US3570247A - Jet nozzle thrust spoiling and thrust reversing mechanism - Google Patents
Jet nozzle thrust spoiling and thrust reversing mechanism Download PDFInfo
- Publication number
- US3570247A US3570247A US857029A US3570247DA US3570247A US 3570247 A US3570247 A US 3570247A US 857029 A US857029 A US 857029A US 3570247D A US3570247D A US 3570247DA US 3570247 A US3570247 A US 3570247A
- Authority
- US
- United States
- Prior art keywords
- thrust
- spoiling
- link
- flap
- nozzle
- 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.)
- Expired - Lifetime
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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
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/56—Reversing jet main flow
- F02K1/58—Reversers mounted on the inner cone or the nozzle housing or the fuselage
Definitions
- 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.
- 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.
- 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.
- 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.
- 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.
- 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.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Lift Valve (AREA)
Abstract
THE DISCLOSURE OF THIS INVENTION PERTAINS TO A JET NOZZLE FOR JET PROPULSION ENGINES, THE NOZZLE HAVING A CENTRE BODY PROVIDED WITH FLAPS MOVABLE TO DIVERT THE FLOW OF THE GASES. EACH FLAP IS SUPPORTED ON THE CENTER BODY BY A FIRST AND A SECOND LINK, THE FIRST LINK ENGAGING THE FLAP AT A POINT INTERMEDIATE BETWEEN THE UPSTREAM AND DOWNSTREAN ENDS THEREOF AND BEING ADAPTED TO MOVE THE FLAP AWAY FROM A STOWED POSITION ON THE BODY, THE SECOND LINK BEING ADAPTED TO PIVOT ON THE BODY, THE SECOND LINK OBLIQUELY REARWARD POSITION FOR THRUST-SPOILING OR AN OBLIQUELY FORWARD POSITION FOR THRUST-REVERSING.
Description
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
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4382468 | 1968-09-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3570247A true US3570247A (en) | 1971-03-16 |
Family
ID=10430458
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US857029A Expired - Lifetime US3570247A (en) | 1968-09-14 | 1969-09-11 | Jet nozzle thrust spoiling and thrust reversing mechanism |
Country Status (4)
Country | Link |
---|---|
US (1) | US3570247A (en) |
DE (1) | DE1946592B2 (en) |
FR (1) | FR2018120A1 (en) |
GB (1) | GB1253071A (en) |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3739987A (en) * | 1971-01-08 | 1973-06-19 | Rech Appliquees Serap Soc Et | Arrangement of jacks for controlling flaps and its application to the control of a jet pipe |
US3774868A (en) * | 1972-12-11 | 1973-11-27 | G Goetz | Integrated nozzle |
US3824946A (en) * | 1972-08-30 | 1974-07-23 | D Macardy | Water jet propulsion unit |
US3831376A (en) * | 1973-02-05 | 1974-08-27 | Boeing Co | Thrust reverser |
US4037405A (en) * | 1975-09-30 | 1977-07-26 | United Technologies Corporation | Two dimensional nozzle with rotating plug |
US4050631A (en) * | 1976-03-26 | 1977-09-27 | The Boeing Company | Jet engine nozzle for controlling the direction of thrust |
US4088270A (en) * | 1976-03-31 | 1978-05-09 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Two dimensional wedge/translating shroud nozzle |
US4147027A (en) * | 1976-04-06 | 1979-04-03 | Grumman Aerospace Corporation | Thrust reverser nozzle |
US4175385A (en) * | 1977-12-12 | 1979-11-27 | General Electric Company | Thrust reverser for an asymmetric aircraft exhaust nozzle |
US4865256A (en) * | 1987-11-05 | 1989-09-12 | Societe Anonyme Dite Hispano-Suiza | Turbojet engine having a thrust reverser door and variable exhaust cross-section |
US5699966A (en) * | 1980-03-31 | 1997-12-23 | General Electric Company | Exhaust nozzle of a gas turbine engine |
WO2001046580A1 (en) * | 1999-12-22 | 2001-06-28 | Saab Ab | An outlet device for a jet engine |
AU741469B2 (en) * | 1997-07-24 | 2001-11-29 | Hispano-Suiza Aerostructures | Turboblower thrust reverser |
US20070119151A1 (en) * | 2005-11-28 | 2007-05-31 | Aerojet-General Corporation | Nozzle assembly for rocket and ramjet applications |
US20110083418A1 (en) * | 2008-04-25 | 2011-04-14 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Flying object |
