Information
-
Patent Grant
-
6761530
-
Patent Number
6,761,530
-
Date Filed
Friday, March 21, 200321 years ago
-
Date Issued
Tuesday, July 13, 200419 years ago
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Inventors
-
Original Assignees
-
Examiners
Agents
-
CPC
-
US Classifications
Field of Search
US
- 415 1745
- 415 1735
- 415 230
- 415 1737
- 277 303
- 277 412
- 277 418
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International Classifications
-
Abstract
A method for sealing between a rotary component and a stationary component. The method including positioning a seal assembly having a plurality of teeth adjacent the stationary component and positioning a packing surface to interface with the rotary component. The packing surface at the rotary component includes at least one step that has an axial width that is approximately equal to a distance the rotary component axially shifts relative to the stationary component during transition from startup to steady state operating conditions.
Description
BACKGROUND OF THE INVENTION
The present invention relates generally to rotary machines, and, more particularly, to methods and apparatus to facilitate reducing packing leakage losses in rotary machines.
Steam and gas turbines are used, among other purposes, to generate power for electric generators. A steam turbine has a flow path which typically includes, in serial-flow relationship, a steam inlet, a turbine, and a steam outlet. A gas turbine has a gas path which typically includes, in serial-flow relationship, an air intake (or inlet), a compressor, a combustor, a turbine, and a gas outlet (or exhaust nozzle). Compressor and turbine sections include at least one row of circumferentially-spaced rotating blades.
Turbine efficiency depends at least in part on controlling the radial clearance or gap defined between the tips of the rotor blade and the casing, and maintaining a clearance between the rotor and adjacent diaphragm or end packings. If either clearance is too large, steam or gas flow may leak through the clearance gaps, thus decreasing the turbine's efficiency. Alternatively, if either clearance is too small, the rotor blade tips may undesirably contact the surrounding casing during certain turbine operating conditions. Gas or steam leakage, either out of the flow path or into the flow path, from an area of higher pressure to an area of lower pressure, is generally undesirable.
To facilitate minimizing gas-path leakage, at least some known turbines use a plurality of labyrinth seals. Known labyrinth seals include longitudinally spaced-apart rows of labyrinth seal teeth to seal against high-pressure differentials that may be present in a turbine. However, labyrinth seals may wear-out after extended use, and prior to replacement, worn labyrinth seals may be ineffective for controlling leakage of fluid between the areas of generally high and low pressure. Furthermore, because of changing centrifugal forces induced to the blade tips, and thermal growth differences between the rotating rotor and stationary casing, the effectiveness of the labyrinth seals may be limited as the operating clearances change during periods of acceleration, deceleration, or transient operations during turbine startup. More specifically, during periods of differential centrifugal and thermal growth of the rotor and casing, clearance changes may cause undesirable rubbing of the moving blade tips against the stationary casing. A resulting increase in blade tip clearance may result in additional efficiency loss.
The anchor positions of the stationary parts do not typically align with the rotor thrust bearing and the steady state temperature of the rotor is typically hotter than the shells, therefore the thermal expansions of these components can result in large relative movements between the rotating and stationary parts, especially for the low pressure sections of steam turbines when the trust bearing is placed far from this section. The ability to predict (calculate) these relative axial differential expansions between the rotating and stationary parts, hereinafter referred as “axial shift”, fosters the use of this invention. All design variations of the invention serve to open radial clearances to avoid rubs during start-up (cold condition), when rotor vibrations are highest, and to close (tighten) the radial clearances during steady state (hot condition) to effectively lower secondary flow losses and increase machine efficiency.
BRIEF DESCRIPTION OF THE INVENTION
In one aspect, a method for sealing between a rotary component and a stationary component. The method including positioning a seal assembly having a plurality of teeth adjacent the stationary component and positioning a packing surface to interface with the rotary component. The packing surface at the rotary component includes at least one step that has an axial width that is approximately equal to a distance the rotary component axially shifts relative to the stationary component during transition from startup to steady state operating conditions.
