U.S. patent application number 15/244055 was filed with the patent office on 2017-06-29 for airfoil having internal elongated rib.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to Benjamin T. Fisk, Agnes Klucha, Sergio M. Loureiro, Tracy A. Propheter-Hinckley, Anita L. Tracy.
Application Number | 20170184120 15/244055 |
Document ID | / |
Family ID | 49378832 |
Filed Date | 2017-06-29 |
United States Patent
Application |
20170184120 |
Kind Code |
A1 |
Propheter-Hinckley; Tracy A. ;
et al. |
June 29, 2017 |
AIRFOIL HAVING INTERNAL ELONGATED RIB
Abstract
An airfoil includes an airfoil body including a first side wall
and a second side wall that is spaced apart from the first side
wall. A longitudinally elongated rib connects the first side wall
and the second side wall and divides a cavity into a forward
section and an aft section. The longitudinally elongated rib
includes at least one opening fluidly connecting the forward
section and the aft section of the cavity. The opening is located
in a lateral central portion of the longitudinally elongated rib
with regard to the longitudinal axis such that first and second
sections of the longitudinally elongated rib bound respective
lateral sides of the at least one opening. The opening defines a
maximum dimension along a direction perpendicular to the
longitudinal axis. The maximum dimension is greater than a minimum
dimension of each of the first and second sections in the same
direction.
Inventors: |
Propheter-Hinckley; Tracy A.;
(Manchester, CT) ; Loureiro; Sergio M.;
(Glastonbury, CT) ; Klucha; Agnes; (Colchester,
CT) ; Fisk; Benjamin T.; (East Granby, CT) ;
Tracy; Anita L.; (Middletown, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Family ID: |
49378832 |
Appl. No.: |
15/244055 |
Filed: |
August 23, 2016 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
13454283 |
Apr 24, 2012 |
9470095 |
|
|
15244055 |
|
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|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F04D 29/388 20130101;
F05D 2240/30 20130101; F02C 3/04 20130101; F04D 29/325 20130101;
F01D 5/16 20130101; F02K 3/06 20130101; F05D 2240/24 20130101; F05D
2220/32 20130101 |
International
Class: |
F04D 29/38 20060101
F04D029/38; F02C 3/04 20060101 F02C003/04; F02K 3/06 20060101
F02K003/06; F04D 29/32 20060101 F04D029/32 |
Claims
1. An airfoil comprising: an airfoil body defining a longitudinal
axis, the airfoil body including a leading edge and a trailing edge
and a first side wall and a second side wall that is spaced apart
from the first side wall, the first side wall and the second side
wall joining the leading edge and the trailing edge and at least
partially defining a cavity in the airfoil body; and a
longitudinally elongated rib connecting the first side wall and the
second side wall and dividing the cavity into a forward section and
an aft section, the longitudinally elongated rib including at least
one opening there through fluidly connecting the forward section
and the aft section of the cavity, the at least one opening being
located in a lateral central portion of the longitudinally
elongated rib with regard to the longitudinal axis such that first
and second sections of the longitudinally elongated rib bound
respective lateral sides of the at least one opening, the opening
defining a maximum dimension along a direction perpendicular to the
longitudinal axis, the maximum dimension being greater than a
minimum dimension of each of the first and second sections in the
same direction.
2. The airfoil as recited in claim 1, wherein the at least one
opening is longitudinally elongated.
3. The airfoil as recited in claim 2, wherein the at least one
opening includes two of the openings, and the two openings are
longitudinally spaced apart.
4. The airfoil as recited in claim 3, wherein the cavity further
comprises a forward-most section adjacent the forward section and
an aft-most section aft of the aft section.
5. The airfoil as recited in claim 1, wherein the at least one
opening is ovular.
6. The airfoil as recited in claim 1, wherein the cavity, including
the forward section and the aft section, has four cavity sections
from the leading edge to the trailing edge.
7. The airfoil as recited in claim 6, wherein the at least one
opening is longitudinally elongated.
