U.S. patent number 3,689,177 [Application Number 05/135,310] was granted by the patent office on 1972-09-05 for blade constraining structure.
This patent grant is currently assigned to General Electric Company. Invention is credited to David Dubble Klassen.
United States Patent |
3,689,177 |
|
September 5, 1972 |
BLADE CONSTRAINING STRUCTURE
Abstract
In an axial flow apparatus including stator and rotor elements,
means are included for constraining axial movement of individual
blade members relative to the rotor axis when the rotor is
subjected to high centrifugal loading. The constraining means
include a ring which is circumferentially expandable under
centrifugal loading. Part of the outward radial force causing the
expansion of the ring is directed axially against the blade members
to provide an axially constraining force which is proportional to
the centrifugal loading on the rotor. The invention herein
described was made in the course of or under a contract or
subcontract thereunder, (or grant) with the Department of the
Army.
Inventors: |
David Dubble Klassen (Reading,
MA) |
Assignee: |
General Electric Company
(N/A)
|
Family
ID: |
22467508 |
Appl.
No.: |
05/135,310 |
Filed: |
April 19, 1971 |
Current U.S.
Class: |
416/198R;
416/198A; 415/173.7; 416/220R |
Current CPC
Class: |
F01D
5/22 (20130101); F01D 5/06 (20130101); F01D
5/3007 (20130101); F01D 11/006 (20130101); F01D
5/24 (20130101) |
Current International
Class: |
F01D
11/00 (20060101); F01D 5/22 (20060101); F01D
5/00 (20060101); F01D 5/06 (20060101); F01D
5/02 (20060101); F01D 5/24 (20060101); F01D
5/30 (20060101); F01D 5/12 (20060101); F01d
005/06 (); F01d 005/32 () |
Field of
Search: |
;416/219-220,500,198,200 |
References Cited
[Referenced By]
U.S. Patent Documents
|
|
|
2356605 |
August 1944 |
Meininghaus |
2656147 |
October 1953 |
Brownhill et al. |
3356339 |
December 1967 |
Thomas et al. |
|
Foreign Patent Documents
|
|
|
|
|
|
|
1145755 |
|
May 1, 1957 |
|
FR |
|
284188 |
|
Nov 1, 1952 |
|
CH |
|
Primary Examiner: Everette A. Powell, Jr.
Attorney, Agent or Firm: Edward S. Roman Derek P. Lawrence
Frank L. Neuhauser Oscar B. Waddell Joseph B. Forman
Claims
Having thus described one embodiment of the invention, what is
desired to be secured by letters patent is as follows:
1. In an axial flow apparatus having stator and rotor elements, a
blade constraining structure comprising: a first rotor element
having axially opposed faces and a plurality of open-ended
generally radial slots extending from one face to the other, with
each slot having side walls which are undercut to provide inwardly
directed abutment faces; a second rotor member axially spaced from
said first member and including an axially extending
circumferential flange, the tip of which is in closely spaced
opposing relation to said slots and is axially undercut to provide
an inwardly directed surface; a wedge ring whose outer radial
annular surface is axially overcut to provide an outwardly directed
surface abutting said inwardly directed surface of said flange,
such that under the influence of centrifugal loading said wedge
ring circumferentially expands and said overcut surface slides over
said undercut surface in both an outward radial direction and an
axial direction, effecting an axial translation of said wedge ring;
a plurality of blades having root portions inserted into said slots
so that the forward inserted face of each root abuts said wedge
ring, wherein each root is thickened to provide outwardly extending
shoulders which abut the inwardly extending shoulders of said slots
so as to radially retain said blades under centrifugal loading;
locking means constraining the other face of each root to inhibit
axial movement of said roots such that under centrifugal loading
the axial translation of said wedge ring is directed against the
abutting root faces and cooperates with said locking means to
further restrict axial movement of said blades.
2. The structure of claim 1 wherein said second rotor member
includes a plurality of circumferentially spaced blades disposed
about its periphery wherein said blades are radially and axially
retained by means of a circumferential dovetail groove around the
outer periphery of said second rotor member.
3. The structure of claim 1 wherein said wedge ring provides an air
seal between the rotor elements.
4. The structure of claim 1 wherein said wedge ring is a
plastic-like resilient material which allows the circumference of
the ring to be expanded slightly without fracture, yet is of
sufficient stiffness to resist axial cross-sectional compression
without substantial deformation.
5. The structure of claim 4 wherein said wedge ring is
polyimide.
6. The structure of claim 4 wherein said locking means includes a
locking ring abutting the other faces of said blade roots and
maintained in abutting relation by a plurality of projections
axially extending from said first rotor with each projection
including an inward extending radial lip overlapping said locking
ring.
