U.S. patent application number 13/744954 was filed with the patent office on 2014-07-24 for oil cooling arrangement and method of cooling oil.
This patent application is currently assigned to HAMILTON SUNDSTRAND SPACE SYSTEMS INTERNATIONAL. The applicant listed for this patent is HAMILTON SUNDSTRAND SPACE SYSTEMS INTERNATIONAL. Invention is credited to Zachary J. Delong, Michael Wilbur Denius, Mark E. Gilbert.
Application Number | 20140205425 13/744954 |
Document ID | / |
Family ID | 51207816 |
Filed Date | 2014-07-24 |
United States Patent
Application |
20140205425 |
Kind Code |
A1 |
Denius; Michael Wilbur ; et
al. |
July 24, 2014 |
OIL COOLING ARRANGEMENT AND METHOD OF COOLING OIL
Abstract
An oil cooling arrangement includes a first manifold and a
second manifold, each configured to route an oil. Further included
is a first tube having a first end proximate the first manifold and
a second end proximate the second manifold, wherein the first tube
is configured to receive the oil and route the oil toward the
second manifold. Yet further included is a second tube having a
third end proximate the second manifold and a fourth end proximate
the first manifold, wherein the second tube is configured to route
the oil from the second manifold toward the first manifold. Also
included is a turbine exhaust path configured to route an exhaust
flow, wherein the first tube and the second tube are disposed along
the turbine exhaust path, wherein the oil is cooled upon passage of
the exhaust flow over the first tube and the second tube.
Inventors: |
Denius; Michael Wilbur;
(Sycamore, IL) ; Delong; Zachary J.; (Roscoe,
IL) ; Gilbert; Mark E.; (Rockford, IL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
HAMILTON SUNDSTRAND SPACE SYSTEMS INTERNATIONAL |
Windsor Locks |
CT |
US |
|
|
Assignee: |
HAMILTON SUNDSTRAND SPACE SYSTEMS
INTERNATIONAL
Windsor Locks
CT
|
Family ID: |
51207816 |
Appl. No.: |
13/744954 |
Filed: |
January 18, 2013 |
Current U.S.
Class: |
415/1 ;
415/111 |
Current CPC
Class: |
F05D 2260/20 20130101;
F01D 25/18 20130101 |
Class at
Publication: |
415/1 ;
415/111 |
International
Class: |
F01D 25/12 20060101
F01D025/12 |
Goverment Interests
[0001] This invention was made with Government support under
contract NNM07AB03C awarded by NASA. The Government has certain
rights in the invention.
Claims
1. An oil cooling arrangement comprising: a first manifold; a
second manifold, wherein the first manifold and the second manifold
are each configured to route an oil; a first tube having a first
end proximate the first manifold and a second end proximate the
second manifold, wherein the first tube is configured to receive
the oil and route the oil toward the second manifold; a second tube
having a third end proximate the second manifold and a fourth end
proximate the first manifold, wherein the second tube is configured
to route the oil from the second manifold toward the first
manifold; and a turbine exhaust path configured to route an exhaust
flow, wherein the first tube and the second tube are disposed along
the turbine exhaust path, wherein the oil is cooled upon passage of
the exhaust flow over the first tube and the second tube.
2. The oil cooling arrangement of claim 1, further comprising a
plurality of fins extending from an outer surface of each of the
first tube and the second tube.
3. The oil cooling arrangement of claim 1, further comprising a rod
disposed within each of the first tube and the second tube, wherein
the rod and an inner surface of the first tube and the second tube
define an annulus within the first tube and the second tube for the
oil to flow through.
4. The oil cooling arrangement of claim 1, further comprising a
cover member operatively coupled to the first manifold.
5. The oil cooling arrangement of claim 4, wherein the cover member
comprises an inlet region and an outlet region.
6. The oil cooling arrangement of claim 4, further comprising a
thermal control valve disposed within the cover member and
proximate an oil cooling arrangement bypass, wherein the thermal
control valve is in fluid communication with the inlet region and
the outlet region.
