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公开(公告)号：US3614024A
公开(公告)日：1971-10-19
申请号：US3614024D
申请日：1970-04-06
申请人： ROHR CORP
发明人： MILLMAN VICTOR
摘要： A motorless aircraft carrying a pilot, and, if desired, one or more passengers, is mounted on a high-speed water surface craft having servocontrolled propulsion and steering mechanism. Each of one or more power winches in the surface craft controls the reeling out and in of a towing cable and, optionally, electrical conductors. Electrical pilot controlled means in the aircraft are operatively connected to electrically responsive individual servo means controlling the propulsion, steering and winch means in the surface craft, so that a pilot in the aircraft can maneuver the surface craft with the aircraft mounted thereon on the surface of the water, and can take off from the water craft at a determined minimum air speed upon unreeling the tow cable. He then flies the aircraft in the manner of a towed glider, while still maintaining full operational control of both the surface and air craft.
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公开(公告)号：US3611726A
公开(公告)日：1971-10-12
申请号：US3611726D
申请日：1969-09-29
申请人： ROHR CORP
发明人： MEDAWAR GEORGE E
摘要： THRUST GAS OF JET ENGINE IS DISCHARGED FROM FRUSTOCONICAL NOZZLE. CYLINDRICAL FORWARD END OF TUBULAR EJECTOR IS CONCENTRICALLY SPACED AROUND END OF NOZZLE SO THAT SLIPSTREAM AIR FLOWING PAST THE LATTER ENTERS EJECTOR IN ANNULAR STREAM SURROUNDING THRUST GAS ISSUING FROM NOZZLE. THE AFT END OF THE EJECTOR IS RECTANGULAR AND HAS VANES MOUNTED THEREIN, THE LONG SIDES OF SAID AFT END EXTENDING VERTICALLY.
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公开(公告)号：US3601992A
公开(公告)日：1971-08-31
申请号：US3601992D
申请日：1970-06-10
申请人： ROHR CORP
发明人： MAISON RICHARD L
CPC分类号： F02K1/70
摘要： Fan jet engine has cowl surrounding engine and terminating in jet exhaust nozzle. Elongate streamlined shroud surrounds fan and engine to define annular duct for fan air terminating forward of exit end of nozzle. Main body of shroud terminates in transverse plane, and peripherally spaced support struts extend rearwardly to define peripherally spaced outflow passages for diverted fan air. Nozzle ring may be attached to aft ends of support struts to provide unit structure. Set of blocker doors overlie each other in each passage and are pivoted on transverse axes which are spaced fore and aft. All doors in a set are stowed and deployed in unison by an actuator. Aft ends of aft doors when deployed contact cowl and block rearward flow. When deployed, all doors diverge forward to produce cascade effect with forward air flow component. Forward doors do not contact shrouds, and aft end of each succeeding door is closer to the cowl to intercept and deflect different portions of air stream. Forward ends of doors are similarly stepped to deliver reverse thrust air at different radial distances outward of the shroud.
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公开(公告)号：US3599749A
公开(公告)日：1971-08-17
申请号：US3599749D
申请日：1969-07-28
申请人： ROHR CORP
发明人： MILLMAN VICTOR
CPC分类号： F02K1/34
摘要： Jet engine exhaust nozzle is surrounded at its exit margin with multiplicity of small jet discharge ducts which direct discrete small jets of gas rearwardly in a ring surrounding the jetstream. These jets intercept the expanding boundary of the jetstream immediately behind the nozzle and produce small eddy turbulence with lower sound energy level and higher frequency level. Gas is supplied by bleed from compressor or turbine through shell surrounding nozzle. In form shown, tailpipe boundary layer is drawn off to improve engine efficiency. Gas jets travel at velocity between those of jetstream and free air, reducing shearing forces and consequent sound energy and producing two mixing zones.
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公开(公告)号：US3587778A
公开(公告)日：1971-06-28
申请号：US3587778D
申请日：1969-11-06
申请人： ROHR CORP
发明人： ELLIS PETER H
摘要： A TURBOFAN JET AIRCRAFT ENGINE HAS A USUAL TAIL CONE MOUNTED COAXIALLY ON THE AFT ROTOR BEARING HOUSING. A CONICAL HOUSING IS MOUNTED COAXIALLY ON, ABD IS SEALED TO THE DOWNSTREAM END OF THE ENGINE EXHAUST, TUBE TO FORM AN EXHAUST GAS PLENUM CHAMBER BETWEEN SAID CONICAL HOUSING AND THE ENGINE TAIL CONE. THE APEX OF SAID HOUSING IS OPEN TO FORM A CENTRAL EXHAUST NOZZLE, AND A PLURALITY OF OTHER EXHAUST NOZZLES EXTEND RADIALLY FROM THE CONICAL HOUSING AND EXTEND DOWNSTREAM TO TERMINATE IN A PLURALITY OF CONCENTRIC, CIRCULAR ROWS ABOUT THE APEX NOZZLE. A TAILPIPE IS SEALED COEXTENSIVELY TO THE DOWNSTREAM END OF THE OUTER WALL OF THE USUAL ANNULAR FAN AIR DUCT OF THE ENGINE TO ENCLOSE AN ANNULAR SPACE BETWEEN THE CONICAL HOUSING AND THE TAILPIPE, THROUGH WHICH SPACE EXTEND THE CURVED EXHAUST NOZZLES. THE DOWNSTREAM ENDS OF THE OUTERMOST ROW OF NOZZLES EXTEND OUTWARDLY THROUGH OPENINGS PROVIDED THEREFOR IN THE TAILPIPE. A RETRACTABLE EJECTOR RING FOR DEPLOYMENT DURING LANDING APPROACH AND TAKEOFF PREFERABLY IS PROVIDED, AND IS MOVABLE FROM A DEPLOYED POSITION JUST DOWNSTREAM OF THE NOZZLE EXIT PLANE TO A RETRACTED POSITION ENCLOSING, AND FLUSH WITH, THE DOWNSTREAM END OF THE ENGINE NACELLE.
