US3700189A - Vtol propulsion system - Google Patents

Vtol propulsion system Download PDF

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Publication number
US3700189A
US3700189A US51923A US3700189DA US3700189A US 3700189 A US3700189 A US 3700189A US 51923 A US51923 A US 51923A US 3700189D A US3700189D A US 3700189DA US 3700189 A US3700189 A US 3700189A
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United States
Prior art keywords
pod
passageway
units
ports
unit
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US51923A
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English (en)
Inventor
Eugene L Timperman
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General Electric Co
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General Electric Co
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Publication date
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Publication of US3700189A publication Critical patent/US3700189A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage

Definitions

  • ABSTRACT 52 US. (:1 ..244/12, 244/23 A Propulsion System is described which comprises two 51 1111.121. ..B64C 15/00, B64c 29/00 tip-turbine driven fan units Pivotally mounted in a 5 Field f Search 244/12 23 52 5 53 12 A pod.
  • EUGENE L TIMPERMAN While many proposals have been made to provide vertical propulsion for fixed wing aircraft, none had any substantial measure of commercial success. This may be attributed to various shortcomings. Where separate powerplants are employed for vertical and forward propulsion, expense and weight have been prime problems. When vectorable nozzle have been considered, complexity has been a deterrent factor. Where powerplants have been swiveled relative to the aircraft,
  • one object of the invention is to pro I vide an improved propulsion system having a relatively high mass flow for vertical propulsion and a high pressure rise for forward propulsion of winged aircraft.
  • Another object of the invention is to additionally provide inlets and nozzles which are specifically suited for the differing requirements of vertical and forward propulsion.
  • a propulsion system comprising two ormore air pressurizing units which pressurize separate air streams for vertical propulsion and a single air stream for forward propul- SlOn.
  • these air pressurizing units are mounted in a pod having a horizontal passageway with a thin edged inlet at one end and a discharge nozzle at its other end.
  • the units have ducts which are registered with vertically aligned inlet and discharge ports in the vertical mode. In the forward mode, these ducts are registered with the horizontal passagewayof the pod.
  • the inlet ports may be rounded for efficient vertical propulsion.
  • the air pressurizing units comprise fans having tip-turbines driven from remote gas generators. Special features are provided for handling the hot gas discharge from the units and .also for transitioning between vertical and forward propulsion.
  • FIG. 1 is a fragmentary perspective view of an aircraft incorporating a propulsion system embodying the present invention and illustrating it in a vertical flight mode;
  • FIG. 2 is a section, on an enlarged scale, taken on line II--II in FIG. 1;
  • FIG. 3 is a section, on a further enlarged scale, taken on line III-III in FIG. 2;
  • FIG. 4 is a perspective view similar to FIG. 1 illustrating the propulsion system in its forward mode
  • FIG. 5 is a section taken on line V--V in FIG. 4;
  • FIG. 6 is a section, on an enlarged scale, taken on line VI -VI in FIG. 5;
  • FIGS. .7 and 8 are sections similar to FIGS. 2 and 5 illustrating transition between vertical and horizontal driven by a pair of gas generators 22 mounted at the forward end of the pod 16. 1
  • Each of the units 18 and 20 comprises a central frame structure 24 which is supported on a casing 26. 4
  • the casing 26 has a central duct 28 and an outer sphericalsurface 30 which is received by a corresponding surface formed in the pod 16.
  • Trunnions 32 mount the casings for pivotal movement on the pod l6.
  • Actuators 34 are provided to rotate the units 18 and 20 as will later be described.
  • the units 18 and 20 each further comprise a rotor 36 having fan blades 38 projecting therefrom and outlet guide vanes 40 also supported from the casing 26.
  • the hot gas streamfrom one of the gas generators 22 is discharged into alongitudinal passageway 42 (FIGS. 3 and 6) and passes through the trunnion 32 to a scroll 44 formed in the casing 26.
  • Scroll 44 directs the hot gas stream to turbine blades 46 secured to the outer ends of the fan blades 38.
  • the rotor 36 is thus rotated so that the fan blades 38 pressurize air entering through the passageway 28 and discharge the pressurized air through the outlet guide vanes 40 to provide a propulsive force.
  • the hot gasstream after being discharged from the turbine blades 46, is directed through outlet guide vanes 48 and then a concentric outlet passageway 50.
  • the left fan unit 20 is similarly powered by the discharge of the other gas generator 22 which is directed through a longitudinal passageway 52 to the hollow trunnion of that unit.
  • the construction of the units may be identical and like reference characters are employed to identify like components. It will also be pointed out that the tip-turbine driven fans are well known per se so that further description of these air pressurization devices is not required.