7. The oil cooling arrangement of claim 6, wherein the thermal
control valve is moveable between a first position and a second
position.
8. The oil cooling arrangement of claim 7, wherein the first
position comprises a fully open position and the second position
comprises a fully closed position.
9. The oil cooling arrangement of claim 8, wherein the thermal
control valve is in the fully open position at a temperature less
than and equal to about 250.degree. F. (about 121.degree. C.) and
is in the fully closed position at a temperature greater than and
equal to about 270.degree. F. (about 132.degree. C.).
10. The oil cooling arrangement of claim 5, further comprising a
pressure relief valve disposed within the cover member and
configured to detect a pressure differential between the inlet
region and the outlet region.
11. The oil cooling arrangement of claim 1, further comprising: a
third tube having a fifth end proximate the first manifold and a
sixth end proximate the second manifold, wherein the third tube is
configured to receive the oil and route the oil toward the second
manifold; and a fourth tube having a seventh end proximate the
second manifold and an eighth end proximate the first manifold,
wherein the fourth tube is configured to route the oil from the
second manifold toward the first manifold.
12. The oil cooling arrangement of claim 11, further comprising a
cover member operatively coupled to the first manifold, wherein the
cover member comprises an inlet region and an outlet region.
13. The oil cooling arrangement of claim 12, wherein the first
manifold separates the oil into the first tube and the third tube
for routing toward the second manifold.
14. The oil cooling arrangement of claim 13, wherein the second
manifold includes a first fluid path and a second fluid path,
wherein the first fluid path fluidly couples the first tube to the
second tube, and wherein the second fluid path fluidly couples the
third tube to the fourth tube.
15. A method of cooling oil comprising: supplying an oil to a first
manifold of an oil cooling arrangement; routing the oil through a
first tube from the first manifold to a second manifold, wherein
the first tube is disposed in a turbine exhaust path; routing the
oil through a second tube from the second manifold to the first
manifold, wherein the second tube is disposed in the turbine
exhaust path; and flowing an exhaust flow through the turbine
exhaust path and over the first tube and the second tube for
cooling the oil routed therein.
16. The method of claim 15, further comprising increasing a heat
transfer rate by flowing the exhaust flow over a plurality of fins
operatively coupled to an outer surface of the first tube and the
second tube.
17. The method of claim 15, further comprising positioning a
thermal control valve in a fully open position, wherein the thermal
control valve is disposed within a cover member and proximate an
oil cooling arrangement bypass, wherein the thermal control valve
is in fluid communication with an inlet region and an outlet
region, wherein the thermal control valve is in the open position
at a temperature less than or equal to about 250.degree. F. (about
121.degree. C.).
18. The method of claim 17, wherein the thermal control valve is in
a fully closed position at a temperature greater than or equal to
about 270.degree. F. (about 132.degree. C.).
19. The method of claim 15, further comprising: routing the oil to
an inlet disposed proximate the first manifold; and separating the
oil into the first tube and a third tube for routing toward the
second manifold.
20. The method of claim 19, further comprising: flowing the oil
from the first tube to the second tube through a first fluid path
of the second manifold; flowing the oil from the third tube to the
fourth tube through a second fluid path of the second manifold; and
routing the oil through the second tube and the fourth tube from
the second manifold toward the first manifold.
Description
BACKGROUND OF THE INVENTION
[0002] The present invention relates to aerospace systems, and more
particularly to an oil cooling arrangement for an aerospace system,
as well as a method of cooling oil.
[0003] A large number of applications require cooling of various
system fluids, such as oil, for example. One application relates to
a space launch vehicle that requires a power source for an engine
thrust vector control system. Currently, the power source utilizes
a hot gas, such as hydrazine, to drive a turbine that provides
mechanical rotating power to a hydraulic pump, generator or other
power conversion device. Transmission of this power typically
results in heat generation within the power device due to
mechanical efficiency losses. In applications having operating
durations exceeding several minutes or hours, heat generation must
be managed to avoid system failure. Efforts to effectively manage
the heat generation are complicated by the requirement that the
power device must operate in a space vacuum operating environment.
