U.S. patent application number 13/053638 was filed with the patent office on 2011-08-04 for system for regulating a cooling fluid within a turbomachine.
This patent application is currently assigned to General Electric Company. Invention is credited to Don Conrad Johnson, Sivaraman Vedhagiri.
Application Number | 20110189000 13/053638 |
Document ID | / |
Family ID | 44341846 |
Filed Date | 2011-08-04 |
United States Patent
Application |
20110189000 |
Kind Code |
A1 |
Vedhagiri; Sivaraman ; et
al. |
August 4, 2011 |
SYSTEM FOR REGULATING A COOLING FLUID WITHIN A TURBOMACHINE
Abstract
Embodiments of the present invention provide a system for
regulating a cooling fluid within a turbomachine. The system may
include a plurality of bypass chambers, wherein each of the
plurality of bypass chambers allows for the cooling fluid to pass
from the compressor section to a wheelspace area. The system
includes a plurality of angular passages that aid in the mixing of
a cooling fluid with a working fluid in the wheelspace area.
Inventors: |
Vedhagiri; Sivaraman;
(Greer, SC) ; Johnson; Don Conrad; (Simpsonville,
SC) |
Assignee: |
General Electric Company
|
Family ID: |
44341846 |
Appl. No.: |
13/053638 |
Filed: |
March 22, 2011 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
11799162 |
May 1, 2007 |
7914253 |
|
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13053638 |
|
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Current U.S.
Class: |
415/178 |
Current CPC
Class: |
F01D 25/08 20130101 |
Class at
Publication: |
415/178 |
International
Class: |
F01D 25/08 20060101
F01D025/08 |
Claims
1. A system for regulating a cooling fluid, the system comprising:
a turbomachine comprising: a compressor section comprising an inner
barrel casing; a compressor discharge casing; and bypass chambers
that allow a cooling fluid to pass from the inner barrel casing to
the compressor discharge casing; a turbine section comprising
rotating components; stationary components; and wheelspace areas,
wherein each wheelspace area comprises a rotating component and a
stationary component and each bypass chamber allows for the cooling
fluid to pass from the compressor section to the wheelspace area;
and a nozzle cooling circuit comprising a primary passage and a
header, which are both substantially located within each stationary
component, wherein a first end of the primary passage receives the
cooling fluid and a second end of the primary passage is connected
to the header such that the cooling fluid flows from the primary
passage to the header; wherein the header comprises an upstream
port and a downstream port that allows the cooling fluid to
discharge from the header.
2. The system of claim 1, wherein a downstream end of each port is
connected to a tuning plug that comprises an opening which directs
the cooling fluid out of the nozzle cooling circuit.
3. The system of claim 2, wherein the tuning plug determines
mechanical properties of the cooling fluid.
4. The system of claim 1, wherein the stationary component
comprises multiple nozzle cooling circuits.
5. The system of claim 6, wherein each of the multiple nozzle
cooling circuits comprises: a designated primary passage and a
designated header.
6. The system of claim 1, wherein each port is offset from the
header at an angle which pre-swirls the cooling fluid in a manner
that aids in mixing with the working fluid.
7. The system of claim 6, wherein the angle orients the flow of the
cooling fluid in a direction similar to that of the working fluid
and the rotating components.
8. The system of claim 1, wherein the header is the form of a hole
extending through the stationary component.
9. The system of claim 8, wherein each end of the header is
enclosed by a cap.
10. A system for regulating a cooling fluid, the system comprising:
a gas turbine comprising: a combustion system that generates a
working fluid; a compressor section comprising an inner barrel
casing; a compressor discharge casing; and bypass chambers; wherein
the cooling fluid flows through the inner barrel casing to the
compressor discharge casing; a turbine section comprising rotating
components; stationary components; and wheelspace areas, wherein
each wheelspace area comprises a rotating component and a
stationary component and each bypass chamber allows for the cooling
fluid to pass from the compressor section to the wheelspace area;
and a nozzle cooling circuit substantially located within each
stationary component, wherein the nozzle cooling circuit comprises
a primary passage and a header; wherein a first end of the primary
passage receives the cooling fluid and a second end of the primary
passage is connected to the header and the cooling fluid flows from
the primary passage to the header; wherein the header comprises an
upstream port and a downstream port that allows the cooling fluid
to discharge from the header and mixing with the working fluid.
11. The system of claim 10 further comprising a tuning plug located
downstream of the header, which allows the cooling fluid to exit
the nozzle cooling circuit.
