U.S. patent number 3,880,435 [Application Number 05/426,311] was granted by the patent office on 1975-04-29 for sealing ring for turbo machines.
This patent grant is currently assigned to Stal-Lavel Turbin AB. Invention is credited to Per Gosta Thornbald.
United States Patent |
3,880,435 |
Thornbald |
April 29, 1975 |
Sealing ring for turbo machines
Abstract
A sealing ring for a turbo machine to limit and define the
radial clearance between the outer edge of a turbine disc and its
corresponding stator part is disclosed. The sealing ring is divided
into discrete sealing block segments, each comprising a smooth
metallic inner strip, an intermediate corrugated metallic strip,
and a bundle of flat metal plate layers, with provision for cooling
air to be introduced and distributed through each segment.
Inventors: |
Thornbald; Per Gosta (Finspong,
SW) |
Assignee: |
Stal-Lavel Turbin AB (Finspong,
SW)
|
Family
ID: |
20316254 |
Appl.
No.: |
05/426,311 |
Filed: |
December 19, 1973 |
Foreign Application Priority Data
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|
|
|
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Jan 5, 1973 [SW] |
|
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73001588 |
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Current U.S.
Class: |
277/416; 277/417;
277/930; 415/173.1; 415/178 |
Current CPC
Class: |
F01D
11/08 (20130101); F16J 15/445 (20130101); Y10S
277/93 (20130101) |
Current International
Class: |
F01D
11/08 (20060101); F16J 15/44 (20060101); F16j
015/44 () |
Field of
Search: |
;415/174,173,115,116
;277/53,22,235R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Smith; Robert I.
Attorney, Agent or Firm: Munson; Eric Y.
Claims
I claim:
1. Sealing ring for a turbo machine for limiting and defining the
radial clearance between the outer edges of the vanes of a turbine
rotor disc and the corresponding stator housing, the sealing ring
being composed of a plurality of sealing block segments which are
mounted circumferentially on the stator housing, spaced from each
other by peripheral gaps, cooled by air flowing through them, and
which comprise:
a smooth arcuate metallic strip on the inner surface of each
sealing block segment facing the turbine rotor disc;
a sinusoidally corrugated metallic strip mounted on the radially
outward side of said smooth metallic strip so that its inner
corrugations are secured to said smooth metallic strip along the
lines of contact between said two strips; and
a stack of parallel flat metallic sheets mounted on the radially
outward side of said corrugated metallic strip, the faces of said
metallic sheets being oriented transversely to the corrugations of
said corrugated metallic strip and perpendicular to the turbine
shaft, said metallic sheets being divided into sectors having a
width corresponding to the pitch of the corrugations of said
corrugated strip, the inner edge contour of said sheet sectors
being so adapted to the shape of said corrugated strip that a
channel for cooling air is formed between said corrugated strip and
sectors of said sheet stack.
2. Sealing ring according to claim 1, further comprising:
a pair of sheet layers for each sealing block segment each divided
into sectors, positioned as a cover layer on either side of said
sheet stack and extending radially outwardly from said smooth
metallic strip to the outer periphery of the sealing block, thereby
sealing the block and said cooling channel on both sides.
3. Sealing ring according to claim 1, wherein said sheet sectors in
each layer of said sheet stack are displaced half the pitch of the
corrugations of said corrugated strip with respect to the sectors
of the adjacent sheet layer.
4. Sealing ring according to claim 3, wherein the radially inwardly
directed point of each said sector in every second sheet layer of
said sheet stack is attached to the bottom of the corresponding
corrugation in said corrugated strip, while the alternate sheet
layers of said sheet stack are attached at each of their said
sectors to the radially outward top of the corresponding
corrugation in said corrugated strip.
5. Sealing ring according to claim 1, wherein in every second sheet
layer of said sheet stack the radial height of said sectors is less
than the radial height of said sectors in the alternate sheet
layers, so that distribution channels for cooling air are formed
between the sheet layers in the outward portion of each sealing
block segment, all said sectors at the ends of each block segment
having full radial height to close said air distribution channels
at their ends.
6. Sealing rings according to claim 1, wherein cooling air is
supplied to each sealing block segment through an air introduction
channel in the stator, and wherein said sectors of the layers of
said sheet stack in an axial zone adjacent to said air introduction
channel are formed with reduced radial height, to distribute
cooling air over each sealing block.
7. Sealing ring according to claim 1, wherein cooling air is
supplied to each sealing block segment through said air
introduction channel in the stator and, in order to provide for
passage of cooling air to said channel between said corrugated
strip and said sheet stack, a suitable selected number of said
sectors of the layers of said sheet stack are omitted.
