U.S. patent number 3,893,782 [Application Number 05/452,867] was granted by the patent office on 1975-07-08 for turbine blade damping.
This patent grant is currently assigned to Westinghouse Electric Corporation. Invention is credited to Frank J. Kuchma, Mario F. Pierpoline.
United States Patent |
3,893,782 |
Pierpoline , et al. |
July 8, 1975 |
Turbine blade damping
Abstract
A baffle arrangement to limit vibration in rotating blades of a
elastic fluid turbine apparatus. The turbine comprises a casing
enclosing a rotating shaft having a plurality of blades thereon.
The casing has a circumferential groove disposed on the interior
surface thereof. A predetermined number of radial baffles traverse
the groove. The baffles are disposed in the circumferential groove
at a predetermined circumferential distance from one another. The
elastic fluid is directed by the rotating blades into the groove.
Fluid in the groove is deflected by the baffles against the
backside of the rotating blades. The impingement of the deflected
elastic fluid on the rotating blades exerts a force on the blade in
a direction opposite the direction of rotation of the blade and
thereby limits vibration in the blade to provide an effective blade
damper. In addition, each blade is contour fitted with a metallic
coating of a predetermined thickness to provide added rigidity to
the blade and limit vibration in the blade.
Inventors: |
Pierpoline; Mario F. (Media,
PA), Kuchma; Frank J. (Lansdowne, PA) |
Assignee: |
Westinghouse Electric
Corporation (Pittsburgh, PA)
|
Family
ID: |
23798281 |
Appl.
No.: |
05/452,867 |
Filed: |
March 20, 1974 |
Current U.S.
Class: |
415/119;
416/241R; 416/500 |
Current CPC
Class: |
F01D
5/28 (20130101); F01D 5/26 (20130101); F01D
25/06 (20130101); F01D 11/08 (20130101); Y10S
416/50 (20130101) |
Current International
Class: |
F01D
25/00 (20060101); F01D 11/08 (20060101); F01D
25/06 (20060101); F01D 5/26 (20060101); F01D
5/28 (20060101); F01D 5/12 (20060101); F01d
005/16 (); F01d 005/10 () |
Field of
Search: |
;415/119,172,DIG.1,219R
;416/190,500 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Freeh; William L.
Assistant Examiner: Casareyola; L. J.
Attorney, Agent or Firm: Medwick; G. M.
Claims
What we claim is:
1. An axial flow elastic fluid turbine apparatus comprising:
a casing having a central axial bore extending therethrough, said
casing having a circumferential groove disposed on the interior
surface thereof,
a predetermined plurality of baffle members disposed in said
groove, said baffle members being disposed at a predetermined
circumferential distance from one another, each of said baffle
members traversing said groove and extending radially inward from
said groove relative to an axis extending through said bore,
a predetermined number of nozzles directing the flow of elastic
fluid in said turbine, and,
a rotating member extending centrally and axially through said
bore, said rotating member having a predetermined number of
rotating blades thereon, each of said blades having a root portion
attached to said rotating member and a tip portion thereon, said
tip portion of each of said blades being adjacent to said groove in
said casing, said rotating member being operable to direct said
elastic fluid from said nozzles into said groove, said elastic
fluid directed into said groove being deflected by said baffle
members against said rotating blades to reduce vibration in said
blades.
2. The turbine of claim 1, wherein said tip of said blades are
disposed so as to extend a radial distance into said
circumferential groove.
3. The turbine of claim 1, wherein said baffle members are disposed
so as to define a predetermined oblique angle with said axis
extending through said bore.
4. The turbine of claim 3 wherein said baffles are disposed so as
to align with said tip portion of one of said predetermined number
of rotating blades.
5. The turbine of claim 1, wherein said predetermined number of
baffles is different from said predetermined number of rotating
blades disposed on said rotating member.
6. The turbine of claim 5, wherein said predetermined number of
baffles is different from said predetermined number of nozzles.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to steam turbines, and in particular, to an
improved damping arrangement for limiting vibration in the rotating
blades of an axial flow steam turbine apparatus.