In another aspect of the invention, a seal assembly for use in a turbine is provided. The seal assembly includes a rotary component including a packing surface and a stationary component including a plurality of teeth extending from the stationary component towards the packing surface. The packing surface including at least one step having an axial width that is approximately equal to a distance the rotary component axially shifts relative to the stationary component when the turbine transitions from a startup to a steady-state condition such that the seal assembly facilitates sealing between the rotary component and the stationary component.
In a further aspect, a turbine is provided. The turbine includes a housing, a rotor shaft rotatably coupled within the housing, a diaphragm coupled to the housing; and a seal assembly extending between the rotor shaft and the diaphragm. The seal assembly includes a rotary component including a packing surface and a stationary component including a plurality of teeth extending from the diaphragm stationary housing towards the packing surface to provide a seal therebetween. The packing surface comprising at least one step having an axial width that is approximately equal to a distance of axial shift of the rotary component relative to the stationary component when the turbine transitions from a startup to a steady state condition such that the seal assembly facilitates sealing between the rotary component and the stationary component.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1
is a cross-sectional view of an exemplary steam turbine;
FIG. 2
is a cross-sectional view of an exemplary seal assembly that may be used with the steam turbine shown in
FIG. 1
;
FIG. 3
is an enlarged view of the seal shown in FIG.
2
and in a cold (start-up) condition;
FIG. 4
is an enlarged view of the seal shown in FIG.
2
and in a hot (steady state) condition;
FIG. 5
is an enlarged cross-sectional view of an alternative embodiment of a seal that may be used with the steam turbine shown in a hot condition in
FIG. 1
;
FIG. 6
is an enlarged cross-sectional view of another alternative embodiment of a seal that may be used with the steam turbine in a hot condition shown in
FIG. 1
;
FIG. 7
is an enlarged cross-sectional view of a further alternative embodiment of a seal that may be used with the steam turbine in a cold (start-up) condition shown in
FIG. 1
; and
FIG. 8
is an enlarged view of the seal shown in FIG.
7
and in a hot (steady state) condition.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1
is a cross-sectional view of an exemplary steam turbine
10
. Steam turbine
10
includes a shaft
12
extending through turbine
10
and rotatably supported at each end by bearing supports
14
. A plurality of rows of turbine blades
16
are coupled to shaft
12
, and a plurality of stationary turbine nozzles
18
are positioned between adjacent rows of turbine blades
16
. Turbine blades
16
are coupled to turbine shaft
12
, and turbine nozzles
18
are coupled to support members or nozzle diaphragms
20
attached to a housing or shell
22
surrounding turbine blades
16
and nozzles
18
. Steam inlet ports
24
channel steam supplied from a steam source into turbine
10
, and main steam control valves
26
control the flow of steam into turbine
10
.
In operation, steam is directed through nozzles
18
to impact blades
16
, which causes blades
16
to rotate with turbine shaft
12
. A portion of steam discharged through nozzles
18
enters extraction chambers
30
and
32
, and a predetermined amount of steam is also routed to various feedwater heaters (not shown). After the steam passes through turbine blades
16
, the steam is discharged through steam exhaust casing
34
and exhaust outlet
36
and returned to a condenser (not shown) for recovery.
FIG. 2
is a cross-sectional view of an exemplary seal assembly
40
that may be used with turbine
10
.
FIG. 3
is an enlarged cross-sectional view of seal assembly
40
in a cold (start-up) condition.
FIG. 4
is an enlarged cross-sectional view of seal assembly
40
in a hot (steady-state) condition. Diaphragm
20
includes an outer ring, portion
41
that is coupled to turbine housing
22
(shown in FIG.
1
), and an inner ring portion
42
. Turbine blades
16
include roots
44
that are coupled to wheels
46
extending from turbine shaft
12
. Shaft
12
and wheels
46
are rotatable about an axis of rotation
48
. Alternatively, seal assembly may be positioned at the rotor end, whereby the position of seal assembly is not affected at the method of sealing.