8. A turbine engine comprising: a compressor section; a combustor
in fluid communication with the compressor section; and a turbine
section in fluid communication with the combustor, the turbine
section being coupled to drive the compressor section, and at least
one of the fan, the compressor section and the turbine section
having an airfoil including an airfoil body defining a longitudinal
axis, the airfoil body including a leading edge and a trailing edge
and a first side wall and a second side wall that is spaced apart
from the first side wall, the first side wall and the second side
wall joining the leading edge and the trailing edge and at least
partially defining a cavity in the airfoil body, and a
longitudinally elongated rib connecting the first side wall and the
second side wall and dividing the cavity into a forward section and
an aft section, the longitudinally elongated rib including at least
one opening there through fluidly connecting the forward section
and the aft section of the cavity, the at least one opening being
located in a lateral central portion of the longitudinally
elongated rib with regard to the longitudinal axis such that first
and second sections of the longitudinally elongated rib bound
respective lateral sides of the at least one opening, the opening
defining a maximum dimension along a direction perpendicular to the
longitudinal axis, the maximum dimension being greater than a
minimum dimension of each of the first and second sections in the
same direction.
9. The turbine engine as recited in claim 8, further comprising a
fan coupled to be driven by the turbine section.
10. The turbine engine as recited in claim 8, wherein the at least
one opening is longitudinally elongated.
11. The turbine engine as recited in claim 10, wherein the at least
one opening includes two of the openings, and the two openings are
longitudinally spaced apart.
12. The turbine engine as recited in claim 11, wherein the cavity
further comprises a forward-most section adjacent the forward
section and an aft-most section aft of the aft section.
13. The turbine engine as recited in claim 8, wherein the at least
one opening is ovular.
14. The turbine engine as recited in claim 8, wherein the cavity,
including the forward section and the aft section, has four cavity
sections from the leading edge to the trailing edge.
15. The turbine engine as recited in claim 14, wherein the at least
one opening is longitudinally elongated.
16. The turbine engine as recited in claim 8, wherein the airfoil
is in the fan.
Description
CROSS-REFERENCE TO RELATED APPLICATION
[0001] The present disclosure is a divisional of U.S. patent
application Ser. No. 13/454,283 filed Apr. 24, 2012.
BACKGROUND
[0002] This disclosure relates to an airfoil, such as an airfoil
for a gas turbine engine.
[0003] Turbine, fan and compressor airfoil structures are typically
manufactured using die casting techniques. For example, the airfoil
is cast within a mold that defines an exterior airfoil surface. A
core structure may be used within the mold to form impingement
holes, cooling passages, ribs or other structures in the airfoil.
The die casting technique inherently limits the geometry, size,
wall thickness and location of these structures. Thus, the design
of a traditional airfoil is limited to structures that can be
manufactured using the die casting technique, which in turn may
limit the performance of the airfoil.
SUMMARY
[0004] An airfoil according to an example of the present disclosure
includes an airfoil body that defines a longitudinal axis. The
airfoil body has a leading edge and a trailing edge and a first
side wall and a second side wall that is spaced apart from the
first side wall. The first side wall and the second side wall join
the leading edge and the trailing edge and at least partially
define a cavity in the airfoil body.
[0005] A longitudinally elongated rib connects the first side wall
and the second side wall and divides the cavity into a forward
section and an aft section. The longitudinally elongated rib has at
least one opening there through fluidly connecting the forward
section and the aft section of the cavity. At least one opening is
located in a lateral central portion of the longitudinally
elongated rib with regard to the longitudinal axis such that first
and second sections of the longitudinally elongated rib bound
respective lateral sides of the at least one opening. The opening
defines a maximum dimension along a direction perpendicular to the
longitudinal axis. The maximum dimension is greater than a minimum
dimension of each of the first and second sections in the same
direction.
[0006] In a further embodiment of any of the foregoing embodiments,
the at least one opening is longitudinally elongated.
[0007] In a further embodiment of any of the foregoing embodiments,
the at least one opening includes two of the openings, and the two
openings are longitudinally spaced apart.
[0008] In a further embodiment of any of the foregoing embodiments,
the cavity further comprises a forward-most section adjacent the
forward section and an aft-most section aft of the aft section.
