U.S. patent application number 13/005752 was filed with the patent office on 2012-07-19 for seal system for cooling fluid flow through a rotor assembly in a gas turbine engine.
Invention is credited to Abdullatif M. Chehab, Ching-Pang Lee, Shantanu P. Mhetras, Manjit Shivanand.
Application Number | 20120183389 13/005752 |
Document ID | / |
Family ID | 46490889 |
Filed Date | 2012-07-19 |
United States Patent
Application |
20120183389 |
Kind Code |
A1 |
Mhetras; Shantanu P. ; et
al. |
July 19, 2012 |
SEAL SYSTEM FOR COOLING FLUID FLOW THROUGH A ROTOR ASSEMBLY IN A
GAS TURBINE ENGINE
Abstract
A sealing system for a rotor assembly in a gas turbine engine is
disclosed. The sealing system may include a seal formed from a side
block and an upper seal that seals a gap between a radially outward
extending first rotor supply channel in a rotor assembly
terminating at an inlet of an axially extending second rotor supply
channel that is in fluid communication with an internal blade
cooling system of a turbine blade. The seal may include components
that enhance the flow of cooling fluids over conventional
configurations. In another embodiment, the sealing system may
include an integrated sealing block configured to seal a gap
between adjacent turbine blades at an intersection between the
first and second rotor supply channels. The integrated sealing
block may be formed from a radially inward extending leg and
central body.
Inventors: |
Mhetras; Shantanu P.;
(Orlando, FL) ; Shivanand; Manjit; (Orlando,
FL) ; Chehab; Abdullatif M.; (Oviedo, FL) ;
Lee; Ching-Pang; (Cincinnati, OH) |
Family ID: |
46490889 |
Appl. No.: |
13/005752 |
Filed: |
January 13, 2011 |
Current U.S.
Class: |
415/115 |
Current CPC
Class: |
F01D 5/3015
20130101 |
Class at
Publication: |
415/115 |
International
Class: |
F01D 5/18 20060101
F01D005/18 |
Claims
1. A sealing system for a turbine blade and rotor assembly for a
gas turbine engine, comprising: a rotor assembly having at least
one row of turbine blades extending radially outward; at least one
internal rotor cooling system in fluid communication with an
internal blade cooling system within at least one turbine blade;
wherein the at least one internal rotor cooling system comprises a
radially outward extending first rotor supply channel terminating
at a radially outward end of the outward extending first rotor
supply channel and at an inlet of an axially extending second rotor
supply channel that is in fluid communication with the internal
blade cooling system; at least one side block sealing a portion of
a gap between adjacent turbine blades at an intersection between
the first and second rotor supply channels, wherein the at least
one side block extends partially circumferentially around the rotor
assembly, is curved circumferentially, is attached to a radially
outer end of a wall defining the first rotor supply channel, and
has a generally linear inner surface forming a portion of the first
rotor supply channel; and at least one upper seal sealing a
remaining portion of the gap between adjacent turbine blades at the
intersection between the first and second rotor supply channels,
wherein the at least one upper seal contacts the at least one side
block and includes a radially inner surface that is generally flat
and flush with an inner surface forming the second rotor supply
channel.
2. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 1, further comprising at least one
tooth on the at least one upper seal extending radially outward
from the at least one upper seal and contacting two turbine blades
of the at least one row of turbine blades.
3. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 2, further comprising an arm extending
axially from the at least one upper seal away from the intersection
between the at least one upper seal and the at least one side
block, wherein the at least one tooth extends radially outward from
the at least one arm.
4. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 3, wherein the at least one tooth
extending radially outward from the at least one arm comprises two
teeth extending radially outward from the at least one arm.
5. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 3, wherein at least one tooth forms an
interference fit in a cavity in each of the two turbine blades to
reduce leakage.
6. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 1, wherein the at least one upper seal
further includes at least one tooth extending radially inward from
a radially inner surface of the at least one upper seal, wherein
the at least one tooth has a width that is less than a width of the
at least one side block and the tooth contacts that at least one
side block.
7. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 1, wherein the at least one side block
further includes at least one wire seal extending radially inward
from a radially inner surface of the at least one side block,
wherein the at least one wire seal has a width that is less than a
width of the at least one side block.
8. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 1, wherein the first rotor supply
channel has a diameter of about 15 millimeters.
9. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 1, wherein the at least one side block
sealing a portion of a gap between adjacent turbine blades at an
intersection between the first and second rotor supply channels
extends circumferentially to seal at least two gaps between
multiple sets of turbine blades in the at least one row of turbine
blades.
10. A sealing system for a turbine blade and rotor assembly for a
gas turbine engine, comprising: a rotor assembly having at least
one row of turbine blades extending radially outward; at least one
internal rotor cooling system in fluid communication with an
internal blade cooling system within at least one turbine blade;
wherein the at least one internal rotor cooling system comprises a
radially outward extending first rotor supply channel terminating
at a radially outward end of the outward extending first rotor
supply channel and at an inlet of an axially extending second rotor
supply channel that is in fluid communication with the internal
blade cooling system; at least one integrated sealing block sealing
a gap between adjacent turbine blades at an intersection between
the first and second rotor supply channels, wherein the at least
one integrated sealing block includes a radially inward extending
leg and central body; wherein the at least one integrated sealing
block extends partially circumferentially around the rotor
assembly, is curved circumferentially, wherein the radially inward
extending leg is attached to a radially outer end of a wall
defining the first rotor supply channel and has a generally linear,
radially extending, inner surface on the leg forming a portion of
the first rotor supply channel; and wherein the central body
includes an axially extending inner surface that is generally flat
and flush with an inner surface forming the second rotor supply
channel.
11. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 10, further comprising at least one
tooth extending axially from the central body into a cavity within
a turbine blade forming a portion of the at least one row of
turbine blades.
12. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 11, wherein a radially inner surface of
the at least one tooth is generally flat and flush with an inner
surface forming the second rotor supply channel.
13. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 12, wherein the at least one tooth
comprises two teeth extending axially from the central body into
cavities within the turbine blade forming a portion of the at least
one row of turbine blades, wherein each of the teeth contact at
least one surface within each cavity to reduce leakage.
14. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 13, further comprising a filleted
intersection between the radially inward extending leg and the
central body.
15. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 10, further comprising at least one
tooth extending radially outward from the central body and
contacting two turbine blades of the at least one row of turbine
blades.
16. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 15, further comprising an arm extending
axially from the central body away from the intersection between
the central body and the radially inward extending leg, wherein the
at least one tooth extends radially outward from the at least one
arm.
17. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 16, wherein the at least one tooth
extending radially outward from the at least one arm comprises two
teeth extending radially outward from the at least one arm.
18. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 17, wherein at least one tooth forms an
interference fit in a cavity in each of the two turbine blades to
reduce leakage.
19. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 10, further comprising at least one
wire seal extending radially inward from a radially inner surface
of the radially inward extending leg, wherein the at least one wire
seal has a width that is less than a width of the radially inward
extending leg.
20. The sealing system for a turbine blade and rotor assembly for a
gas turbine engine of claim 10, wherein the first rotor supply
channel has a diameter of about 15 millimeters.
Description
FIELD OF THE INVENTION
[0001] This invention is directed generally to turbine engines, and
more particularly to cooling fluid feed systems in turbine
engines.
BACKGROUND
[0002] Typically, gas turbine engines include a compressor for
compressing air, a combustor for mixing the compressed air with
fuel and igniting the mixture, and a turbine blade assembly for
producing power. Combustors often operate at high temperatures that
may exceed 2,500 degrees Fahrenheit. Typical turbine combustor
configurations expose turbine blade assemblies to these high
temperatures. As a result, turbine blades and turbine vanes must be
made of materials capable of withstanding such high temperatures.
