U.S. patent number 3,923,420 [Application Number 05/355,772] was granted by the patent office on 1975-12-02 for blade platform with friction damping interlock.
This patent grant is currently assigned to General Electric Company. Invention is credited to Paul Chifos.
United States Patent |
3,923,420 |
Chifos |
December 2, 1975 |
Blade platform with friction damping interlock
Abstract
A turbomachinery rotor blade for disposition within a fluid flow
path in cooperation with a rotatable disc is provided with a
platform for partially defining the flow path of the fluid. The
platform is disposed between the airfoil of the blade and
preselected means for mounting the blade to a rotatable disc. The
platform is provided with means for resisting circumferential and
radial vibratory displacement by the action of frictional damping.
The damping is supplied by frictional engagement with platforms of
laterally adjacent blades. To enhance this function, the
circumferential extremities of the platforms are provided with two
diagonal edges axially spaced from one another along the same axial
line, the edges having predetermined angular offsets from the
radial direction. The two edges along each circumferential
extremity have anuglar offsets of opposite senses, and adjacent
platforms effectively interlock with one another.
Inventors: |
Chifos; Paul (Cincinnati,
OH) |
Assignee: |
General Electric Company
(Cincinnati, OH)
|
Family
ID: |
23398786 |
Appl.
No.: |
05/355,772 |
Filed: |
April 30, 1973 |
Current U.S.
Class: |
416/190;
416/193R; 416/212R; 416/500; 416/193A; 416/212A |
Current CPC
Class: |
F01D
5/3038 (20130101); Y10S 416/50 (20130101); F05D
2240/80 (20130101) |
Current International
Class: |
F01D
5/00 (20060101); F01D 5/30 (20060101); F01D
005/10 () |
Field of
Search: |
;416/191,212A,193,190,215,216,196,500 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Policinski; Henry J. Lawrence;
Derek P.
Government Interests
The invention herein described was made in the course of or under a
contract, or a subcontract thereunder, with the U.S. Department of
the Air Force.
Claims
What is claimed as new and intended to be secured by Letters Patent
of the United States is:
1. A turbomachinery rotor blade for disposition within a fluid flow
path in cooperation with a rotatable disc, the blade
comprising:
an airfoil;
mounting means extending radially from the airfoil for attaching
the blade to the disc; and
a platform disposed between the airfoil and the mounting means, the
platform comprising first and second circumferential extremities
and first means for abutting and interlocking said platform
radially, axially and circumferentially with a similar adjacent
platform to partially define the flow path and for frictionally
damping radial and circumferential relative movement between said
platform and said adjacent platform, said first means including
first and second diagonal edges on said first extremity of said
platform, said first diagonal edge being canted from the radial
direction by a predetermined first angle, said second diagonal edge
being canted from the radial direction by a predetermined second
angle of opposite sense from said first angle, said first and
second diagonal edges positioned to abut and interlock with an edge
of the adjacent platform in sliding frictional engagement therewith
and further positioned to effect damping of radial and
circumferential relative movement between said diagonal edges and
said adjacent edge during said frictional engagement.
2. The blade of claim 1 wherein said first and second diagonal
edges lie axially upstream and downstream relative to one
another.
3. The blade of claim 2 wherein said first and second diagonal
edges lie along a substantially common axial line.
4. The blade of claim 3 wherein said first circumferential
extremity is divided approximately into halves axially, one of said
halves comprising said first edge, and the second of said halves
comprising said second edge.
5. The blade of claim 1 wherein said first means includes third and
fourth diagonal edges on said second extremity, said second
extremity being disposed to the side of the platform laterally
opposite said first extremity, said third diagonal edge canted from
the radial direction by a predetermined third angle and said fourth
diagonal edge canted from the radial direction by a predetermined
fourth angle of opposite sense from said third angle.
6. The blade of claim 5 wherein said first and third angles are
substantially equal and said second and fourth angles are
substantially equal.