[0009] In a further embodiment of any of the foregoing embodiments,
the at least one opening is ovular.
[0010] In a further embodiment of any of the foregoing embodiments,
the cavity, including the forward section and the aft section, has
four cavity sections from the leading edge to the trailing
edge.
[0011] In a further embodiment of any of the foregoing embodiments,
the at least one opening is longitudinally elongated.
[0012] A turbine engine according to an example of the present
disclosure includes a compressor section, a combustor in fluid
communication with the compressor section, and a turbine section in
fluid communication with the combustor. The turbine section is
coupled to drive the compressor section. At least one of the fan,
the compressor section, and the turbine section have an airfoil
that has an airfoil body defining a longitudinal axis. The airfoil
body has a leading edge and a trailing edge and a first side wall
and a second side wall that is spaced apart from the first side
wall. The first side wall and the second side wall join the leading
edge and the trailing edge and at least partially defining a cavity
in the airfoil body, and a longitudinally elongated rib connecting
the first side wall and the second side wall and dividing the
cavity into a forward section and an aft section. The
longitudinally elongated rib has at least one opening there through
fluidly connecting the forward section and the aft section of the
cavity. The at least one opening is located in a lateral central
portion of the longitudinally elongated rib with regard to the
longitudinal axis such that first and second sections of the
longitudinally elongated rib bound respective lateral sides of the
at least one opening. The opening defines a maximum dimension along
a direction perpendicular to the longitudinal axis. The maximum
dimension is greater than a minimum dimension of each of the first
and second sections in the same direction.
[0013] A further embodiment of any of the foregoing embodiments
includes, a fan coupled to be driven by the turbine section.
[0014] In a further embodiment of any of the foregoing embodiments,
the at least one opening is longitudinally elongated.
[0015] In a further embodiment of any of the foregoing embodiments,
the at least one opening includes two of the openings, and the two
openings are longitudinally spaced apart.
[0016] In a further embodiment of any of the foregoing embodiments,
the cavity further comprises a forward-most section adjacent the
forward section and an aft-most section aft of the aft section.
[0017] In a further embodiment of any of the foregoing embodiments,
the at least one opening is ovular.
[0018] In a further embodiment of any of the foregoing embodiments,
the cavity, including the forward section and the aft section, has
four cavity sections from the leading edge to the trailing
edge.
[0019] In a further embodiment of any of the foregoing embodiments,
the at least one opening is longitudinally elongated.
[0020] In a further embodiment of any of the foregoing embodiments,
the airfoil is in the fan.
BRIEF DESCRIPTION OF THE DRAWINGS
[0021] The various features and advantages of the present
disclosure will become apparent to those skilled in the art from
the following detailed description. The drawings that accompany the
detailed description can be briefly described as follows.
[0022] FIG. 1 shows an example gas turbine engine.
[0023] FIG. 2 shows a perspective view of an airfoil.
[0024] FIG. 3 shows the airfoil of FIG. 2 with a portion cutaway to
reveal an internal cavity.
[0025] FIG. 4 shows a portion of another example airfoil with a
portion cutaway to reveal an internal cavity and free-floating
damper member.
[0026] FIG. 5 shows another example airfoil having a longitudinally
elongated rib.
[0027] FIG. 6 shows a method of processing an airfoil using an
additive manufacturing process.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
[0028] FIG. 1 schematically illustrates a gas turbine engine 20.
The gas turbine engine 20 is disclosed herein as a two-spool
turbofan that generally incorporates a fan section 22, a compressor
section 24, a combustor section 26 and a turbine section 28.
Alternative engines might include an augmentor section (not shown)
among other systems or features. The fan section 22 drives air
along a bypass flowpath while the compressor section 24 drives air
along a core flowpath for compression and communication into the
combustor section 26 then expansion through the turbine section 28.
Although depicted as a turbofan gas turbine engine in the disclosed
non-limiting embodiment, it should be understood that the concepts
described herein are not limited to use with turbofans as the
teachings may be applied to other types of turbine engines
including three-spool architectures.