  • the units 18 and 20 are positioned with their axes vertically disposed and with their ducts 28, respectively, in registration with inlet ports 54 in the top of the pod l6 and also in registration with discharge ports 56 in the bottom of the pod 16.
  • Cover 58 for the inlet ports 54 is opened in the vertical flight mode by actuators 55 through a mechanical connection 57.
  • Covers 60 for the discharge ports 56 are swung to open positions for the vertical mode by actuators 59 through a mechanical connection 61. It will also be seen that struts 63 support the covers 60.
  • the pod 16 has a central passageway 62 with which the vide the forward propulsive force.
  • the hot stream discharge of the unit 18, through the concentric passageway 50, is directed through a passageway 66 in the pod 16 so that it is angled outwardly along the outerdownstream surface of the pod 16.
  • Passageway 66 extends circumferentially around the pod a limited angular distance to preventdischarge of hot gases toward the wing 14..
  • FIGS. 7 9 illustrate transition of the propulsion system from vertical to horizontal operation.
  • the first step is to progressively swing the lower covers 60
  • fan 20 is 2 horizontal forward thrust component is produced as ilrapidly rotated into its horizontal posture and then the covers 58 and 60 for the fan unit 20 are closed as are the flaps 70, 72, returning thepropulsion system to the position illustrated in FIGS. 4 6.
  • the described propulsion system provides a high mass flow with a relatively low pressure ratio during vertical propulsion and a higher pressure ratio and lower mass flow for efficient forward propulsion.
  • the inlet and discharge ports 54 and 56 for vertical propulsion are independent of the inlet and nozzle for forward propulsion. This enables the use of bellmouth inlets for better vertical performance and a sharp edge, high speed inlet for better forward performance.
  • the discharge ports or nozzles 56 can have the proper area for vertical propulsion while the nozzle 64 has the proper area for forward propulsion. Also, by conforming the covers 58 and 60 to the cylindrical shape of the pod, more efficient forward propulsion is obtained.
  • the fan or air pressurizing units could have selfcontained gas generators, asfor example, after the nature of a turbofan engine, or in certain aspects a turbojet engine.
  • the fan or air pressurizing units could have selfcontained gas generators, asfor example, after the nature of a turbofan engine, or in certain aspects a turbojet engine.
  • the pod could have other than a cylindrical shape.
  • the pod could contain any number of propulsion units similarly arranged.
  • the rear fan unit could be in a horizontal position while the forward unit is in a vertical position.
  • the forward unit would be aerodynamically bypassed by opening passageways in the pod to introduce air to the second unit.
  • a propulsion system comprising:
  • first and second'air pressurizing units each having a duct through which air flows as it is pressurized
  • the means for selectively registering said ducts includes means for pivotally mounting said units on said pod and means for pivoting said units on their pivots between vertical and horizontal positions.
  • Apropulsion system as in claim 2 further comprismg: I
  • vane means in the discharge port which are pivotally mounted about axes perpendicular to the direction of forward thrust
  • said one unit is the upstream pressurizing unit moved to a horizontal position during transition
  • bypassing means comprise passageways extending at a low angle through said pod to its exterior intermediate said units, flap means normally closing the bypass passageways and means for swinging said flap means outwardly to provide said bypass function.
  • each of said units comprise a casing and v the means for pivotally mounting said units includes trunnion means having axes disposed at the intersection of the axes of said pod passageway and said ports, and
  • the pod, its passageway, the ducts and ports are circular in cross section;
  • the sealing means are spherical.
  • each of said units comprises a casing, a gas generator mounted remotely therefrom, a fan rotor having a tip-turbine, means for ducting hot gases from the gas generator to the tip-turbine and an annular discharge from the tip-turbine for the hot gases,
  • the pod, its passageways, the ducts and the ports are circular in cross section
  • the inlet ports are formed on a relatively large radii after the nature of the bellmouth
  • the means for pivotally mounting said units includes trunnion means having axes disposed at the intersection of the axes of the pod passageway and said ports, and v further including spherical means for sealing said unit ducts from said ports when they are registered from said pod passageway and sealing said ducts from said pod passageway when they are registered with said ports, a
  • bypass passageways extending at a low angle through said pod to its exterior intermediate said units to direct the fan discharge from the upstream unit to the exterior of the pod during transition
  • flap means normally closing the bypass passageways and means for swinging said flap means outwardly to provide said bypass function.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US51923A 1970-07-02 1970-07-02 Vtol propulsion system Expired - Lifetime US3700189A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US5192370A 1970-07-02 1970-07-02

