GB2469615A - Jet propulsion efflux outlets - Google Patents

Jet propulsion efflux outlets Download PDF

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Publication number
GB2469615A
GB2469615A GB9006310A GB9006310A GB2469615A GB 2469615 A GB2469615 A GB 2469615A GB 9006310 A GB9006310 A GB 9006310A GB 9006310 A GB9006310 A GB 9006310A GB 2469615 A GB2469615 A GB 2469615A
Authority
GB
United Kingdom
Prior art keywords
outlet
powerplant
aircraft
nozzle
fuselage
Prior art date
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.)
Granted
Application number
GB9006310A
Other versions
GB9006310D0 (en
GB2469615B (en
Inventor
Peter Angus
K Rogers
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
British Aerospace PLC
BAE Systems PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by British Aerospace PLC, BAE Systems PLC filed Critical British Aerospace PLC
Priority to GB9006310A priority Critical patent/GB2469615B/en
Publication of GB9006310D0 publication Critical patent/GB9006310D0/en
Anticipated expiration legal-status Critical
Publication of GB2469615A publication Critical patent/GB2469615A/en
Application granted granted Critical
Publication of GB2469615B publication Critical patent/GB2469615B/en
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/008—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector in any rearward direction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
    • 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
    • B64C29/0041—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 jet motors
    • 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
    • B64C29/0041—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 jet motors
    • B64C29/005—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 jet motors the motors being fixed relative to the fuselage
    • 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
    • B64C29/0041—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 jet motors
    • B64C29/0066—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 jet motors with horizontal jet and jet deflector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/004—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector by using one or more swivable nozzles rotating about their own axis
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An efflux outlet for a V/STOL aircraft having a duct10including an arcuate portion14which terminates in a spherical nozzle assembly15forwardly of the powerplant. The assembly includes a spherical bearing16and an efflux nozzle17having smooth contours18in order to give smooth efflux flow in either a vertical or deflected flow configuration. The assembly allows a smooth transition to or from fully wing-supported flight and contributes minimally to the drag of the aircraft. The nozzle does not protrude beyond fuselarge21in the vertical or forward flight positions.

Description

Jet Propulsion Efflux Outlets This invention relates to jet propulsion efflux outlet assemblies and to aircraft incorporating such assemblies.
V/STOL aircraft have been proposed which incorporate a RALS (remote augmented lift system). Such aircraft include a downwardly directed outlet assembly located forwardly of the powerplant which is supplied with reheated fan air during V/STOL modes of flight. Reheat has been essential in earlier RALS proposals because, without reheat, the flow delivered to the outlet assembly would be insufficient to develop the required thrust. It will be understood that the reheat system means that the outlet assembly is of large diameter and bulky to accommodate the reheat equipment, fuel supply and burner arrangements and to withstand and reheat temperatures (typically in excess of 1000°C). In a modern fighter aircraft space and weight are at a premium, and the additional space and weight demands of a system incorporating a vectorable RALS nozzle mean that such a system is difficult to install. In existing RALS proposals, it is thus not practical to vary the direction in which ef flux exhausts from the outlet assembly.
With the new generation of variable by-pass ratio engines and the mass-flow of by-pass air that can be delivered is substantially increased and studies by the applicants have shown that such engines may be adapted to provide a remote lift system which does not require reheat to provide the desired remote thrust. The applicants have designed an arrangement which allows a smooth transition to or from fully wing supported flight and which contributes minimally to the drag of the aircraft, whilst occupying a small volume in the aircraft body.
One such arrangement is described in our co-pending British Patent application 8905506-9 in which there is provided a jet propulsion ef flux outlet assembly comprising delivery duct means and an outlet nozzle means mounted for telescopic movement with respect to said delivery duct means between a retracted and an extended position. That same patent application provides an aircraft of the vertical and short take-off type having a powerplant with spaced forward and rearward outlet assemblies for receiving at least a part of the ef flux from the powerplant. The forward outlet assembly comprises a delivery duct and an outlet nozzle for generating at least a component of lift and means for varying the direction in which the ef flux exhausts from the nozzle outlet.
The outlet nozzle assembly of that co-pending application is of substantially arcuate form longitudinally and includes a telescopic duct position and movable about a pivot axis between a retracted position in which it does not protrude from the lower aircraft surface and an extended position in which it protrudes from an aperture in the aircraft lower surface. In the retracted position the outlet nozzle exhausts substantially vertically downwards and in the extended position it lies at about 20° to the horizontal to give a rearward component of thrust.
It is the object of the present invention to provide an alternative outlet nozzle assembly and which over its range of movement is substantially contained within the fuselage lower profile.
According to one aspect of the present invention there is provided a jet propulsion ef flux outlet assembly for a V/STOL Aircraft comprising delivery duct means and an outlet nozzle means mounted for pivotal rotation with respect to said delivery duct means whereby the direction in which said ef flux exhausts may be angularly adjusted and in which said outlet nozzle means over its range of movement is substantially contained within the fuselage lower profile.
According to further aspect of the present invention there is provided an aircraft of at least one of the vertical and short take-off type, including a powerplant longitudinally, spaced forward and rearward outlet assemblies each for receiving at least a part of the ef flux from said powerplant, wherein said forward outlet assembly is spaced generally forwardly of said powerplant and comprises delivery duct means, an outlet nozzle means for generating at least a component of lift and means for varying the direction in which the ef flux exhausts from said nozzle outlet means, characterised in that over its range of movement said outlet nozzle is substantially contained within the fuselage lower profile.
One embodiment of the present invention will now be described by way of example only and with reference to the following drawings in which:-Figure 1 is a side view of the forward part of a V/STOL Aircraft incorporating the outlet assembly of Figure 2.
Figure 2 is a side view of the jet propulsion ef flux outlet assembly of our co-pending patent application 8905806-9.
Figures 3-5 inclusive illustrates in diagrammatic side view the efflux outlet assembly of this present invention in three operational settings.
Figure 6 is a diagrammatic sectional view through the nozzle assembly taken along a line 6 -6 in Figure 4.
Referring to the drawings Figure 1 illustrates the forward part of a V/STOL aircraft in which a forward delivery duct 10 terminates forwardly in a substantially arcuate telescopic ef flux outlet nozzle assembly 11 and as in Figure 2 in which the telescopic duct portion 12 located about a pivot axis 13 is movable between a retracted position 12a to give a substantially vertical thrust and extended position 12b giving an exhaust flow at about 20° to the horizontal.
The present invention is described by reference to Figures 3 -6 inclusive in which the forward delivery duct
S
terminates forwardly in a substantially arcuate duct portion 14 connected to a spherical ef flux nozzle assembly 15. This includes a spherical bearing 16 suitably mounted off the fuselage structure or duct support structure (not shown) and an ef flux nozzle 17 having smoothly curving contours 18 to give smooth ef flux flow in either the vertical or deflected flow configurations. The efflux nozzle 17 is movable by suitable means not shown about a transverse pivot axis 19 lying on the duct centre line 20.
It will be noted the nozzle assembly 15 is so positioned that in the vertical and fully deflected thrust configuration it never protrudes outside the fuselage lower profile 21 but in order to achieve the rearward component of thrust the fuselage is suitably shaped as illustrated at 22.
In the present embodiment, as shown in Figure 5 this beneficial nozzle configuration permits a maximum angle of 60°deflected thrust.