Seal assembly
40
is positioned between rotor shaft
12
and inner ring portion
42
, and includes a packing ring
54
that is mounted in a groove
56
that extends circumferentially about diaphragm inner ring portion
42
. Packing ring
54
includes a seal shroud
58
and a sealing member
64
. In the exemplary embodiment, sealing member
64
is a plurality of axially-spaced seal teeth
64
that extend radially outwardly from seal shroud
58
. Seal teeth
64
are positioned to substantially obstruct the flow of fluid from a high pressure region to a low pressure region on opposite sides of the seal assembly
40
. Alternatively, packing sealing member
64
includes, but is not limited to, a brush seal (not shown) or a combination of axially-spaced seal teeth
64
and a brush seal. Turbine shaft
12
includes a packing surface
66
, and packing ring
54
is coupled to turbine shaft
12
to facilitate sealing a gap
68
defined between packing surface
66
and diaphragm inner ring portion
42
.
Seal teeth
64
include at least one long teeth region
70
and at least one short teeth region
72
, whereas region
72
includes a plurality of teeth
64
that extend outwardly a shorter distance than the teeth
64
within region
70
. Packing surface
66
includes at least one step
74
that is formed by at least one recess
76
in packing surface
66
.
Seal teeth
64
force the fluid to follow a tortuous path whereby a pressure drop is created. The aggregate of the pressure drops across seal assembly
40
defines the pressure difference between the high and low pressure regions on each side of seal assembly
40
. Packing ring
54
is typically biased and is movable radially when subjected to severe rotor/seal interference. In one embodiment, packing ring
54
is biased radially outwardly away from rotor shaft
12
, for example, during startup and shutdown operations, such that fluid pressure between packing ring
54
and rotor shaft
12
displaces packing ring
54
radially inwardly to maintain a smaller clearance with rotor shaft
12
, after rotor shaft
12
is at a desired operating space.
During a cold or startup condition, long teeth region
70
is positioned opposite recess
76
and short teeth region
72
is positioned opposite step
74
. Furthermore, teeth
64
positioned within long teeth region
70
do not experience rubbing contact with packing surface
66
during the startup condition. As turbine
10
transitions to the hot or steady state condition, the temperature change of rotor shaft
12
causes an axial shift of rotor shaft
12
in the direction of arrow
78
, as shown in FIG.
4
. More specifically, rotor shaft
12
shifts axially relative to sealing members
64
a distance approximately equal to the width of step
74
. The axial shift of rotor shaft
12
causes step
74
to facilitate sealing between step
74
and long teeth region
70
, while recess
76
is positioned opposite short teeth region
72
. Furthermore, because of the axial shift between the startup and steady state positions, the number of working teeth
64
prevented from rubbing facilitates operating with minimum leakage losses.
The change in axial shift by rotor shaft
12
can be measured or calculated, such as through computer modeling or analysis, for determining and configuring the axial width of step
74
. Thus, step
74
is provided with an axial width approximately equal to the amount of axial shift of rotor shaft
12
relative to sealing members
64
between the startup condition and the steady state condition.
FIG. 5
is a cross-sectional view of an alternative embodiment of seal assembly
40
about rotor shaft
12
in turbine
10
in a hot (steady state) condition. Seal assembly
40
in
FIG. 5
is substantially similar to seal assembly
40
in
FIGS. 3 and 4
, and components in seal assembly
40
that are identical to components in seal assembly
40
used in
FIGS. 3 and 4
are identified in
FIG. 5
using the same reference numerals used in
FIGS. 3 and 4
. As shown in
FIG. 5
, plurality of teeth
64
have approximately the same length.
FIG. 6
is a cross-sectional view of an alternative embodiment of seal assembly
40
about rotor shaft
12
in turbine
10
in a hot (steady state) condition. Seal assembly
40
in
FIG. 6
is substantially similar to seal assembly
40
in
FIGS. 3 and 4
, and components in seal assembly
40
that are identical to components in seal assembly
40
used in
FIGS. 3 and 4
are identified in
FIG. 6
using the same reference numerals used in
FIGS. 3 and 4
. As shown in
FIG. 6
, plurality of teeth
64
have at least one region without teeth
80
. In the startup condition, plurality of teeth
64
are positioned opposite recess
76
and at least one region without teeth
80
is positioned opposite step
74
. In the steady state condition, rotor shaft
12
shifts axially relative to sealing members
64
a distance approximately equal to the width of step
74
so that step
74
provides a seal between step
74
and plurality of teeth
64
while recess
76
is positioned opposite at least one region without teeth
80
.