12. The system of claim 11, wherein each port is integrated with a
dedicated tuning plug.
13. The system of claim 11, wherein the dedicated tuning plug
comprise a variable internal diameter through which the cooling
fluid discharges the header.
14. The system of claim 13, wherein the dedicated tuning plug
determines at least one of the following properties of the cooling
fluid: velocity, flowrate, or pressure.
15. The system of claim 10, wherein the stationary component
comprises multiple nozzle cooling circuits.
16. The system of claim 15, wherein each of the multiple nozzle
cooling circuits comprises: a designated primary passage and a
designated header.
17. The system of claim 11, wherein the dedicated tuning plug
directs the cooling fluids towards an outer surface of the
stationary component.
18. The system of claim 10, wherein each port is offset from the
header at an angle which pre-swirls the cooling fluid in a manner
that aids in mixing with the working fluid.
19. The system of claim 18, wherein the angle orients the flow of
the cooling fluid in a direction similar to that of the working
fluid and the rotating components.
20. The system of claim 11, wherein the header is the form of a
circular opening that extends through the stationary component in
an upstream to downstream orientation, and wherein each end of the
header is enclosed by a cap.
Description
[0001] This is a continuation-in-part application claiming priority
to commonly-assigned U.S. patent application Ser. No. 11/799,162
[GE Docket 208397-1], entitled "System For Regulating A Cooling
Fluid Within A Turbomachine", filed May 1, 2007; which is
incorporated herein by reference in its entirety.
BACKGROUND OF THE INVENTION
[0002] The present application relates generally to a cooling
system on a turbomachine; and more particularly to, a system for
regulating a cooling fluid within a wheelspace area of a
turbomachine.
[0003] In some turbomachines, such as gas turbines, a portion of
the air compressed by the compressor is typically diverted from
combustion to cool various stationary and rotating components or to
purge cavities within a gas turbine. The diverted airflow
(hereinafter "cooling fluid",) consumes a considerable amount of
the total airflow compressed by the compressor. The diverted
cooling fluid is not combusted, reducing the performance of the gas
turbine. Regulating and controlling the cooling fluid can
dramatically increase the performance of the turbine.
[0004] Typically, the cooling fluid is extracted from the
compressor, bypasses the combustion system, and flows through a
cooling circuit. The cooling circuit is typically located near
various turbine components including the rotor compressor-turbine
joint (hereinafter "marriage joint"), and various wheelspace areas.
The cooling circuit is typically integrated with a seal system.
Relatively tight clearances may exist between the seal system
components and the gas turbine rotor.
[0005] The seal system may include labyrinth seals located between
rotating and stationary components. The typical leakages that may
occur through the labyrinth seal clearances are commonly used for
cooling or purging areas downstream of the seals. For example, a
high-pressure packing seal system (HPPS) may include a labyrinth
and brush seal arrangement, wherein the leakage flow past the HPPS
cools the downstream components including the wheelspace areas. The
effectiveness of the cooling circuit is highly dependent on the
performance of the HPPS.
[0006] The configuration of the cooling circuit determines whether
or not adequate cooling fluid flows to the aforementioned turbine
components. The cooling circuit may include a chamber that directs
the cooling fluid flow to a specific wheelspace area.
[0007] There may be a few issues with the currently known seal
systems. Wear may enlarge the seal system clearances. Seals may
wear during a "trip" (an emergency shutdown of the turbomachine).
Also, seals gradually wear over time from gas turbine operation.
Wear allows excessive cooling fluid to flow downstream of the
seals; reducing the overall efficiency of the gas turbine. The
unpredictable nature of the seal system wear occurrence does not
allow for a deterministic flow of the cooling fluid through the
cooling circuit. Furthermore, known seal systems do not compensate
for seal system wear. Therefore, the known seal systems do not
provide a way to adjust the amount of cooling fluid flowing to the
wheelspace areas.
[0008] For the foregoing reasons, there is a desire for a system
that allows regulating the cooling fluid passing into the
wheelspace areas of the gas turbine. The system should adequately
cool while improving the gas turbine efficiency. The system should
also provide for a deterministic flow through the cooling
circuit.
BRIEF DESCRIPTION OF THE INVENTION
[0009] Certain embodiments commensurate in scope with the
originally claimed invention are summarized below. These
embodiments are not intended to limit the scope of the claimed
invention, but rather these embodiments are intended only to
provide a brief summary of possible forms of the invention. Indeed,
the invention may encompass a variety of forms that may be similar
to or different from the embodiments set forth below.