One prior effort to manage the heat included utilizing an external
water spray boiler to achieve heat dissipation, but a specialized
heat exchanger, controller and an on-board source of water are all
required. Such a complicated system inherently imposes several
undesirable effects, including additional weight and reduced
efficiency of the overall system.
BRIEF DESCRIPTION OF THE INVENTION
[0004] According to one embodiment, an oil cooling arrangement
includes a first manifold. Also included is a second manifold,
wherein the first manifold and the second manifold are each
configured to route an oil. Further included is a first tube having
a first end proximate the first manifold and a second end proximate
the second manifold, wherein the first tube is configured to
receive the oil and route the oil toward the second manifold. Yet
further included is a second tube having a third end proximate the
second manifold and a fourth end proximate the first manifold,
wherein the second tube is configured to route the oil from the
second manifold toward the first manifold. Also included is a
turbine exhaust path configured to route an exhaust flow, wherein
the first tube and the second tube are disposed along the turbine
exhaust path, wherein the oil is cooled upon passage of the exhaust
flow over the first tube and the second tube.
[0005] According to another embodiment, a method of cooling oil is
provided. The method includes supplying an oil to a first manifold
of an oil cooling arrangement. The method also includes routing the
oil through a first tube from the first manifold to a second
manifold, wherein the first tube is disposed in a turbine exhaust
path. The method further includes routing the oil through a second
tube from the second manifold to the first manifold, wherein the
second tube is disposed in the turbine exhaust path. The method yet
further includes flowing an exhaust flow through the turbine
exhaust path and over the first tube and the second tube for
cooling the oil routed therein.
BRIEF DESCRIPTION OF THE DRAWINGS
[0006] The subject matter which is regarded as the invention is
particularly pointed out and distinctly claimed in the claims at
the conclusion of the specification. The foregoing and other
features and advantages of the invention are apparent from the
following detailed description taken in conjunction with the
accompanying drawings in which:
[0007] FIG. 1 is a perspective view of an oil cooling
arrangement;
[0008] FIG. 2 is a perspective view of a cover member of the oil
cooling arrangement;
[0009] FIG. 3 is a side, elevational, cross-sectional view of the
oil cooling arrangement;
[0010] FIG. 4 is a side elevational view of the oil cooling
arrangement; and
[0011] FIG. 5 is a flow diagram illustrating a method of cooling
oil.
DETAILED DESCRIPTION OF THE INVENTION
[0012] Referring to FIG. 1, an oil cooling arrangement 10 is
generally shown. The oil cooling arrangement 10 is in fluid
communication with a system requiring an oil 12. The oil cooling
arrangement 10 is configured to manage the temperature of the oil
12 that is commonly heated due to heat dissipation associated with
operation of the system. The oil cooling arrangement 10 is
operatively coupled to a power device, such as a turbine system 14
that provides mechanical rotating power to a hydraulic pump,
generator or other power conversion device. The oil cooling
arrangement 10 and the turbine system 14 may be integrated with
various applications, but in one embodiment the oil cooling
arrangement 10 and the turbine system 14 are employed in
conjunction with an aerospace application. More particularly, it is
contemplated that a space launch vehicle operating in vacuum in
space may benefit from the oil cooling arrangement 10 described
herein.
[0013] The turbine system 14 includes at least one turbine nozzle
16 configured to distribute a propellant fuel 18 to the turbine
system 14. In an exemplary embodiment, the propellant fuel 18 is a
cold gas, such as helium or hydrogen gas, for example. Irrespective
of the precise fuel employed, the propellant fuel 18 drives a
turbine wheel 20 and the mechanical power is converted to a desired
power type. Subsequent to passing over and driving the turbine
wheel 20, the propellant fuel 18, and any air mixed therewith, is
routed through an exhaust housing 22 as an exhaust flow 24. The
interior region defined by the exhaust housing 22 is referred to as
a turbine exhaust path 26. The illustrated embodiment is shown with
a shipping port cover 28 proximate an exhaust outlet 30. By
employing the cold gas in the space vacuum environment, the exhaust
flow 24 passing through the turbine exhaust path 26 is cold,
relative to temperatures of operating environments for adjacent
components and systems, such as a component or system employing the
oil 12 described above. In one embodiment, the temperature of the
exhaust flow 24 ranges from about -100.degree. F. (about
-73.degree. C.) to about -200.degree. F. (about -129.degree.
