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Publication numberUS3570247 A
Publication typeGrant
Publication dateMar 16, 1971
Filing dateSep 11, 1969
Priority dateSep 14, 1968
Also published asDE1946592A1, DE1946592B2
Publication numberUS 3570247 A, US 3570247A, US-A-3570247, US3570247 A, US3570247A
InventorsDenning Ralph Murch, Lewis William James, Nightingale Douglas John, Wiltshire Reginald Harold
Original AssigneeRolls Royce
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Jet nozzle thrust spoiling and thrust reversing mechanism
US 3570247 A
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Description  (OCR text may contain errors)

JET NOZ'ZLE THRUST SPOILING AND THRUST REVEHSI'NG MECHANISM 4 Sheets-Sheet 1 Filed Sept.

March 16, 1971 Filed Sept. 11, 1969 R. M. DENNING ETAP. i JET NOZZLE THRUST SPOILING AND THRUST REVERS ING 11H2 CHANISM Y 4 Sheets-Sheet 2 Wim-*y March 16, 1971 l R M, DENNlNG ETAL 3,570,247

JET NGZZLE THRUST SPOILING AND THRUST REVERSING-MECHNISM Filed sept. 11, 1969 4 sheets-sheet s FIG. 3.

IIIIIIIIIIII F March 16, 1971 R. M. DENNING ET AL 3,570,247

J' ET NOZZLE THRUST SPOILING AND THRUST REVERSING MECHANISM Filed Sept. 11, 1969 4 Sheets-Sheet L In t ATU/f.

United States Patent Oil 3,570,247, Patented Mar. 16, 1971 tice ABSTRACT F THE DISCLOSURE The disclosure of this invention pertains to a jet nozzle for jet propulsion engines, the nozzle having a centre body provided with aps movable to` divert the tlow of the gases. Each tlap is supported on the centre body by a first and a second link, the irst link engaging the ap at 3 Claims stream ends thereof and being adapted to move the np away from a stowed position on the body, the second link being adapted to pivot the flap about said point into an obliquely rearward position for thrust-spoiling or an obliquely forward position for thrust-reversing.

This invention relates to a sion engine.

It is known to provide such nozzles with a centre body on which are supported aps adapted to be moved into the jet stream for the purpose of deilecting the gases from their normal rearward direction. However, in the known jet nozzle for a jet propulpivoted.

According to the present invention there is provided in a jet propulsion engine a jet nozzle comprising a centre body and flow-diverting tiaps pivoted thereto, characterthe ap into an obliquely rearward or thrust-spoiling posithrust-reversing the large range of pivotal movement which is required if the flap is pivoted about one or other of its ends. Particularly, there arises the advantage of the ap not having to project unduly far from the centre body so that good clearance can be obtained between the ilap and the ground during the landing of an aircraft employing such a nozzle in its propulsion plant.

An example of a jet nozzle according to this invention will now be described with reference to the accompanying drawings wherein:

FIGS. 1, 2 and 3 are sectional elevations of the nozzle and show the nozzle in first, second and third operational positions, respectively.

FIG. 4 is a perspective view of the nozzle.

The nozzle comprises a main duct 10 divided into two branch ducts 11 by a centre body 12. An exhaust flow from a jet propulsion engine (not shown) to the duct 10 is exhausted to atmosphere through the ducts 11. The ducts 11 are of rectangular cross-sectior1 and are each defined by an outer wall 13, a wall 14 of the centre body 12 and two oppositeside walls 15. The wall 13 is exthe How has the direction of arrows 2l, i.e. obliquely upstream to and away from the direction 17.

In the inoperative position (FIG. l) the flap 19 is situated in a recess 23 of the centre body 12 and is tlush with the wall 14 so as to cooperate therewith in guiding the gas llow over the centre body.

Means for moving the flap from the first to the second position comprise a piston and cylinder tluid pressure and downstream ends 28 and 29 respectvely, of the Hap. The llap is supported on the body 12 for arcuate movement about a pivot 30 lying adjacent disection 20.

For the purpose of its movement into the third position the Hap is supported on the links 26 for movement about the to turn the ap into the third position.

The connection between the flap and the pivot 30 is the ilap in a. position parallel to thelink 36 as if the flap were a part of that link. During movement of the flap between the second and third positions, i.e. the movement about the pivot 27, the links 36, 26 cooperate to retain the pivot 27 in the FIG. 2 position while the motor 33 causes the movement of the ap between the second and third positions and retains lthe ap in either of those positions.

are provided for moving the extension between said two FOREIGN PATENTS POS'UOHS *hfev 1,035,814 4/1953 France Z39-265.19

References Clfed 1,262,596 4/1961 France 239-265.19

UNITED STATES PATENTS 2,822,996 2/1958 von zborowski 50`23ox 5 CLARENCE R- GORDON Primary Examiner 3,241,313 3/1966 Aldel'SOIl 3,280,561 10/1966 Kumey 239-265.192(

3,507,450 4/1970 Weigmann 239-265.19X 239 265'19

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3739987 *Jan 7, 1972Jun 19, 1973Rech Appliquees Serap Soc EtArrangement of jacks for controlling flaps and its application to the control of a jet pipe
US3774868 *Dec 11, 1972Nov 27, 1973Goetz GIntegrated nozzle
US3824946 *Aug 30, 1972Jul 23, 1974Kelly IWater jet propulsion unit
US3831376 *Feb 5, 1973Aug 27, 1974Aeritalia SpaThrust reverser
US4037405 *Sep 30, 1975Jul 26, 1977United Technologies CorporationTwo dimensional nozzle with rotating plug
US4050631 *Mar 26, 1976Sep 27, 1977The Boeing CompanyJet engine nozzle for controlling the direction of thrust
US4088270 *Mar 31, 1976May 9, 1978The United States Of America As Represented By The Administrator Of The National Aeronautics And Space AdministrationTwo dimensional wedge/translating shroud nozzle
US4147027 *Jun 28, 1977Apr 3, 1979Grumman Aerospace CorporationThrust reverser nozzle
US4175385 *Dec 12, 1977Nov 27, 1979General Electric CompanyThrust reverser for an asymmetric aircraft exhaust nozzle
US4865256 *Nov 1, 1988Sep 12, 1989Societe Anonyme Dite Hispano-SuizaTurbojet engine having a thrust reverser door and variable exhaust cross-section
US5699966 *Mar 31, 1980Dec 23, 1997General Electric CompanyExhaust nozzle of a gas turbine engine
US6681561Dec 22, 2000Jan 27, 2004Saab AbOutlet device for a jet engine
US7568348Nov 28, 2005Aug 4, 2009Aerojet-General CorporationNozzle assembly for rocket and ramjet applications
US8561385Oct 13, 2010Oct 22, 2013Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V.Flying object
WO2001046580A1 *Dec 22, 2000Jun 28, 2001Berglund HansAn outlet device for a jet engine
Classifications
U.S. Classification60/230, 62/305, 239/265.19
International ClassificationF02K1/58, F02K1/00
Cooperative ClassificationF02K1/58
European ClassificationF02K1/58