[0029] The engine 20 generally includes a first spool 30 and a
second spool 32 mounted for rotation about an engine central axis A
relative to an engine static structure 36 via several bearing
systems 38. It should be understood that various bearing systems 38
at various locations may alternatively or additionally be
provided.
[0030] The first spool 30 generally includes a first shaft 40 that
interconnects a fan 42, a first compressor 44 and a first turbine
46. The first shaft 40 may be connected to the fan 42 through a
gear assembly of a fan drive gear system 48 to drive the fan 42 at
a lower speed than the first spool 30. The second spool 32 includes
a second shaft 50 that interconnects a second compressor 52 and
second turbine 54. The first spool 30 runs at a relatively lower
pressure than the second spool 32. It is to be understood that "low
pressure" and "high pressure" or variations thereof as used herein
are relative terms indicating that the high pressure is greater
than the low pressure. An annular combustor 56 is arranged between
the second compressor 52 and the second turbine 54. The first shaft
40 and the second shaft 50 are concentric and rotate via bearing
systems 38 about the engine central axis A which is collinear with
their longitudinal axes.
[0031] The core airflow is compressed by the first compressor 44
then the second compressor 52, mixed and burned with fuel in the
annular combustor 56, then expanded over the second turbine 54 and
first turbine 46. The first turbine 46 and the second turbine 54
rotationally drive, respectively, the first spool 30 and the second
spool 32 in response to the expansion.
[0032] FIG. 2 illustrates an example airfoil 60. In this example,
the airfoil 60 is a turbine blade of the turbine section 28. The
airfoil 60 may be mounted on a turbine disk in a known manner with
a plurality of like airfoils. Alternatively, it is to be understood
that although the airfoil 60 is depicted as a turbine blade, the
disclosure is not limited to turbine blades and the concepts
disclosed herein are applicable to turbine vanes, compressor
airfoils (blades or vanes) in the compressor section 24, fan
airfoils in the fan section 22 or any other airfoil structures.
Thus, some features that are particular to the illustrated turbine
blade are to be considered optional.
[0033] The airfoil 60 includes an airfoil portion 62, a platform 64
and a root 66. The platform 64 and the root 66 are particular to
the turbine blade and thus may differ in other airfoil structures
or be excluded in other airfoil structures.
[0034] The airfoil 60 includes a body 68 that defines a
longitudinal axis L between a base 70 at the platform 64 and a tip
end 72. The longitudinal axis L in this example is perpendicular to
the engine central axis A. The body 68 includes a leading edge (LE)
and a trailing edge (TE) and a first side wall 74 (pressure side)
and a second side wall 76 (suction side) that is spaced apart from
the first side wall 74. The first side wall 74 and the second side
wall 76 join the leading edge (LE) and the trailing edge (TE) and
at least partially define a cavity 78 (FIG. 3) in the body 68.
[0035] The airfoil portion 62 connects to the platform 64 at a
fillet 80. The platform 64 connects to the root 66 at buttresses
82. The root 66 generally includes a neck 84 and a serration
portion 86 for securing the airfoil 60 in a disk.
[0036] It should be understood that relative positional terms such
as "forward," "aft," "upper," "lower," "above," "below,"
"circumferential," "radial" and the like are with reference to the
normal operational attitude and engine central axis A, unless
otherwise indicated. Furthermore, with reference to the engine 20,
the tip end 72 of the airfoil 60 is commonly referred to as the
outer diameter of the airfoil 60 and the root 66 is commonly
referred to as the inner diameter of the airfoil 60. The platform
64 includes an upper surface 64a that bounds an inner diameter of a
gas path, generally shown as G, over the airfoil portion 62. Some
airfoils may also include a platform at the tip end 72 that bounds
an outer diameter of the gas path G.
[0037] FIG. 3 shows the airfoil 60 with a portion cutaway to reveal
the cavity 78. A lattice network 88 is enclosed within the cavity
78 and connects the first side wall 74 and the second side wall 76.
The lattice network 88 includes at least one enlarged node 90
spaced apart from the first side wall 74 and the second side wall
76 and ribs 92 that extend from the enlarged node 90. Each of the
ribs 92 connects to one of the first side wall 74 or the second
side wall 76.