Description
BACKGROUND OF THE INVENTION
The present invention relates to blades for use in turbomachinery
and, more particularly, to frictional vibration-damping systems
therefor.
For the purpose of defining an aerodynamically efficient flow path
for the working fluid within a gas turbine engine, airfoil blades
are provided with platforms which combine with abutting similar
platforms of adjacent blades to separate the fluid flow path from
associated rotor cavities. High-speed rotation of rotor blades
combines with the impingement upon the platforms and associated
airfoils of a moving fluid to produce vibrational excitation which
can do severe damage to the blade. More particularly, certain of
these excitations may create various vibrational modes within the
aforementioned platforms which can result in the dismemberment of
the platforms by the breaking off of portions thereof.
Particularly susceptible to such breakage are the angular corners
of platforms of typical design. Elimination of such angular corners
might provide assistance in solving this problem. However,
aerodynamic efficiency requies a substantially cylindrical path
definition in this area which, when translated into terms of
adjacent abutting platforms requires such angular corners.
Other damage to the rotor blades through vibration can occur. For
example, certain modes of vibration often result in damage to
portions of the airfoil surfaces thereof by breakage and loss of
corners or by cracking and splitting in various directions. All of
this vibrational damage is harmful to the useful life of the blades
and is therefore advantageously eliminated.
Prior attempts at eliminating such vibration has included attempts
to "tune" resonant frequencies of the various vibrational modes
within the blades in order to remove them from the operating regime
of the engine. These attempts have been successful to only a
limited extent for the reason that such engines are operable within
a wide range with the result that certain resonant frequencies
cannot be eliminated. In recognition of this problem, prior
attempts have been made to damp the amplitudes of vibrations which
remain within operating ranges.
Damping has commonly taken the form of frictional engagement of a
portion of the blade by a member added for that purpose. In
particular, one prior attempt has involved the circumferential
lengthening of blade platforms and the further addition of
circumferentially extending overlapping plates between blades which
members cooperate to damp vibrational amplitudes. Unfortunate
characteristics of this and similar devices include the weight and
expense required in the addition of elements which serve no
function other than damping. Furthermore, lack of an effective
interlock between blades and engaging dampers allows the damping
elements to become separated over extended use with the possibility
of no longer performing their damping function.
The present invention remedies these and other objections to blade
damping members of the prior art by the provision for an
interlocking blade platform which performs efficient frictional
damping without the necessity of increasing the weight or size of
the platform.
The invention relies, in part, upon recognition that, since typical
blade airfoils are mounted substantially diagonally of the blade
platforms, the corners proximate the leading and trailing edges of
the airfoil will be stiffened thereby and experience vibrational
amplitudes substantially lower than the unreinforced corners remote
from the airfoil.
BRIEF SUMMARY OF THE INVENTION
It is therefore a primary object of the present invention to
provide a frictional damping system for turbomachinery rotor blades
which effectively damps vibrations while maintaining an effective
interlock for reliable extended use and which does not necessitate
the addition of costly and heavy materials to perform this
function.
In order to accomplish this and other objectives, which will become
apparent from the detailed description which follows, the present
invention provides a rotor blade having a laterally extending
platform disposed along its length between its diagonally disposed
airfoil and the means for mounting the blade upon an associated
rotor disc. The platform has a circumferential extremity disposed
to either side of the airfoil, and this extremity is provided with
diagonal edges which are canted from the radial direction by
predetermined angles. Each extremity has two such edges, the
aforementioned angles of which are of opposite sense. The diagonal
edges of each platform are positioned to engage in an interlocking
abutting relationship opposed edges of adjacent blade platforms.
The edges thus formed provide frictional damping for vibration
tending to cause relative radial motion between adjacent platforms
as well as relative circumferential motion therebetween.