7. The structure of claim 6 wherein said first and second rotor
members are mated by a series of axially extending interlocking
male and female splines so as to prevent circumferential slippage
between the rotor elements.
8. The structure of claim 7 including an annular resilient plastic
ring, the outside surface of which is in abutting relation with the
inside surfaces of the interlocking splines to provide an air seal
therebetween.
Description
This invention generally relates to a blade constraining structure
for use in an axial flow apparatus of the type having stator and
rotor elements and more particularly to structure for constraining
axial movement of blades under high centrifugal loading in axial
flow compressors.
In axial flow compressors, blades are commonly retained by
inserting root portions into either circumferentially or axially
extending dovetail slots around the periphery of rotor elements. It
is well known to retain the blades in the forward stages of a
compressor by means of axially extending dovetail slots while the
smaller blades in the aft stages are retained by means of
circumferentially extending dovetail slots. The reason is simply
that circumferential dovetail slots, due to inherent strength
limitations, are not as well suited for retaining the larger and
heavier forward stage blades under high centrifugal loading as are
the axially extending dovetail slots.
Problems arise, however, from the use of axially extending dovetail
slots. Axial translation of the blade root portions is extremely
difficult to constrain, particularly under high centrifugal loading
and any change in the axial position of the blade alters the rotor
balance leading to severe vibrational damage. On today's high speed
engines the problem becomes multiplied due to the more critical
nature of the rotor balancing.
Therefore, it is an object of this invention to provide a new means
for constraining the axial movement of blades relative to a rotor
axis when the blades and rotor are subjected to high centrifugal
loading.
It is also an object of this invention to provide a new means for
imparting an axially constraining force on rotor blade elements,
such that the force applied is directly proportional to the
centrifugal loading on the rotor and blade elements.
The blade constraining structure of an axial flow compressor
includes rotor and stator elements. A first rotor element has
axially opposed faces together with a plurality of open ended
generally radial slots extending from one face to the other. Each
slot has a pair of side walls which are undercut to provide
inwardly directed abutment faces. A second rotor member is axially
spaced from the first rotor and includes an axially extending,
circumferential flange. The tip of the flange is closely spaced
opposite the slots of the first rotor and is axially undercut to
provide an inwardly directed surface.
A wedge ring has an outer annular surface which is axially overcut
to provide an outwardly directed surface which abuts the inwardly
directed surface of the flange. Under centrifugal loading the wedge
ring circumferentially expands, and the overcut surface slides over
the undercut surface in both an outward radial direction and an
axial direction, effecting both a radial and axial translation of
the wedge ring.
A plurality of blades having root portions are inserted into the
slots so that the forward inserted face of each root abuts the
wedge ring. Each root has a thickened portion to provide outwardly
extending shoulders which abut the inwardly extending shoulders of
the slots, thereby radially retaining the blades under centrifugal
loading. After insertion, locking means constrain retraction of the
other face of each root so that under centrifugal loading, the
axial translation of the wedge ring is directed against the
abutting root face and cooperates with the locking means for
further restrict axial movement of the blades. The wedge ring
provides an additional advantage of serving as an extremely
effective air seal between rotor elements.
While the specification concludes with claims distinctly claiming
and particularly pointing out the invention described herein, it is
believed that the invention will be more readily understood by
reference to the discussion below and the accompanying drawings in
which:
FIG. 1 is a partial cross-sectional view of an axial flow
compressor embodying the invention;
FIG. 2 is a section view taken along the line 2--2 of FIG. 1;
FIG. 3 is a section view taken along the line 3--3 of FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT
FIG. 1 shows a partial cross-sectional view of two intermediate
stages of an axial flow compressor of the type that is suitable for
use in a gas turbine engine. Referring now to both FIGS. 1 and 2,
two intermediate stages of an axial flow compressor are shown
generally at 10. The axial flow compressor includes an annular
outer casing 20. A rotor assembly is shown generally at 11 and
includes first and second disc like rotor elements 12 and 14 which
are rotatably disposed around a central axis 15.
Rotor disc 12 has opposed faces 13 and 17 and includes a plurality
of open-ended, uniform dovetail cross-sectional slots 16 in its
periphery for retaining blades 24. The slots 16 extend from the
face 13 to the face 17 of the rotor disc 12 and each has side walls
21 as shown in FIG. 2 which are undercut to provide inwardly
directed abutment faces 18 on the side walls 21.
Each of the blades 24 has a platform 29 and a root portion 26 which
is thickened at the inner radial end to provide outwardly extending
shoulders 19 which abut the inwardly directed faces 18 of the
dovetail slot, thereby radially retaining the blades under
centrifugal loading.
