Power plants – Reaction motor – Interrelated reaction motors
Reexamination Certificate
1998-10-19
2001-01-09
Thorpe, Timothy S. (Department: 3746)
Power plants
Reaction motor
Interrelated reaction motors
C060S228000, C239S265310
Reexamination Certificate
active
06170253
ABSTRACT:
FIELD OF THE INVENTION
This invention relates to a ducted fan gas turbine engine. More particularly but not exclusively this invention relates to a gas turbine engine comprising a thrust reverser.
BACKGROUND OF THE INVENTION
Ducted gas turbine engines are designed to enable a stream of cold air from the fan to pass through a channel formed by a duct between the casing of the engine and outer ducting or cowling. It is known to provide ducted fan gas turbines with means for deflecting this by-pass flow of air so as to assist in braking of an aircraft on which the engine is mounted. Such thrust reversing means are designed in various forms. One prior art proposal is to provide a plurality of doors which are translatable into positions which block the by-pass air. A plurality of deflector vanes are provided within cowling which is uncovered when the thrust reverser is in the deployed position. Thus the fan exhaust air is directed generally radially outward and partially forward by the deflector vanes to provide braking.
It is important to provide access to gas turbine engines so that maintenance and inspection of parts can be conducted. One method of allowing access is to provide doors within the engine casing. These doors are generally C shaped and hinged at a location adjacent the pylon from which the engine is mounted on the aeroplane. One main problem with such doors is that because they form part of the actual casing of the engine, the coupling is inherently heavy and complicated. Also, because of the weight of the doors, hydraulic jacks are normally employed to control movement of the doors. Such C ducts must also be designed to accommodate the space requirements of thrust reversers. Such an arrangement is disclosed in prior patent GB1,304,212 and GB2,045,179 among others.
Another method of providing access to ducted, large by-pass gas turbines has been by actual entry into the ducting by the maintenance crew. However on some engines the by-pass areas have been reduced and the area is not large enough to allow access.
SUMMARY OF THE INVENTION
It is an object therefore of the present invention to provide improved access to a gas turbine engine for maintenance or inspection and/or provide improvements generally.
According to the invention there is provided a gas turbine engine comprising a cowl, an annular portion of which is translatable relative to the remainder thereof, a cascade structure being nested within the translatable portion of the cowl in a non-operative position and being exposed, in an operative position upon translation of said annular portion wherein said cascade structure comprises at least one C shaped section capable of rotation to an open position about an axis substantially parallel to a longitudinal axis of the gas turbine engine, thereby allowing access to the core engine.
Preferably the C section is hingeably connected to the non-translatable portion of the cowl.
In one embodiment of the invention the translatable portion and said cascade portion form a gas turbine engine thrust reverser.
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Evora Robert Z.
Farkas & Manelli PLL
Rolls-Royce plc
Taltavull W. Warren
Thorpe Timothy S.
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