U.S. patent application number 11/584062 was filed with the patent office on 2008-04-24 for fluid brush seal with segment seal land.
Invention is credited to Ioannis Alvanos, John P. Virtue.
Application Number | 20080095616 11/584062 |
Document ID | / |
Family ID | 38710451 |
Filed Date | 2008-04-24 |
United States Patent
Application |
20080095616 |
Kind Code |
A1 |
Alvanos; Ioannis ; et
al. |
April 24, 2008 |
Fluid brush seal with segment seal land
Abstract
A turbine rotor for a turbine engine includes multiple rotor
disks having rotor blades mounted about the circumference of each
of the rotor disks. A fluid seal extends about the circumference of
each rotor disk in close proximity to a stationary component of the
rotor to separate the space between the rotor blades and a
stationary component into separate cavities. The fluid seal
includes a seal land on the rotor disk and a brush seal extending
from the stationary component. A plurality of disk land segments
and a plurality of blade land segments form the seal land. The disk
seal segments are located on the rotor disk between the rotor
blades. The blade land segments are located on the rotor blades.
After the rotor blades are assembled, the blade land segments and
the disk land segments fit together to form a segmented ring-like
seal land around the circumference of the rotor disk.
Inventors: |
Alvanos; Ioannis; (West
Springfield, MA) ; Virtue; John P.; (Middletown,
CT) |
Correspondence
Address: |
CARLSON, GASKEY & OLDS/PRATT & WHITNEY
400 WEST MAPLE ROAD, SUITE 350
BIRMINGHAM
MI
48009
US
|
Family ID: |
38710451 |
Appl. No.: |
11/584062 |
Filed: |
October 20, 2006 |
Current U.S.
Class: |
415/173.7 |
Current CPC
Class: |
F01D 5/3007 20130101;
F01D 11/001 20130101; F05D 2240/56 20130101 |
Class at
Publication: |
415/173.7 |
International
Class: |
F01D 11/00 20060101
F01D011/00 |
Claims
1. A turbine engine comprising: a rotor disk to rotate about an
axis defining a disk rim and having a plurality of rotor blades
mounted to the disk rim; a plurality of disk land segments
extending from the disk rim between each of the plurality of rotor
blades; a plurality of blade land segments extending from each of
the plurality of rotor blades, wherein the plurality of disk land
segments and the plurality of blade land segments form a seal land
located about a circumference of the disk rim; and a brush seal
extending from a stationary component of the turbine engine and
contacting the seal land.
2. The turbine engine of claim 1, wherein the plurality of disk
land segments are integrally formed in the rotor disk.
3. The turbine engine of claim 1, wherein the plurality of blade
land segments are integrally formed in each of the plurality of
rotor blades.
4. The turbine engine of claim 1, wherein the seal land comprises a
radial face and the brush seal extends axially to contact the
radial face.
5. The turbine engine of claim 1, wherein the seal land comprises
an axial face and the brush seal extends radially inward to contact
the axial face.
6. The turbine engine of claim 1, wherein the stationary component
is a tangential on-board injector.
7. The turbine engine of claim 1, wherein the brush seal further
comprises an axial locking feature to prevent axial movement of the
brush seal.
8. The turbine engine of claim 1, wherein an interfitting structure
on each of the plurality of disk land segments and the plurality of
blade land segments align the plurality of disk land segments and
the plurality of blade land segments.
9. A fluid seal assembly for a jet engine comprising: a plurality
of rotor disks rotating about an axis and each defining a disk rim
and having a plurality of rotor blades mounted to the disk rim; a
plurality of disk land segments extending from the disk rim between
each of the plurality of rotor blades; a plurality of blade land
segments extending from each of the plurality of rotor blades,
wherein the plurality of disk land segments and the plurality of
blade land segments form a seal land located about the
circumference of the disk rim; and a brush seal extending from a
stationary component of the turbine engine to contact the seal
land.
10. The fluid seal assembly of claim 9, wherein the plurality of
disk land segments are integrally formed with the rotor disk.
11. The fluid seal assembly of claim 9, wherein the plurality of
blade land segments are integrally formed with each of the
plurality of rotor blades.
12. The fluid seal assembly of claim 9, wherein the seal land
comprises a radial face and the brush seal extends axially to
contact the radial face.
