U.S. patent application number 15/588871 was filed with the patent office on 2018-11-08 for pin to reduce relative rotational movement of disk and spacer of turbine engine.
The applicant listed for this patent is Solar Turbines Incorporated. Invention is credited to Kenneth Gregory Thomas.
Application Number | 20180320708 15/588871 |
Document ID | / |
Family ID | 64015221 |
Filed Date | 2018-11-08 |
United States Patent
Application |
20180320708 |
Kind Code |
A1 |
Thomas; Kenneth Gregory |
November 8, 2018 |
PIN TO REDUCE RELATIVE ROTATIONAL MOVEMENT OF DISK AND SPACER OF
TURBINE ENGINE
Abstract
An axial compressor of a turbine engine includes a plurality of
disk and spacer pairs oriented along a common axis of rotation.
Each of a disk and a spacer of the disk and spacer pairs has a
contacting face defining an engagement between the disk and the
spacer. The contacting face of each of the disk and the spacer
includes a recessed area. A pin has a stem received within the
recessed area of the disk and a head received within the recessed
area of the spacer. The head of the pin includes at least two flats
corresponding to complementary surfaces of the recessed area of the
spacer.
Inventors: |
Thomas; Kenneth Gregory;
(San Diego, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Solar Turbines Incorporated |
San Diego |
CA |
US |
|
|
Family ID: |
64015221 |
Appl. No.: |
15/588871 |
Filed: |
May 8, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F05D 2250/13 20130101;
F04D 29/321 20130101; F05D 2250/132 20130101; F04D 19/02 20130101;
F04D 29/644 20130101; F01D 5/066 20130101; F05D 2260/36
20130101 |
International
Class: |
F04D 29/64 20060101
F04D029/64; F04D 19/02 20060101 F04D019/02; F04D 29/32 20060101
F04D029/32 |
Claims
1. An axial compressor of a turbine engine, including: a plurality
of disk and spacer pairs oriented along a common axis of rotation,
each of a disk and a spacer of the disk and spacer pairs having a
contacting face defining an engagement between the disk and the
spacer; the contacting face of each of the disk and the spacer
including a recessed area; and a pin having a stem received within
the recessed area of the disk and a head received within the
recessed area of the spacer; the head of the pin including at least
two flats corresponding to complementary surfaces of the recessed
area of the spacer.
2. The axial compressor of claim 1, wherein the disk and the spacer
have a thermal interference engagement.
3. The axial compressor of claim 1, wherein the head of the pin has
a hexagonal shape.
4. The axial compressor of claim 3, wherein the recessed area of
the spacer has a shape corresponding to the hexagonal shape of the
head of the pin.
5. The axial compressor of claim 3, wherein the stem of the pin has
a cylindrical shape.
6. The axial compressor of claim 5, wherein the recessed area of
the disk has a shape corresponding to the cylindrical shape of the
stem of the pin.
7. The axial compressor of claim 3, wherein the pin has a passage
therethrough oriented along a longitudinal axis of the pin.
8. The axial compressor of claim 1, further including a plurality
of recessed areas spaced about each of the disk and the spacer, and
four pins configured for receipt within the plurality of recessed
areas.
9. The axial compressor of claim 1, further including a
predetermined clearance between a top surface of the head of the
pin and an inner surface of the recessed area of the spacer.
10. A method of operating a turbine engine, including steps of:
rotating a disk and spacer pair of a plurality of disk and spacer
pairs about a common axis of rotation; engaging a contacting face
of a disk of the disk and spacer pairs with a contacting face of a
spacer of the disk and spacer pairs during rotation; and
restricting relative rotation of the disk and the spacer using a
pin having a stem received within a recessed area of the disk and a
head received within a recessed area of the spacer; wherein the
restricting step includes contacting at least two flats of the head
of the pin with complementary surfaces of the recessed area of the
spacer.
11. The method of claim 10, further including forming a thermal
interference engagement of the disk and the spacer during operation
of the turbine engine.