[0010] In an embodiment of the present invention, a system for
regulating a cooling fluid, the system comprising: a turbomachine
comprising: a compressor section comprising an inner barrel casing;
a compressor discharge casing; and bypass chambers that allow a
cooling fluid to pass from the inner barrel casing to the
compressor discharge casing; a turbine section comprising rotating
components; stationary components; and wheelspace areas, wherein
each wheelspace area comprises a rotating component and a
stationary component and each bypass chamber allows for the cooling
fluid to pass from the compressor section to the wheelspace area;
and a nozzle cooling circuit comprising a primary passage and a
header, which are both substantially located within each stationary
component, wherein a first end of the primary passage receives the
cooling fluid and a second end of the primary passage is connected
to header such that the cooling fluid flows from the primary
passage to the header; wherein the header comprises an upstream
port and a downstream port that allows the cooling fluid to
discharge from the header.
[0011] In an alternate embodiment of the present invention, a
system for regulating a cooling fluid, the system comprising: a gas
turbine comprising: a combustion system that generates a working
fluid; a compressor section comprising an inner barrel casing; a
compressor discharge casing; and bypass chambers; wherein the
cooling fluid flows through the inner barrel casing to the
compressor discharge casing; a turbine section comprising rotating
blades; diaphragms; nozzles; and wheelspace areas, wherein each
wheelspace area comprises a series of rotating blades, a diaphragm,
and a nozzle, and each bypass chamber allows the cooling fluid to
flow from the compressor discharge casing to the wheelspace areas;
and a nozzle cooling circuit substantially located within each
stationary component, wherein the nozzle cooling circuit comprises
a primary passage and a header; wherein a first end of the primary
passage receives the cooling fluid and a second end of the primary
passage is connected to header and the cooling fluid flows from the
primary passage to the header; wherein the header comprises an
upstream port and a downstream port that allows the cooling fluid
to discharge from the header and mixing with the working fluid.
BRIEF DESCRIPTION OF THE DRAWING
[0012] These and other features, aspects, and advantages of the
present invention may become better understood when the following
detailed description is read with reference to the accompanying
figures (FIGS) in which like characters represent like
elements/parts throughout the FIGS.
[0013] FIG. 1 is a schematic view, in cross-section, of a gas
turbine, illustrating the environment in which an embodiment of the
present invention operates.
[0014] FIG. 2 is an enlarged view of a portion of the gas turbine
illustrated in FIG. 1.
[0015] FIG. 3 illustrates a schematic view of a stationary
component of FIG. 2 having a known nozzle cooling circuit.
[0016] FIG. 4 illustrates a schematic view of a stationary
component of FIG. 2 having a nozzle cooling circuit, in accordance
with an embodiment of the present invention.
[0017] FIG. 5 illustrates an exploded schematic view of the
stationary. component of FIG. 4, in accordance with an embodiment
of the present invention.
[0018] FIG. 6 illustrates a schematic view of the stationary
component of FIG. 4 in use, in accordance with an embodiment of the
present invention.
DETAILED DESCRIPTION OF THE INVENTION
[0019] One or more specific embodiments of the present invention
will be described below. In an effort to provide a concise
description of these embodiments, all features of an actual
implementation may not be described in the specification. It should
be appreciated that in the development of any such actual
implementation, as in an engineering or design project, numerous
implementation-specific decisions are made to achieve the specific
goals, such as compliance with system-related and/or
business-related constraints, which may vary from one
implementation to another. Moreover, it should be appreciated that
such effort might be complex and time consuming, but would
nevertheless be a routine undertaking of design, fabrication, and
manufacture for those of ordinary skill having the benefit of this
disclosure.
[0020] Detailed example embodiments are disclosed herein. However,
specific structural and functional details disclosed herein are
merely representative for purposes of describing example
embodiments. Embodiments of the present invention may, however, be
embodied in many alternate forms, and should not be construed as
limited to only the embodiments set forth herein.
[0021] Accordingly, while example embodiments are capable of
various modifications and alternative forms, embodiments thereof
are illustrated by way of example in the figures and will herein be
described in detail. It should be understood, however, that there
is no intent to limit example embodiments to the particular forms
disclosed, but to the contrary, example embodiments are to cover
all modifications, equivalents, and alternatives falling within the
scope of the present invention.
