U.S. patent number 3,708,244 [Application Number 05/132,675] was granted by the patent office on 1973-01-02 for bladed rotor for a gas turbine engine.
This patent grant is currently assigned to Rolls-Royce Limited. Invention is credited to Kenneth Edward George Bracey, Lindsay Grahame Dawson, James Alexander Petrie.
United States Patent |
3,708,244 |
Dawson , et al. |
January 2, 1973 |
BLADED ROTOR FOR A GAS TURBINE ENGINE
Abstract
A bladed rotor for a gas turbine engine comprising a row of
blades in which each blade is tied to the next adjacent blade by a
Z-shaped metal tie having a center section which is inwardly curved
such that centrifugal forces acting on itself are evidenced as
compressive stresses within the tie and end limbs or lugs extending
from the center section in opposite directions generally chordally
of the blades and each being attached to the blades by bolts spaced
apart transversely of the blade, the bolts extending through the
blade to also attach a similar limb or lug to the opposite blade
face.
Inventors: |
Dawson; Lindsay Grahame (Castle
Donington, EN), Petrie; James Alexander (Littleover,
EN), Bracey; Kenneth Edward George (Findern,
EN) |
Assignee: |
Rolls-Royce Limited (Derby,
EN)
|
Family
ID: |
10097090 |
Appl.
No.: |
05/132,675 |
Filed: |
April 9, 1971 |
Foreign Application Priority Data
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Apr 13, 1970 [GB] |
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17,546/70 |
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Current U.S.
Class: |
416/196R;
416/193R |
Current CPC
Class: |
F01D
5/22 (20130101) |
Current International
Class: |
F01D
5/22 (20060101); F01D 5/12 (20060101); F01d
005/10 (); F01d 005/24 () |
Field of
Search: |
;416/196,194,195 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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|
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|
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563,458 |
|
Nov 1932 |
|
DD |
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818,806 |
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Oct 1951 |
|
DT |
|
315,722 |
|
Feb 1930 |
|
GB |
|
Primary Examiner: Powell, Jr.; Everette A.
Claims
We claim:
1. A bladed rotor for a gas turbine engine comprising:
a row of blades and ties, each blade being connected to a next
adjacent blade by at least one tie, each tie comprising a single
Z-shaped piece of metal having limbs bent up to form lugs extending
in opposite directions generally chordally of the adjacent blades
and having a center section interconnecting said lugs and being
curved inwardly so that operational centrifical forces on the ties
cause them to be under com-pressive stress, and a plurality of
bolts for retaining each lug to a particular blade, said bolts
being spaced apart transversely of and extending through the
particular blade and also retaining a similar lug on an opposite
face of the particular blade.
2. A bladed rotor as claimed in claim 1 including pads secured to
each face of each blade to provide a flat bearing surface for said
lugs of said ties.
3. A bladed rotor as claimed in claim 2 in which said pads are made
from a glass reinforced plastic material and are adhesively secured
to the blade surface.
Description
This invention relates to a bladed rotor for a gas turbine
engine.
In certain circumstances it is necessary to stiffen the blades of
such a rotor by interconnecting the blades in each row by ties. It
is difficult to design ties which are light in weight and
sufficiently rigid in the high G environment of such a bladed
rotor.
The present invention provides a rotor having ties which are both
light in weight and rigid under high centrifugal stresses. At the
same time they can adjust themselves to a change in diameter due to
the stretch of the assembly.
According to the present invention a bladed rotor for a gas turbine
engine comprises a row of blades, each blade being connected to the
next adjacent blade by a tie, each tie comprising an inwardly
curved metal strip attached at each end to the blades and having a
substantially catenary shape so that in operation centrifugal
effects on the ties cause the metal strips to be under mainly
compressive stress.
Preferably each tie has an outwardly extending lug at each end by
which it is attached to the blade.
The lug may be retained to the blade by two bolts which extend
through the blade and also retain a similar lug on the opposite
blade face.
Thus the ties may be "staggered" and the lugs extend substantially
along the chord of the blade from one tie to the next.
In a preferred embodiment the ties are made from single pieces of
sheet metal or forgings having a Z-shape, the limbs of the Z-shape
being bent up to form the lugs and the interconnection being curved
inwardly to form the tie.
The invention will now be particularly described merely by way of
example with reference to the accompanying drawings in which:
FIG. 1 is a frontal view of the fan of a gas turbine engine in
accordance with the invention:
FIG. 2 is an enlarged section through the fan of FIG. 1 and
FIG. 3 is a section on the line 3--3 of FIG. 2.
In FIG. 1 there is shown a fan comprising a row of rotor blades 10
driven from a hub 11 and working inside a shroud 12. The hub 11 is
driven from the gas generator section comprising the remainder of
the gas turbine engine (not shown). In order to strengthen, and
modify the vibration characteristics, of the fan blades 10, each
blade is attached to its next adjacent blades by means of ties 13.
The ties 13 are seen in greater detail in FIGS. 2 and 3.
Each tie 13 comprises an inwardly curved center section 14 of
substantially constant cross-section. This center section is
arranged to lie on substantially a catenary curve. To anchor the
center section to the blades at either end, each end is provided
with an upstanding lug 15. Each of the lugs 15 has a considerable
chordal extent, and is bolted through the blade section in two
chordally separated locations 16 and 17. The bolts which fasten the
lug 15 of one tie also fasten the lug to the next adjacent tie.
In order to provide a flat location for the lugs on the blade
section, the blade section is build up at 16 and 17 on the
corresponding points on the opposite surface by pads 18 and 19. In
the present case the pads 18 and 19 are formed from glass
reinforced plastic, and are stuck by adhesive to the blade. The
pads thus provide flat surfaces and also help to spread loads into
the blade section.
It will be seen from FIG. 3 that the lugs 15 are formed as
continuations of the central portions of the ties and extend in one
direction only from the ends of the ties, and in fact they are
formed from a Z-shaped piece of sheet material. Thus any tendency
for the central section to rotate is opposed by the more distant of
the two bolts holding the flanges in place, this bolt acts about a
considerable moment arm to oppose such a tendency. It will also be
noted that due to the inwardly curved catenary shape of the center
portion of the ties, this portion will be under a compressive
stress when centrifugal loads act on the tie in operation. The
loads transferred to each blade through the lugs 15 will be opposed
to some extent by opposite loads produced by the next adjacent
tie.
As briefly mentioned above, the ties illustrated are simply
manufactured from a Z-shaped piece of sheet metal. It will be seen
that by drilling the bolt holes, bending up the lugs 15 and forming
the center section to the required catenary shape, the complete tie
may be made. It is preferable if the edges of at least the center
section of the tie are rounded off both to improve the aerodynamic
qualities of the tie and to reduce the possibility of stress
raisers and consequent cracks.
It will be appreciated that various modifications can be made to
the invention as described above. Thus various methods could be
used to fasten the ties to the blades, and the ties need not be
made from sheet metal as described in the preferred embodiment. The
standard bolts shown on FIG. 2 and 3 are for test purposes only. A
preferred bolt would have a shallow domed head as shown at 20 in
FIG. 3. It would be used with a sunk sleeve nut which would also
serve as a dowel.
* * * * *