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公开(公告)号：US3587777A
公开(公告)日：1971-06-28
申请号：US3587777D
申请日：1969-10-23
申请人： ROHR CORP
发明人： ELLIS PETER H
摘要： LOBED NOZZLE IS ATTACHED TO AFT END OF HOUSING SPACED AROUND TURBOFAN ENGINE, FAN AIR OF THE LATTER FLOWING THROUGH GAP BETWEEN HOUSING AND ENGINE CASING AND THEN THROUGH LOBE PASSAGES OF SAID NOZZLE, HOLLOW FRUSTOCONICAL INNER MEMBER IS DISPOSED WITHIN THE NOZZLE AND ATTACHED AT ITS BASE TO AFT END OF ENGINE CASING. PIPES ARE MOUNTED ON OUTER SIDE OF INNER MEMBER IN ROWS EXTENDING AXIALLY THEREOF AND RESPECTIVELY RADIALLY ALIGNED WITH LOBE PASSAGES, THE PIPES COMMUNICATING WITH INTERIOR OF INNER MEMBER SO THAT ENGINE EXHAUST GAS IS DISCHARGED THERETHROUGH INTO SAID LOBE PASSAGES, WHERE IT MIXES WITH FAN AIR. SLIPSTREAM AIR FLOWS BETWEEN NOZZLE LOBES AND THEN BETWEEN STREAMS OF COMBINED EXHAUST GAS AND FAN AIR ISSUING FROM THE LOBE PASSAGES.
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公开(公告)号：US3585349A
公开(公告)日：1971-06-15
申请号：US3585349D
申请日：1963-04-15
申请人： ROHR CORP
发明人： KALBFELL DAVID C
IPC分类号： H01J29/94 , H01J37/30 , H01J37/301 , B23K9/00
CPC分类号： H01J29/94 , H01J37/3005 , H01J37/301
摘要： The invention relates to apparatus for bringing an electron beam outside the high vacuum chamber of its electron gun to direct the same onto a workpiece. The apparatus comprises beam aligning means, a visual optical system, at least one buffer vacuum chamber, means for surrounding the beam with a shield gas, and pumping mans individual to each chamber for individual pumping of them. The high vacuum chamber and buffer chamber have pyrex windows disposed within the field of view of the optical system. The high vacuum and buffer chambers also have aligned flow limiting orifices drilled in the said windows for passing the beam from the high vacuum chamber to the workpiece, one of the orifices interconnecting the two chambers and the other orifice being the exit orifice adjacent the workpiece.
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公开(公告)号：US3581841A
公开(公告)日：1971-06-01
申请号：US3581841D
申请日：1970-07-27
申请人： ROHR CORP
发明人： RAYNES BURT F
摘要： Tubular ejectors are arranged so that in a retracted position they are concentrically disposed around a thrust nozzle projecting from aircraft jet engine nacelle and in a deployed sound-suppressing and thrust-augmenting position they are disposed downstream from the nozzle in coaxial relation therewith and telescope relative to one another with the largest ejector spaced farthest from the nozzle. Blocker doors are arranged to close apertures in the wall of largest ejector or to extend transverse to the apertures and deflect engine jet stream forwardly therethrough to thereby reverse the thrust of the downstream. At takeoff ejectors are deployed to augment thrust and blocker doors are closed. If takeoff must be aborted, blocker doors can be deployed to reverse thrust. During landing only the largest ejector is deployed downstream from nozzle and the blocker doors are deployed.
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公开(公告)号：US3579993A
公开(公告)日：1971-05-25
申请号：US3579993D
申请日：1969-08-04
申请人： ROHR CORP
发明人： TANNER CAROLE S , TONTINI REMO
CPC分类号： F02K1/40 , F02K1/36 , F05D2260/962 , Y02T50/671
摘要： System includes a nozzle connected to turbine exhaust outlet to confine and direct gas stream. Nozzle is corrugated to form peripherally spaced radially extending lobes to divide gas into small jet streams. Conduit surrounds exhaust outlet and discharges to exterior of nozzle, and fan air flows through passages between lobes to meet gas streams at exit margin of nozzle. Shroud or ejector sleeve defines and surrounds a mixing zone aft of the exit margin. Leading edge of shroud is spaced aft of fan air conduit to provide annular flow path for entry of ambient air to surround and mix with fan air and gas. Shroud is retractable to surround nozzle in spaced relation and prevent dispersion of fan air before mixing in normal cruising flight.
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公开(公告)号：US3579991A
公开(公告)日：1971-05-25
申请号：US3579991D
申请日：1970-01-08
申请人： ROHR CORP
发明人： NELSON HAROLD E JR
CPC分类号： F02K1/60
摘要： Thrust reversing doors are mounted on an aircraft jet engine housing by means of links each pivoted at one end to the housing and pivoted at its other end to the aft portion of one of the two side edges of a respective one of the doors. Means are provided to limit the rotation of the links relative to the housing and the rotation of the doors relative to the links. Drive links are connected to the doors and to actuators which are mounted on the housing and which can be operated to thereby move the doors between stowed and deployed positions relative to the housing.
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