Referring to FIG. 1 only, there is shown an adjacent rotor disc 14
which includes a first axially extending flange member 31, the end
of which mates with rotor disc 12 to prevent circumferential
slippage between the rotor elements. The mating structure may
include a series of interlocking male splines 51 and female splines
52 as shown in the limited cross-sectional view of FIG. 3. An air
seal may be provided between the interlocking male and female
splines by an annular resilient plastic ring 53 inserted into
abutting relation with the inside surfaces of the interlocking
splines. The plastic ring 53 is maintained in fixed relation to the
splines during rotation by the centrifugal forces which urge
outward circumferential expansion of the ring.
Rotor disc 14 includes a plurality of circumferentially spaced
blades 25 disposed about its periphery. The blades 25 may be
radially and axially retained by means of a circumferential
dovetail groove 37 extending around the outer periphery of the
rotor disc 14. Each blade 25 includes a dovetail root section 27
for engagement with the opposing surfaces of the dovetail groove 37
and must be inserted through a notch (not shown) in the dovetail
groove 37 and circumferentially slid around the slot into abutting
relation with an adjoining blade. When the last blade 25 has been
inserted through the notch in the dovetail slot so that all root
sections 27 are in abutting relation, the notch may then be locked
in a manner well known to the art.
An intervening row of stator vanes 22 is shown disposed between
blades 24 and 25 and is fixedly attached to compressor casing 20.
The vanes may also be rotatably attached to casing 20 in a manner
well known to the art which is described in U.S. Pat. No. 3,216,700
filed by R. H. Bostock Jr., and assigned to General Electric
Company.
Rotor disc 14 includes a second axially extending, circumferential
flange member 32, the annular tip portion 35 of which is in close
proximity to the trailing edge of the blade platform 29 in order to
establish a smooth flow path and minimize flow losses. The outer
tip portion of the flange member 32 is axially undercut to provide
an inwardly directed surface 34.
Blades 24 are individually inserted into their respective dovetail
slots 16 from a forward axial direction and retained from outward
radial travel under centrifugal loading by the interaction of the
blade roots 26 and the dovetail slots 16 in the manner previously
described. Axial movement of the blades, however, is also critical
and any shift of the axial blade position would alter the rotor
balance, causing vibrational damage. Accurate axial blade retention
even under high centrifugal loading is accomplished in the
following manner.
Before insertion of the individual blades 24, a wedge ring 30 is
stationed in abutting relation to the inwardly directed surface 34
which axially undercuts the outer tip 35 of the flange member 32.
An outside surface 36 of the wedge ring is axially overcut to
provide an outwardly directed surface for sliding contact with the
inwardly directed surface 34. The undercut and overcut surfaces of
the flange 32 and wedge ring 30 are preferably nominally planar,
although curvilinear surfaces could also be utilized. The wedge
ring may be formed of any resilient, plastic-like material which
allows the circumference of the ring to be expanded slightly
without fracture. Although the wedge ring must exhibit resiliency,
it must also be of sufficient stiffness to resist axial
cross-sectional compression without substantial deformation. A
highly suitable plastic for use in the wedge ring of this invention
is polyimide sold under the trade name of Vespel.
After the wedge ring is seated, the individual blades 24 are
inserted into their respective dovetail slots 16. The blades 24 are
inserted so that the forward inserted face 39 of the root portion
26 of each blade abuts against the wedge ring 30, thereby
prohibiting further forward axial movement of the blades.
Withdrawal of the blades 24 from the dovetail slots 16 is prevented
by a locking ring 44. The rotor disc 12 is provided with a
plurality of circumferentially spaced apart projections 40, axially
extending from the face 13 thereof. Each projection 40 has a
downward extending lip 42 for receiving and retaining the locking
ring 44. The projections 40 are spaced radially outward to coincide
with the spaced apart dovetail slots 16 so that locking ring 44
abuts the root portions 26 of the individual blades, thereby
constraining axial movement.
Upon rotation of the rotor assembly 11, centrifugal force operates
on the wedge ring 30, causing it to circumferentially expand.
Circumferential expansion of the wedge ring causes the overcut
surface 36 of the wedge ring to slide outward along the abutting
undercut surface 34 of the flange 32. The abutting undercut surface
of the flange 32 restrains the outward radial movement of the wedge
ring 30, imparting an axial component thereto, so as to increase
the axial constraining force operating on the individual blades
24.
Therefore, a portion of the centrifugal force operating on the
wedge ring is directed to the forward inserted faces of the blade
roots and cooperates with the locking ring to further restrict
axial movement of the blades upon rotation of the rotor. The wedge
ring also serves as an effective air seal between rotor elements
preventing high pressure compressor air from leaking out of the
main flow path into the cavities between the rotor elements.
Although the invention has been described in relation to an axial
flow compressor, it is readily understood to have broader
application. It may be useful for maintaining the axial integrity
of axially inserted blades in any high speed rotating part such as
the fan assembly of a turbofan engine.
* * * * *