The Boeing Company

Other

Garry W Klees

Mark L Sloan

Gary L Lidstone

Russel L Thornock

Charles P Wright

A combination flashlight/candle lantern with a modified lower base designed to be used with the standard, metallic cover on a candle lantern. The modified lower base has an upper neck designed to selectively attach to the metallic cover. The modified lower base also includes an upward extending cavity and a transversely aligned candle platform designed to receive a tube candle. Formed on the opposite side of the candle platform is a downward extending lower cavity designed to receive a low profile flashlight assembly. The flashlight assembly includes a cylindrical-shaped housing designed to partially extend into the lower base. Located centrally on the housing is a longitudinally extending LED electrically connected to two side-by-side watch batteries. Attached over the lower opening on the housing is a combination lens/switch which, when rotated, controls operation of the LED. The flashlight assembly may also include a bail located on the base member opposite the combination lens/switch. The bail may be disposed in a concealed manner when the flashlight assembly is attached to the lower base, or may allow the separated flashlight assembly to be independently supported from a hook or aimed on a flat surface.

Combination flashlight and candle lantern

A supersonic aircraft engine, either turbojet or turbofan, having a compressor, a diffuser, a combustion chamber, a turbine, and a nozzle passageway, and a turbine bypass passageway for bypassing compressor exit flow around the turbine. The bypass passageway comprises a plurality of supply pipes, and a flow control valve is mounted in each of the plurality of supply pipes. Under given flight conditions, a predetermined number of these flow control valves are fully closed, while the remaining flow control valves are opened as necessary for the given flight condition to obtain a desired rate of turbine bypass flow. The turbine bypass flow is supersonically mixed with the turbine exit flow during transonic acceleration or discharged externally of the engine housing. The turbine bypass flow is primarily composed of boundary layer air flowing along the inner and outer walls of the diffuser.

Turbine bypass engines

A supersonic engine having an ejector/suppressor. The engine has a rear discharge portion with an ambient air inlet section, a mixing section, and a rear discharge section. For noise suppression, arms mounted in the air inlet section are moved to open air inlet passageways causing air to flow there through. Primary exhaust from the engine flows through primary passageways interspersed with the ambient air passageways. The primary supersonic air from the primary passageways mixes with the ambient air in the mixing section and flows out the final nozzle which is in the open position. For cruise mode, the arms are moved to close the air inlet passageways, and the final nozzle is in a position to cause the flow upstream thereof to be a subsonic, and the flow aft of the final nozzle to be supersonic. The arms can be placed in an intermediate position for thrust reversal, with the final nozzle being moved a blocking position.

Supersonic engine apparatus and method with ejector/suppressor

A portable candle lantern with safety features designed to be used with a tub candle. The candle lantern includes an upper cover that selectively attaches to a lower base. The lower base has a plurality of feet with enable it to be supported in an elevated position on a support surface. Located inside the lower base is a candle holding assembly which removably holds a tub candle in an elevated, longitudinally aligned position therein. Formed inside the lower base is a centrally located, longitudinally aligned, upward extending, air delivery tube which delivers cool air directly against the sides of the tub candle and the candle holding assembly. By delivering cool air in this manner, the temperature inside the candle lantern is reduced thereby preventing a 'flash' condition from occurring. Also, a collection cavity is formed between the air delivery tube and the sides of the lower base in which spilled wax from the tub candle is collected.

Portable, tub candle lantern

A supersonic jet engine having a nozzle section into which ambient air can be selectively introduced for a noise suppressing mode of operation, with this ambient air being intermixed with engine exhaust flow, through passageway segments. Flow modulating plugs or vanes are positioned at the exhaust end of engine exhaust outlet segments in a mixing section, and these are operated during noise suppression mode to match engine requirements. There is a final nozzle section which during the noise suppressing mode is opened to present a relatively large cross sectional flow area to accommodate the mixed flow. During the non-noise suppressing mode, the final nozzle has a convergent/divergent configuration to control flow, and the plug or vane flow modulating means are positioned to permit unrestricted flow from the engine exhaust outlet segments.

Supersonic jet engine installation and method with sound suppressing

The present invention relates to a jet engine, where there is an outer housing, an engine, a mixing section, and an exhaust section. Ambient air is drawn into the mixing section. The gaseous exhaust from the core engine is directed through primary passageway segments in the mixing section, and the ambient air that is drawn into the mixing section means flows into secondary passageway segments in the mixing section. The primary and secondary flow segments passing from the mixing section mix as these pass into the exhaust section to be discharged as mixed supersonic jet flow.

Jet engine with noise suppressing mixing and exhaust sections

A supersonic jet engine for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and into the secondary air passageway. Exhaust from the engine and the secondary air are directed into primary and secondary segments to mix in a stream direction as supersonic flow. Selectively controllable primary bypass passageways are provided at the primary passageway segments and are operated to bypass the primary flow through the primary segments at times when greater primary flow area is required.

