U.S. patent application number 13/221009 was filed with the patent office on 2013-02-28 for pin-fin array.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is Aaron Ezekiel Smith. Invention is credited to Aaron Ezekiel Smith.
Application Number | 20130052036 13/221009 |
Document ID | / |
Family ID | 46679213 |
Filed Date | 2013-02-28 |
United States Patent
Application |
20130052036 |
Kind Code |
A1 |
Smith; Aaron Ezekiel |
February 28, 2013 |
PIN-FIN ARRAY
Abstract
The present application provides an airfoil with a cooling flow
therein. The airfoil may include an internal cooling passage, a
number of cooling holes in communication with the internal cooling
passage, and a number of pin-fins positioned within the internal
cooling passage. The pin-fins are arranged with one or more turning
openings and one or more guiding openings so as to direct the
cooling flow towards the cooling holes.
Inventors: |
Smith; Aaron Ezekiel;
(Simpsonville, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Smith; Aaron Ezekiel |
Simpsonville |
SC |
US |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schnectady
NY
|
Family ID: |
46679213 |
Appl. No.: |
13/221009 |
Filed: |
August 30, 2011 |
Current U.S.
Class: |
416/97R |
Current CPC
Class: |
F05D 2240/304 20130101;
F05D 2260/2212 20130101; F05D 2260/2214 20130101; F01D 5/188
20130101 |
Class at
Publication: |
416/97.R |
International
Class: |
F01D 5/18 20060101
F01D005/18 |
Claims
1. An airfoil with a cooling flow therein, comprising: an internal
cooling passage; a plurality of cooling holes in communication with
the internal cooling passage; and a plurality of pin-fins
positioned within the internal cooling passage; the plurality of
pin-fins comprising one or more turning openings and one or more
guiding openings so as to direct the cooling flow towards the
plurality of cooling holes.
2. The airfoil of claim 1, wherein the plurality of pin-fins
comprises a non-uniform array.
3. The airfoil of claim 1, further comprising a plurality of
internal cooling passages.
4. The airfoil of claim 1, wherein the plurality of pin-fins
comprises a staggered positioning across a pair of columns.
5. The airfoil of claim 4, wherein the plurality of pin-fins
comprises a staggered positioning across a plurality of
columns.
6. The airfoil of claim 1, wherein the one or more turning openings
comprise a first distance between a first pair of the plurality of
pin-fins, the one or more guiding openings comprise a second
distance between a second pair of the plurality of pin-fins, and
wherein the first distance is greater than the second distance.
7. The airfoil of claim 1, wherein the one or more turning openings
turn the cooling flow about ninety (90) degrees.
8. The airfoil of claim 1, wherein the plurality of cooling holes
comprises a plurality of trailing edge cooling holes.
9. The airfoil of claim 1, further comprising a plurality of
turning openings over a plurality of columns.
10. The air foil of claim 1, further comprising a plurality of
guiding openings over a plurality of columns.
11. An airfoil with a cooling flow therein, comprising: an internal
cooling passage; a plurality of cooling holes in communication with
the internal cooling passage; and a plurality of pin-fins
positioned within the internal cooling passage in a non-uniform
array; the plurality of pin-fins comprising one or more turning
openings and one or more guiding openings in a staggered
positioning so as to direct the cooling flow towards the plurality
of cooling holes.
12. The airfoil of claim 11, wherein the one or more turning
openings comprise a first distance between a first pair of the
plurality of pin-fins, the one or more guiding openings comprise a
second distance between a second pair of the plurality of pin-fins,
and wherein the first distance is greater than the second
distance.
13. The airfoil of claim 11, wherein the one or more turning
openings turn the cooling flow about ninety (90) degrees.
14. The airfoil of claim 11, wherein the plurality of cooling holes
comprises a plurality of trailing edge cooling holes.
15. The airfoil of claim 11, further comprising a plurality of
turning openings over a plurality of columns.
16. The air foil of claim 11, further comprising a plurality of
guiding openings over a plurality of columns.
17. An internal cooling passage with a cooling flow therein,
comprising: a plurality of cooling holes; and a plurality of
pin-fins positioned within the internal cooling passage; the
plurality of pin-fins comprising one or more turning openings with
a first distance between a first pair of the plurality of pin-fins,
one or more guiding openings with a second distance between a
second pair of the plurality of pin-fins, and wherein the first
distance is greater than the second distance.
18. The internal cooling passage of claim 17, wherein the plurality
of pin-fins comprises a non-uniform array.
19. The internal cooling passage of claim 17, wherein the one or
more turning openings turn the cooling flow about ninety (90)
degrees.
20. The internal cooling passage of claim 17, further comprising a
plurality of turning openings over a plurality of columns.
Description
TECHNICAL FIELD
[0001] The present application and the resultant patent relate
generally to gas turbine engines and more particularly relate to a
flow guiding pin-fin array for use in gas turbine airfoils and the
like.
