Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Laminated – embedded member or encased material
Reexamination Certificate
1999-12-14
2001-11-06
Look, Edward K. (Department: 3745)
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Laminated, embedded member or encased material
C416S22900R, C416S248000
Reexamination Certificate
active
06312224
ABSTRACT:
The invention relates to bladed structures for fluid flow propulsion engines, and particularly to compressor rotors for gas turbine engines. More specifically, the invention relates to an improved annulus filler, particularly for the low pressure compressor or fan stage of a gas turbine engine.
BACKGROUND OF THE INVENTION
A compressor for a gas turbine engine includes at least one rotor disc having an array of rotor blades mounted thereon. Until relatively recently, it was common practice to produce rotor blades with integral platforms, the platforms forming the inner wall of the rotor annulus in use. The blade and platform were manufactured as a single unit from a common material. This had the disadvantage that the platforms were formed from a relatively heavy material. Further, any damage to the platform often necessitated the replacement of the entire blade.
Recent developments have led to the use of separate annulus fillers, as an alternative to blade platforms. The annulus fillers are located between adjacent rotor blades and generally have their own features for removably locating them on the rotor disc rim. Such fillers may be manufactured from relatively lightweight materials and, in the event of damage, may be replaced independently of the rotor blades.
SUMMARY OF THE INVENTION
According to the invention there is provided a component for a gas turbine engine rotor assembly including a rotor disc, the component including a root member for engagement with the rotor disc to locate the component thereon and the root member including bearing surfaces for bearing against complementary surfaces on the disc on rotation of the disc, wherein the component includes a plurality of layers of fibre reinforced material, the layers being orientated substantially perpendicular to said bearing surfaces.
Preferably the component includes layers of a first fibre reinforced material having fibres orientated in each of two mutually perpendicular directions and the fibres in the layers of first fibre reinforced material being arranged substantially perpendicular to said bearing surfaces.
The component may include layers of a first fibre reinforced material having fibres orientated in each of two substantially mutually perpendicular directions, and layers of a second fibre reinforced material having fibres orientated substantially in a single direction.
Preferably the fibre reinforced material includes carbon fibre reinforced plastics material.
The root member may be substantially dovetail shaped in cross section, for engaging a dovetail groove in the rotor disc. Alternatively, the root member may include a fir tree root portion, for engaging a complementary groove in the rotor disc.
The root member may be adapted to engage a groove extending in the circumferential direction of the rotor disc. Alternatively, the root member may be adapted to engage a groove extending in the axial direction of the rotor disc.
The component may be an annulus filler for a gas turbine engine rotor assembly including a rotor disc mounting a plurality of radially extending rotor blades and the component may include a wall member for at least partially bridging a space between adjacent rotor blades. The wall member and root member are preferably formed as a single integral moulding. Preferably, at least one layer of fibre reinforced material extends from the wall member into the root member.
The wall member may include a substantially smooth outer surface and an inner surface from which the root member projects.
The component may further include an elongate stiffening web extending along the wall member on said inner surface thereof, substantially in the axial direction of the rotor assembly when fitted thereto. Preferably, at least one layer of fibre reinforced material extends from the wall member into the stiffening web. At least one layer of fibre reinforced material may extend from the wall member into the stiffening web and further into the root member.
According to the invention there is also provided a rotor assembly for a gas turbine engine, the rotor assembly incorporating at least one component according to any of the preceding definitions.
According to the invention there is further provided a gas turbine engine including a rotor assembly according to the preceding paragraph.
REFERENCES:
patent: 3756745 (1973-09-01), Alver et al.
patent: 4045149 (1977-08-01), Ravenhall
patent: 4343593 (1982-08-01), Harris
patent: 5403153 (1995-04-01), Goetze
patent: 5573377 (1996-11-01), Bond et al.
patent: 1408492 SP (1975-10-01), None
patent: 1408491 SP (1975-10-01), None
patent: 2171151 A (1986-08-01), None
patent: 2262966 A (1993-07-01), None
Knott David S
White Kevin A
Look Edward K.
Manelli Denison & Selter PLLC
Nguyen Ninh
Rolls-Royce plc
Taltavull W. Warren
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