Publications (1)

Publication Number Publication Date
US3700189A true US3700189A (en) 1972-10-24

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ID=21974229

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Application Number Title Priority Date Filing Date
US51923A Expired - Lifetime US3700189A (en) 1970-07-02 1970-07-02 Vtol propulsion system

Country Status (6)

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US (1) US3700189A (enExample)
BE (1) BE769445A (enExample)
CA (1) CA936514A (enExample)
DE (1) DE2132494A1 (enExample)
FR (1) FR2097150B1 (enExample)
GB (1) GB1349775A (enExample)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4474345A (en) * 1982-07-30 1984-10-02 Ltv Aerospace And Defence Company Tandem fan series flow VSTOL propulsion system
US5070955A (en) * 1990-05-04 1991-12-10 Aerovironment, Inc. Passively stable hovering system
US5082079A (en) * 1990-05-04 1992-01-21 Aerovironment, Inc. Passively stable hovering system
US6138946A (en) * 1997-08-07 2000-10-31 Saiz; Manuel Munuoz Device for lift and to reduce resistance to aircraft advance
US20070017209A1 (en) * 2005-07-20 2007-01-25 Welker Engineering Company Newtonian thrust cowl array
US20090250557A1 (en) * 2008-04-02 2009-10-08 Kodzo Obed Abledu Whirling Wheel Airborne Vehicles
US20100193643A1 (en) * 2008-12-31 2010-08-05 Sidelkovskiy Dmitriy B Lift fan system
DE102014213215A1 (de) 2014-07-08 2016-01-14 Lilium GmbH Senkrechtstarter
US20180362171A1 (en) * 2017-06-15 2018-12-20 Donald Butler Curchod Advanced drag reduction system for jet aircraft
CN115605397A (zh) * 2020-05-19 2023-01-13 保时捷股份公司（De） 在机翼上具有涵道风扇的飞行器
US20230331469A1 (en) * 2022-04-19 2023-10-19 Kihomac Advanced aerial, internal carriage-compatible travel pod
US12077325B2 (en) 2020-05-19 2024-09-03 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Aircraft
US20250282505A1 (en) * 2024-03-11 2025-09-11 Ideaforge Technology Limited Landing gears for aerial vehicle to minimise aerodynamic drag during flight

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE450480B (sv) * 1982-08-30 1987-06-29 Tech Gerete Und Entwicklungsge Styvvingad flygkropp
US5390877A (en) * 1993-06-25 1995-02-21 Rolls Royce Plc Vectorable nozzle for aircraft