2. Description of the Prior Art
In an axial flow elastic fluid turbine apparatus having a rotating
shaft with a plurality of blades thereon, uncontrolled vibration in
the rotating blades is an undesirable element of turbine operation.
Vibration in the blades can limit the efficiency of the turbine
apparatus in many ways. Vibration can, for example, damage the
bearings on which the shaft member rotates or can cause undue
stress and fatigue of blades, leading to the possibility of early
failure in the rotating blades.
The vibration has a variety of sources, including operational
vibration of the rotating shaft, or the periodic impingement of the
elastic fluid on the blades at the nozzles of the turbine. In
addition, turbulence caused by leakage of the elastic fluid through
a narrow clearance that exists between the tip of the rotating
blade and the interior surface of the casing a reverse flow
striking the backside of the blades in the last rotating blade row,
thus adding to the vibration of those blades.
In the prior art, the rotating blades are braced by the disposition
of a shroud member on the blade. The shroud serves to brace the
turbine blades against one another so as to minimize or limit
vibration of the blades. Various methods of disposing the shroud
are utilized by the prior art, including rim shrouding, which
places the shroud between the tip portions of the blades to brace
the blades against each other. Another method utilized in the prior
art is lashing, or tieing the blades together at a point
intermediate between the root and the tip of each blade, to brace
each blade against the other. However, disposition of the shroud or
blade lashing is an expensive and time-consuming process, and does
not completely eliminate blade vibration.
SUMMARY OF THE INVENTION
This invention limits vibration of the rotating turbine blades by
use of an improved damping arrangement disposed in the casing of
the turbine. A groove is disposed circumferentially about the
interior surface of the casing of the turbine apparatus. The groove
is disposed so that the tips of the corresponding rotating blade
row lie adjacent the groove. A predetermined number of baffles are
disposed at predetermined circumferential positions in the groove.
The baffles are disposed so as to substantially traverse the width
of the groove. As the shaft rotates, the elastic fluid in the
turbine is directed by the rotating blades into the groove disposed
on the interior surface of the casing. The elastic fluid in the
groove is carried circumferentially about the interior of the
casing groove, and impinges upon the baffles disposed in the
groove. The elastic fluid flow in the groove is deflected and
disrupted by the radial baffles disposed in the groove. The
deflected elastic fluid strikes against the blades and imparts a
force on the blades directed in a direction opposite the direction
of rotation of the blades. The force exerted by the deflected
elastic fluid on the back surface of the rotating blades acts in
the direction opposite the direction of rotation of the blades to
limit vibration in the blades.
In addition, a contoured application of a metallic material to the
rotating blades provides a further mechanical damper to prevent
vibration in the blades.
An object of the invention is to provide a damping arrangement to
limit vibration in the rotating blades of an axial flow elastic
fluid turbine apparatus.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be more fully understood from the following
detailed description of an illustrative embodiment taken in
connection with the accompanying drawings in which:
FIG. 1 is an elevation view, partially in section, of the last row
of turbine blades in an axial flow, elastic fluid turbine;
FIG. 2 is a view, partially in section, taken along section lines
II--II of FIG. 1;
FIG. 3 is a section view taken along section line III--III in FIG.
1; and,
FIG. 4 is a section view taken along section line IV--IV in FIG.
3.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Throughout the following description similar reference characters
refer to similar elements in all figures of the drawings.
Referring first to FIG. 1, an elevation view of the last row of
rotating blades and nozzles in an elastic fluid turbine 10 is
shown.
