Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or... – Axially extending shroud ring or casing
Patent
1994-09-16
1995-11-14
Look, Edward K.
Fluid reaction surfaces (i.e., impellers)
Rotor having flow confining or deflecting web, shroud or...
Axially extending shroud ring or casing
F01D 522
Patent
active
054661250
DESCRIPTION:
BRIEF SUMMARY
FIELD OF THE INVENTION
The present invention relates to air compressing rotors and in particular to a fan rotor for a gas turbine engine.
BACKGROUND OF THE INVENTION
A conventional fan rotor for compressing air comprises a disc having a plurality of radially extending blades mounted thereon. The fan blades are mounted on the disc by inserting the radially inner end of the blades in correspondingly shaped retention grooves in the radially outer face of the disc. The fan blades do not have platforms so the inner wall of an annulus for the compressed air is formed by fastening separate wall members to the radially outer face of the disc. The separate wall members bridge the space between pairs of adjacent blades to define the inner annulus wall.
It is known to fasten the wall members, defining the inner wall of the compressed air annulus, to the disc by feet which extend radially inwardly. The feet of the wall members engage complementary grooves, of dovetail cross-section, in the radially outer face of the disc. Fitting of the wall members is achieved by sliding the feet into the grooves in a direction axially of the disc.
This known method of attaching the wall members to the disc has the disadvantage that the grooves in the radially outer face of the disc have to be manufactured to within quite close tolerances to receive the feet of the wall members.
The present invention seeks to provide a rotor in which the inner wall of the flow annulus is defined by a plurality of wall members which are fastened to the disc in such away that grooves for their attachment are not required in the radially outer face of the disc.
SUMMARY OF THE INVENTION
According to the present invention a rotor for a gas turbine engine comprises a rotor disc which has a radially outer face on which a plurality of radially extending blades are mounted, separate wall members are provided to bridge the space between adjacent blades to define an inner wall of a flow annulus through the rotor, each of the wall members have a plurality of hooks which extend radially inwardly to engage correspondingly shaped hooks provided on the radially outer face of the disc, characterised in that an at least one further hook is provided on each of the wall members which extends radially outward to engage an annular member mounted on the rotor adjacent the disc to ensure engagement of the hooks on the wall member with the hooks on the radially outer face of the disc.
In one embodiment of the present invention the at least one further hook extends radially outward to engage an annular member mounted on the rotor downstream of the disc.
In a further embodiment of the present invention two further hooks are provided on each wall member, one of the further hooks extends radially inward to engage an annular member mounted on the rotor upstream of the disc, the other further hook extends radially outward to engage an annular member mounted on the rotor downstream of the disc.
Preferably the at least one further hook which extends radially outward is urged into engagement with an annular member mounted on the rotor by centrifugal forces acting thereon.
A strip of flexible material may be provided at the edges of each of the wall members adjacent the fan blades, the strips of material effecting a seal between the wall members and the adjacent blades.
The wall members may be turned out of metal, made from a composite or a made from a combination of metal and composite material.
BRIEF DESCRIPTION OF THE DRAWINGS
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 incorporating a rotor in accordance with the present invention.
FIG. 2 is a view of the rotor in the direction of arrow A in FIG. 1.
FIG. 3 is a cross-sectional view along line BB in FIG. 2 of a wall member in accordance with one embodiment of the present invention.
FIG. 4 is a pictorial view of a wall member in accordance with the embodiment of the present invention shown in FIG. 3.
FIG. 5 is a cros
REFERENCES:
patent: 4655687 (1987-04-01), Atkinson
patent: 5049035 (1991-09-01), Marlin
patent: 5161949 (1992-11-01), Brioude et al.
patent: 5232346 (1993-08-01), Mitchell, Jr. et al.
Larson James A.
Look Edward K.
Rolls-Royce plc
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