U.S. patent number 3,700,354 [Application Number 05/139,642] was granted by the patent office on 1972-10-24 for compressor blade root seal.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to James P. Memery.
United States Patent |
3,700,354 |
Memery |
October 24, 1972 |
COMPRESSOR BLADE ROOT SEAL
Abstract
A sealing device for restricting leakage across the stages of an
axial coessor through the clearances around the root fittings of
replaceable blades. A compliant dished annulus is attached on the
high pressure side of each compressor stage at its inside radius.
The combination of centrifugal force and pressure differential
across each compressor stage deforms the sealing device against the
blade root fittings thereby restricting the leakage.
Inventors: |
Memery; James P. (Manchester,
CT) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (N/A)
|
Family
ID: |
22487623 |
Appl.
No.: |
05/139,642 |
Filed: |
May 3, 1971 |
Current U.S.
Class: |
416/219R;
416/221 |
Current CPC
Class: |
F04D
29/164 (20130101); F01D 11/006 (20130101); F01D
5/3015 (20130101); F01D 5/323 (20130101) |
Current International
Class: |
F01D
11/00 (20060101); F01D 5/00 (20060101); F01D
5/30 (20060101); F04D 29/08 (20060101); F04D
29/16 (20060101); F01d 005/32 () |
Field of
Search: |
;416/219,500,220,230,221 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Claims
What is claimed is:
1. In a multistage axial compressor having replaceable blades
mounted in transverse slots around the periphery of each disc, the
improvement comprising:
annular sealing means concentrically disposed near the periphery of
each disc on the high pressure side occluding the exposed ends of
the slots for preventing fluid leakage therethrough, said sealing
means compliantly mating with the disc and attached adjacent to the
disc along the inside edge by diffusion bonding, the outer edge
extending outwardly to be urged into sealing contact across the
slots when subjected to a centrifugal force and pressure
differential, said sealing means further being formed of a metallic
foil in the order of 2 to 3 mills thickness and having a deformable
bead at the outer edge thereof adjacent to the disc.
2. A rotor, comprising:
a disc including a peripheral rim with axial-facing surfaces
increasing in cross section radially outwardly, and having a
plurality of convoluted transverse slots about the rim formed to
receive removable blades;
blades having root sections with axial-facing surfaces coplanar
with the rim surfaces inserted in each of the slots; and
a continuous annular seal concentrically attached near the inner
edge thereof to the side of the disc occluding the exposed ends of
the slots.
3. A rotor according to claim 2, further comprising:
said annular seal being flexible and compliantly mating with the
rim and attached adjacent to the rim along the inside edge, the
outer edge extending outwardly to be urged into sealing contact
across the slots when subjected to a centrifugal force and pressure
differential.
4. A rotor according to claim 3 further comprising:
said annular seal being formed of a metallic foil in the order of 2
to 3 mills thickness and attached to the disc by diffusion
bonding.
5. A rotor according to claim 4, further comprising:
said annular seal having a deformable bead at the outer edge
thereof adjacent to the disc.
6. A rotor according to claim 5, further comprising:
a plurality of key means respectively interposed between said
blades and said disc for retaining said blades to said disc;
and
cutouts formed in said seal for permitting installation of said
keys.
Description
STATEMENT OF GOVERNMENT INTEREST
The invention described herein may be manufactured and used by or
for the Government of the United States of America for governmental
purposes without the payment of any royalties thereon or
therefor.
BACKGROUND OF THE INVENTION
The present invention relates to improvements in axial compressors,
and more particularly to a sealing device for restricting blade
root fitting leakage in compressor rotor stages having removable
blades.
Axial gas turbine compressor rotors commonly use dovetail broached
slots for the attachment of the blades to the rotor disk. This
attachment technique is used for the purpose of facilitating blade
replacement. Consequently in order to accommodate the normal
manufacturing tolerances of the blade root fitting a clearance is
necessary in each slot. The result is that some of the compressed
gas behind each compressor stage leaks back through these
clearances into the preceding stage reducing substantially the
overall efficiency of the gas turbine power plant. In particular
where the pressure increment across the stage is large the leakage
rate becomes significant, thus degradation of compressor efficiency
is not minimized by staging optimization.
Various techniques of providing blade root sealing have been
developed within the prior art to limit this leakage. Most of these
techniques provide individual sealing devices attached at each
blade root, thereby multiplying the number of components in a
compressor with the attendant problems of reliability and
weight.
SUMMARY OF THE INVENTION
Accordingly, it is the general purpose and object of the present
invention to provide a blade root seal integrally formed as one
unit. Other objects are to provide a blade root seal that is
durable, replaceable and minimally affecting the existing
compressor disc parameters.