In another embodiment, packing surface
66
has a plurality of teeth forming a plurality of steps and a plurality of recesses between plurality of steps for sealing engagement with plurality of teeth
64
of packing ring
54
to provide a seal between the plurality of steps and the plurality of teeth.
FIG. 7
is a cross-sectional view of an alternative embodiment of seal assembly
40
about rotor shaft
12
in turbine
10
in a cold (start-up) condition.
FIG. 8
is a cross-sectional view of the alternative embodiment of seal assembly
40
in
FIG. 7
in a hot (steady state) condition. Seal assembly
40
in
FIG. 7
is substantially similar to seal assembly
40
in
FIGS. 3 and 4
, and components in seal assembly
40
that are identical to components in seal assembly
40
used in
FIGS. 3 and 4
are identified in
FIG. 7
using the same reference numerals used in
FIGS. 3 and 4
. Packing surface
66
includes a plurality of steps
74
staggered lower than packing surface
66
, such that each step
74
is staggered lower than the previous step in the direction of a rotor axial movement from the startup to the steady state operation condition resulting in a “stairs” formation. Plurality of teeth
64
are similarly staggered with respect to each corresponding step
74
so as to maintain substantially the same clearance between plurality of teeth
64
and plurality of staggered steps
74
along the length of gap
68
.
During startup, radial clearance increases by the step height and prevents plurality of teeth
64
from rubbing. In the steady state condition as shown in
FIG. 7
, rotor shaft
12
moves the amount of axial clearance or the step width to provide a seal between steps
74
and plurality of teeth
64
. This reduces the radial clearance of the labyrinth thus reducing labyrinth losses and increasing turbine efficiency. In addition, the axial length of the packing surface
66
is reduced and plurality of teeth
64
are working during the steady state condition.
The above described labyrinth seal allows reduced packing leakage losses and also minimizes rubbing of teeth during transient (startup and shutdown) operation for turbines with axial differences between startup and steady state rotor and stator positions. Determining the axial shift of the rotor relative to stationary component between startup and steady state conditions facilitates designing the step to have an axial width approximately equal to the axial shift of the rotor relative to stationary component so as to minimize the amount of contact between the labyrinth teeth and the packing surface. As a result, the labyrinth seal significantly improves the performance of the turbine in a cost effective and time saving manner.
Although the invention is herein described and illustrated in association with a turbine for a steam turbine engine, it should be understood that the present invention may be used for controlling leakage of any fluid between any generally high pressure area and any generally low pressure area within a steam turbine engine. Accordingly, practice of the present invention is not limited to steam turbine engines.
While the invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
Claims
- 1. A method for sealing between a rotary component and a stationary component, said method comprising:positioning a seal assembly having a plurality of teeth adjacent the stationary component; positioning a packing surface to interface with the rotary component, wherein the packing surface at the rotary component includes at least one step that has an axial width that is approximately equal to a distance the rotary component axially shifts relative to the stationary component during transition from startup to steady state operating conditions; and determining the distance the rotary component shifts axially relative to the stationary component during the transition between startup and steady-state operating conditions.
- 2. The method of claim 1, wherein coupling a packing surface to the rotary components further comprises coupling a packing surface including a plurality of steps and a plurality of recesses between the steps to the rotary component, wherein the plurality of teeth include at least one long teeth region that is opposite to at least one recess, and at least one short teeth region that is opposite to at least one step in the startup condition such that a seal is facilitated to be formed between the at least one step and the at least one long teeth region, following an axial shift of the rotary component relative to the stationary component.
- 3. The method of claim 1, wherein coupling a packing surface to the rotary components further comprises coupling a packing surface including a plurality of steps and a plurality of recesses between the steps to the rotary component, wherein the plurality of teeth including at least one region without teeth that is opposite to at least one step in the startup condition such a seal is facilitated between the at least one step and the plurality of teeth, following an axial shift of the rotary component relative to the stationary component.
