Aeronautics and astronautics – Aircraft power plants – Mounting
Patent
1994-05-20
1995-12-12
Barefoot, Galen L.
Aeronautics and astronautics
Aircraft power plants
Mounting
248554, 60 3931, B64D 2700
Patent
active
054742587
DESCRIPTION:
BRIEF SUMMARY
The present invention relates to a mounting arrangement by which a gas turbine engine is attached to an aircraft. In particular it relates to a mounting arrangement suitable for connecting a gas turbine engine to a pylon of an aircraft wing.
According to the present invention a mounting arrangement for a gas turbine engine having a casing provided with an at least one annular flange comprises a support member for attachment to an aircraft structure from which the engine is to be mounted, the support member having a first connection means which engages the at least one annular flange on the engine casing to support the engine in a vertical plane, the vertical loads acting peripherally of the engine casing through the at least one annular flange, second connection means which engages the engine casing directly to prevent axial and lateral movement of the engine relative to the aircraft structure and a third connection means which in normal operation carries no load unless the first connection means fails whereby the third connection means engages with a further annular flange on the engine casing to support the engine in a vertical plane, the vertical loads acting peripherally of the engine casing through the further annular flange, characterised in that the first, second and third connection means are an integral part of the support member and the support member and the connection means are split in a direction parallel to the longitudinal axis of the engine to render them damage tolerant.
Preferably the connection means are pins. The first pin may be located in a number of links attached to the annular flange which disperse the load to a number of points on the annular flange.
The connection means are preferably coated with a wear resistance coating, such as tungsten carbide cobalt, which reduces the amount of wear.
The mounting arrangement is for use on a gas turbine engine which is also provided with a connection means which prevents rotation of the engine relative to the aircraft structure from which the engine is mounted. The aircraft structure from which the engine is mounted is preferably a pylon attached to the main beam of an aircraft wing.
The present invention will now be described with reference to the accompanying drawings in which:
FIG. 1 is a diagrammatic view of a gas turbine engine having a mounting arrangement in accordance with the present invention.
FIG. 2 is an enlarged pictorial view of the front engine mount shown in FIG. 1.
FIG. 3 is a plan view of the front engine mount shown in FIG. 2 when viewed in the direction of arrow A.
FIG. 4 is a part cross-sectional view of the front engine mount shown in FIG. 3 when viewed in the direction of arrow B.
Referring to FIG. 1 a gas turbine engine generally indicated at 10 is secured to an aircraft wing (not shown) via a pylon 12. The gas turbine engine 10 comprises an engine casing 15 which encloses a core engine of generally well known type. The engine casing 15 comprises a number of consecutive sections which are bolted together at annular flagged joints 16 and 18.
The engine 10 is suspended from the pylon 12 in conventional manner wherein the engine casing 15 is secured to the pylon 12 by a front mount 20 and a rear mount 40.
The front mount 20 comprises a bracket 22 which is bolted to the underside 11 of the upstream end 13 of the pylon 12. The bracket 22 is provided with a number of integral pins 26, 28 and 30, shown in FIG. 3, which engage the engine casing 15.
A first pin 26 (FIG. 2) at the upstream end 21 of the bracket 22 engages a link 25 which is attached by plates 27 to the annular flange 16 around the engine casing 15. The first pin 26 supports the engine 15 in the vertical plane and any vertical loads which are generated by the weight of the engine 10 act through the annular flange 16. The vertical loads are not therefore concentrated at specific points on the engine casing 15 but act peripherally thereof. Distortion of the casing 15 is thus substantially minimised.
A second pin 28 on the underside 24 of the bracket 22 engages the
REFERENCES:
patent: 3561707 (1971-02-01), Strock
patent: 4044973 (1977-08-01), Moorehead
patent: 5277382 (1994-01-01), Seelen et al.
Hodgkinson Carl
Perry Derek
Taylor Mike C.
Wright Kenneth W.
Barefoot Galen L.
Rolls-Royce plc
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