U.S. patent number 3,754,839 [Application Number 05/249,336] was granted by the patent office on 1973-08-28 for filament reinforced rotor assembly.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to Robert R. Bodman.
United States Patent |
3,754,839 |
Bodman |
August 28, 1973 |
FILAMENT REINFORCED ROTOR ASSEMBLY
Abstract
This invention relates to a rotor assembly reinforced with a
filament wound composite ring. The rotor assembly comprises a rotor
including a plurality of radially extending circumferentially
spaced blades. The composite ring surrounds the blade tips and is
closely spaced therefrom by radially flexible support means. During
rotor operation the blade tips grow radially outwardly and come
into centrifugal load carry relationship to the composite ring,
whereupon the ring carries a portion of the centrifugal loads thus
reducing the strength requirements of the blades and rotor.
Inventors: |
Bodman; Robert R. (Riviera
Beach, ER) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
22943038 |
Appl.
No.: |
05/249,336 |
Filed: |
May 1, 1972 |
Current U.S.
Class: |
416/195; 416/190;
416/218; 416/230; 416/241A; 416/241R |
Current CPC
Class: |
F01D
21/045 (20130101); F01D 5/22 (20130101); Y02T
50/60 (20130101); Y02T 50/672 (20130101) |
Current International
Class: |
F01D
21/00 (20060101); F01D 21/04 (20060101); F01D
5/22 (20060101); F01D 5/12 (20060101); F04d
029/26 (); F01d 005/24 () |
Field of
Search: |
;416/218,189,230,241A,244A,195,190 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Claims
Having thus described a typical embodiment of my invention, that
which we claim as new and desire to secure by Letters Patent of the
United States is:
1. A filament reinforced rotor assembly comprising:
a rotor;
a plurality of radially extending blades circumferentially spaced
about the periphery of said rotor and attached thereto;
an annular filament wound composite ring closely surrounding the
tips of said blades and radially spaced therefrom when said rotor
is at rest; and
radially flexible support means disposed on said rotor,
concentrically positioning said ring with respect to said blades
and adapted to permit said ring to come into centrifugal load
bearing relationship to said blades during rotor operation due to
the different centrifugal and thermal growth rates of said blades
and said composite ring.
2. The filament reinforced rotor assembly according to claim 1
including barrier means between said ring and said blades to
prevent contact between said ring and said blades.
3. The filament reinforced rotor assembly according to claim 1
wherein said support means includes barrier means between said ring
and said blades to prevent contact between said ring and said
blades.
4. The filament reinforced rotor assembly according to claim 2
wherein said barrier means is an annular tube encapsulating said
ring.
5. The filament reinforced rotor assembly according to claim 3
wherein said barrier means is an annular tube encapsulating said
ring.
6. The filament reinforced rotor assembly according to claim 5
wherein said annular tube is filled with inert gas.
7. The filament reinforced rotor assembly according to claim 1
wherein said support means includes an axially extending radially
flexible annular ring connected to said blades and adapted to
provide said radial flexibility to said support means.
8. The filament reinforced rotor assembly according to claim 7
wherein each of said blades includes a tip shroud and a radially
extending seal segment, and said composite ring is connected to
said seal segments by said axially extending radially flexible
annular ring.
Description
BACKGROUND OF THE INVENTION
1. Field of Invention
This invention relates to the use of circumferentially wound
filaments to reinforce a rotor assembly.
2. Description of the Prior Art
The use of circumferentially wound filaments to reinforce a rotor
assembly is well known in the prior art as evidenced by U.S. Pat.
No. 3,393,436 to Blackhurst et al, and British Pat. No. 1,252,544
issued April 9, 1970 to General Motors Corporation. The chief
advantage of these filaments is their high tensile strength and
lightweight; when these filaments are wound about a rotatable body
their high tensile strength translates into a high hoop strength
giving the filaments the ability to carry large centrifugal
loads.
Two basic problems are encountered with the use of these filaments.
One is the difference in thermal and centrifugal expansion rates
between the filaments and noncomposite materials; the other problem
is that many of these filaments, depending upon the material from
which they are made, deteriorate in certain environments, such as
in a high temperature oxygen environment as is present in gas
turbine engines.
It is often desirable to add a tip shroud and/or a tip seal to the
ends of rotor blades to improve efficiency and to reduce vibration;
often, however, blades cannot withstand the additional centrifugal
loads created by the added mass located near their tip. This is
particularly true in the turbine area of a gas turbine engine where
temperatures and rotational speeds are very high. This problem
becomes more acute as turbine inlet temperatures increase.
SUMMARY OF THE INVENTION
It is an object of the present invention to provide a lightweight
filament reinforced rotor assembly.
It is a further object of the present invention to reduce stresses
in the blades of a rotor assembly.
Accordingly, the present invention contemplates an annular filament
wound composite ring surrounding the tips of a set of rotor
assembly blades, radially spaced therefrom by radially flexible
support means and adapted to come into centrifugal load bearing
relationship to the tips of said blades at operating speeds and
temperatures for carrying a portion of the centrifugal loads of the
rotor assembly.
