GB2200878A - Improvements in or relating to aircraft and powerplant combinations - Google Patents
Improvements in or relating to aircraft and powerplant combinations Download PDFInfo
- Publication number
- GB2200878A GB2200878A GB08729684A GB8729684A GB2200878A GB 2200878 A GB2200878 A GB 2200878A GB 08729684 A GB08729684 A GB 08729684A GB 8729684 A GB8729684 A GB 8729684A GB 2200878 A GB2200878 A GB 2200878A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- powerplant
- wing
- cowl
- combination
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
- B64C7/02—Nacelles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
Description
4 t 1 i 2" 0 0 8 7 8 L 1 IMPROVEMENTS IN 01 RELATING TO AIRCRAFT AND
POWERPLANT COMBINATIONS This invention concerns the mounting oil a fluid flow powerplant on an aircraft.
It is the accepted practice to connect a fluid flow powerplant via a pylon, to the underside of an aircraft wing. Moreover, it is the accepted practice, to position the pylon at bop dead centre of the powerplant, in alignment with the longitudinal axis thereof.
Virtually all air-craft which have such powerplants mounted thereon in the manner mentioned hereinbefore, also share a common wing plan i.e. the wings are swept ba-ckwards. The design has many advantages but also a disadvantage, and that is the airflow tends to veer from the leading edges of the wings and spread spanwise thereof, away from the aircraft fuselage, rather than flowing entirely chordwise. There results a piling up of air against the inboard side-of the pylon, in the narrow space between the wing undersurface and the top of the powerplant cowl. By inboard is meant that side surface of the pylon which is nearest the aircraft fuselage. Local flow velocity increases occur, which are of a nature which generates shock waves in the area.
The present invention seeks to provide an improved combination of an aircraft and its fluid flow powerplant.
According to the present invention a combination comprises an aircraft, a fluid flow powerplant connected via link means to the underside of the wing structure of said aircraft and wherein the improvement -comprises the provision of link connecting points on one side only of the longitudinal centreline of the powerplant, said one side being inboard with respect to the aircraft fuselage and an aerodynamically shaped box structure enclosing said links, said box structure including a wall which is inboard with respect to the aircraft fuselage and lies in a plane, which is at least substantially normal to the wing undersurface.
2 1 The invention will now be described, by way of example and with reference to theaccompanying drawings in which:
Figure 1 is a part cross-sectional view on line 1-1 of Figure 2.
Figure 2 is a view in the direction of arrow 2 in Figure 1.
Figure 3 is a view in the direction of arrow 3 in Figure 1 and Figure 4 is a pictorial part view in the general direction of arrow 4 in Figure 3.
Referring to Figure 1. A ducted fan gas turbine engine 10 is supported from the wing 12 of an aircraft. The support is achieved as follows. A pair of links 14 and 16 support the weight of the ducted fan gas turbine engine 10 and resist torque loads. Each link 14 and l6 has one end pinned to locally strengthened structure which forms part of the fan cowl 18 and the other end pinned to a front main beam 20 of the wing 12. The pinned connections ard only diagrammatically shown as centre marks since such joints are well known in the ar.t.
A further elongate link 22 has one end pinned to the aforementioned structure.which forms part of the fan cowl 18 and the other end pinned to a rear main beam 24 of the wing 12. The terms of art used to describe the link 22 is "drag link" and its function is to transmit the thrust loads of the engine 10 to the main beam 24 in the form of a tensible load, hence Mrag" which results in the _forward movement of the associated aircraft. Again, the connections of the link 22 are diagrammatic, such joining being well known.
A further, redundant link connected between t-he front main reinforced structure of the cowl 18.
216 is provided and beam 20 and the Its purpose is to-at least temporarily -transmit those loads normally transmitted by the link 22, in the event that the latter link fails.
1 3 1.
A sheet metal structure 28 encloses the links and provides an aerodynamically shaped box around which ambient air flows with minimum turbulence, during flight of the associated aircraft. The box structure 28 extends forwardly to a position adjacent the leading edge of the air intake 30 of the cowl 18. The extension is shown in dotted lines because the links 14,16,18,22 and 24 are all offset, behind a vertical plane which includes the centreline of the engine 10 as viewed in Figure 1. This is more clearly seen in Figures 2 to 4 inclusive. As the box structure 28 encloses the links, if follows that the box structure 2B is also offset in a manner similar thereto.
It is essential to the efficacy of the invention, that the offset is tothat side of the engine 10 which is i board with respect to the aircraft fuselage 32 (Figures 3 and 4). This is so that if that ambient air which on reaching the leading edge of the wing 12 and flows t.,b.ereu-n.der, starts to 1Curn towards the wing tip as indicated by the arrows 34 (Figure 2) rather than travel chordwise of the wing, the inboard side of the box structure 28 stops it piling up between the cowl 18 and the underside of the wing 12. The -offset mounting thus obviates what -has been an accepted through highly undesirable condition, which generated local high increases in flow velocity with accompanying shock waves.
Swept wing aircraft i.e. aircraft, the wings of which are angled in a rearward direction so that the wing tips are rearwards of the wing roots, always display the sideways turning airflow characteristic. Subsequently, present invention has considerable efficacy if utilised on such aircraft.