US20140271169A1 (en) * | 2012-07-25 | 2014-09-18 | Rohr, Inc. | Nacelle for a high bypass ratio engine with multiple flow paths |
US20160053718A1 (en) * | 2014-08-19 | 2016-02-25 | The Boeing Company | Thrust Reverse Variable Area Fan Nozzle |
RU2758875C1 (en) * | 2020-07-23 | 2021-11-02 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Output apparatus of a flat jet nozzle |
RU2758867C1 (en) * | 2020-07-23 | 2021-11-02 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Output apparatus of a flat jet nozzle |
RU2786871C1 (en) * | 2022-02-17 | 2022-12-26 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Exhaust unit of a flat jet nozzle with a central body |
-
1968
- 1968-09-14 GB GB4382468A patent/GB1253071A/en not_active Expired
-
1969
- 1969-09-11 US US857029A patent/US3570247A/en not_active Expired - Lifetime
- 1969-09-12 FR FR6931064A patent/FR2018120A1/fr not_active Withdrawn
- 1969-09-15 DE DE19691946592 patent/DE1946592B2/en active Granted
Cited By (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3739987A (en) * | 1971-01-08 | 1973-06-19 | Rech Appliquees Serap Soc Et | Arrangement of jacks for controlling flaps and its application to the control of a jet pipe |
US3824946A (en) * | 1972-08-30 | 1974-07-23 | D Macardy | Water jet propulsion unit |
US3774868A (en) * | 1972-12-11 | 1973-11-27 | G Goetz | Integrated nozzle |
US3831376A (en) * | 1973-02-05 | 1974-08-27 | Boeing Co | Thrust reverser |
US4037405A (en) * | 1975-09-30 | 1977-07-26 | United Technologies Corporation | Two dimensional nozzle with rotating plug |
US4050631A (en) * | 1976-03-26 | 1977-09-27 | The Boeing Company | Jet engine nozzle for controlling the direction of thrust |
US4088270A (en) * | 1976-03-31 | 1978-05-09 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Two dimensional wedge/translating shroud nozzle |
US4147027A (en) * | 1976-04-06 | 1979-04-03 | Grumman Aerospace Corporation | Thrust reverser nozzle |
US4175385A (en) * | 1977-12-12 | 1979-11-27 | General Electric Company | Thrust reverser for an asymmetric aircraft exhaust nozzle |
US5699966A (en) * | 1980-03-31 | 1997-12-23 | General Electric Company | Exhaust nozzle of a gas turbine engine |
US4865256A (en) * | 1987-11-05 | 1989-09-12 | Societe Anonyme Dite Hispano-Suiza | Turbojet engine having a thrust reverser door and variable exhaust cross-section |
AU741469B2 (en) * | 1997-07-24 | 2001-11-29 | Hispano-Suiza Aerostructures | Turboblower thrust reverser |
WO2001046580A1 (en) * | 1999-12-22 | 2001-06-28 | Saab Ab | An outlet device for a jet engine |
US6681561B2 (en) | 1999-12-22 | 2004-01-27 | Saab Ab | Outlet device for a jet engine |
US20070119151A1 (en) * | 2005-11-28 | 2007-05-31 | Aerojet-General Corporation | Nozzle assembly for rocket and ramjet applications |
US7568348B2 (en) | 2005-11-28 | 2009-08-04 | Aerojet-General Corporation | Nozzle assembly for rocket and ramjet applications |
US20110083418A1 (en) * | 2008-04-25 | 2011-04-14 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Flying object |
US8561385B2 (en) | 2008-04-25 | 2013-10-22 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Flying object |
US20140271169A1 (en) * | 2012-07-25 | 2014-09-18 | Rohr, Inc. | Nacelle for a high bypass ratio engine with multiple flow paths |
US9623976B2 (en) * | 2012-07-25 | 2017-04-18 | Rohr, Inc. | Nacelle for a high bypass ratio engine with multiple flow paths |
US20160053718A1 (en) * | 2014-08-19 | 2016-02-25 | The Boeing Company | Thrust Reverse Variable Area Fan Nozzle |
US10001080B2 (en) * | 2014-08-19 | 2018-06-19 | The Boeing Company | Thrust reverse variable area fan nozzle |
RU2758875C1 (en) * | 2020-07-23 | 2021-11-02 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Output apparatus of a flat jet nozzle |
RU2758867C1 (en) * | 2020-07-23 | 2021-11-02 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Output apparatus of a flat jet nozzle |
RU2786871C1 (en) * | 2022-02-17 | 2022-12-26 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Exhaust unit of a flat jet nozzle with a central body |
Also Published As
Publication number | Publication date |
---|---|
DE1946592A1 (en) | 1970-05-21 |
DE1946592B2 (en) | 1977-02-24 |
GB1253071A (en) | 1971-11-10 |
FR2018120A1 (en) | 1970-05-29 |
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