C.).
[0014] The oil cooling arrangement 10 is operatively coupled at a
plurality of locations with the turbine system 14. Specifically,
the oil cooling arrangement 10 is at least partially disposed
within the turbine exhaust path 26 and coupled at an interior
location of the exhaust housing 22. Additionally, as illustrated,
the oil cooling arrangement 10 is coupled to an exterior surface 32
of the exhaust housing 22, such as with a plurality of mechanical
fasteners 34. The oil cooling arrangement 10 comprises a plurality
of tubes 36 predominantly or fully disposed within the exhaust
housing 22 along the turbine exhaust path 26. In one embodiment,
the plurality of tubes 36 comprises a first tube 38, a second tube
40, a third tube 42 and a fourth tube 44. Each of the plurality of
tubes 36 extends between and is fluidly coupled with a first
manifold 46 and a second manifold 48 at respective ends of each of
the plurality of tubes 36. The first manifold 46 is operatively
coupled to the exhaust housing 22 and is disposed proximate the
exhaust housing 22. In the exemplary embodiment, the first manifold
46 is disposed partially or fully at an exterior region to the
turbine exhaust path 26. Integrally formed with, or operatively
coupled to, the first manifold 46 is a cover member 50 that
includes an inlet 52 and an outlet 54 for receiving and expelling
the oil 12 relative to the oil cooling arrangement 10. The second
manifold 48 is disposed fully within the turbine exhaust path 26
and is operatively coupled to the turbine system 14 therein.
[0015] Referring now to FIG. 2, the cover member 50 is illustrated
in greater detail with a portion cutaway for clarity. As noted
above, the cover member 50 is integrally formed with, or
operatively coupled to, the first manifold 46. The oil 12 is
initially received by the oil cooling arrangement 10 via the inlet
52 from a supply (not illustrated). The inlet 52 is fluidly coupled
to the first manifold 46, which is configured to route the oil 12
to at least one, but typically a plurality of tubes configured to
route the oil 12 from the first manifold 46 to the second manifold
48. In the exemplary embodiment, the oil 12 is split and routed to
the first tube 38 and the third tube 42. The inlet 52 is also
fluidly coupled to the outlet 54 by an oil cooling arrangement
bypass 56 configured to divert the oil 12 from routing through the
plurality of tubes 36 of the oil cooling arrangement 10. Diversion
of the oil 12 is selectively controlled with a thermal control
valve 58 that is moveable between a first position and a second
position. The first position corresponds to a fully open position
that opens the oil cooling arrangement bypass 56, thereby causing
the oil 12 to be diverted to the outlet 54. Bypassing the oil
cooling arrangement 10 is desirable at operating temperatures that
do not require cooling of the oil 12. In one embodiment, the
thermal control valve 58 is in the fully open position at
temperatures less than and equal to about 250.degree. F. (about
121.degree. C.). As the temperature of the operating environment
begins to rise, thereby requiring cooling of the oil 12, the
thermal control valve 58 transitions toward the second position.
The second position corresponds to a fully closed position that
closes the oil cooling arrangement bypass 56, thereby causing the
oil 12 to be routed to the plurality of tubes 36 of the oil cooling
arrangement 10. In one embodiment, the thermal control valve 58 is
in the fully closed position at temperatures greater than and equal
to about 270.degree. F. (about 132.degree. C.).
[0016] Integrally formed with the thermal control valve 58 is a
pressure relief valve 60 that detects a pressure within passages of
the oil cooling arrangement 10. The pressure relief valve 60 is
configured to alter the cross-sectional area of one or more
passages proximate the inlet 52 and/or outlet 54, thereby
increasing the volumetric flow rate of the oil 12 in the event of a
partial blockage due to oil clotting or the like. In one
embodiment, the pressure relief valve 60 initiates relief at about
pressure differential of about 25 psid (about 172 kPa
differential).