The box structure 28 has an outboard sidewall 35 (Figures 1 to 4), an inboard sidewall 36 (Figures 2 to 4) and an underside 38 (Figures 1 to 4), the latter wall forming a propulsive fluid expansion surface which extends from the outer periphery of the fan nozzle 40, to a position intermediate the fan nozzle 40 and the downst ream end of the box structure 28.
4 In the present example, the propulsive fluid is air which has been worked upon by the ducted fan of the ducted fan, gas turbine engine 10. The invention is not restricted to ducted fan gas turbine engines. A gas-. turbine engine of the kind that provides propulsive" forces only from the exhausted products of combustion may be connected to the wing of an associated aircraft by the mouting described and claimed in this specification.
Referring now to Figure 3, the cowl 18 of the ducted fan is of double walled construction and that part of the double wall to which the ends of the links 14,16,22 and 26 are connected, is reinforced relative to the remainder thereof. The cowl of a gas turbine engine would also be strengthened at a corresponding location, should such an engine be utilised and mounted in the manner described ore.
hereinbef The core gas generator which drives the ducted fan is supported within a casing 42 via struts 44 and 44a from the fan cowl 18. Those struts 44a which are in the vicinity of the strengthened portion of cowl 18, and that portion of the casing 42 which encloses the core gas generator ' 42 and through which the inner ends of the struts 44a pass to -connections (not shown) with the core gas generator proper,are all appropriately reinforced, so as to enable working loads to be passed therethrough via the reinforced portion of the cowl 18 and links 14,16,22 and 2.6, to the respective beams 20 and 24.
It is -known, to support a ducted fan gas turbine engine about its top dead centre from an aircraft wing main beam, by connecting struts which extend radially from the core gas generator to the cowl of the fan. The known arrangement obviates the need to us-e a drag link which normally extends from the rearward main beam of the wing, across the fan duct, to connect with the core gas generator. Consequently, there is no need to extend the aerodynamic fairing across the fan duct to cover the drag link. Flow efficiency losses are thus obviated.
4 arrangement of the present of an engine such that ir from the present invention on only one side of 'the either side, can be avoided connecting points resnective wina The present invention utilises a drag link 22. Its connection to the cowl 18 however, also avoids the need to extend the aerodynamic box structure 28 across the fan duct. It is thus seen that not only does the present invention obviate losses which are attributed to flow conditions between the cowl 18 and the underside of the wing 12, it also enables maintenance of---theadvantages gained by the known mounting arrangement.
"Handing" of an engine which incorporates the linkage invention i.e. the cons-truction order to achieve the benefit it must be fitted to the wing aircraft fuselage rather than by providing mirror image link on both sides of the cowl 18 and on the beams on each side of the aircraft. However, handed blanking sheets 'oT appropriate curvature would have to be provided to cover those parts of the cowl 18 which would normally be covered by the box structure 28. Further, handed box structures 28 would also have to be provided.
6
Claims (4)
1. In combination an aircraft, a fluid flow powerplant connected via link means to the underside of the wing structure of said aircraft and wherein the improvement comprises the provision -of link connecting points on one side only of the longitudinal centreline of the powerplant, said one side being inboard with respect to the aircraft fuselage and an aerodynamically shaped box structure enclosing said links, said box structure enclosing said links, said_box structure including a wall which is inboard with respect to the aircraft fuselage and lies in a plane which is at least substantially normal to the wing undersurface.
2. The combination as claimed in claim 1 wherein said inboard wall is substantially tangential to the outer surface of a cowl which surrounds the powerplant.
3. The combination as claimed in claim 1 or claim 2 wherein the powerplant is a ducted fan gas turbine engine.
4. The combination of claim 3 wherein said cowl defines the outer wall.of the fan duct.
t.
Published 1988 at The Patent Office, State House. 6671 High F-ciborn,. uondon WC' IR 4TP. Further copies may be ortane:! from ThePatent Office.