[0038] In this example, each of the ribs 92 extends along a
respective central axis 92a that is inclined relative to the
longitudinal axis L of the airfoil body 68. Moreover, each of the
ribs 92 is discrete and is thus individually distinct with regard
to other ribs 92, the enlarged node 90, the side walls 74 and 76 or
other structures.
[0039] In this example, the lattice network 88 includes a plurality
of the enlarged nodes 90, although the lattice network 88 could
alternatively include only a single enlarged node 90 or additional
enlarged nodes 90 depending on the degree of reinforcement desired.
Each enlarged node 90 is longitudinally spaced apart from at least
one other enlarged node 90 and is also laterally spaced apart from
at least one other enlarged node 90.
[0040] Each of the enlarged nodes 90 defines a cross-sectional
area, represented at 90a, along a direction perpendicular to the
longitudinal axis L. Similarly, each of the ribs 92 defines a
respective cross-sectional area, represented at 92b, along the same
perpendicular direction. The cross-sectional area 90a is larger
than the cross-sectional area 92b. Thus, the nodes 90 are enlarged
with respect to the ribs 92.
[0041] Each of the ribs 92 extends to and connects with an enlarged
wall node 94 on one of the first side wall or the second side wall
76. The enlarged wall node 94 is enlarged with respect to the
cross-sectional areas 92b of the ribs 92, similar to the enlarged
nodes 90. Another of the ribs 92 that extends from a different one
of the enlarged nodes 90 also connects with the enlarged wall node
94 such that at least two ribs 92 connect to the first side wall 74
or the second side walls 76 at a common one of the enlarged wall
nodes 94.
[0042] In this example, the inclinations of the ribs 92 form
rectilinear openings 96 in the lattice network 88. If the airfoil
60 is a cooled structure, the rectilinear openings 96 permit air
flow through the cavity 78. Additionally, the rectilinear openings
96 provide a weight reduction in the airfoil 60 in comparison to a
solid support structure.
[0043] The lattice network 88 serves to reinforce the side walls 74
and 76. For example, using the additive manufacturing method that
will be described below, the side walls 74 and 76 can be made with
a through-thickness that is not obtainable using traditional die
casting techniques. For example, the side walls 74 and 76 may have
a through-thickness of 0.010 inches/254 micrometers to 0.060
inches/1524 micrometers, or specifically 0.015 inches/381
micrometers or less. The lattice network 88 reinforces the side
walls 74 and 76 to prevent buckling and limit vibration, for
example. Furthermore, the inclination of the ribs 92 provides a
self-supporting structure with regard to pressures generated over
the areas of the lattice network 88 during engine 20 operation and
thus, additional support structure is not needed to support the
lattice network 88 within the cavity 78.
[0044] Optionally, the first side wall 74, the second side wall 76
or both additionally include one or more cross-ribs 98 that extend
along the respective side wall 74 or 76 from the enlarged wall
nodes 94. For example, the cross-ribs 98 define an increased
thickness of, respectively, the first side wall 74 or the second
side wall 76 and extend partially across the cavity 78 toward the
other of the first side wall 74 or second side wall 76. The
cross-ribs 98 serve to further reinforce the side walls 74 and
76.
[0045] FIG. 4 illustrates another example airfoil 160 with a
portion cutaway to reveal a cavity 178. In this disclosure, like
reference numerals designate like elements where appropriate and
reference numerals with the addition of one-hundred or multiples
thereof designate modified elements that are understood to
incorporate the same features and benefits of the corresponding
elements. In this example, the airfoil 160 further includes a free
floating damper member 198 adjacent the lattice network 188. The
free-floating damper member 198 in this example is longitudinally
elongated with regard to the longitudinal axis L. The lattice
network 188 includes at least one bearing surface 188a that, upon
rotation of the airfoil 160, contacts the free-floating damper
member 198. The free-floating damper 198 may also contact the side
walls 174 and 176. The term "free-floating" as used in this
disclosure refers to the damper member 198 being free of any rigid
connections to the side wall 74 and 74, or other structures, within
the cavity 178 such that the damper member 198 is free to move
within the confines of other structures in the cavity 178.
