas turbine engine to its accessories are so constructed as to allow the accessories to be selectively positioned to any one of several predetermined circumferential positions about the perimeter of the engine. This feature permits convenient mounting of the |
| 4068469 |
Variable thrust nozzle for quiet turbofan engine and method of operating same |
January 17, 1978 |
| 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 maintains high inlet Mach numbers for |
| 4055041 |
Integrated gas turbine engine-nacelle |
October 25, 1977 |
| A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inne |
| 4051289 |
Composite airfoil construction |
September 27, 1977 |
| An article such as a blade fabricated from a plurality of high-strength, reinforcing filaments embedded in a matrix material and characterized by a portion of the filaments oriented transverse to the blade longitudinal axis in a direction through the blade to enhance transverse shear |
| 4047840 |
Impact absorbing blade mounts for variable pitch blades |
September 13, 1977 |
| A variable pitch blade and blade mount which is suitable for propellers, fans and the like and which has improved impact resistance. The invention is particularly directed to composite fan blades and blade mounting arrangements wherein the blades are permitted to pivot relative to a |
| 3977728 |
Wheel |
August 31, 1976 |
| A wheel comprising a plurality of wheel plies, each wheel ply including concentric inner and outer hoops and a plurality of circumferentially spaced spoke loops therebetween, wherein each of the spoke loops is entrapped within the hoops. In one embodiment the wheel comprises a lamina |
