Device for mounting a turboreactor on an aeroplane
Integrated gas turbine engine-nacelle
Attachment for attaching jet propulsion engines to fixed structure
Uniflange coupling assembly Patent #: 4361296
ApplicationNo. 06/394773 filed on 03/26/1982
US Classes:244/54, Mounting244/121, Shields and other protective devices248/554, AIRCRAFT ENGINE SUPPORT415/9, INCLUDING DESTRUCTIBLE, FUSIBLE, OR DEFORMABLE NON-REUSABLE PART60/39.091, With safety device60/797For motor
ExaminersPrimary: Blix, Trygve M.
Assistant: Shum, Ivy M.
Attorney, Agent or Firm
International ClassesB64D 29/00 (20060101)
B64D 27/00 (20060101)
B64D 27/18 (20060101)
AbstractAircraft gas-turbine engines (10) are often mounted and supported by strut type structures (12) which contain fuel, oil, electrical and hydraulic engine supply lines. The engine fan (18) is surrounded by a belt (24) made of tough flexible material designed to restrict travel of broken fan blade pieces, ingested objects or other debris (20). The forward strut section (12), adjacent the belt (24), is located outside of the maximum belt deflection envelope (26) except for the engine right and left cowl hinges (62 and 64) and its support structure (30), which structure (30) is made collapsible. This collapsible cowl hinge structure (30) utilizes mechanical fuse connections (68) which upon a dislocation force from the belt (24) allows the structure (30) to disconnect from the strut support structure (12). The collapsible cowl hinge structure (30) will successively move outwards and return, without severe damage to strut, cowl, strut fairing or supply lines (50 and 52) in the event debris ( 20) hits the belt (24) adjacent the forward strut portion.
Field of SearchMounting