13. The fluid seal assembly of claim 9, wherein the seal land
comprises an axial face and the brush seal extends in a radial
inward direction to contact the axial face.
14. The fluid seal assembly of claim 9, wherein the brush seal
further comprises an axial locking feature to prevent axial
movement of the brush seal.
15. The fluid seal assembly of claim 9, the wherein interfitting
structure on each of the plurality of disk land segments and the
plurality of blade land segments align the plurality of disk land
segments and the plurality of blade land segments.
16. A rotor blade comprising: a blade platform having a blade root
extending from the blade platform for receiving in a blade slot of
a rotor disk; and a blade seal segment extending from the blade
root, wherein the blade seal segment defines a seal land for
contacting a brush seal extending from a stationary turbine engine
component.
17. The rotor blade of claim 16, comprising a first interlocking
feature on the blade seal segment for interfitting with a second
interlocking feature on a disk seal segment of the rotor disk.
Description
[0001] This application discloses subject matter related to
co-pending US patent applications "HAMMERHEAD FLUID SEAL" (U.S.
patent application Ser. No. 11/146,801), "COMBINED BLADE ATTACHMENT
AND DISK LUG FLUID SEAL" (U.S. patent application Ser. No.
11/146,798) and "BLADE NECK FLUID SEAL" (U.S. patent application
No. 11/146,660), each filed on Jul. 7, 2005, and "INTEGRATED BLADED
FLUID SEAL" (U.S. patent application Ser. No. 11/260,357) filed on
Oct. 27, 2005.
BACKGROUND OF THE INVENTION
[0002] The invention generally relates to an arrangement for fluid
seals within a gas turbine engine.
[0003] Turbine engines include high and low pressure rotor spools
comprising multiple rotor disks. Fluid seals are formed integrally
into each rotor disk to contact stator components, such as a
tangential on-board injector. The seals restrict leakage of
compressed air from between the stator component and the rotor
disks and separate the lower pressure gaspath air from high
pressure air used for cooling.
[0004] Due to the rotor disk geometry, multiple machining passes
are required to produce the thin sectional area required for the
fluid seal. This is unduly complex. Also, during operation of the
engine, the fluid seal may contact an abradable material on the
stationary components, causing wear. Because the fluid seal is
integrally formed with the rotor disk of the compressor, the entire
rotor disk must be repaired or replaced when the fluid seal has
worn.
[0005] An improved arrangement for sealing fluids within a gas
turbine engine is needed.
SUMMARY OF THE INVENTION
[0006] An example turbine engine rotor according to this invention
includes an arrangement for incorporating a fluid seal assembly
while reducing wear on the rotor disk.
[0007] A typical turbine engine rotor includes multiple rotor disks
with rotor blades mounted about the circumference of each of the
rotor disks. A plurality of stator vanes extend axially between
adjacent rotor disks. A fluid seal assembly extends about the
circumference of each rotor disk in close proximity to a stationary
component of the compressor. The fluid seal assembly separates the
space between the rotor blades and stationary components into
separate pressurized cavities.
[0008] The fluid seal includes a seal land in contact with a brush
seal. The seal land extends about the circumference of the disk rim
and includes a plurality of disk land segments and a plurality of
blade land segments fitting together to form a segmented seal land.
The disk land segments are integrally formed with the rotor disk
between the rotor blades. The blade land segments are integrally
formed with the rotor blades. When the rotor blades are assembled
to the rotor disk, the blade land segments and the disk land
segments fit together to form a segmented, ring-like seal land
around the circumference of the rotor disk.
[0009] Each disk land segment has a first interlocking feature
interfitting with a second interlocking feature on the blade land
segments to align the land segments and reduce circumferential and
radial fluid leaks.