- 4. The method of claim 1 wherein coupling a packing surface to the rotary components further comprises coupling a packing surface including a plurality of steps staggered lower than said packing surface, each step being staggered lower than the previous step to the rotary component in the direction of a rotor axial movement from the startup to the steady state operation condition, wherein the plurality of teeth are staggered with respect to the plurality of steps so as to maintain substantially the same clearance between the plurality of teeth and the plurality of staggered steps in the startup condition such that a seal is facilitated to be formed between the steps and the teeth following an axial shift of the rotary component relative to the stationary component.
- 5. A seal assembly for use in a turbine including at least one diaphragm and at least one rotor shaft, said seal assembly extending between the diaphragm and the rotor shaft and comprising:a rotary component comprising a packing surface; and a stationary component comprising a plurality of teeth extending from said stationary component towards said packing surface, said packing surface comprising at least one step having an axial width that is approximately equal to a distance said rotary component axially shifts relative to said stationary component when the turbine transitions from a startup to a steady-state condition such that said seal assembly facilitates sealing between said rotary component and said stationary component.
- 6. A seal assembly according to claim 5 wherein said packing surface comprises a plurality of steps and a plurality of recesses, each said recess between adjacent said steps, said plurality of teeth further comprise at least one long teeth region positioned opposite at least one recess, and at least one short teeth region positioned opposite at least one step in the startup condition such that a seal is formed between said at least one step and said at least one long teeth region following an axial shift of the rotary component relative to said stationary component.
- 7. A seal assembly according to claim 5 wherein said packing surface comprises a plurality of steps and a plurality of recesses each said recess between adjacent said steps, said plurality of teeth further comprise at least one region without teeth, said at least one region without teeth positioned opposite to at least one step in the startup condition such that a seal is formed between said at least one step and said plurality of teeth following an axial shift of said rotary component relative to said stationary component.
- 8. A seal assembly according to claim 5 wherein said packing surface further comprises a plurality of steps staggered lower than said packing surface, each step being staggered lower than the previous step in the direction of a rotor axial movement from the startup to the steady state operation condition, said plurality of teeth staggered with respect to said plurality of steps so as to maintain substantially the same clearance between the plurality of teeth and the plurality of staggered steps in the startup condition such that a seal is formed between said steps and said plurality of teeth following an axial shift of said rotary component relative to said stationary component.
- 9. A turbine comprising:a housing; a rotor shaft rotatably coupled within said housing; a diaphragm coupled to said housing; and a seal assembly extending between said rotor shaft and said diaphragm, said seal assembly comprising: a rotary component comprising a packing surface; and a stationary component comprising a plurality of teeth extending from said diaphragm stationary housing towards said packing surface to provide a seal therebetween, said packing surface comprising at least one step having an axial width that is approximately equal to a distance of axial shift of said rotary component relative to said stationary component when the turbine transitions from a startup to a steady state condition such that said seal assembly facilitates sealing between said rotary component and said stationary component.
- 10. A turbine according to claim 9 wherein said packing surface comprises a plurality of steps and a plurality of recesses, each said recess between adjacent said steps, said plurality of teeth further comprise at least one long teeth region positioned opposite at least one recess, and at least one short teeth region positioned opposite at least one step in the startup condition such that a seal is formed between said at least one step and said at least one long teeth region following an axial shift of said rotary component relative to said stationary component.
- 11. A turbine according to claim 9 wherein said packing surface comprises a plurality of steps and a plurality of recesses each said recess between adjacent said steps, said plurality of teeth further comprise at least one region without teeth, said at least one region without teeth positioned opposite to at least one step in the startup condition such that a seal is formed between said at least one step and said plurality of teeth following an axial shift of said rotary component relative to said stationary component.
- 12. A turbine according to claim 9 wherein said packing surface further comprises a plurality of steps staggered lower than said packing surface, each step being staggered lower than the previous step in the direction of a rotor axial movement from the startup to the steady state operation condition, said plurality of teeth staggered with respect to said plurality of steps so as to maintain substantially the same clearance between the plurality of teeth and the plurality of staggered steps in the startup condition such that a seal is formed between said steps and said plurality of teeth following an axial shift of said rotary component relative to said stationary component.
US Referenced Citations (3)