U.S. patent number 3,843,278 [Application Number 05/366,823] was granted by the patent office on 1974-10-22 for abradable seal construction.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to Spencer P. Torell.
United States Patent |
3,843,278 |
Torell |
October 22, 1974 |
**Please see images for:
( Certificate of Correction ) ** |
ABRADABLE SEAL CONSTRUCTION
Abstract
An abradable tip seal for a compressor rotor, the seal including
closely spaced slots having sleeves of reinforcing material, such
as braided fiberglass, embedded therein surrounding each slot to
reinforce the thin wall between adjacent slots.
Inventors: |
Torell; Spencer P. (New
Britain, CT) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
23444698 |
Appl.
No.: |
05/366,823 |
Filed: |
June 4, 1973 |
Current U.S.
Class: |
415/173.4;
277/415 |
Current CPC
Class: |
F04D
29/526 (20130101); F04D 29/164 (20130101); F04D
29/685 (20130101); F01D 11/125 (20130101) |
Current International
Class: |
F04D
29/66 (20060101); F01D 11/12 (20060101); F01D
11/08 (20060101); F01d 005/20 () |
Field of
Search: |
;415/174
;277/96,DIG.8,230,95 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: Revis; Stephen E.
Claims
Having thus described a typical embodiment of my invention that
which I claim as new and desire to secure by Letters Patent of the
United States is:
1. A compressor case liner for use as an abradable tip seal for a
stage of compressor blades in a gas turbine engine, said liner
comprised of non-metallic, low density moldable abradable material
and having a circumferentially extending radially inwardly facing
surface defining a portion of a gas flow path through the engine,
said liner including a plurality of closely spaced, radially
extending slots circumferentially spaced about said surface, each
slot defining an opening in said surface and forming thin wall
portions between adjacent slots, said linear including a plurality
of separately formed fabric sleeves embedded therein, a sleeve
surrounding each one of said slots to strengthen said thin wall
portions, said liner having an overall specific gravity of about
1.0 or less.
2. The compressor case liner according to claim 1 wherein said
liner comprises a plurality of circumferentially spaced abutting
arcuate segments, each segment having a circumferentially extending
radially inwardly facing surface, said surfaces of said segments
defining, in combination with each other, said inwardly facing
surface of said liner, the surfaces of said thin wall portions
being parallel to said engine axis, said slots being tapered,
decreasing in circumferential width in a radially outward
direction.
3. The compressor case liner according to claim 2 wherein said
liner material is comprised of phenolic resin hollow spheres in a
cured epoxy resin, and said fabric sleeves are comprised of woven
fiber glass.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to a tip seal for a bladed rotor and more
particularly to an abradable tip seal for a compressor rotor.
2. Description of the Prior Art
Compressor case liners made from nonmetallic material and used as
shrouds or tip seals for rotating compressor blades to improve
compressor performance are well known in the art, such as the
abradable coating applied to the compressor casing as shown in
Wiles, U.S. Pat. No. 3,346,175. A further example of such an
abradable casing liner is shown in Lapac et al, U.S. Pat. No.
3,575,427, of common assignee with the present invention. It is
also known to provide slots or openings in these tip seals in the
area over which the blade tips pass to improve performance such as
shown in Mikolajczak, U.S. Pat. No. 3,580,692, of common assignee
with the present invention.
As is often the case, weight and cost are very important factors in
the design of these tip seals. In this respect it is desirable to
form the tip seals from relatively lightweight and inexpensive
compounds such as a thermosetting epoxy resin or rubber. Even these
compounds, however are often heavier than desirable. It is possible
to reduce the density and thus the weight of compounds such as a
thermosetting epoxy resin by the addition of hollow phenolic or
glass spheres of small diameter such as is shown in Moorman U.S.
Pat. No. 3,271,222 or in the hereinbefore referred to Lapac patent.
While these modified compounds are lightweight, they lack strength
and may be very brittle. If it is desirable that the tip seal have
a plurality of closely spaced openings, the walls between adjacent
openings may become quite thin and might break too easily upon
contact with a blade tip or even during handling.
It has been found that forming an abradable tip seal having closely
spaced slots separated by thin walls using prior art techniques and
materials results in either a liner that is strong enough but is
too heavy, or a liner that is light enough but is too weak in the
area of the thin wall sections and thus does not abrade
properly.
SUMMARY OF THE INVENTION
One object of the present invention is an improved tip seal for a
compressor rotor. A further object of the present invention is an
abradable compressor rotor tip seal which is lightweight yet strong
where required.