12. The method of claim 11, further including performing a hot
shutdown of the turbine engine, and reducing a predetermined
clearance between a top surface of the head of the pin and an inner
surface of the recessed area of the spacer.
13. The method of claim 10, further including engaging a
hexagonally shaped head of the pin with the complementary surfaces
of the recessed area of the spacer.
14. The method of claim 10, wherein the restricting step includes
engaging four pins with four recessed areas spaced about each of
the disk and the spacer.
15. A turbine engine, including: an axial compressor, including: a
plurality of disk and spacer pairs oriented along a common axis of
rotation, each of a disk of the disk and spacer pairs and a spacer
of the disk and spacer pairs having a contacting face defining an
engagement between the disk and the spacer, the contacting face of
each of the disk and the spacer including a recessed area; and a
pin having a stem received within the recessed area of the disk and
a hexagonally shaped head received within the recessed area of the
spacer.
16. The turbine engine of claim 15, wherein the pin has a passage
therethrough oriented along a longitudinal axis of the pin.
17. The turbine engine of claim 15, wherein the stem of the pin has
a cylindrical shape.
18. The turbine engine of claim 15, wherein the disk and the spacer
have a thermal interference engagement.
19. The turbine engine of claim 15, further including a
predetermined clearance between a top surface of the head of the
pin and an inner surface of the recessed area of the spacer.
20. The turbine engine of claim 15, further including a plurality
of recessed areas spaced about each of the disk and the spacer, and
four pins configured for receipt within the plurality of recessed
areas.
Description
TECHNICAL FIELD
[0001] The present disclosure relates generally to turbine engines
and, more particularly, to a pin for reducing relative rotational
movement of a disk and a spacer of an axial compressor of the
turbine engine.
BACKGROUND
[0002] Some axial compressors of turbine engines use spacers to
provide an inner flowpath for working fluid. The spacers are
typically thin rings, installed onto each of a plurality of disks
of the axial compressor. An interference engagement or, more
particularly, a thermal interference engagement and a small
cylindrical anti-rotation pin are used to couple each spacer to a
corresponding disk. The disk and spacer pairs are oriented along a
common rotational axis of the axial compressor. During a hot
shutdown of the turbine engine, the spacers typically cool and
shrink at a higher rate than the corresponding disks, thereby
relieving the thermal interference engagement. The rotational
inertia of the spacers often breaks the pins, allowing the spacers
to rotationally shift relative to the corresponding disks from the
factory set positions. To reset the imbalance, the turbine engine
may require removal from service and disassembly.
[0003] U.S. Pat. No. 8,840,375 to Virkler discloses a lock assembly
for a gas turbine engine. The lock assembly includes a lock body
with an undercut slot that receives a retaining wire of a polygon
shape. A rotor disk has a circumferentially intermittent slot
structure extending radially outward relative to an axis of
rotation. A component defined about the axis of rotation has
multiple radial tabs extending radially inward relative to the axis
of rotation. The radial tabs are engageable with the intermittent
slot structure. A lock assembly, which includes the retaining wire,
is engaged with at least one opening formed by the intermittent
slot structure to provide an anti-rotation interface for the
component.
[0004] As should be appreciated, there is a continuing need to
improve efficiency and reliability of turbine engines and
components of turbine engines.
SUMMARY OF THE INVENTION
[0005] In one aspect, an axial compressor of a turbine engine
includes a plurality of disk and spacer pairs oriented along a
common axis of rotation. Each of a disk of the disk and spacer
pairs and a spacer of the disk and spacer pairs have a contacting
face defining an engagement between the disk and the spacer. The
contacting face of each of the disk and the spacer includes a
recessed area. A pin has a stem received within the recessed area
of the disk and a head received within the recessed area of the
spacer. The head of the pin includes at least two flats
corresponding to complementary surfaces of the recessed area of the
spacer.