BACKGROUND OF THE INVENTION
[0002] A gas turbine includes a number of stages with buckets
extending outwardly from a supporting rotor disk. Each bucket
includes an airfoil over which combustion gases flow. The airflow
must be cooled to withstand the high temperatures produced by the
combustion gases. Insufficient cooling may result in undue stress
on the airfoil and may lead or contribute to fatigue and/or damage.
The airfoil thus is generally hollow with one or more internal
cooling flow channels. The internal cooling flow channels may be
provided with a cooling air bleed from the compressor or elsewhere.
Convective heat transfer may be enhanced between the cooling flow
and the internal metal surfaces of the airfoil by the use of
pin-fin arrays, turbulators, and the like. The pin-fin arrays or
the turbulators create a disruption in a surrounding boundary layer
so as to increase heat transfer.
[0003] An airfoil generally has a single cooling flow feed leading
to a pin array and multiple outlets. Such a configuration, however,
typically results in a flow through the pin array that is at an
angle relative to the outlets. This angled flow may lead to a less
effective heat transfer therein. Flow straighteners may be used but
such add space and complexity to the pin array region.
[0004] There is thus a desire for an airfoil with an improved
internal cooling flow scheme with a pin-fin array. Such an improved
cooling flow scheme may provide a pin-fin array for more effective
heat transfer, better flow control, and lower manufacturing
costs.
SUMMARY OF THE INVENTION
[0005] The present application and the resultant patent provide an
airfoil with a cooling flow therein. The airfoil may include an
internal cooling passage, a number of cooling holes in
communication with the internal cooling passage, and a number of
pin-fins positioned within the internal cooling passage. The
pin-fins are arranged with one or more turning openings and one or
more guiding openings so as to direct the cooling flow towards the
cooling holes.
[0006] The present application and the resultant patent further
provide an airfoil with a cooling flow therein. The airfoil may
include an internal cooling passage, a number of cooling holes in
communication with the internal cooling passage, and a number of
pin-fins positioned within the internal cooling passage in a
non-uniform array. The pin-fins are arrange with one or more
turning openings and one or more guiding openings in a staggered
positioning so as to direct the cooling flow towards the cooling
holes.
[0007] The present application and the resultant patent further
provide an internal cooling passage with a cooling flow therein.
The internal cooling passage may include a number of cooling holes
and a number of pin-fins positioned within the internal cooling
passage. The pin-fins are arrange with one or more turning openings
with a first distance between a first pair of the pin-fins, one or
more guiding openings with a second distance between a second pair
of the pin-fins, and wherein the first distance is greater than the
second distance.
[0008] These and other features and improvements of the present
application and the resultant patent will become apparent to one of
ordinary skill in the art upon review of the following detailed
description when taken in conjunction with the several drawings and
the appended claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] FIG. 1 is a schematic view of a gas turbine engine.
[0010] FIG. 2 is a perspective view of a turbine bucket.
[0011] FIG. 3 is a side cross-sectional view of the turbine bucket
of FIG. 2.
[0012] FIG. 4 is a schematic view of a known pin-fin array.
[0013] FIG. 5 is a schematic view of an example of a pin-fin array
as may be described herein.
DETAILED DESCRIPTION
[0014] Referring now to the drawings, in which like numerals refer
to like elements throughout the several views, FIG. 1 shows a
schematic view of gas turbine engine 10 as may be used herein. The
gas turbine engine 10 may include a compressor 12. The compressor
12 compresses an incoming flow of air 14. The compressor 12
delivers the compressed flow of air 14 to a combustor 16. The
combustor 16 mixes the compressed flow of air 14 with a compressed
flow of fuel 18 and ignites the mixture to create a flow of
combustion gases 20. Although only a single combustor 16 is shown,
the gas turbine engine 10 may include any number of combustors 16.
The flow of combustion gases 20 is in turn delivered to a turbine
22. The flow of combustion gases drives the turbine 22 so as to
produce mechanical work. The mechanical work produced in the
turbine 22 drives the compressor 12 via a shaft 24 and an external
load 26 such as an electrical generator and the like.
[0015] The gas turbine engine 10 may use natural gas, various types
of syngas, and/or other types of fuels. The gas turbine engine 10
may be any one of a number of different gas turbine engines offered
by General Electric Company of Schenectady, N.Y., including, but
not limited to, those such as a 7 or a 9 series heavy duty gas
turbine engine and the like. The gas turbine engine 10 may have
different configurations and may use other types of components.
Other types of gas turbine engines also may be used herein.
Multiple gas turbine engines, other types of turbines, and other
types of power generation equipment also may be used herein
together.
[0016] FIG. 2 shows an example of a turbine bucket 28 that may be
used with the turbine 22 described above. The turbine bucket 28
preferably may be formed as a one-piece casting of a super alloy.
The turbine bucket 28 may include a conventional dovetail attached
to a conventional rotor disk. A blade shank 32 extends upwardly
from the dovetail 30 and terminates in a platform 34 that projects
outwardly from and surrounds the shank 32.
[0017] A hollow airfoil 36 extends outwardly from the platform 34.