Turbine blades, vanes and other components often contain cooling
systems for prolonging the life of these items and reducing the
likelihood of failure as a result of excessive temperatures.
[0003] Turbine blades are typically supported by a rotor assembly
that enables turbine blades to extend radially outward
circumferentially about the rotor assembly. The turbine blades may
be positioned in circumferential rows, forming stages, that are
separated by turbine vanes extending radially inward. The turbine
airfoils are exposed to combustion gases and extreme heat. Turbine
airfoils are cooled with internal cooling systems that receive
cooling fluids through channels in the rotor assembly to which the
blades are attached. Conventional cooling channels in the rotor
assembly often have cooling fluid leaks between radially extending
and axially extending cooling channels that direct cooling fluids
to turbine vanes. Additionally, conventional cooling fluid supply
configurations often have choke points that cause pressure losses
and unduly restrict cooling fluid flow.
SUMMARY OF THE INVENTION
[0004] This invention is directed to a sealing system for a rotor
assembly in a gas turbine engine that enhances the flow of cooling
fluids from a rotor assembly to turbine blades. The sealing system
may include a seal configured to seal a conduit directing cooling
fluids from a cooling fluid source into turbine blades attached to
the rotor assembly. In one embodiment, the seal may be formed from
a side block and an upper seal that seal a gap between a radially
outward extending first rotor supply channel in the rotor assembly
terminating at an inlet of an axially extending second rotor supply
channel that is in fluid communication with an internal blade
cooling system of a turbine blade. The seal may include components
that enhance the flow of cooling fluids over conventional
configurations. In another embodiment, the sealing system may
include an integrated sealing block configured to seal the gap
between adjacent turbine blades at an intersection between the
first and second rotor supply channels. The integrated sealing
block may be formed from a radially inward extending leg and a
central body.
[0005] The sealing system may include a rotor assembly having one
or more rows of turbine blades extending radially outward and one
or more internal rotor cooling systems in fluid communication with
an internal blade cooling system within one or more turbine blades.
The internal rotor cooling system may include a radially outward
extending first rotor supply channel terminating at a radially
outward end of the outward extending first rotor supply channel and
at an inlet of an axially extending second rotor supply channel
that is in fluid communication with the internal blade cooling
system. The seal of the sealing system may be formed from one or
more side blocks sealing a portion of a gap between adjacent
turbine blades at an intersection between the first and second
rotor supply channels. The side block may extend partially
circumferentially around the rotor assembly, may be curved
circumferentially, may be attached to a radially outer end of a
wall defining the first rotor supply channel, and may be a
generally linear inner surface forming a portion of the first rotor
supply channel. In one embodiment, the side block may extend
circumferentially to seal at least two gaps between multiple sets
of turbine blades in the at least one row of turbine blades. The
seal may also be formed from one or more upper seals sealing a
remaining portion of the gap between adjacent turbine blades at the
intersection between the first and second rotor supply
channels.
[0006] The upper seal may contact the side block and may include a
radially inner surface that is generally flat and flush with an
inner surface forming the second rotor supply channel. With the
upper seal being flush with the second rotor supply channel, the
upper seal is capable of increasing the cooling fluid flow past the
seal and into the second rotor channel towards the turbine blades.
The upper seal may include one or more teeth on the upper seal
extending radially outward from the upper seal and contacting two
turbine blades. The teeth may be used to assist in attaching the
seal to the turbine blades and to prevent cooling fluid leakage
between the turbine blades and the seal. The seal may include an
arm extending axially from the upper seal away from the
intersection between the upper seal and the side block. One or more
of the teeth may extend radially outward from the arm, and in one
embodiment, two teeth may extend radially outward from the arm. One
or more of the teeth may form an interference fit in a cavity in
each of the two turbine blades to reduce leakage.