The turbine 10 comprises a steel casing 12 having a central axial
bore 14 extending therethrough, with a rotating shaft 16 disposed
centrally and axially in the bore 14. The shaft 16 has a plurality
of radially outward extending rotating blades 18 thereon. Each of
the rotating blades 18 has a root portion (not shown) which is
attached to a disc 20 which is securely affixed to the shaft 16 by
suitable means of attachment, such as a shrink fit. A platform
portion 22 of the blade 18 supports a curved airfoil portion 24
which ends in a tip 25. The blade 18 has a correspondingly curved
back portion 26. The airfoil portion 24 is a curved surface of
predetermined curvature having a rounded leading edge 28 and a
trailing edge 30. The last rotating blade row 18 is disposed
immediately before a diffuser 31 leading to a condenser element
(not shown).
A nozzle diaphragm 32 has a nozzle ring 34 attached to the casing
12. A plurality of nozzle blades 36 are attached to the nozzle ring
34 and are spaced a predetermined axial distance 35 from the
rotating blades 18. The nozzle blades 36 direct an axial flow 37 of
elastic fluid, usually high temperature and high pressure steam,
onto the rotating blades 18. The steam is directed onto the curved
airfoil portion 24 of the blade 18 at a predetermined angle so as
to provide the maximum possible conversion of energy carried by the
steam to rotating mechanical energy of the shaft 16. The nozzle
blades 36 are braced against each other by a shroud 38 to limit
vibration therein.
Although the drawing illustrates the last row of rotating blades 18
and nozzles 32, it is to be understood that the invention can be
utilized with any predetermined array of rotating blades within the
turbine 10.
A circumferential groove 40 is disposed about the interior of the
casing 12. The groove lies adjacent the tips 25 of blades 18. The
groove 40 has a predetermined number of radial baffles 44 disposed
along the inner surface 42 of the groove 40. The baffles 44 are
disposed so as to completely traverse the width of the groove 40.
There have been instances in the prior art where circumferential
grooves have been cut within the casing of the turbine, for
example, U.S. Pat. No. 1,999,711 and U.S. Pat. No. 3,011,763, which
deal primarily with preventing leakages of fluid between the close
clearances between the rotating and stationary members of the
turbine.
Referring now to FIG. 2, section view of the radial baffle 44,
taken along section line II--II of FIG. 1 is shown. The baffle 44
is a thin, metallic member, 1/8inch thick, and extends completely
across the groove 40 in the casing 12. The baffle 44 is a curved
member having a first end 46 and a second end 48, with a curved
surface 50 between the ends 46 and 48. The baffle 44 is disposed in
the groove 40 so that the first end 46 and the second end 48 of the
baffle 44 occupy the same relative positions on the baffle 44 as
the leading edge 28 and the trailing edge 30 occupy on the blade
18. The curved surface 50 of the baffle 44 occupies the same
relative position on the baffle 44 as the curved surface 24
occupies on the blade 18. It is to be understood, however, that the
baffle 44 can be of any desired shape or configuration.
The baffle 44 defines a predetermined angle 52 with a predetermined
axis 54, the axis 54 lying parallel to the axis of the turbine 10.
Although the ends 46 and 48 of the baffle 44 occupy corresponding
positions with the ends 28 and 30 respectively of the blade 18, it
is to be understood that the correspondence between the baffles 44
and the blades 18 describes only the orientation of the baffle 44
in the groove 40. It is also to be understood that the number of
baffles 44 disposed in the groove 40 is not necessarily equal to
the number of blades 18 disposed in the particular blade row of the
turbine 10.
As shown in FIG. 1, the tips 25 of the last row 18 of rotating
blades are adjacent the groove 40 disposed about the interior of
the casing 12. The tips 25 of the last row of blades 18 is of a
dimension sufficient to just fill the central bore 14 of the
casing. However, as the blades 18 rotate, thermal expansion of the
blades 18 and centrifugal force effects on the blades 18 tend to
cause the blade tips 25 to extend into the groove 40 for a
predetermined distance. A predetermined radial clearance 56 lies
between the tips 25 of the blades 18 and the radial baffle 44.