Description
BACKGROUND OF THE INVENTION
For satisfactory efficiency in the operation of a turbo machine
(turbine or compressor), it is vital that the clearance between the
tops of the rotor blades and the surrounding stator parts be kept
as small as possible. Contact between the rotor blades and the
stator, however, might cause considerable damage, and must be
avoided. Fluctuating temperatures in the rotor, blades and stator,
as well as different rates of heating or cooling induced by
changing operating conditions, cause uneven thermal expansion or
contraction of the various turbine parts and hence the top
clearance gap may vary considerably. In order to avoid the complete
disappearance of this clearance gap under the most unfavorable
temperature combinations and conditions, the nominal clearance
provided must often be chosen so large that the turbine opration is
rather inefficient when normal operating conditions prevail.
To improve the above situation, special sealing and screening
elements have been provided, the radial position of which is
determined by the stator, and the function of which is to screen
off the stator from the hot turbine gas and maintain it at a low
temperature during turbine operation. In this manner, variations in
the temperature in the stator which determines the clearancce are
reduced, and the ability to maintain a minimum safe clearance is
greatly enhanced.
SUMMARY OF THE INVENTION
The present invention is directed toward a novel improved
construction of the aforementioned sealing and screening elements,
and provides a sealing device in the form of ring segments, or
"blocks", arranged around the stator housing with small peripheral
gaps for expansion between segments.
Each sealing block comprises a stack of flat sheet metal layers
mounted on a corrugated metal strip, which in turn is supported on
a smooth metal strip facing the turbine rotor. Suitable cooling air
passages are provided within this assembly to counteract the heat
from the turbine gas. The novel construction incorporated into
these block segments supplies flexibility and at the same time
satisfactory cooling of both the sealing ring and the surrounding
stator parts.
Since the successful application of such sealing block segments is
strongly dependent on temperature variations between stator and
rotor, the use of the block segments of this invention is
particularly successful in gas turbines. However, even in steam
turbines and turbo compressors, temperature conditions are such
that considerable demands are placed on the sealing rings, and
hence this invention is of importance for all types of turbo
machines.
The present invention will be further described with reference to
the accompanying drawings, and defined by the accompanying
claims.
DRAWINGS
In the drawings,
FIG. 1 is a sectional view through part of a turbo machine
utilizing a sealing ring constructed in accordance with this
invention;
FIG. 2 is an enlarged, more detailed view of the sealing ring block
and its mounting shown in FIG. 1;
FIG. 3 is a developed view of a sealing ring block seen in axial
direction, and with successive layers removed to show the inner
construction;
FIG. 4 is a view of the sealing ring block of FIG. 3 as seen in
radial direction from the outside; and
FIG. 5 is a view similar to FIG. 3 but showing an alternate
embodiment of the sealing ring structure of this invention.
DESCRIPTION OF PREFERRED EMBODIMENTS
In FIG. 1, part of turbine rotor disc 10 is shown with a vane 11
projecting radially therefrom. Guide vane 12 is secured at its head
13 to a flange 14 in stator housing 15. Turbine disc 10 is
circumferentially encompassed by the sealing ring 16 of this
invention, to ensure that a minimum of gas or steam leaks between
rotor disc 10 and stator housing 15, and therefore to maintain a
gap 17 between vanes 11 and sealing ring 16 as small as possible
consistent with avoiding any contact or catching of vanes 11 by
sealing ring 16. To control the variations in gap 17 which might be
created by fluctuating temperatures in turbo machine operation,
sealing ring 16 is constructed of arcuate stacks of sheet metal
plates with provisions for cooling, as will be more fully described
hereinafter. Attachment ring 18, secured to head 13 of guide vane
12, maintains sealing ring 16 in position, as shown in fuller
detail in FIG. 2.
Attachment ring 18 has flanges 19 and 20 which, in combination with
rivets 21, hold together the stacks of sheet metal plates 3, 4 and
5 of sealing ring 16. Each stack of plates forms a block or
segment; a plurality of these blocks, arranged circumferentially
between flanges 19 and 20 of attachment ring 18 and held in place
by rivets 21, together form sealing ring 16 and are spaced from
each other with a slight gap to permit peripheral expansion. During
operation of the turbo machine, the block segments of sealing ring
16 are cooled by air which is forced inwardly through a cooling
channel 22 formed in attachment ring 18 and is then distributed
over and through each block.
FIGS. 3 and 4 clearly illustrate the construction of block segments
which form sealing ring 16. For simplicity and clarity, FIG. 3 is
shown as a developed straight view, but in reality each block
segment is arcuately curved so that it forms one sector of ring 16.
The main body of each sealing block comprises a bundle of parallel
flat sheet metal plates oriented perpendicularly to the turbine
shaft, the outermost layer on each side of the bundle being a
series of substantially rectangular cover plates 5. Between the two
cover layers 5, alternate layers of differing plates 3 and 4 (to be
described below) are sandwiched to complete the bundle or stack.
The radially innermost end of each sealing block of ring 16,
adjacent to rotor 10, is faced with a smooth metal strip 1, on
which a sinuously corrugated metal strip 2 is superposed. Strips 1
and 2 are attached to each other along their lines of contact by
such conventional means as, for example, point welding. Plates 3
and 4 are shaped at their inner edges to follow generally the
curvature of corrugated strip 2.