Claims (3)

  1. Claims 1. A jet propulsion ef flux outlet assembly for a V/STOL Aircraft comprising delivery duct means and an outlet nozzle means mounted for pivotal rotation with respect to said delivery duct means whereby the direction in which said ef flux exhausts may be angularly adjusted and in which said outlet nozzle means over its range of movement is substantially contained within the fuselage lower profile.
  2. 2. An aircraft of at least one of the vertical and short take-off type, including a powerplant, longitudinally spaced forward and rearward outlet assemblies each for receiving at least a part of the efflux from said powerplant, wherein said forward outlet assembly is spaced generally forwardly of said powerplant and comprises delivery duct means, an outlet nozzle means for generating at least a component of lift and means for varying the direction in which the efflux exhausts from said nozzle outlet means, characterised in that over its range of movement said outlet nozzle is substantially contained within the fuselage lower profile.Amendments to the claims have been filed as follows 1. An Aircraft of at least one of the vertical and short take-off type, including a fuselage housing a powerplant and longitudinally spaced forward and rearward outlet assemblies each for receiving a part of the efflux from said powerplant, wherein said forward outlet assembly is spaced generally forwardly of said powerplant and comprises delivery duct means connecting said forward outlet assembly with said powerplant and, pivotally attached to said delivery duct means and adjacent a forward opening in said fuselage, outlet nozzle means for varying the direction in which that part of the ef flux received by the forward outlet assembly exhausts from said nozzle outlet means, a profile of said forward opening and the location of said outlet nozzle means being such that over its range of pivotal movement said outlet nozzle means Is substantially contained within the lower profile of the fuselage.2. An aircraft, as claimed in claim 1, and wherein the outlet nozzle means is a spherical ef flux nozzle carried in a spherical bearing mounted off the fuselage or duct support structure and moveable about a pivot axis transverse to a centre line of said delivery duct means.
  3. 3. An aircraft substantially as hereinbefore described and with reference to Figures 1 to 6 of the accompanying drawings.
GB9006310A 1990-03-21 1990-03-21 Jet Propulsion Efflux Outlets Expired - Lifetime GB2469615B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9006310A GB2469615B (en) 1990-03-21 1990-03-21 Jet Propulsion Efflux Outlets

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9006310A GB2469615B (en) 1990-03-21 1990-03-21 Jet Propulsion Efflux Outlets

Publications (3)

Publication Number Publication Date
GB9006310D0 GB9006310D0 (en) 2009-12-16
GB2469615A true GB2469615A (en) 2010-10-27
GB2469615B GB2469615B (en) 2011-03-23

Family

ID=41435121

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9006310A Expired - Lifetime GB2469615B (en) 1990-03-21 1990-03-21 Jet Propulsion Efflux Outlets

Country Status (1)

Country Link
GB (1) GB2469615B (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB985944A (en) * 1961-05-25 1965-03-10 Ludwig Bolkow Improvements in vertical take-off and landing aircraft
GB1101042A (en) * 1964-04-16 1968-01-31 M A N Turbo G M B H Improvements in or relating to turbojet engines for vertical take-off and landing aircraft

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB985944A (en) * 1961-05-25 1965-03-10 Ludwig Bolkow Improvements in vertical take-off and landing aircraft
GB1101042A (en) * 1964-04-16 1968-01-31 M A N Turbo G M B H Improvements in or relating to turbojet engines for vertical take-off and landing aircraft

Also Published As

Publication number Publication date
GB9006310D0 (en) 2009-12-16
GB2469615B (en) 2011-03-23

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Date Code Title Description
PE20 Patent expired after termination of 20 years

Expiry date: 20100320