Abstract: A method and system for cementing and perforating a wellbore in a single step by coupling a perforating gun with a wiper plug. The method includes injecting cement in a wellbore having casing therein and an annulus between the casing and wellbore. A wiper plug is dropped on the cement having a perforating gun attached to the wiper plug. The plug is forced downward pulling the perforating gun along. The downward motion of the plug in turn pushes the cement out the bottom end of the casing and into the annulus. The cement in the annulus is allowed to set and the perforating gun is activated.

Abstract: A perforating gun system having a relief system for relieving high pressure during unexpected high temperature or situations that may produce rupture of the gun body. The relief system may be responsive either to high temperatures as well as high pressures. In the high temperature situation, the relief system has a fuseable link that melts thereby allowing movement of a piston to open vent communication between the inside of a gun body in the ambient conditions. Similarly, a pressure device includes a piston responsive to pressure that moves under high pressure within the gun body thereby exposing a port enabling communication between the inside of the gun body and the ambient conditions.

Abstract: A perforating system having a perforating gun with a pressurizable gun body. The gun body can be pressurized prior to deployment in a wellbore, or while in the wellbore. Pressurizing the gun body can include adding fluid into the gun body, such as a pressurized gas, a liquid, or combustion products. A seal diaphragm can be used to transfer wellbore pressure into the gun body.

Abstract: An aircraft includes at least one turbofan engine assembly having a shrouded core engine, a short nacelle surrounding a fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle. A mixer duct shell is positioned substantially coaxial with the engine shroud and extends forwardly into the fan duct to provide an interstitial mixer duct between the mixer duct shell and the core engine shroud. The aft portion of the mixer duct shell extends over a turbine exhaust frame, an attached mixer (if included), and a tail cone exhaust plug. The mixer duct shell can reduce noise and plume exhaust heat radiated from aircraft turbofan engines.

Abstract: A lock for a perforating gun system comprising, a housing, a cylinder formed in the housing, a piston assembly disposed within the cylinder, and anchoring arms coupled with the piston assembly. Detonation of the shaped charges of an associated perforating gun produces a pressure surge which is communicated to a surface of the piston assembly. Appropriate movement of the piston assembly outwardly rotates the anchoring arms into anchoring engagement with an associated tubular. Thus the pressure from the detonation event will anchor a perforating system within its associated tubular.

Abstract: A method and system for cementing and perforating a wellbore in a single step by coupling a perforating gun with a wiper plug. The method includes injecting cement in a wellbore having casing therein and an annulus between the casing and wellbore. A wiper plug is dropped on the cement having a perforating gun attached to the wiper plug. The plug is forced downward pulling the perforating gun along. The downward motion of the plug in turn pushes the cement out the bottom end of the casing and into the annulus. The cement in the annulus is allowed to set and the perforating gun is activated.

Abstract: A lock for a perforating gun system comprising, a housing, a cylinder formed in the housing, a piston assembly disposed within the cylinder, and anchoring arms coupled with the piston assembly. Detonation of the shaped charges of an associated perforating gun produces a pressure surge which is communicated to a surface of the piston assembly. Appropriate movement of the piston assembly outwardly rotates the anchoring arms into anchoring engagement with an associated tubular. Thus the pressure from the detonation event will anchor a perforating system within its associated tubular.

Abstract: A perforating gun system having a relief system for relieving high pressure during unexpected high temperature or situations that may produce rupture of the gun body. The relief system may be responsive either to high temperatures as well as high pressures. In the high temperature situation, the relief system has a fuseable link that melts thereby allowing movement of a piston to open vent communication between the inside of a gun body in the ambient conditions. Similarly, a pressure device includes a piston responsive to pressure that moves under high pressure within the gun body thereby exposing a port enabling communication between the inside of the gun body and the ambient conditions.

Abstract: An aircraft includes at least one turbofan engine assembly having a shrouded core engine, a short nacelle surrounding a fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle. A mixer duct shell is positioned substantially coaxial with the engine shroud and extends forwardly into the fan duct to provide an interstitial mixer duct between the mixer duct shell and the core engine shroud. The aft portion of the mixer duct shell extends over a turbine exhaust frame, an attached mixer (if included), and a tail cone exhaust plug. The mixer duct shell can reduce noise and plume exhaust heat radiated from aircraft turbofan engines.