[0010] These and other features of the present invention can be
best understood from the following specification and drawings, the
following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] FIG. 1 is a schematic view of an example turbine engine of
the present invention;
[0012] FIG. 2 illustrates a portion of a cross-section of a typical
rotor for the example turbine engine of the present invention;
[0013] FIG. 3 is an enlarged view of region 3-3 from FIG. 2,
illustrating a portion of an example fluid seal;
[0014] FIG. 4 is a perspective view of an example disk land segment
and blade land segment of the present invention prior to
assembly;
[0015] FIG. 5 illustrates a portion of a cross-section of another
example turbine rotor of the present invention;
[0016] FIG. 6 is an enlarged view of region 6-6 from FIG. 5,
illustrating a portion of another example fluid seal; and
[0017] FIG. 7 is a perspective view of another example disk land
segment and blade land segment of the present invention prior to
assembly.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
[0018] FIG. 1 is a schematic view of a turbine engine 10. Air is
pulled into the turbine engine 10 by a fan 12 and flows through a
low pressure compressor 14 and a high pressure compressor 16. Fuel
is mixed with the air, and combustion occurs within the combustor
18. Exhaust from combustion flows through a high pressure turbine
20 and a low pressure turbine 22 prior to leaving the engine
through an exhaust nozzle 24.
[0019] FIG. 2 illustrates a portion of a cross-section of a typical
turbine engine turbine, showing a rotor disk 26, which is one of
several defining a rotor. Each rotor disk 26 rotates about an axis
A located along the longitudinal centerline of the turbine engine
10. A plurality of rotor blades 28 are mounted about the
circumference of each rotor disk 26. A plurality of stator vanes 30
extend between the rotor blades 28 of axially adjacent rotor disks
26, as shown.
[0020] Each rotor disk 26 includes a disk rim 32. The disk rim 32
secures the rotor blades 28. A fluid seal 34 is located between the
rotor disk 26 and a stationary part of the turbine, such as a
stator vane, a support or a tangential on-board injector (TOBI) 36.
The fluid seal 34 defines a cavity 38 located axially above the
fluid seal 34 and further defined by the stator vane 30 and the
rotor blade 28. Air within the cavity 38 is flowing
circumferentially about the axis A of rotation for the rotor disk
26. An interior cavity 40 is located axially below the fluid seal
34 and defined by the rotor disk 26 and the stationary component
36. A nozzle 42 leading from the TOBI 36 allows high pressure
cooling air to reach the interior cavity 40 to cool the rotor disk
26.
[0021] FIG. 3 illustrates an enlarged view of the example fluid
seal 34. The fluid seal 34 includes a segmented seal land 44 and a
brush seal 46. The seal land 44 extends about the circumference of
the disk rim 32. The seal land 44 is preferably formed of the same
material as the rotor disk 26, such as any ferrous, nickel, or
ceramic materials. The seal land 44 may also be coated with a wear
resistant hard facing or coating to reduce wear.
[0022] The seal land 44 is in contact with the brush seal 46
extending from the stationary component 36. The seal land 44 is
illustrated as extending axially toward the stationary component 36
along the axis A of the turbine engine 10. However, the seal land
44 can extend toward any stationary component of the turbine engine
10. The brush seal 46 includes an axial locking feature 48 to
retain the brush seal 46 to the stationary component 36 and to
prevent axial movement of the brush seal 46 along the axis A of the
turbine engine 10. The brush seal 46 extends in a radially inward
direction from the stationary component 36 and has bristles 50
which contact a radial face 52 of the seal land 44. The bristles 50
are wire bristles or the like to provide radial resilience and
reduce wear on the seal land 44.
[0023] Referring to FIG. 4, the segmented seal land 44 includes a
plurality of disk land segments 54 and a plurality of blade land
segments 56. Spaced around the circumference of the disk rim 32,
segments 54 and 56 fit together to form a segmented, ring-like seal
land about the disk rim 32. The disk land segments 54 are
integrally formed in the disk rim 32 between the rotor blades
28.
[0024] The blade land segments 56 are integrally formed with the
rotor blades 28. The rotor blade 28 has a root 57 contoured to fit
into a complimentary contoured blade slot 58 in the disk rim 32.
Walls 59 in the disk rim 32 define the individual blade slots 58.
The rotor blade 28 is loaded in the blade slot 58, and each disk
land segment 54 and blade land segment 56 mate with a
circumferentially adjacent land segment 54 or 56 to provide a rigid
structure. When the blade land segments 56 are worn, the individual
rotor blades 28 and blade land segments 56 can be repaired or
replaced. Also, use of the brush seal 46 reduces wear on the seal
land 44, extending the life of the fluid seal 34 compared to the
prior art abradable material.