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3066890A (en) * 1953-01-23 1962-12-04 Lockheed Aircraft Corp Supersonic aircraft
US3179353A (en) * 1958-02-04 1965-04-20 Ryan Aeronautical Co Jet powered ducted fan convertiplane
US3347496A (en) * 1966-05-03 1967-10-17 Ryan Aeronautical Co Engine air inlet system for supersonic v/stol aircraft
US3488018A (en) * 1968-03-13 1970-01-06 Us Navy Ducted propulsion units for vtol aircraft

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3066890A (en) * 1953-01-23 1962-12-04 Lockheed Aircraft Corp Supersonic aircraft
US3179353A (en) * 1958-02-04 1965-04-20 Ryan Aeronautical Co Jet powered ducted fan convertiplane
US3347496A (en) * 1966-05-03 1967-10-17 Ryan Aeronautical Co Engine air inlet system for supersonic v/stol aircraft
US3488018A (en) * 1968-03-13 1970-01-06 Us Navy Ducted propulsion units for vtol aircraft

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4474345A (en) * 1982-07-30 1984-10-02 Ltv Aerospace And Defence Company Tandem fan series flow VSTOL propulsion system
US5070955A (en) * 1990-05-04 1991-12-10 Aerovironment, Inc. Passively stable hovering system
US5082079A (en) * 1990-05-04 1992-01-21 Aerovironment, Inc. Passively stable hovering system
US6138946A (en) * 1997-08-07 2000-10-31 Saiz; Manuel Munuoz Device for lift and to reduce resistance to aircraft advance
US20070017209A1 (en) * 2005-07-20 2007-01-25 Welker Engineering Company Newtonian thrust cowl array
US7493914B2 (en) 2005-07-20 2009-02-24 Welker, Inc. Newtonian thrust cowl array
US20090137165A1 (en) * 2005-07-20 2009-05-28 Welker, Inc. Newtonian thrust cowl array
US8167235B2 (en) * 2008-04-02 2012-05-01 Kodzo Obed Abledu Whirling wheel airborne vehicles
US20090250557A1 (en) * 2008-04-02 2009-10-08 Kodzo Obed Abledu Whirling Wheel Airborne Vehicles
US20100193643A1 (en) * 2008-12-31 2010-08-05 Sidelkovskiy Dmitriy B Lift fan system
DE102014213215A1 (de) 2014-07-08 2016-01-14 Lilium GmbH Senkrechtstarter
US20180362171A1 (en) * 2017-06-15 2018-12-20 Donald Butler Curchod Advanced drag reduction system for jet aircraft
CN115605397A (zh) * 2020-05-19 2023-01-13 保时捷股份公司（De） 在机翼上具有涵道风扇的飞行器
US20230257104A1 (en) * 2020-05-19 2023-08-17 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Aircraft having a ducted fan in the airfoil
US12043367B2 (en) * 2020-05-19 2024-07-23 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Aircraft having a ducted fan in the airfoil
US12077325B2 (en) 2020-05-19 2024-09-03 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Aircraft
US20230331469A1 (en) * 2022-04-19 2023-10-19 Kihomac Advanced aerial, internal carriage-compatible travel pod
US11801991B1 (en) * 2022-04-19 2023-10-31 Kihomac, Inc. Advanced aerial, internal carriage-compatible travel pod
US20250282505A1 (en) * 2024-03-11 2025-09-11 Ideaforge Technology Limited Landing gears for aerial vehicle to minimise aerodynamic drag during flight

Also Published As

Publication number Publication date
CA936514A (en) 1973-11-06
GB1349775A (en) 1974-04-10
FR2097150B1 (enExample) 1974-03-22
FR2097150A1 (enExample) 1972-03-03
DE2132494A1 (de) 1972-01-13
BE769445A (fr) 1971-11-16

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