Nozzle system and method for supersonic jet engine

A supersonic jet engine installation for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and also into the secondary air passageway. The exhaust from the engine and the flow from the secondary air passageway are directed into primary and secondary passageway segments to mix and then be discharged from the engine as a supersonic mixed flow. In the noise suppressing mode, it is desirable that the mixed flow be subsonic.

Mixed exhaust flow supersonic jet engine and method

A jet engine for use in a hypersonic aircraft. A fuel rich injectant is injected into the mixing zone of a duct at a substantial downstream angle to form an ejector. The temperature of the injectant is sufficiently low that spontaneous combustion of the injectant is delayed until the injectant reaches the combustion zone of the duct. In order to prevent combustion from propagating upstream from the combustion zone, the equivalence ratio of the mixture of injectant and ambient air flowing along the wall of the duct is maintained at a relatively high value, and the velocity profile of the flow along the wall of the duct is maintained at a relatively high value.

Low speed engine for supersonic and hypersonic vehicles

A variable geometry gas turbine engine exhaust nozzle includes a variable circumference centerbody and a translating, annular shroud that cooperate to vary the throat area of the exhaust nozzle and the final area of the exhaust gas exiting the nozzle. The shroud includes a substantially constant inside diameter forward portion and a rear portion that has a continuously increasing inside diameter in the rearward direction. The centerbody is coaxially positioned within a circular cross section flow passage formed by the shroud and is configured with an upper and a lower shell that pivot between a retracted and an extended position. In the retracted position, the centerbody presents a circular profile to exhaust gases flowing through the exhaust nozzle. In the extended position, the centerbody presents an oval profile. By coordinating the centerbody shell position with the axial position of the shroud, the throat passage of the exhaust nozzle can be varied between an annular and a nonannular cross section. Additionally, since the shroud can be moved translationally independently of the configuration of the centerbody, the throat area of the exhaust nozzle and the final area of the exhaust gas can be varied independently of one another.

Plug-type exhaust nozzle having a variable centerbody and translating

Internally ventilated noise suppressor with large plug nozzle

A two-piece spout and stopper for thin, volatile liquids, including an adapter piece to be threaded onto the neck of a bottle and a spout piece which threads into the adapter piece. Vent and pouring holes are provided in widely spaced array. The threads are sealed but allowed to be wetted by the fluid when pouring liquid. The shape of the surfaces is such as to minimize surface adhesion or trapping of liquid when the spout is closed.

Pouring cap

A supersonic two spool turbojet engine capable not only of developing sufficient power to accelerate up to supersonic cruise and maintain efficient operation at supersonic cruise, but also arranged to cruise at subsonic velocities with a relatively low specific fuel consumption. The engine is provided with a variable bypass passageway downstream of the compressor. Flow into the bypass passageway is controlled so that during low power setting the bypass passageway is closed so that all the gaseous flow is directed through the turbine. During higher power settings, the bypass passageway is opened to the extent that a selected portion of the gaseous flow is directed through the bypass passageway to bypass the first stage of the turbine section so that the corrected flow to the first turbine stage remains substantially constant for high and low power setting of the engine. The bypass flow is then directed into the area between the first and second turbine to combine with the gaseous flow passing through the first turbine and pass through the second turbine.

Turbine bypass turbojet with mid-turbine reingestion and method of

A supersonic two spool turbofan engine capable not only of developing sufficient power to accelerate up to supersonic cruise and maintain efficient operation at supersonic cruise, but also arranged to cruise at subsonic velocities with a relatively low specific fuel consumption. The engine is provided with a variable bypass passageway downstream of the compressor. Flow into the bypass passageway is controlled so that during low power setting the bypass passageway is closed so that all the gaseous flow is directed through the turbine. During higher power settings, the bypass passageway is opened to the extent that a selected portion of the gaseous flow is directed through the bypass passageway to bypass the first stage of the turbine section so that the corrected flow to the first turbine stage remains substantially constant for high and low power setting of the engine. The bypass flow is then directed into the area between the first and second turbine to combine with the gaseous flow passing through the first turbine and pass through the second turbine.

Turbine bypass turbofan with mid-turbine reingestion and method of

A jet engine having its turbine section and exhaust nozzles particularly arranged to alleviate noise. There is a forward turbine section positioned in a first passageway to receive all or substantially all of the gaseous discharge from the combustion section of the jet engine. There are second and third coannular passageways positioned downstream of the first passageway, with the second passageway being positioned radially inwardly of the third passageway. A second turbine stage is positioned in the second inner passageway to receive a portion of the gaseous flow from the first passageway so as to be driven thereby, with the first portion of gaseous flow being discharged at a relatively low velocity at a radially inward location. A second portion of the gaseous flow passes from the first passageway to the third passageway and is discharged at a relatively high velocity in a generally annular pattern radially outward of the flow of the first portion of the gaseous flow. Thus the gaseous flow is in a velocity profile to alleviate noise from the engine.

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Mercer Island, WA, United States of America

Garry W Klees