[0006] In another aspect, a method of operating a turbine engine
includes steps of rotating a disk and spacer pair of a plurality of
disk and spacer pairs about a common axis of rotation, and engaging
a contacting face of a disk of the disk and spacer pair with a
contacting face of a spacer of the disk and spacer pair during
rotation. The method also includes a step of restricting relative
rotation of the disk and the spacer using a pin having a stem
received within a recessed area of the disk and a head received
within a recessed area of the spacer. The restricting step includes
contacting at least two flats of the head of the pin with
complementary surfaces of the recessed area of the spacer.
[0007] In yet another aspect, a turbine engine includes an axial
compressor. The axial compressor includes a plurality of disk and
spacer pairs oriented along a common axis of rotation, with each of
a disk of the disk and spacer pairs and a spacer of the disk and
spacer pairs having a contacting face defining an engagement
between the disk and the spacer. The contacting face of each of the
disk and the spacer includes a recessed area. A pin has a stem
received within the recessed area of the disk and a hexagonally
shaped head received within the recessed area of the spacer.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIG. 1 is a partial cross section of an axial compressor of
a turbine engine, according to an exemplary embodiment of the
present disclosure;
[0009] FIG. 2 is a perspective view of an exemplary pin that may be
used with the axial compressor of FIG. 1, according to the present
disclosure;
[0010] FIG. 3 is a first side view of the exemplary pin of FIG.
2;
[0011] FIG. 4 is a second side view of the exemplary pin of FIG.
2;
[0012] FIG. 5 is a top view of the exemplary pin of FIG. 2;
[0013] FIG. 6 is a partial cross section of the exemplary pin of
the previous FIGS., assembled with a disk and a spacer of a turbine
engine;
[0014] FIG. 7 is a section view taken along lines 7-7 of FIG.
6;
[0015] FIG. 8 is a perspective view of the spacer of the present
disclosure;
[0016] FIG. 9 is an enlargement of a portion of the spacer of FIG.
8;
[0017] FIG. 10 is a section view taken along lines 10-10 of FIG. 9;
and
[0018] FIG. 11 is a flow diagram of an exemplary method of
operating a turbine engine, according to the present
disclosure.
DETAILED DESCRIPTION
[0019] A portion of an exemplary turbine engine 10 is shown
generally in FIG. 1. In particular, a section view of an axial
compressor 12 of the turbine engine 10 is shown. As will be
appreciated by those skilled in the art, the turbine engine 10 may
also include a combustor and a power turbine and/or a variety of
additional or alternative components for compressing gas. The axial
compressor 12 may include a plurality of disk and spacer pairs 14
oriented along a common axis of rotation A.sub.1. The disk and
spacer pairs 14 may all have similar configurations and, as such,
only a single disk and spacer pair 14 will be described.
[0020] Each of a disk 16 and a spacer 18 of the disk and spacer
pairs 14 may have a respective contacting face 20, 22 defining an
engagement between the disk 16 and the spacer 18. That is, at least
some portion of the contacting face 20 of the disk 16 and at least
some portion of the contacting face 22 of the spacer 18 may
interface or connect to define the engagement. As used herein, the
contacting faces 20, 22 of the disk 16 and the spacer 18 may
include surfaces of the respective components that face one
another.
[0021] The disk 16 may have a generally cylindrical body, which may
or may not be hollow, including or supporting a plurality of static
blades. The spacer 18 may have a thin ring-shaped body for
providing space, along the common axis of rotation A.sub.1, between
the disks 16 and, thus, providing an inner flowpath for working
fluid. Each spacer 18 of the disk and spacer pairs 14 may be the
same material as the corresponding disk 16, which may, for example,
include stainless steel. Although a specific embodiment is
described, the present disclosure may be applicable to disks and
spacers having various shapes, size, materials, and
configurations.
[0022] The contacting face 20, 22 of each of the disk 16 and the
spacer 18 may include a respective recessed area 24, 26. The
recessed areas 24, 26, which may be recessed relative to the
respective contacting face 20, 22, may be aligned such that a pin
28 may be positioned as shown. In particular, the recessed areas
24, 26 may be aligned along an axis parallel to the common axis of
rotation A.sub.1. The pin 28 may generally include a stem 30 and a
head 32 and, as will be discussed below, the stem 30 may be
received at least partly within the recessed area 24 of the disk 16
and the head 32 may be received at least partly within the recessed
area 26 of the spacer 18. During operation of the turbine engine
10, a thermal interference engagement between the disk 16 and the
spacer 18 may secure the engagement of the disk 16, spacer 18, and
pin 28.
