FIELD: aeronautical engineering. SUBSTANCE: device includes hinges with hinged flaps whose one arm adjoins outer surface of nozzle and other arm adjoins engine nacelle. Hinges are mounted on engine nacelle. Hinged flap and engine nacelle adjoin by their and surfaces; to this end, engine nacelle is provided with end circular section on side of inner surface of wall. Cavity between flaps and outlet section of engine nacelle is brought in communication with atmosphere through holes which may be made in outlet section of engine nacelle or which may be made in form of slot between end faces of engine nacelle and flaps in area of hinged joint. Each arm of flap adjoining engine nacelle is fitted with spring pressed to its inner side. End circular section is toroidal in form with center of circle passing through axis of rotation of hinged flaps. EFFECT: minimum wear due to reliable adjoining of hinged flap to outer surface of swivel nozzle and engine nacelle. 6 cl, 3 dwg
Title | Year | Author | Number |
---|---|---|---|
DEVICE TO JOINT TURBOJET ENGINE HINGED JET NOZZLE WITH THE AIRPLANE ENGINE NACELLE | 2006 |
|
RU2328613C1 |
DEVICE FOR COUPLING OF JET ENGINE NOZZLE OUTER SURFACE AND AIRCRAFT NACELLE | 2019 |
|
RU2743539C1 |
METHOD OF OPERATION OF ROTATING ROUND SUPERSONIC REACTION NOZZLE OF TURBOJET ENGINE AND DEVICE FOR IMPLEMENTING THIS METHOD | 1998 |
|
RU2145670C1 |
DEVICE FOR ARTICULATING THE OUTER SURFACE OF THE ENGINE VECTORABLE JET NOZZLE AND THE AIRCRAFT ENGINE NACELLE | 2017 |
|
RU2656172C1 |
PLANAR NOZZLE WITH CENTRAL BODY | 1995 |
|
RU2153591C2 |
TURBOJET ENGINE NOZZLE FLAPS SYNCHRONIZING SYSTEM | 2006 |
|
RU2317432C1 |
AIR-JET ENGINE WITH REVERSAL OF THRUST | 2003 |
|
RU2232282C1 |
HIGH BY-PASS RATIO TURBOJET ENGINE | 2005 |
|
RU2315887C2 |
ADJUSTABLE SUPERSONIC NOZZLE OF GAS TURBINE ENGINE | 2015 |
|
RU2614903C1 |
DOUBLE-FLOW TURBOJET ENGINE WITH BIROTATIVE FAN | 2005 |
|
RU2302544C1 |
Authors
Dates
1999-12-27—Published
1998-03-20—Filed