It can be observed in FIG. 3, where successive layers of plates
have been removed from left to right to show the interior plates of
a sealing block segment, that outer cover plates 5 are
substantially rectangular and extend the entire height of the
block. Behind the cover layer 5 is a layer of plates 3, each shaped
with a peak extending into and secured to one of the radially
inward depressions of corrugated strip 2, preferably by point
welding. Except for these secured peaks, the inner edges of plates
3 are spaced from corrugated strip 2, providing cooling gaps 6
therebetween.
Analogously, the next successive layer of plates 4 are shaped to
contact and be secured in the same manner to the radially outward
peaks of corrugated strip 2, while the remaining inner edge
surfaces of plates 4 are spaced from strip 2, thus also forming
cooling gaps 6. The interruption of cooling gaps 6 by welded
contact points forces cooling air on its way along corrugated strip
2 to cross over constantly between the metal layers 3 and 4,
ensuring efficient cooling of strip 2 and the inner portions of
plates 3 and 4. The cooling air emerges from cooling gap 6 into
space 7 between adjacent sealing blocks.
As previously described, the cooling air is introduced into sealing
ring 16 through channel 22 in attachment ring 18. Plates 4 are made
shorter in height than plates 3, between which air distribution
channels 8 are thereby formed. At either end of each sealing block
and in each plate 4 layer, plates 4a, similar to plates 4 but of a
height equal to plates 3, serve as end boundaries to channels 8,
while the radially outward limit of these channels 8 is defined by
attachment ring 18.
In addition, plates 3 are omitted from their layers in the area of
air introduction channel 22, so that a transverse connection
between distribution channels 8 is created, as well as openings 9
down through the sealing block for direct communication with
cooling gaps 6 along corrugated strip 2.
During operation of the turbo machine, it is evident that smooth
metal strip 1 comes into direct contact with the hot gas or steam
in vanes 11 and 12 so that strip 1, which receives substantially no
cooling, assumes the ambient temperature and correspondingly
expands. This causes corrugated strip 2 to be straightened out
somewhat and plates 3 and 4 are slightly separated from each other
so that cooling air from distribution channels 8 can penetrate
between the plates along the entire sealing block providing uniform
and efficient cooling, the cooling process becoming more effective
the more strip 1 is expanded by increasing temperature. Spaces 7
between adjacent sealing blocks permit this expansion freely, like
the rail gaps in a railway track. Flanges 19 and 20 of attachment
ring 18 may be interrupted as shown in FIG. 4 so that they overlap
spaces 7.
It should be noted that in FIG. 4, for clarity, the boundary lines
between different layers of sheet metal, as well as between metal
sheets and spaces, have been drawn in heavy lines, while the
boundaries between similar sheets are designated by lighter
lines.
As may be seen in FIG. 2, a groove 23 in attachment ring 18 may be
provided in order to assist in the distribution of air from channel
22 to the sealing block segment.
It has been noted above that, although shown straight in FIG. 3,
each sealing block segment is in reality arcuate, constituting a
sector of sealing ring 16. For this purpose, plates 3 and 4 may be
shaped with non-parallel converging side edges so that they
automatically form a ring sector when the plates for each layer are
fitted together. Alternatively, it is possible to make all the
plates with parallel edges so that narrow wedge-shaped spaces
formed between the plates in any layer will permit cooling air to
pass from distribution channels 8 toward cooling gaps 6. The latter
arrangement makes it possible to use the same plates for sealing
rings of different diameters.
Each block segment of sealing ring 18 is formed by providing the
sheet layer 3, 4 and 5 with holes to accept rivets 21, and its
shape when mounted is determined by the curvature of flanges 19 and
20 of attachment ring 18.
In the embodiment of the inventive sealing ring 16 of FIGS. 1-4,
and as clearly shown in FIG. 3, the radial height of each block
segment is defined by the height of plates 3. Since plates 3,
attachment ring 18 and stator housing 15 are all cooled to a
certain known temperature, only the temperature expansion of rotor
10 need be considered when determining the size of gap 17 between
vanes 11 and sealing ring 16.
FIG. 5 illustrates an alternate embodiment of a sealing block
segment, in which plates 4' correspond to plates 4 but have full
height. In this construction, when the sealing block segment
stretches peripherally due to the expansion of strip 1, it shrinks
radially, since, as corrugated strip 2 is stretched and
straightened, high plate layers 4' are pulled down between low
plate layers 3'. By suitable dimensioning of the corrugations in
strip 2 in relation to the coefficient of expansion of strip 1,
this feature can be exploited to predetermine the width of gap 17
between stator sealing 16 and rotor vane 11, and thus to maintain
gap 17 at a constant minimum value with varying temperature and
load in the turbo machine.
For compressors and gas turbines, the cooling of the block segments
of sealing ring 16 is preferably accomplished by providing
compressed air to channel 22, whereas for steam turbines, cool
steam of suitable pressure may be employed.
* * * * *