Accordingly, a compressor rotor tip seal with a plurality of
circumferentially spaced slots open at the sealing surface is
provided, the tip seal including an individual sleeve of
reinforcing material embedded therewithin around each slot to
increase the strength of the wall between adjacent slots.
In a preferred embodiment the tip seal is abradable and is made
from a molding compound comprising epoxy resin, curing agent, small
phenolic hollow spheres and chopped fiberglass particles. The
overall specific gravity of the molding compound is approximately
0.8. The sleeves surrounding each slot are made from woven
fiberglass material. The tip seal, sleeves included, has a specific
gravity of just under 1.0, yet the wall sections between adjacent
slots have good strength characteristics in that each wall has a
double thickness of fiberglass fabric embedded in it.
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 preferred embodiments thereof as
illustrated in the accompanying drawing.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is a sectional view of a portion of the fan section of the
compressor of a gas turbine engine.
FIG. 2 is a view looking in the direction A of FIG. 1.
FIG. 3 is a sectional view taken along the line 3--3 of FIG. 1.
FIG. 4 is a view of a braided fiberglass sleeve used in the
construction of the present invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT
As an exemplary embodiment of the present invention, consider the
portion of the compressor 10 of a gas turbine engine shown in FIG.
1. The compressor 10 comprises an annular case 12, a case liner 14
and a plurality of rotor blades 16, only the tip portion of one
blade being shown. In this embodiment the blades 16 are first stage
fan blades, and the case liner 14 is an abradable tip seal for
these fan blades 16.
The liner 14 in this instance is bonded with an epoxy adhesive 24
along its radially outwardly facing surface 18 to the radially
inwardly facing surface 20 of an annular groove 22 formed in the
case 12; however, any suitable technique for securing the liner 14
to the case 12, such as with rivets or bolts, is contemplated as
being within the scope of this invention.
Referring now to FIGS. 2 and 3, the liner 14 is shown as being
comprised of a plurality of arcuate segments 26 circumferentially
spaced within the groove 22 and in abutting relationship with each
other such as at 28 and 30. The radially inwardly facing
circumferentially extending surface 32 of each segment 26 forms a
portion of the gas flow path wall 33 of the compressor 10. As best
shown in FIG. 2, each segment 26 includes a double row of
circumferentially spaced slots 34. (These slots are not shown in
the cross section of FIG. 1 for the purpose of clarity.) The slots
in this embodiment are incorporated to improve aerodynamic
performance of the fan, but they might be incorporated in a tip
seal for any number of reasons such as to reduce noise. As seen in
FIG. 3, the slots 34 in this embodiment, although extending
generally radially outwardly, are skewed with respect to a radial
line and they do not extend completely through the segment 26. As
stated, their size, shape, and spacing is dictated by aerodynamic
and abradability considerations. With regard to slot spacing, the
wall portions 36 between circumferentially adjacent slots 34 are
quite thin, being on the order of 86 mils at their thinnest section
which is at the surface 32. In this embodiment the wall portions 36
are straight and their surfaces 37 are parallel to the engine axis
which is in the plane of the drawing and runs from right to left in
FIG. 1.
According to he present invention, woven fiberglass sleeves 38 are
embedded within the segments 26, one sleeve surrounding each slot
34 in order to reinforce the thin wall portions 36. These sleeves
provide each wall section 36 with a double layer of fiberglass and
reduce the brittleness and increase the strength of the wall
section. It was found that liners 14 made without these fiberglass
sleeves 38 were too weak and too brittle at the wall portions 36 to
provide proper abradability characteristics. As can be seen in FIG.
3, the sleeves 38 in this embodiment extend from the radially inner
face 32 to the radially outerface 18; however, the length of the
sleeves 38 and their positions within the segments 26 might vary
from design to design according to slot size and spacing and the
practical aspects of manufacturing the segments, which in this
embodiment are molded.
As stated in the summary of the invention, the preferred material
for the liner 14 is a molding compound comprising epoxy resin mixed
with small phenolic hollow spheres and chopped fiberglass
particles, the overall specific gravity of the molding compound
being approximately 0.8. FIG. 4 is a drawing of a sleeve 38 prior
to its being molded into the segments 26. The sleeve of FIG. 4 is
cut to shape from a continuous tube of woven fiberglass of the
appropriate diameter. The sleeves are cured to their desired shape
with an epoxy resin to stiffen them so that they will retain their
shape during the molding process for the segment 26. As best shown
in FIG. 3, the slots 34 are tapered for ease of molding the
individual segments 26, the slot circumferential width W decreasing
in a radially outward direction. Although, for ease of
manufacturing, the preferred embodiment shows a plurality of
segments 26, it is contemplated that the liner 14 could be made
from a single annular piece.
Although this 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.
* * * * *