These and other objects are accomplished according to the present
invention by providing an annular seal generally dished to conform
with the convolutions of the blade attachment rim of the compressor
disc attached on the high pressure side thereof. The seal is formed
from a compliant material such as metal foil and is pressed into
sealing contact by the combination of the pressure differential
across the stage and the centrifugal force.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is an overall side view of an axial compressor shown partly
in cross section illustrating a three stage compressor;
FIG. 2 is a plan view of a fragment of a compressor disc assembly
as viewed from the high pressure side along section 2--2 of FIG. 1;
and
FIG. 3 is an enlarged fragmentary view in cross section of the
compressor disc assembly taken along section 2--2 of FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT
As shown in FIG. 1 an axial compressor section 25 of a gas turbine
is contained within the compressor housing 26. A rotor unit
consisting of three compressor disc assemblies 10 mounted on a
rotor shaft is enclosed by the housing 26 having stator rings 27
mounted to the housing 26 interspaced between adjacent assemblies
10. Each compressor disc assembly 10 includes blades 16
peripherally mounted on a disc 15 having an annular seal 11
covering the high pressure side of the blade mounting interface
according to the present invention.
As shown in more detail in FIG. 2 each compressor disc assembly 10
includes a plurality of removable blades 16 radially extending from
mounting slots 12 formed in a peripheral flange 14 of a disc 15.
Each blade 16 includes a root end fitting 17 formed to engage in
locking arrangement the convolutions of the slot 12. A locking
device 19 commonly engages each blade 16 to disc 15. Each blade
root fitting 17 is shown in partial contact with the convolutions
of the slot 12 generally in the areas of radial stress force
transfer path being placed in abutment therewith either by the
centrifugal force generated by the rotation of disc 15 or by the
locking mechanism 19. Thus the blade 16 is located in the slot 12
in a manner that produces the highest leakage rates if clearances
exist between the convolutions of the slot 12 and the blade root
fitting 17. As illustrated each blade root end fitting 17 is
dimensionally limited to allow for clearances 18 as is necessary to
accommodate various manufacturing tolerances. The total area of
clearances 18, which typically accumulates to an order of magnitude
of approximately 1 to 2 square inches in a medium sized jet power
plant, is a primary source of unwanted pressure leakage across the
compressor disc. To limit this leakage a thin foil annular seal 11
is installed according to the present invention extending outwardly
from rim 14.
Referring to FIG. 3 the peripheral rim 14 of disc 15 typically
increases in cross section with increasing radius in order to most
effectively transmit the bearing forces generated by the angular
motion of the blades 16 within corresponding slots 12. Accordingly,
the seal 11 placed across the slots 12 will be pressed against the
blade roots 17 by centrifugal force C.F. Seal 11 is formed out of
thin metal sheet stock of a thickness sufficient to straddle the
clearances 18, attached by diffusion bonding at the inside radius
thereof to the inside radius of the peripheral flange of disc 15,
being preformed in the shape of a concave annulus to generally mate
with the convolutions of the flange and is placed in sealing
contact therewith by the centrifugal force C.F. and pressure
differential .DELTA.P. The outer radius of seal 11 is formed to
provide a sealing lip 20 thereby increasing the centrifugal mass on
the exterior radius of the seal and providing an easily deformable
localized bearing surface.
In operation each compressor disc assembly 10 comprises one stage
within a multistage axial compressor. Each stage progressively
compresses the intake air, thus the radial dimension of the disc 15
and the size of blades 16 are adjusted to conform with the
theoretical volumetric decrease of the gas upon compression.
Accordingly, the leakage rate for the same mass flow rate within
any stage increases with the pressure differential across that
stage since the leakage area is generally constant. The present
invention utilizes this pressure differential .DELTA.P across the
compressor stage in order to provide sealing. The inventive seal 11
is formed from a metallic foil in the order to 2 to 3 mills thick
attached by diffusion bonding at the inside radius thereof to the
peripheral flange 14 of disc 15. Although other methods of bonding
are possible within the scope of the present invention diffusion
bonding offers the best compromise of durability and weight. The
installation of blade locks 19 can be performed through the open
side of the disc, however, in the case where blade lock insertion
is necessarily from the sealed side appropriate openings, where
necessary, are provided in the seal. Blade replacement is not
restricted by the seal since the installation can be from either
side in view of the flexibility of seal 11.
Some of the many advantages of the present invention should now be
readily apparent. The inventive seal reduces leakage across the
compressor stages of a gas turbine engine, characteristically a
major concern in the development of gas turbines, without affecting
the critical design parameters of the compressor disc itself such
as stress distribution, changing of disc modes and disc loading.
Thus the seal is adaptable to be installed on existing compressors
without entailing large expenses in disc alteration. Above features
are possible in view of the advantageous utilization of centrifugal
forces and pressure differentials by the invention allowing for a
seal structure which minimally affects the critical parameters of
the disc.
Obviously many modifications and variations of the present
invention are possible in the light of the above teachings. It is
therefore to be understood that within the scope of the appended
claims the invention may be practiced otherwise than as
specifically described.
* * * * *