[0007] The upper seal further may include one or more teeth
extending radially inward from a radially inner surface of the
upper seal into contact with the side block. The tooth may have a
width that is less than a width of the side block. The side block
may also include one or more wire seals extending radially inward
from a radially inner surface of the side block. The wire seal may
have a width that is less than a width of the side block.
[0008] The first rotor supply channel extending radially outward
may be sized to increase the cooling fluid flow to the turbine
blades. The size of the first rotor supply channel may be
increased. Increasing the size of the first rotor supply channel
increases the flow of cooling fluids to the turbine blades. In one
embodiment, the first rotor supply channel may have a diameter of
about 15 millimeters.
[0009] In another embodiment, the seal may be formed from one or
more integrated sealing blocks sealing a gap between adjacent
turbine blades at an intersection between the first and second
rotor supply channels. The integrated sealing block may include a
radially inward extending leg and central body. The integrated
sealing block may extend partially circumferentially around the
rotor assembly may be curved circumferentially. The radially inward
extending leg may be attached to a radially outer end of a wall
defining the first rotor supply channel and may have a generally
linear, radially extending, inner surface on the leg forming a
portion of the first rotor supply channel. The central body may
include an axially extending inner surface that is generally flat
and flush with an inner surface forming the second rotor supply
channel. The integrated sealing block further increases the ability
of the seal to seal the gap between the first and second rotor
supply channels and increase the amount of cooling fluid flow past
the seal to the turbine blades. The filleted inner surface of the
sealing block and positioning the inner surface of the central body
to be flush with the inner surface of the second rotor supply
channel increases the flow of cooling fluids.
[0010] An advantage of this invention is that the seal is
configured to increase the flow of cooling fluids from a cooling
fluid supply source to the turbine blades.
[0011] Another advantage of this invention is a size of the first
radially extending rotor supply channel is larger than conventional
configurations, thereby increasing cooling fluid flow.
[0012] Yet another advantage of this invention is that the inner
radial surface of the seal is positioned flush relative to an inner
surface of the axially extending second rotor supply channel,
thereby eliminating a conventional flow pinch point.
[0013] Another advantage of this invention is that the seal may be
formed from an integrated sealing block that further reduces
leakage.
[0014] Still another advantage of this invention is that the seal
may include one or more radially or axially extending teeth to
attach the seal to the adjacent turbine blades and the rotor
assembly, whereby cooling fluid leakage is reduced.
[0015] Another advantage of this invention is that the seal may
include a curved corner between the axially extending leg and the
radially extending central body, thereby further reducing cooling
air pressure losses.
[0016] These and other embodiments are described in more detail
below.
BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The accompanying drawings, which are incorporated in and
form a part of the specification, illustrate embodiments of the
presently disclosed invention and, together with the description,
disclose the principles of the invention.
[0018] FIG. 1 is a perspective view of partial view of a seal
system attached to a rotor assembly to seal a gap within a cooling
fluid system directing cooling fluids to turbine blades attached to
the rotor assembly.
[0019] FIG. 2 is a detailed view of a seal of the seal system
sealing the gap in the cooling fluid system shown in FIG. 1 at
detail 2.
[0020] FIG. 3 is a detailed view of another embodiment of the seal
of the seal system sealing the gap in the cooling fluid system
shown in FIG. 1 at detail 3.
[0021] FIG. 4 is a detailed view of yet another embodiment of the
seal of the seal system sealing the gap in the cooling fluid system
shown in FIG. 1 at detail 4.
[0022] FIG. 5 is a detailed view of still another embodiment of the
seal of the seal system sealing the gap in the cooling fluid system
shown in FIG. 1 at detail 5.
