Aeronautics and astronautics – Aircraft power plants – Mounting
Patent
1983-12-08
1986-08-05
Blix, Trygve M.
Aeronautics and astronautics
Aircraft power plants
Mounting
248554, B64D 2700
Patent
active
046038221
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
This invention relates to engine mounts for jet aircraft engines and more particularly relates to an aft engine mount that is stiff enough to provide support for the engines while accommodating thermal growth of the engine.
Typically, a jet engine is mounted beneath the wing of a commercial airliner by forward and aft engine mounts attached to struts affixed to and extending downwardly from the wing structure. The forward mount is typically rigid and thermal expansion of the engine, both radially and longitudinally, is accounted for in the aft engine mount. The aft engine mount is generally also designed to react against vertical, side, and engine seizure (torque) loads. Using previous engine mount designs, the engine mount many times exceeds the external dimensions of the cowl surrounding the engine. In such cases it is necessary to provide a local blister fairing over the engine mount fittings. Such a fairing "bump" on the cowl causes interference effects and blowing drag penalty in the engine fan exits and the wing lower surface. In some cases, the bump is as high as 2.4 inches and exhibits considerable drag on the aircraft. In addition, the construction of the cowl is complicated by the addition of the blister fairing.
The distance between the engine and the wing is fixed in the initial aircraft design and the space must be shared by the engine-mounting struts and the engine mount. The space restriction caused by the design of the aircraft tends to make the strut shallow so that any increases in the vertical height of the strut will pay off well in terms of the stiffness-to-weight ratio of the strut structure. Therefore, it is desirable that the engine mount fittings be made as low-profile as possible without sacrificing load handling and other requirements in order to both fit the engine mount within the cowl contour and also to permit as deep an engine-mounting strut as possible in the space between the engine and the wing.
It is therefore an object of the present invention to provide a low-profile aft engine mount that tolerates thermal growth of the engine.
It is a further object of this invention to provide such an aft engine mount that permits a maximum depth engine strut to be utilized in a predetermined amount of space between the engine and the wing.
It is another object of this invention to provide such an aft engine mount that meets all the usual requirements of load handling, ease of manufacture, ease of installation, and maintenance.
SUMMARY OF THE INVENTION
In accordance with the above-stated objects, an engine mount for use in a position at the aft end of the core of a jet engine which is mounted to and beneath a wing of the aircraft, is provided. In aircraft design, the engine is located a predetermined distance from the wing and the present invention contemplates a low-profile engine mount that attaches to an engine-mounting strut, which in turn is affixed to aircraft wing structure. The low-profile mount of the present invention occupies a minimum amount of the space between the wing and the engine, thereby permitting the maximum vertical dimension in the strut. The engine mount includes a yoke and means for mounting the yoke to the strut such that the yoke is capable of pivotal movement about an axis transverse to the axis of the engine core. The yoke includes a first arm having a first link attached thereto by means of a pin parallel to the engine axis; the second end of the link is pivotally attached to a mounting ring on the engine core by means of a spherical bearing. A second arm of the yoke extends in a direction opposite to the first arm and has a second link attached between the second arm and the engine mounting ring. A first end of the second link is attached to the second arm of the yoke by means of a pin parallel to the engine axis and the second end of the link is attached to the engine-mounting ring by a spherical bearing. A third link is mounted between the central portion of the yoke and the engine-mounting ring, the first end of the th
REFERENCES:
patent: 3318554 (1967-05-01), Ward et al.
patent: 3397855 (1968-08-01), Newland
patent: 3727862 (1973-04-01), Kaufhold et al.
patent: 3750983 (1973-08-01), Morris
patent: 3809340 (1974-05-01), Dolgy et al.
patent: 4044973 (1977-08-01), Moorehead
Blix Trygve M.
Corl Rodney
The Boeing Company
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