The airfoil 36 has a root 38 at the junction with the platform 34
and a tip 40 at its outer end. The airfoil 36 has a concave
pressure sidewall 42 and a convex suction sidewall 44 joined
together at a leading edge 46 and a trailing edge 48. The airfoil
36 may include a number of trailing edge cooling holes 50 and a
number of leading edge cooling holes 52. The airfoil 36 and the
turbine bucket 28 as a whole are described herein for the purposes
of example only. The airfoil 36 and the turbine bucket 28 may have
any size or shape suitable for extracting energy from the flow of
combustion gases 20. Other components and other configurations may
be used herein.
[0018] FIG. 3 shows a side cross-sectional view of the airfoil 36.
As is shown, the airfoil 36 may include a number of internal
cooling pathways 54. The airfoil 36 may be air cooled, steam
cooled, open circuit, or closed circuit. The leading edge cooling
hole 52 may be in communication with one or more of the internal
cooling pathways 54. Likewise, the trailing edge cooling holes 50
may be in communication with one or more of the internal cooling
pathways 54. One or more of the internal cooling pathways 54 also
may include a pin array 56. The pin array 56 may be an array of
pin-fins 58. The pin-fins 58 may have any desired size, shape, or
configuration. In this example, the pin array 56 is positioned
about the trailing edge cooling holes 50. Other types of heat
transfer techniques may be used herein.
[0019] FIG. 4 shows an example of the pin array 56. In this
example, the pin-fins 58 are arranged in a uniform array 60. As is
shown, the pin-fins 58 are arranged with a generally uniform
distance between each pin-fin 58. As a result, a cooling flow 62
may flow through the pin array 56 or other type of dump region at
an angle relative to the trailing edge cooling holes 50. As
described above, such an angle may compromise overall heat
transfer.
[0020] FIG. 5 shows a portion of an airfoil 100 as may be described
herein. The airfoil 100 includes a number of internal cooling
pathways 110 and a number of cooling holes 120 therethrough. A
cooling flow 130 may flow through the internal cooling pathways 110
and exit via the cooling holes 120 so as to cool the airfoil 100.
The cooling holes 120 may be positioned along the internal cooling
pathway 110 such that the cooling flow 130 is required to make a
turn in order to pass therethrough. Other configurations and other
components may be used herein.
[0021] The airfoil 100 also includes a pin array 140 within one or
more of the internal cooling pathways 110. The pin array 140 may
includes a number of pin-fins 150. The pin-fins 150 may have any
desired size, shape or configuration. Any number of the pin-fins
150 may be used. Other types of flow disrupters such as turbulators
and the like also may be used herein.
[0022] In this example, the pin-fins 150 may be positioned in a
non-uniform array 160. By the term "non-uniform" array 160, we mean
that the distances between the individual pin-fins 150 may vary.
Specifically, a turning opening 170 and a guiding opening 180 may
be used between individual pin-fins 150. The turning opening 170
simply has a larger open area between the pin-fins 150 as compared
to the guide opening 180. Specifically, the turning openings 170
may be about fifteen percent (15%) to about sixty percent (60%)
larger than the guiding openings 180, although other ranges may be
used herein. The larger open area of the turning openings 170 tends
to turn the cooling flow 130 in the desired direction. The pin-fins
150 also may have a variable downstream staggered positioning 190.
The variable downstream staggered positioning 190 also aids in
directing the cooling flow 130 as desired. In the example shown,
the pin array 140 may have a number of columns: a first column 200,
a second column 210, a third column 220, and a fourth column 230.
Any number of columns may be used herein. The staggered positioning
190 thus extends across the columns.
[0023] The cooling flow 130 thus turns into the turning opening 170
in the first column 200 and continues into the turning openings 170
of the second column 210, the third column 220, and the fourth
column 230. The cooling flow 130 largely takes about a ninety (90)
degree turn along the internal cooling pathway 110 into the cooling
holes 120. The pin array 140 shown herein is for the purpose of
example only. The positioning of the individual pin-fins 150 may
vary according to the geometry of the airfoil 100, the internal
cooling pathway 110, the cooling holes 120, the pin-fins 150, and
the like. The positioning also may vary due to any number of
different operational and performance parameters.
[0024] The use of the turning openings 170 so as to turn the
cooling flow 130 thus results in a more effective pin array 140 for
improved heat transfer and flow control. The cooling flow 130 will
have significant momentum component normal thereto. The cooling
flow 130 thus is efficiently directed into the cooling holes 120 or
other dump region. Specifically, the cooling flow 130 stagnates
alternatively on different pin rows so as to provide this
direction. Moreover, the pin-fins 150 are positioned so as to
optimize local flow velocity. Improved heat transfer may result in
lower flow requirements and enhance increased overall efficiency.
The pin array 140 also has larger pin spacings so as to reduce
manufacturing costs and complexity while still providing effective
heat transfer and flow control.
[0025] It should be apparent that the foregoing relates only to
certain embodiments of the present application and the resultant
patent. Numerous changes and modifications may be made herein by
one of ordinary skill in the art without departing from the general
spirit and scope of the invention as defined by the following
claims and the equivalents thereof.
* * * * *