DETAILED DESCRIPTION OF THE INVENTION
[0023] As shown in FIGS. 1-5, this invention is directed to a
sealing system 10 for a rotor assembly 12 in a gas turbine engine
that enhances the flow of cooling fluids from a rotor assembly 12
to turbine blades 16. The sealing system 10 may include a seal 14
configured to seal a conduit directing cooling fluids from a
cooling fluid source into turbine blades 16 attached to the rotor
assembly 12. In one embodiment, the seal 14 may be formed from a
side block 18 and an upper seal 20 that seal a gap 22 between a
radially outward extending first rotor supply channel 24 in the
rotor assembly 12 terminating at an inlet 26 of an axially
extending second rotor supply channel 28 that is in fluid
communication with an internal blade cooling system 30 of a turbine
blade 16. The seal 14 may include components that enhance the flow
of cooling fluids over conventional configurations. In another
embodiment, the sealing system 10 may include an integrated sealing
block 32 configured to seal the gap 22 between adjacent turbine
blades 16 at an intersection 34 between the first and second rotor
supply channels 24, 28. The integrated sealing block 32 may be
formed from a radially inward extending leg 36 and a central body
38.
[0024] As shown in FIGS. 1-3, the sealing system 10 for a turbine
blade 16 and rotor assembly 12 for a gas turbine engine may be
configured to seal a gap 22 within the sealing system 10. The rotor
assembly 12 may have at least one row of turbine blades 16
extending radially outward. In at least one embodiment, the rotor
assembly 12 may have a plurality of rows of turbine blades 16
forming multiple stages. The rotor assembly 12 may have any
appropriate configuration and is not limited to any particular
configuration or number of stages of turbine blades 16. The rotor
assembly 12 may include one or more internal rotor cooling systems
40 in fluid communication with the internal blade cooling system 30
within one or more turbine blades 16. The internal rotor cooling
system 40 may include a radially outward extending first rotor
supply channel 24 terminating at a radially outward end 42 of the
outward extending first rotor supply channel 24, which is at the
inlet 26 of an axially extending second rotor supply channel 28
that is in fluid communication with the internal blade cooling
system 30.
[0025] The seal 14 may be formed from one or more side blocks 18
sealing a portion of the gap 22 between adjacent turbine blades 16
at the intersection 34 between the first and second rotor supply
channels 24, 28. The side block 18 may extend partially
circumferentially around the rotor assembly 12, may be curved
circumferentially, and may have a generally rectangular shape.
[0026] In one embodiment, as shown in FIG. 2, the side block 18 may
extend circumferentially to seal at least two gaps 22 between
multiple sets of turbine blades 16 in the at least one row of
turbine blades 16. The side block 18 may be attached to a radially
outer end 44 of a wall defining the first rotor supply channel 24
and may have a generally linear inner surface 46 forming a portion
of the first rotor supply channel 24. The side block 18 may extend
to seal an area covering multiple gaps between adjacent turbine
blades 16, as shown in FIG. 1.
[0027] The seal 14 may also include one or more upper seals 20
sealing a remaining portion of the gap 22 between adjacent turbine
blades 16 at the intersection 34 between the first and second rotor
supply channels 24, 28. The upper seal 20 may contact the side
block 18 and may include a radially inner surface 48 that is
generally flat and flush with an inner surface 49 forming the
second rotor supply channel 28.
[0028] The seal 14 may include one or more teeth 50 on the upper
seal 20 extending radially outward from the upper seal 20 and
contacting two turbine blades 16. The teeth 50 may extend from an
arm 52 extending axially from the upper seal 20 away from the
intersection 34 between the upper seal 20 and the side block 18.
The tooth 50 may extend radially outward from the arm 52. The tooth
50 may extend generally orthogonal to the arm 52. As shown in FIG.
33, the seal 14 may include two teeth 50 extending radially outward
from the arm 52. The tooth 50 may be sized such that the tooth 50
contacts at least one surface 56 of the cavity 54 in which the
tooth 50 is inserted so that leakage of cooling fluids can be
limited, if not prevented. In at least one embodiment, the tooth 50
may be sized to form an interference fit in the cavity 54 in each
of the two turbine blades 16 to reduce leakage.