[0017] Referring now to FIGS. 3 and 4, the oil cooling arrangement
10 is shown in greater detail. As indicated by the arrows
representing the direction of flow of the oil 12, it can be
appreciated that the second tube 40 and the fourth tube 44 are
shown from the illustrated side, while the first tube 38 and the
third tube 42 are hidden from view. Similarly, the outlet 54 is
illustrated, while the inlet 52 is hidden. As described in detail
above, the inlet 52 routes the oil to the first manifold 46 for
splitting of the oil 12 into the first tube 38 and the third tube
42. Upon reaching the second manifold 48, the oil 12 is directed to
the second tube 40 and the fourth tube 44. Specifically, the second
manifold 48 includes a first fluid path 62 fluidly coupling the
first tube 38 and the second tube 40, as well as a second fluid
path 64 fluidly coupling the third tube 42 and the fourth tube 44.
Within the second tube 40 and the fourth tube 44, the oil 12 is
routed from the second manifold 48 toward the first manifold 46 and
is subsequently expelled via the outlet 54.
[0018] While flowing through the plurality of tubes 36, which are
disposed within the turbine exhaust path 26, the oil 12 is cooled
due to heat transfer associated with the exhaust flow 24 passing
over an outer surface 68 of the plurality of tubes 36. As described
above, the exhaust flow 24 is relatively cold and is therefore
suitable for cooling of the oil 12 flowing within the plurality of
tubes 36. To enhance the heat transfer to the plurality of tubes 36
from the exhaust flow 24, a plurality of fins 70 extend outwardly
from the outer surface 68 of the plurality of tubes 36 to increase
the surface area in contact with the exhaust flow 24. To further
ensure adequate cooling of the oil 12, at least one rod 72 is
disposed within each of the plurality of tubes 36 to form an
annulus 76 through which the oil 12 flows. Formation of the annulus
76 causes the oil 12 to flow through the plurality of tubes 36 at
regions in close proximity to an inner surface 78 of the plurality
of tubes 36, thereby increasing the beneficial cooling effects of
the exhaust flow 24. Additionally, the rod 72 includes a machined
surface that may include various features to increase turbulence of
the oil flow, thereby enhancing cooling of the oil 12 while flowing
within the annulus 76. Specifically, the machined surface of the
rod 72 may include a knurled surface, for example.
[0019] A method of cooling oil 100 is also provided, as illustrated
in FIG. 5 and with reference to FIGS. 1-4. The oil cooling
arrangement 10 and the associated turbine system 14 have been
previously described and specific structural components need not be
described in further detail. The method of cooling oil 100 includes
supplying 102 an oil to a first manifold of an oil cooling
arrangement. The oil is routed through a first tube 104 from the
first manifold to a second manifold, wherein the first tube is
disposed in a turbine exhaust path. The oil is routed through a
second tube 106 from the second manifold to the first manifold,
wherein the second tube is disposed in the turbine exhaust path.
The method also includes flowing an exhaust flow 108 through the
turbine exhaust path and over the first tube and the second tube
for cooling the oil routed therein.
[0020] Advantageously, the oil cooling arrangement 10 and the
method of cooling oil 100 simplifies the heat exchanger structure
with higher reliability by enhancing the cooling capability of the
structure. Additionally, elimination of an on-board water source
that constitutes unnecessary mass is achieved. The reduction in
mass provides the opportunity to increase payload mass or reduce
fuel consumption.
[0021] While the invention has been described in detail in
connection with only a limited number of embodiments, it should be
readily understood that the invention is not limited to such
disclosed embodiments. Rather, the invention can be modified to
incorporate any number of variations, alterations, substitutions or
equivalent arrangements not heretofore described, but which are
commensurate with the spirit and scope of the invention.
Additionally, while various embodiments of the invention have been
described, it is to be understood that aspects of the invention may
include only some of the described embodiments. Accordingly, the
invention is not to be seen as limited by the foregoing
description, but is only limited by the scope of the appended
claims.
* * * * *