[0023] The exemplary pin 28, including the stem 30 and the head 32,
is shown generally in FIGS. 2-5. The head 32 of the pin 28 may
include a plurality of flats, or planar surfaces, 40. According to
the exemplary embodiment, the head 32 may have a hexagonal shape,
including six straight sides and angles. As such, the recessed area
26, or portions thereof, of the spacer 18 may have a shape
corresponding to the hexagonal shape of the head 32, or a portion
of the head 32, of the pin 28. As shown, the stem 30 of the pin 28
may have a cylindrical shape, with the recessed area 24, or
portions thereof, of the disk 16 having a shape corresponding to
the cylindrical shape of the stem 30, or a portion of the stem 30,
of the pin 28. The pin 28 may be made from a variety of different
materials, including, for example, the same material as one or both
of the disk 16 and the spacer 18. Further, according to some
embodiments, the pin 28 may have a passage 42 therethrough oriented
along a longitudinal axis A.sub.2 of the pin 28. The passage 42 may
provide an escape of air when the pin 28 is pressed into a blind
hole.
[0024] As stated above, but referring now to FIGS. 6 and 7, the
stem 30 of the pin 28 is shown received within the recessed area 24
of the disk 16, and the head 32 of the pin 28 is shown received
within the recessed area 26 of the spacer 18. The stem 30 of the
pin 28 may have a substantially cylindrical body, which may be
received within a substantially cylindrical opening or cavity of
the recessed area 24. Thus, the recessed area 24 may be shaped,
sized, and/or configured to receive the stem 30, such as with a
frictional fit.
[0025] The head 32 of the pin 28, according to the present
disclosure, may include at least two flats 40 corresponding to
complementary surfaces of the recessed area 26 of the spacer 18.
That is, the recessed area 26 may include planar surfaces having
similar angles as corresponding surfaces of the head 32 of the pin
28. Thus, the recessed area 26 may be shaped, sized, and/or
configured such that at least one of the flats 40 contacts or
engages a corresponding surface of the recessed area 26 during
operation and/or shutdown of the turbine engine 10.
[0026] As shown in FIG. 7, a predetermined clearance 50 may be
provided between a top surface 52 of the head 32 of the pin 28 and
an inner surface 54 of the recessed area 26 of the spacer 18. As
will be discussed below, the predetermined clearance 50 may be
reduced, such as during a hot shutdown of the turbine engine 10, as
the spacer 18 cools and shrinks more quickly than the corresponding
disk 16. The predetermined clearance 50 may be as small as, for
example, 0.005 inch; however, the predetermined clearance 50 may
vary, depending on the particular application.
[0027] The spacer 18 is shown in FIGS. 8, 9 and 10 and may include
a thin ring-shaped body. The spacer 18 may be sized, shaped, and/or
configured to interact with the corresponding disk 16 in the manner
described herein. The spacer 18 may include at least one recessed
area 26. As shown more specifically in FIG. 8, the spacer 18 may
include a plurality of recessed areas 26, such as, for example,
four recessed areas 26, spaced about the spacer 18. According to
such an embodiment, the disk 16 may have a corresponding number of
recessed areas 24, with a corresponding number of pins 28, such as
four pins 28, configured for receipt within the plurality of
recessed areas 24, 26.
[0028] As stated above, the head 32 of the pin 28 may include a
plurality of flats 40. As such, the recessed area 26 of the spacer
18 may have a shape corresponding to the shape of the head 32 of
the pin 28. During operation of the turbine engine 10 or during a
shutdown, such as a hot shutdown, the spacer 18 may cool more
quickly than the corresponding disk 16, thus reducing the
predetermined clearance 50 and causing one or more of the flats 40
to engage one or more corresponding surface of the recessed area
26.