[0029] As shown in FIGS. 2 and 3, the upper seal 20 may include one
or more teeth 58 extending radially inward from a radially inner
surface 60 of the upper seal 20. The tooth 58 may have a width that
is less than a width of the side block 18. The tooth 58 may contact
that side block 18 to seal the upper seal 20 to the side block 18.
Similarly, the side block 18 may include one or more seals 62
extending radially inward from a radially inner surface 64 of the
side block 18 into a cavity 66. The seal 62 may have a width that
is less than a width of the side block 18. The seal may be, but is
not limited to being, a wire seal.
[0030] As shown in FIGS. 1-3, the first rotor supply channel 24 is
configured to direct cooling fluids towards the turbine blades 16
through the second rotor supply channel 28. The first rotor supply
channel 24 may be configured to provide an increased flow of
cooling fluids to the turbine blades 16. The forward radially
extending wall 68 may be moved forward, which is further away from
the body 70 of the rotor assembly 12, to increase the
cross-sectional size of the first rotor supply channel 24. In at
least one embodiment, the first rotor supply channel 24 may have a
diameter of about 15 millimeters, but is not limited to this size,
such as larger or smaller than this size.
[0031] In another embodiment, as shown in FIGS. 4 and 5, the seal
14 may be a one or more integrated sealing blocks 32 sealing a gap
22 between adjacent turbine blades 16 at the intersection 34
between the first and second rotor supply channels 24, 28. The
integrated sealing block 32 may include a radially inward extending
leg 36 and central body 38. The integrated sealing block 32 may
extend partially circumferentially around the rotor assembly 12 may
be curved circumferentially. The radially inward extending leg 36
may be attached to a radially outer end 72 of the wall 68 defining
the first rotor supply channel 24 and has a generally linear,
radially extending, inner surface 74 on the leg 36 forming a
portion of the first rotor supply channel 24. The central body 38
may include an axially extending inner surface 48 that is generally
flat and flush with an inner surface 49 forming the second rotor
supply channel 28.
[0032] One or more teeth 78 may extend axially from the central
body 38 into a cavity 54 within a turbine blade 16 forming a
portion of the row of turbine blades 16. A radially inner surface
80 of the tooth 78 may be generally flat and flush with an inner
surface 48 forming the second rotor supply channel 28. As shown in
FIG. 5, the tooth 78 may include two teeth 78 extending axially
from the central body into cavities 54 within the turbine blade 16
forming a portion of the row of turbine blades 16. Each tooth 78
may contact at least one surface within each cavity 54 to reduce
leakage. As shown in FIGS. 4 and 5, the intersection 34 between the
radially inward extending leg 36 and the central body 38 may be
filleted forming a filleted intersection.
[0033] In another embodiment, as shown in FIG. 4, the seal 14 may
include an arm 52 extending axially from the central body 38 away
from the intersection 34 between the central body 38 and the
radially inward extending leg 36. One or more teeth 78 may extend
radially outward from the arm 52 and may contact two turbine blades
16. The tooth 78 may form an interference fit in the cavity 54 in
each of the two turbine blades to reduce leakage. As shown in FIG.
4, the seal 14 may include two teeth 78 extending radially outward
from the arm 52.
[0034] As shown in FIGS. 4 and 5, the seal 14 may include one or
more seals 82 extending radially inward from a radially inner
surface 84 of the radially inward extending leg 36. The seal 82 may
have a width that is less than a width of the radially inward
extending leg 36 such that the seal 82 may fit into a cavity 66 in
the forward radially extending wall 68. The seal 82 may be, but is
not limited to being, a wire seal.
[0035] The foregoing is provided for purposes of illustrating,
explaining, and describing embodiments of this invention.
Modifications and adaptations to these embodiments will be apparent
to those skilled in the art and may be made without departing from
the scope or spirit of this invention.
* * * * *