BRIEF DESCRIPTION OF THE DRAWING
The present invention will become more easily understood upon
reading the following detailed description in combination with the
appended drawing wherein:
FIG. 1 is a perspective view of a plurality of rotor blades
according to the present invention in their operating position upon
an associated disc;
FIG. 2 is a perspective view of an individual rotor blade according
to the present invention;
FIG. 3 is a top view of a rotor blade according to the present
invention;
FIG. 4 is a side view of such a blade;
FIG. 5 is a cross-sectional view along line 5--5 of FIG. 1;
FIG. 6 is a cross-sectional view along line 6--6 of FIG. 1 and
illustrating cooperation between opposed platform edges of adjacent
blades, and
FIG. 7 is a view similar to that of FIG. 6 but illustrating
cooperation between different platform edges.
DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT
Referring to FIG. 1, a rotor designated generally by the numeral 10
is shown to include a rotatable disc 12 carrying a circumferential
groove 14 in the periphery thereof which is adapted to receive and
retain dovetail mounting means 16 by which the individual blades 18
are attached to the disc. This particular variety of disc includes
a loading slot 20 for accommodating the blades within the groove 14
of the disc 12. The dovetail 16 extends radially into conjunction
with a platform 22 of each blade, which combines with adjacent
platforms to partially define a fluid flow path 23 within the
engine and to which the present invention particularly pertains.
Extending radially outwardly from the platform is an airfoil 24
which is particularly configured to cooperate efficiently with a
fluid stream directed therepast.
In operation, this rotor functions substantially similarly to
typical rotors of this variety in that the disc 12 is attached to a
shaft (not shown) about which it rotates in response to the
interaction of the fluid stream with the blades 18 or in response
to torque applied to the shaft by similar blades elsewhere disposed
(depending upon whether the blades 18 shown are part of a turbine
or a compressor). At any rate, the airfoils 24 of the various
blades serve to transmit energy between disc 12 and the fluid
stream. During this process, the rotational velocity of the blades,
as well as aerodynamic disturbances within the fluid flow, create
vibrations of various frequencies which tend to excite the blades
at various frequencies. As mentioned hereinabove, such excitation
may be undesirable since damage to the airfoils, platforms or other
blade structure may result. In order to reduce the destructive
amplitude of resonant frequencies in the blade material, which
cannot be tuned out of the operating range of the engine, the
present invention provides for frictional damping between adjacent
blade platforms 22.
Referring to the remaining figures, the particular configuration by
which this damping is accomplished is disclosed. It can be seen
that each platform 22 includes two lateral extremities 30 and 32,
respectively, which are provided with interlocking as well as
damping means which will be described hereinafter. The platform
also includes an upstream end 34 and a downstream end 36.
The platform of the present invention includes both radial damping
means for frictionally damping radial relative movement between
adjacent platforms, and circumferential damping means for
frictionally damping circumferential relative movement between
adjacent platforms. Generally these damping devices depend upon
engagement by each platform with the platform of the
circumferentially adjacent blade. To this end, each platform
extends circumferentially outwardly of each airfoil and into
substantial abutment with the adjacent platforms.
To enhance damping as well as to provide an effective interlock
between platforms, the present invention provides unique treatment
for each circumferential extremity 30 and 32 of each blade 18. More
particularly, extremity 30 can be seen to include a first diagonal
edge 40 which comprises a surface disposed at an angle .theta.
.sub.1 from the radial direction, as represented by line 41. In
addition, extremity 30 includes a second diagonal edge 42 which is
comprised of a canted surface offset by an angle .theta. .sub.2
from the radial direction. It can be seen that angles .theta.
.sub.1 and .theta. .sub.2 are of the opposite sense.
For simplicity of manufacture, diagonal edges 40 and 42 lie axially
upstream and downstream relative to one another and substantially
along a common axial line. (However, a similar arrangement might be
made wherein the edges are radially spaced from one another and
engage opposed edges of adjacent platforms.) It can also be seen
that in the present embodiment, the extremity 30 is divided
approximately into halves axially by the presence of the diagonal
edges with the first of the halves comprising the edge 40 and the
second of the halves comprising the edge 42.