Abstract: A connection system to be used in conjunction with a perforating gun comprising a top sub formed to receive one end of a gun body of a perforating gun, a circumferential groove disposed on the outer surface of the gun body, and a collet secured to the top sub. The collet has at least one finger that engages the groove. Engaging the groove with the at least one finger of the collect connects the gun body to the top sub. A cover sleeve is included that retains the finger in connective engagement with the groove.

Abstract: A connection system to be used in conjunction with a perforating gun comprising a top sub formed to receive one end of a gun body of a perforating gun, a circumferential groove disposed on the outer surface of the gun body, and a collet secured to the top sub. The collet has at least one finger that engages the groove. Engaging the groove with the at least one finger of the collect connects the gun body to the top sub. A cover sleeve is included that retains the finger in connective engagement with the groove.

Abstract: A convergent/divergent chevron flow nozzle for use with a jet engine. The flow nozzle includes a converging portion that terminates at a throat portion. Extending from the throat portion is a plurality of chevrons spaced apart by ventilation areas. The chevrons diverge from the nozzle exit flow direction of the flow nozzle. The diverging chevrons serve to increase the thrust produced by a jet engine associated with the flow nozzle during and reduce shock related noise at cruise conditions. The ventilation areas prevent over-expansion of the nozzle flow at takeoff and resulting shock related noise from the plume, and increases plume mixing to reduce jet exhaust noise during takeoff without negatively affecting the thrust generated by the exhaust flow. The flow nozzle can be implemented at both the fan nozzle and exhaust nozzle areas of a dual flow jet engine.

Abstract: One embodiment of the present invention discloses a system and method for orienting perforating guns inside of slanted or deviated wellbores. The invention involves adding a weight inside of the guns to gravitate the gun to a specified orientation. The weight is situated on the outer circumference of the gun tube and within the inner diameter of the gun body. The invention is capable of orienting the gun in any radial position without affecting the shot performance of any of the shaped charges.

Abstract: One embodiment of the present invention discloses a system and method for orienting perforating guns inside of slanted or deviated wellbores. The invention involves adding a weight inside of the guns to gravitate the gun to a specified orientation. The weight is situated on the outer circumference of the gun tube and within the inner diameter of the gun body. The invention is capable of orienting the gun in any radial position without affecting the shot performance of any of the shaped charges.

Abstract: A cooling system (18) for supplying an even distribution of cooling air within a payload chamber (14) of a launch vehicle is disclosed. The cooling system (18) includes an elongate duct (20), a diverter (22), and a plurality of partitions (24a, 24b, 24c . . . ). The diverter (22) is attached to a distal end (21) of the elongate duct (20) by the plurality of partitions (24a, 24b, 24c . . . ). A turning vane (26) integral with two of the plurality of partitions (24a, 24b, 24c . . . ) extends into the elongate duct (20) dividing part of the elongate duct (20) into two separate halves. Cooling air passes through the elongate duct (20) and strikes the diverter (22) which evenly distributes the cooling air within the payload chamber (14) of the launch vehicle.

Abstract: An aircraft for vertical or short take off and landing operations having two main lift nozzles, both positioned at or near the aircraft center of gravity utilizes one or more jet screen nozzles, arranged in a variety of shapes and combinations, discharging bypass air from a position forward of the center of gravity, and a variable pitch nozzle discharging engine exhaust gas mixed with bypass air from a position aft of the center of gravity, to achieve pitch control while airborne in vertical take off or landing mode. The jet screen nozzle also prevents or reduces ingestion of mixed hot exhaust gas and bypass air discharged through the main lift nozzles. The jet screen nozzle further prevents or reduces ingestion of foreign object debris disturbed by the vertical lift discharge flowing from the main lift nozzles.

Abstract: 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.

Abstract: 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.

Abstract: In the representative embodiments of the new and improved methods and apparatus disclosed herein, a well logging instrument includes an elongated body member having a funnel configuration fluid collector mounted thereon. An aperture in the body member, proximate the apex of the collector, allows discharge of the fluid through a passage in the body member, past a pair of radiation detectors, thereafter returning into the well. A tracer ejector valve assembly is mounted proximate the apex of the funnel and the aperture therein for selectively injecting a quantity of radioactive tracer element into the fluid flow. The tracer element is detected by the pair of detectors with the signals provided therefrom used to determine flow characteristics of the fluids within the well.