[0046] For example, during operation of the engine 20, the airfoil
160 rotates about engine central axis A and the damper member 198
is thrown longitudinally outwardly such that the damper member 198
contacts the bearing surface or surfaces 188a of the lattice
network 188. The contact causes friction between the bearing
surface or surfaces 188a of the lattice network 188 and the damper
member 198. The friction removes energy from the system and thus
mitigates vibrations in the airfoil 160.
[0047] Optionally, as shown in FIG. 4, the airfoil 160 includes an
additional damper member 198' that, in this example, is located
adjacent the trailing edge (TE) of the airfoil 160. The
free-floating damper member 198 is located adjacent the leading
edge (LE) of the airfoil 160. It is to be understood, however, that
the free-floating damper member 198 and additional damper member
198' may alternatively be located in other positions within the
cavity 178, to provide dampening at certain locations or tailor
dampening to predetermined target vibrational modes.
[0048] FIG. 5 illustrates another example airfoil 260. In this
example, the airfoil 260 includes one or more longitudinally
elongated ribs 202 that connect the first side wall 74 and the
second side wall 76. Each longitudinally elongated rib 202 divides
the cavity 278 into a forward section 278a and an aft section 278b.
The longitudinally elongated rib 202 includes at least one opening
204 there through that fluidly connects the forward section 278a
and the aft section 278b of the cavity 278. In this example, the
airfoil 260 includes a plurality of such longitudinally elongated
ribs 202 and each of the longitudinally elongated ribs 202 may
include one or more openings 204. Each of the openings 204 is
longitudinally elongated and, in this example, is ovular.
[0049] Each of the openings 204 is located in a lateral central
portion of the longitudinally elongated rib 202 with respect to a
direction perpendicular to the longitudinal axis L such that first
and second sections 202a and 202b of the longitudinally elongated
rib 202 bound respective lateral sides 268a and 268b of the opening
268. The opening 204 defines a maximum dimension D.sub.1 along a
direction perpendicular to the longitudinal axis L. Each of the
first and second sections 202a and 202b of the longitudinally
elongated rib 202 define a minimum dimension in a same
perpendicular direction, represented, respectively, at D.sub.2 and
D.sub.3. The maximum dimension D.sub.1 of the opening 204 is
greater than the each of the minimum dimensions D.sub.2 and
D.sub.3.
[0050] The geometries disclosed herein may be difficult to form
using conventional casting technologies. Thus, a method of
processing an airfoil having the features disclosed herein includes
an additive manufacturing process, as schematically illustrated in
FIG. 6. Powdered metal suitable for aerospace airfoil applications
is fed to a machine, which may provide a vacuum, for example. The
machine deposits multiple layers of powdered metal onto one
another. The layers are selectively joined to one another with
reference to Computer-Aided Design data to form solid structures
that relate to a particular cross-section of the airfoil. In one
example, the powdered metal is selectively melted using a direct
metal laser sintering process or an electron-beam melting process.
Other layers or portions of layers corresponding to negative
features, such as cavities or openings, are not joined and thus
remain as a powdered metal. The unjoined powder metal may later be
removed using blown air, for example. With the layers built upon
one another and joined to one another cross-section by
cross-section, an airfoil or portion thereof, such as for a repair,
with any or all of the above-described geometries, may be produced.
The airfoil may be post-processed to provide desired structural
characteristics. For example, the airfoil may be heated to
reconfigure the joined layers into a single crystalline
structure.
[0051] Although a combination of features is shown in the
illustrated examples, not all of them need to be combined to
realize the benefits of various embodiments of this disclosure. In
other words, a system designed according to an embodiment of this
disclosure will not necessarily include all of the features shown
in any one of the Figures or all of the portions schematically
shown in the Figures. Moreover, selected features of one example
embodiment may be combined with selected features of other example
embodiments.
[0052] The preceding description is exemplary rather than limiting
in nature. Variations and modifications to the disclosed examples
may become apparent to those skilled in the art that do not
necessarily depart from the essence of this disclosure. The scope
of legal protection given to this disclosure can only be determined
by studying the following claims.
* * * * *