Referring now to FIG. 3, a section view of the turbine taken along
section line III--III of FIG. 1 is shown. In FIG. 3, each of the
plurality of radial baffles 44 is shown disposed a predetermined
circumferential distance 58 from the other. The tip 25 of the blade
18 is shown as extending into the groove 40 disposed in the casing
12. The portion of the blade 18 adjacent the tip 25 which extends
into the groove 40 is not subjected to the axial flow 37 (FIG. 1)
of elastic fluid and is not loaded as compared to that section of
the blade upon which the axial flow 37 (FIG. 1) of elastic fluid
impinges.
As the blades 18 rotate on the shaft 16 in a direction indicated by
the arrow 60, the elastic fluid is directed by the rotating blades
18, and by centrifugal force, into the groove 40 disposed on the
interior surface of the casing 12. The elastic fluid so directed
then begins to circumferentially flow in the direction 60, the flow
direction being the same as the direction of rotation of the blade
18. The elastic fluid flow in the groove 40 impinges upon the
plurality of radially disposed baffles 44 disposed traversely
across the groove 40. The baffles 44 deflect the circumferentially
rotating elastic fluid in the groove 40 and disrupt the flow of
fluid from the circumferential flow path in the groove 40.
A portion of the deflected fluid is deflected in a direction
indicated by an arrow 62 and impinges the backside 26 of the
rotating blades 18. The deflected elastic fluid imposes a force on
the backside 26 of the blades 18 in a direction 64 that is opposite
to the direction of motion 60. The force in direction 64 tends to
limit vibration in the rotating blades 18. By judicious spacing a
predetermined number of the radial baffles 44 in the groove 40,
selected harmonics of the frequency of vibration imposed on the
blades 18, such as particular vibratory modes at the blade tip 25,
can be eliminated.
As stated previously, one source of vibration to the rotating
blades 18 is the leakage of the elastic fluid through clearance
spaces which lie between the tip of the blade and interior portion
of the casing. Utilization of the teachings of the invention
eliminates this leakage flow. Without the groove 40 disposed on the
interior surface of the casing, the flow of the elastic fluid would
continue, as in the prior art, through a clearance space between
the tip of the blade and the interior surface of the casing and
cause reverse flow in certain portions of the last blade row.
However, since the groove 40 is disposed substantially
perpendicular to the axial flow path 37 of the elastic fluid, to
leak past the blade tip 25 the steam flow 37 must take a right
angle turn into the groove 40, therefore the leakage flow as just
described in the prior art is eliminated. The vibrations in the
blade 18 are also limited by the shearing action of the baffle 44
in shearing a portion of the volume of steam that is moving
circumferentially in the groove 40.
Referring now to FIG. 4, a section view of a rotating blade 18
taken along section line IV--IV of FIG. 1 is illustrated. It is
common practice to place on the backside of each of the rotating
blades 18 a strip of metallic material, commonly a Stellite, to
protect the blades, especially the last blade row, from corrosion
or erosion caused by impingement of condensed steam on the blade.
In this invention, the stellite strip is eliminated and a contour
fitting of Stellite is disposed on each of the rotating blades 18.
The Stellite possesses a modulus of elasticity which differs from
the modulus of elasticity of the steel utilized to fabricate the
rotating blades 18. Juxtapositioning of two materials having
dissimilar moduli of elasticity provides a further mechanical
damper to limit vibration of the rotating blades 18. The Stellite
is plasma applied in a manner well-known to those skilled in the
art so as to form a uniformly contoured coating 70, approximately
1/8 inch thick around each rotating blade 18.
It is thus seen that disposing a predetermined number of baffles at
predetermined spacing in a groove cut circumferentially into the
interior surface of the casing of an axial flow elastic fluid
turbine provides an effective damper arrangement to limit vibration
in the rotating blades of the turbine. The baffles deflect the
elastic fluid onto the rotating blades so that a force is exerted
in a direction that opposes limiting vibration in the blades. In
addition, disposing a coating of metallic material uniformly about
the blade also limits vibration in the rotating blades of an
elastic fluid turbine apparatus.
* * * * *