[0025] After the rotor blade 28 is assembled in the blade slot 58,
the disk land segments 54 and the blade land segments 56 fit
together to form a segmented, ring-like fluid seal 34 around the
circumference of the rotor disk 26. Each disk land segment 54 has a
first interlocking feature 60, and each blade land segment 56 has a
second interlocking feature 62. The first interlocking feature 60
and the second interlocking feature 62 interfit to align the disk
land segments 54, with the blade land segments 56. In the example
shown, the first interlocking feature 60 is a protrusion extending
from the disk land segment 54, and the second interlocking feature
62 is a protrusion extending from the blade land segment 56. The
protrusions overlap one another to create a shiplap joint and
reduce circumferential and radial fluid leaks between the disk land
segments 54 and the blade land segments 56. Alternatively, the
first interlocking feature 60 and the second interlocking feature
can be tongue and groove or other interfitting elements.
[0026] FIG. 5 illustrates a portion of a cross-section of another
example embodiment of a turbine including a rotor disk 26 defining
a turbine rotor. A fluid seal 102 is located between the rotor disk
26 and a stationary component 36. The fluid seal 102 defines a
cavity 38 located axially above the fluid seal 102 and further
defined by the stator vane 30 and the rotor blade 28. An interior
cavity 40 is located axially below the fluid seal 102 and defined
by the rotor disk 26 and the stationary component 36. A nozzle 42
leading from the stationary component 36 allows high pressure
cooling air to reach the interior cavity 40 to cool the rotor disk
26.
[0027] FIG. 6 illustrates an enlarged view of the example fluid
seal 102. The fluid seal 102 includes a seal land 104 and a brush
seal 106. The seal land 104 extends about the circumference of the
disk rim 32. The seal land 104 is preferably formed of the same
material as the rotor disk 26, such as any ferrous or nickel
materials. The seal land 104 may also be coated with a wear
resistant hard facing or coating to reduce wear.
[0028] The seal land 104 is in contact with the brush seal 106
extending axially from the stationary component 36. The seal land
104 is illustrated as extending axially toward the stationary
component 36 along the axis A of the turbine engine 10. The brush
seal 106 includes an axial locking feature 108 to retain the brush
seal 106 to the stationary component 36 and to prevent axial
movement of the brush seal 106 along the axis A of the turbine
engine 10. The brush seal 106 extends in an axial direction from
the stationary component 36 and has bristles 110 which contact a
radial face 112 of the seal land 104. The bristles 110 are wire
bristles or the like to provide radial resilience and to reduce
wear on the seal land 104.
[0029] Referring to FIG. 7, the seal land 104 includes a plurality
of disk land segments 114 and a plurality of blade land segments
116 spaced around the circumference of the disk rim 32 and fitting
together to form a solid seal land 104 about the disk rim 32. The
disk land segments 114 are integrally formed in the disk rim 32
between the rotor blades 28.
[0030] The blade land segments 116 are integrally formed in the
rotor blades 28. The rotor blade 28 is loaded into a blade slot 58
in the disk rim 32. Walls 59 in the disk rim 32 define the
individual blade slots 58. When the rotor blade 28 is loaded in the
blade slot 58, each disk land segment 114 and blade land segment
116 mate with a circumferentially adjacent land segment 114 or 116
to provide a rigid structure. When the blade land segments 116 are
worn, the individual rotor blades 28 and blade land segments 116
can be repaired or replaced. The brush seal 106 reduces wear on the
seal land 104 extending the life of the fluid seal 102.
[0031] After the rotor blade 28 is assembled in the blade slot 58,
the disk land segments 114 and the blade land segments 116 fit
together to form a segmented, ring-like fluid seal 34 around the
circumference of the rotor disk 26. Each disk land segment 114 can
have a first interlocking feature 60, and each blade land segment
116 can have a second interlocking feature 62 as illustrated in
FIG. 4 of the previous example. The first interlocking feature and
the second interlocking feature interfit to align the disk land
segments 114 with the blade land segments 116. The first
interlocking feature and the second interlocking feature can be a
ship lap, a tongue and a groove or other interfitting elements.
[0032] Although the example embodiment discloses an arrangement of
assembling fluid seal segments onto a rotor disk for a turbine, the
arrangement may be used for any rotor and seal assembly.
[0033] Although a preferred embodiment of this invention has been
disclosed, a worker of ordinary skill in this art would recognize
that certain modifications would come within the scope of this
invention. For that reason, the following claims should be studied
to determine the true scope and content of this invention.
* * * * *