Referring now to the second circumferential extremity 32, it can be
seen that this extremity incorporates a similar pair of diagonal
edges 48 and 50 which are canted from a radial line 52 by angles
.theta. .sub.3 and .theta. .sub.4, respectively. These angles are
respectively of the same sense as are angles .theta. .sub.1 and
.theta. .sub.2 stated above. In the present embodiment it can be
seen that angles .theta. .sub.1, .theta. .sub.2, .theta. .sub.3 and
.theta. .sub.4 are all substantially equal in magnitude with one
another. However, for proper functioning of the platform this is
not necessarily so. In order to achieve proper abutting cooperation
between the flat surfaces of the adjacent edges, angles .theta.
.sub.1 and .theta. .sub.3 are kept substantially equal, and angles
.theta. .sub.2 and .theta. .sub.4 are substantially equal. Also,
the surfaces of the diagonal edges 40, 42, 48 and 50 may be
provided with a frictionally enhanced surface to increase damping,
but this also is optional.
Thus described, the damping system of the present invention
functions as follows. Having been loaded by means of slot 20 into
circumferential groove 14 and brought into abutting relationship
with one another, the blades 18, according to the present
invention, are retained within the groove and rotate in unison upon
rotation of disc 12. During operation of the gas turbine engine,
the disc 12 rotates about an associated shaft as described
hereinabove. Interaction between the airfoils 24 and the flow of
fluid through the engine flow path 23 induces vibrations of various
frequencies, which are transmitted through the blade material to
the platform 22 of each blade. In addition, vibration induced to
the blade dovetails 16 is transmitted through the blade material to
the platforms 22. Also the platforms may be excited directly by
periodic fluid pressure fluctuations on the platform surface. As a
result, the platforms as well as the airfoils tend to vibrate in
various modes.
As already indicated, the resonant frequencies of the blades are
"tuned out" of the operating ranges of the engine to the extent
possible. Nevertheless, certain of the resonant frequencies of the
blades remain within the operating regime of the engine. The
present invention operates to reduce the amplitude of such
vibrations, as well as in some instances to further tune the
associated blades.
Typical vibrational modes can occur wherein the platforms 22
vibrate in such a way that the platforms are placed in radial
relative motion with respect to adjacent platforms. Other
vibrational modes might place the platforms in circumferential
motion relative to one another. The present invention functions to
damp each of these relative movements by means of frictional energy
dissipation.
As stated hereinabove, the blade platforms 22 are formed with four
corners for the purpose of defining a relatively cylindrical and
thus aerodynamically efficient fluid flow path. For example, in
FIG. 3, the corners are designated A, B, C and D. As further stated
above, those corners of the blade platform which lie relatively
closely to the leading and trailing edges of the airfoil 24 will be
reinforced and stiffened thereby against steady state centrifugal
as well as vibratory motion. In the Figure, corners A and C
exemplify such corners. On the other hand, the remaining corners,
labeled B and D in FIG. 3, are not stiffened by the airfoils and
thus tend to vibrate with greater amplitude. The present invention
takes advantage of this characteristic by bringing into abutment
blade platforms in such a fashion that the reinforced corners A and
C cooperate closely with mating unreinforced corners B and D of
adjacent blades, and vice versa. As a result, vibration of each
corner A, B, C or D of one blade platform meets with frictional
resistance provided by adjacent blade platforms.
More particularly, with reference to the present configuration,
each corner A, a stiff corner, abuts a more flexible corner D of an
adjacent blade, as shown in FIG. 6. Similarly, each corner C, a
stiff corner, abuts a flexible corner B. Under the influence of a
given vibratory stimulus, corners A and C will tend to vibrate with
an amplitude smaller than corners B and D. Hence, each corner,
throughout its vibratory motion will be rubbing against an adjacent
corner having a different amplitude of vibration. As a result, each
corner tends to damp the vibration of its abutting mate and vice
versa. This is the basic mechanism by which the present invention
operates to effectively damp vibrational amplitudes, both in the
radial and circumferential directions.