SaJes Branch, St Mary Cray, Orpington, Kent BR5 3RD, Printed by Mull1plex techniques ltd. St Mary C ray, Kent. Con 1/87.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US07/011,215 US4801058A (en) | 1987-02-05 | 1987-02-05 | Aircraft and powerplant combinations |
Publications (3)
Publication Number | Publication Date |
---|---|
GB8729684D0 GB8729684D0 (en) | 1988-02-03 |
GB2200878A true GB2200878A (en) | 1988-08-17 |
GB2200878B GB2200878B (en) | 1990-09-19 |
Family
ID=21749360
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB8729684A Expired - Fee Related GB2200878B (en) | 1987-02-05 | 1987-12-21 | Improvements in or relating to aircraft and powerplant combinations |
Country Status (5)
Country | Link |
---|---|
US (1) | US4801058A (en) |
JP (1) | JPS63195099A (en) |
DE (1) | DE3800512A1 (en) |
FR (1) | FR2610592B1 (en) |
GB (1) | GB2200878B (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5102069A (en) * | 1989-12-12 | 1992-04-07 | British Aerospace Public Limited Company | Aircraft wing pylon extensions for minimized aerodynamic penalties |
WO1995017334A1 (en) * | 1993-12-21 | 1995-06-29 | United Technologies Corporation | Aircraft wing/nacelle combination |
FR2926536A1 (en) * | 2008-01-23 | 2009-07-24 | Snecma Sa | ATTACHING A PROPULSIVE SYSTEM TO A STRUCTURE ELEMENT OF AN AIRCRAFT |
FR2935353A1 (en) * | 2008-09-03 | 2010-03-05 | Airbus France | MAT FOR THE SUSPENSION OF A TURBOMOTEUR UNDER AN AIRCRAFT WING |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2622507B1 (en) * | 1987-10-28 | 1990-01-26 | Snecma | |
JP2606289Y2 (en) * | 1993-06-07 | 2000-10-10 | 富士重工業株式会社 | Aircraft nacelle equipment |
JP3714722B2 (en) * | 1996-05-09 | 2005-11-09 | 本田技研工業株式会社 | Peeling suppression device |
US5934607A (en) * | 1997-01-21 | 1999-08-10 | Lockheed Martin Corporation | Shock suppression supersonic aircraft |
US7216922B2 (en) * | 2005-06-29 | 2007-05-15 | The Boeing Company | Fairing panel retainer apparatus |
FR2892999B1 (en) * | 2005-11-08 | 2008-02-01 | Airbus France Sas | AIRCRAFT COMPRISING A CENTRAL CARRIAGE PRESSURE ADJUSTER VESSEL BY LOCAL GEOMETRIC DEFORMATIONS |
US8720815B2 (en) | 2010-04-27 | 2014-05-13 | Rolls-Royce Corporation | Aircraft propulsion system |
US8740139B1 (en) | 2012-04-23 | 2014-06-03 | The Boeing Company | Leading edge snag for exposed propeller engine installation |
US9211955B1 (en) * | 2012-12-10 | 2015-12-15 | The Boeing Company | Methods and apparatus for supporting engines and nacelles relative to aircraft wings |
GB201809822D0 (en) | 2018-06-15 | 2018-08-01 | Rolls Royce Plc | Gas turbine engine |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3031157A (en) * | 1958-11-05 | 1962-04-24 | Billie J Varden | Controllable mount for aircraft power plant |
GB1069781A (en) * | 1963-02-14 | 1967-05-24 | British Aircraft Corp Ltd | Improvements in aeroplanes having ducted fan,by-pass or other jet propulsion engines |
US3229933A (en) * | 1964-06-05 | 1966-01-18 | Gen Electric | Cruise fan powerplant |
GB1599730A (en) * | 1978-05-30 | 1981-10-07 | Greenmeadow Engs Ltd | Attachment of masses to aircraft and spacecraft |
-
1987
- 1987-02-05 US US07/011,215 patent/US4801058A/en not_active Expired - Lifetime
- 1987-12-21 GB GB8729684A patent/GB2200878B/en not_active Expired - Fee Related
-
1988
- 1988-01-11 DE DE3800512A patent/DE3800512A1/en not_active Withdrawn
- 1988-01-20 JP JP63010551A patent/JPS63195099A/en active Pending
- 1988-01-25 FR FR8800776A patent/FR2610592B1/en not_active Expired - Fee Related
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5102069A (en) * | 1989-12-12 | 1992-04-07 | British Aerospace Public Limited Company | Aircraft wing pylon extensions for minimized aerodynamic penalties |
WO1995017334A1 (en) * | 1993-12-21 | 1995-06-29 | United Technologies Corporation | Aircraft wing/nacelle combination |
FR2926536A1 (en) * | 2008-01-23 | 2009-07-24 | Snecma Sa | ATTACHING A PROPULSIVE SYSTEM TO A STRUCTURE ELEMENT OF AN AIRCRAFT |
EP2082960A1 (en) | 2008-01-23 | 2009-07-29 | Snecma | Attachment of a propulsion system to an aircraft structural element |
RU2483002C2 (en) * | 2008-01-23 | 2013-05-27 | Снекма | Aircraft power plant attachment to aircraft structural element |
US8827203B2 (en) | 2008-01-23 | 2014-09-09 | Snecma | Connecting a propulsion system to a structural element of an aircraft |
FR2935353A1 (en) * | 2008-09-03 | 2010-03-05 | Airbus France | MAT FOR THE SUSPENSION OF A TURBOMOTEUR UNDER AN AIRCRAFT WING |
US8336813B2 (en) | 2008-09-03 | 2012-12-25 | Airbus Operations Sas | Engine pylon for the suspension of a turbo engine under an aircraft wing |
Also Published As
Publication number | Publication date |
---|---|
JPS63195099A (en) | 1988-08-12 |
FR2610592B1 (en) | 1993-12-24 |
US4801058A (en) | 1989-01-31 |
GB8729684D0 (en) | 1988-02-03 |
GB2200878B (en) | 1990-09-19 |
DE3800512A1 (en) | 1988-08-18 |
FR2610592A1 (en) | 1988-08-12 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20011221 |