Since the composite ring carries a portion of the centrifugal loads
of the rotor assembly, the mass of the disc used to carry the
blades may be substantially reduced, possibly to the point of only
requiring a thin drum; also, by locating the composite ring around
the tips of the blades, the stresses within the blades themselves
are reduced to the point where tip shrouds and/or seals may be
located near the tips of the blades without overstressing the
blades. The overall effect of this invention is to substantially
reduce the total weight of a rotor stage by reducing the strength
requirements of the rotating parts.
In order to protect the composite ring from a contaminating
environment, if one exists, as it would if such a ring were used in
the turbine area of a gas turbine engine, and to prevent direct
contact between said composite material and said blades, the ring
is encapsulated by suitable means such as an annular tube of
noncomposite material; if necessary, the tube can be filled with an
inert gas for further protection of the composite ring. In the
preferred embodiment of the invention as hereinafter described, the
flexible connecting means also serves to encapsulate the ring. As
should become apparent, this invention also has application with
bladed rotors in other than a gas turbine engine environment.
The foregoing and other objects, features and advantages of the
present invention will become more apparent in the light of the
following detailed description of a preferred embodiment thereof as
illustrated in the accompanying drawing.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is a partial side elevation view, partly in section, showing
a turbine rotor assembly utilizing one embodiment of the present
invention.
FIG. 2 is a partial view in perspective looking in direction A in
FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT
As an example of a rotor assembly utilizing one embodiment of the
present invention, consider the gas turbine engine turbine rotor
assembly generally represented by the numeral 10 in FIG. 1. The
rotor assembly 10 comprises a disc 12 and a plurality of radially
extending blades 14 each having a root 15 and a tip 16, said blades
being circumferentially spaced around the periphery of said disc 12
and attached thereto by any suitable means such as by the
well-known fir tree root configuration which is contemplated in
this embodiment. Suitable blade locks 17 may also be provided. The
root attachment for the blade is not intended to be a part of the
present invention.
The rotor assembly 10 also comprises an annular ring 18 made from
one or more circumferentially wound carbon filaments embedded in a
carbon matrix material. Choice of the filament and matrix material
depends upon the particular environment in which the invention is
used and may also be, for example, graphite filaments in a resin
matrix, boron filaments in an aluminum matrix, saphire filaments in
a nickel matrix, or any other suitable filament-matrix combination.
The ring 18 is positioned around the tips 16 of the turbine blades
14 and is radially spaced therefrom to allow for differences in
thermal and centrifugal growth rates of the ring 18, the blade 14,
and the disc 12. As temperature and rotational speed increase the
blade tips 16 move toward the ring 18 fastener than the ring moves
away from the blade tips; the inner diameter of the ring is sized
to result in the ring coming into the centrifugal load bearing
relationship to the blade tips when the rotor assembly reaches
operating speeds and temperatures. Prior to that time, the blades
and disc are sufficiently strong to carry the loads imposed upon
them.
In this embodiment each blade is provided with a tip shroud 26. As
best shown in FIG. 3, adjacent tip shrouds 26 are in abutting
relationship to each other helping to damp blade vibration while at
the same time forming the outer wall 28 of the engine gas path. At
one end of each shroud 26 is a radially extending labyrinth type
seal segment 30. The adjacent seal segments 30 form an annular
labyrinth seal ring 32 which cooperates with an outer turbine
casing, not shown. The annular composite ring 18 is connected to
the rotor assembly through these seal segments 30 by means of an
axially extending annular support ring 34. The support ring 34
serves to position the composite ring 18 concentrically about the
blade tips 16, and is flexible enough in a radial direction to
allow for the differential rates of radial growth between the blade
tips and the composite ring 18. The flexibility is accomplished, in
this example, by making the connecting ring 34 from thin sheet
metal and by giving the ring a Z-shaped cross section as shown in
FIG. 1. In some situations it may be desirable that the ring 34 be
slotted in an axial direction in several locations such that the
composite ring 18 is supported by a plurality of fingers rather
than by a full annular ring.
A barrier 36 is provided between the composite ring 18 and the
blade tips 16, because direct contact between the blade tips and
the composite ring might damage the filaments within the composite
ring. In the present embodiment the barrier 36 is an annular tube
which also serves to encapsulate the composite ring to protect it
from a contaminating environment, such as the high temperature
oxygen environment in the turbine section of a gas turbine engine.
Further protection may be afforded the composite ring 18, if
necessary by filling the annular tube with an inert gas.
As hereinbefore stated, a composite ring, such as the ring 18,
surrounding the tips of rotor blades is particularly useful when
tip shrouds and tip seals are desired; indeed, in the turbine
section of a jet engine, where temperatures and rotational speeds
are extremely high, such a composite ring may sometimes be a
necessity if tip shrouds are used. In any event, this invention is
attractive, notwithstanding the use of tip shrouds, simply to allow
a reduction in the mass of the disc supporting the blades. Under
certain conditions the requirement for a disc as a centrifugal load
carrying member may be eliminated altogether by this invention; in
that instance the composite ring would, of course, have to be
sufficiently strong to take all the centrifugal loads.
Although the invention has been shown and described with respect to
a preferred embodiment thereof, it should be understood by those
skilled in the art that various changes and omissions in the form
and detail thereof may be made therein without departing from the
spirit and the scope of the invention.
* * * * *