To further enhance this action, the stiff corners (A and C) are
associated with inwardly facing surfaces 48 and 42 respectively.
Similarly, flexible corners B and D are associated with outwardly
facing surfaces 50 and 40. As a result, the steady state
centrifugal force upon the platform at any given RPM results in
mating surfaces being brought into a more intimate contact, thus
increasing the frictional damping effect of the present
invention.
In addition, this mechanism is enhanced by the particular
configuration of the blade platforms of the present invention. To
this end, the interlocking dual edges of each circumferential
extremity 30 and 32 have been provided. As stated, the angles of
departure of .theta. .sub.1 and .theta. .sub.3 of the surfaces 40
and 48, respectively, from the radial direction are equal in
magnitude and of the same sense. Similarly, angles .theta. .sub.2
and .theta. .sub.4 by which surfaces 42 and 50 depart from the
radial are also equal in magnitude and of the same sense. As a
result, when adjacent blades are brought into abutment, surfaces 40
and 48 of adjacent blades overlie one another in substantially
flush cooperation across their entire surfaces. The same is true of
adjacent surfaces 42 and 50. The effect of this configuration is,
in part, to provide surfaces having frictional engagement with one
another both in the radial and circumferential vibratory modes. In
addition, the contacting surfaces vibrating in each direction are
maximized in area to likewise maximize frictional force.
Furthermore, the fact that each circumferential extremity
incorporates two edges of opposite sense which engage two edges of
likewise opposite sense of an adjacent blade provides for an
interlocking mechanism for retaining the platforms against
tendencies to separate from one another. This is a distinct
improvement over prior art dampers which tend to become
non-functional after lengthy service has resulted in material
deformations. Another advantage of this configuration is that the
interlocking platform function minimizes the separation of adjacent
platforms under the influence of various vibrations and thus
increases damping affect.
In addition to damping the amplitude of the various vibrations, the
present invention offers means for further tuning the resonant
frequencies of the blades as may be desired. It is well known that
resonant frequency is a function of the mass in vibration as well
as the spring constant associated therewith. Each platform involves
a predetermined mass, a portion or all of which can be in vibration
at any given time. In addition, each platform incorporates a
material and predetermined thickness which jointly lead to the
spring constant thereof. By bringing adjacent blade platforms into
interlocking cooperation with one another, it is possible to change
the vibrating mass as well as the spring constant of the mass in
vibration without adding or subtracting material from the platform
itself. More particularly, when a given portion of one platform is
placed in vibration and rubs against an adjacent platform tending
to draw the adjacent platform into the same vibrational mode, the
effective mass in vibration may be greater or less than that where
the first platform is not engaged by the second. Similarly, the
spring constant of the two vibrating masses may be different and
may supplement one another. These interactions may be utilized to
adjust the resonant frequencies of vibration of platforms utilizing
the present invention while the frictional damping means of these
devices are used to reduce vibrational amplitude as described
hereinabove.
Thus may be described one embodiment of the present invention. It
is readily apparent that those skilled in the art may make
substantial variations of the structure presented herein without
departing from the spirit of the present invention. For example,
the particular configuration of the circumferential extremities of
the present blade platforms may be varied substantially but their
function maintained. One such example was mentioned hereinabove
wherein it was stated that the oppositely angled edges of one
extremity might be radially displaced from one another rather than
axially. Equalivantly, a tongue and groove cooperation might be
established between adjacent blade platforms which would serve to
both frictionally damp the amplitude of vibrations and partially
tune the resonant frequencies thereof. Such variations are intended
to be comprehended within the scope of the following claims.
* * * * *