US 3570247 A
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