INDUSTRIAL APPLICABILITY
[0029] The present disclosure relates generally to turbine engines
and, more particularly, to an axial compressor of a turbine engine.
Further, the present disclosure relates to an axial compressor
having a plurality of disk and spacer pairs. Yet further, the
present disclosure is applicable to a pin for reducing relative
rotational movement of a disk and a spacer of the disk and spacer
pairs.
[0030] Referring generally to FIGS. 1-11, an exemplary turbine
engine 10 includes an axial compressor 12. The axial compressor 12
includes a plurality of disk and spacer pairs 14 oriented along a
common axis of rotation A.sub.1. Each of a disk 16 and a spacer 18
of the disk and spacer pairs 14 have a contacting face 20, 22
defining an engagement between the disk 16 and the spacer 18. The
contacting face 20, 22 of each of the disk 16 and the spacer 18
includes at least one recessed area 24, 26 for receiving a pin 28.
The pin 28 has a stem 30 received within the recessed area 24 of
the disk 16, and a head 32, including a plurality of flats 40,
received within the recessed area 26 of the spacer 18.
[0031] Referring specifically to FIG. 11, a flow diagram 60
representing primary steps of a method of operating the turbine
engine 10 or, more particularly, the axial compressor 12, according
to the present disclosure, is shown. At a first step, at box 62,
the method includes a step of rotating the disk and spacer pair 14
about a common axis of rotation A.sub.1. At some point during
rotation of the disk and spacer pair 14, such as during operation
and/or shutdown of the turbine engine 10, a contacting face 20 of
the disk 16 may engage a contacting face 22 of the spacer 18, at
box 64.
[0032] During operation of the turbine engine 10, a thermal
interference engagement between the disk 16 and the spacer 18 of
the disk and spacer pair 14 may form. That is, the disk 16, spacer
18, and pin 28 may be configured to rotate together using a
frictional fit or engagement. During a hot shutdown, or other
similar condition, of the turbine engine 10, a predetermined
clearance 50 between a top surface 52 of the head 32 of the pin 28,
and an inner surface 54 of the recessed area 26 of the spacer 18
may be reduced.
[0033] During the operation and/or shutdown, relative rotation of
the disk 16 and the spacer 18 may be reduced or restricted using
the pin 28, which has the stem 30 received within the recessed area
24 of the disk 16, and the head 32 received within the recessed
area 26 of the spacer 18, at box 66. The restricting step includes
contacting at least two flats 40 of the head 32 of the pin 28 with
complementary surfaces of the recessed area 26 of the spacer 18, at
box 68. According to some embodiments, the restricting step may
include engaging four pins 28 with four recessed areas 24, 26
spaced about each of the disk 16 and the spacer 18.
[0034] Some conventional axial compressors utilize small
cylindrical pins having an interference fit with one or both of a
disk and spacer. During a hot shutdown of the turbine engine, the
spacer may cool and shrink at a higher rate than the corresponding
disk. This may relieve the designed interference fit and cause the
spacer to become loose on the disk. The small cylindrical pin is
often insufficient to restrain the spacer in the circumferential
direction. The force exerted on the pin by the rotational inertia
of the spacer may cause the pin to break, thereby freeing the
spacer to rotate relative to the disk from the factory setting.
[0035] The pin of the present disclosure, as described herein,
reduces clocking and provides a more durable and robust engagement
of the disk and spacer in the context of an axial compressor, or
other similar context. In particular, for example, and during a hot
shutdown, of the turbine engine, the spacer may cool more quickly
than the corresponding disk, thus reducing the predetermined
clearance and causing one or more of the flats to engage one or
more corresponding surface of the recessed area.
[0036] It should be understood that the above description is
intended for illustrative purposes only, and is not intended to
limit the scope of the present disclosure in any way. Thus, those
skilled in the art will appreciate that other aspects of the
disclosure can be obtained from a study of the drawings, the
disclosure and the appended claims.
* * * * *