[0022] The terminology used herein is for describing particular
embodiments only and is not intended to be limiting of example
embodiments. As used herein, the singular forms "a", "an" and "the"
are intended to include the plural forms as well, unless the
context clearly indicates otherwise. The terms "comprises",
"comprising", "includes" and/or "including", when used herein,
specify the presence of stated features, integers, steps,
operations, elements, and/or components, but do not preclude the
presence or addition of one or more other features, integers,
steps, operations, elements, components, and/or groups thereof.
[0023] Although the terms first, second, etc may be used herein to
describe various elements, these elements should not be limited by
these terms. These terms are only used to distinguish one element
from another. For example, a first element could be termed a second
element, and, similarly, a second element could be termed a first
element, without departing from the scope of example embodiments.
As used herein, the term "and/or" includes any, and all,
combinations of one or more of the associated listed items.
[0024] Certain terminology may be used herein for the convenience
of the reader only and is not to be taken as a limitation on the
scope of the invention. For example, words such as "upper",
"lower", "left", "right", "front", "rear", "top", "bottom",
"horizontal", "vertical", "upstream", "downstream", "fore", "aft",
and the like; merely describe the configuration shown in the FIGS.
Indeed, the element or elements of an embodiment of the present
invention may be oriented in any direction and the terminology,
therefore, should be understood as encompassing such variations
unless specified otherwise.
[0025] The present invention may be applied to a variety of
air-ingesting turbomachines. This may include, but is not limiting
to, heavy-duty gas turbines, aero-derivatives, or the like.
Although the following discussion relates to the gas turbine
illustrated in FIG. 1, embodiments of the present invention may be
applied to a gas turbine with a different configuration. For
example, but not limiting of, the present invention may apply to a
gas turbine with different, or additional, components than those
illustrated in FIG. 1.
[0026] Referring now to the FIGS, where the various numbers
represent like components throughout the several views, FIG. 1 is a
schematic view, in cross-section, of a portion of a gas turbine,
illustrating the environment in which an embodiment of the present
invention operates. In FIG. 1, a gas turbine 100 includes: a
compressor section 105; a combustion section 150; and a turbine
section 180.
[0027] Generally, the compressor section 105 includes a plurality
of rotating blades 110 and stationary vanes 115 structured to
compress a fluid. The compressor section 105 may also include an
extraction port 120, an inner barrel 125, a compressor discharge
casing 130, a marriage joint 135, and a marriage joint bolt
137.
[0028] The combustion section 150 generally includes a plurality of
combustion cans 155, a plurality of fuel nozzles 160, and a
plurality of transition sections 165. The plurality of combustion
cans 155 may be coupled to a fuel source. Within each combustion
can 155, compressed air is received from the compressor section 105
and mixed with fuel received from the fuel source. The air and fuel
mixture is ignited and creates a working fluid. The working fluid
generally proceeds from the aft end of the plurality of fuel
nozzles 160 downstream through the transition section 165 into the
turbine section 180.
[0029] The turbine section 180 may include a plurality of rotating
components 185; a plurality of stationary components 190, which
include nozzles and diaphragms; and a plurality of wheelspace areas
195. The turbine section 180 converts the working fluid to a
mechanical torque.
[0030] Typically, during the operation of the gas turbine 100, a
plurality of components experience high temperatures and may
require cooling or purging. These components may include a portion
of the compressor section 105, the marriage joint 135, and the
plurality of wheelspace areas 195.
[0031] The extraction port 120 draws cooling fluid from the
compressor section 105. The cooling fluid bypasses the combustion
section 150, and flows through a cooling circuit 200 (illustrated
in FIG. 2), for cooling or purging various components, including
the marriage joint 135, and a plurality of wheelspace areas
195.
[0032] Referring now to FIG. 2, which is a close-up view of the gas
turbine illustrated in FIG. 1. FIG. 2 illustrates a non-limiting
example of an embodiment of the cooling circuit 200. The flow path
of the cooling circuit 200 may start at the extraction port 120
(illustrated in FIG. 1), flow through a portion of the compressor
discharge casing 130, the inner barrel casing 125, and then a
cavity at the aft end of the compressor section 105. Next, the
cooling circuit 200 may reverse direction, flowing past the
marriage joint 135, the seal system components 140, and to the
wheelspace area 195.
[0033] FIG. 3 illustrates a schematic view of the stationary
component 190 of FIG. 2 having a known nozzle cooling circuit. The
stationary component 190 comprises a nozzle cooling circuit 300
that is located internally. The nozzle cooling circuit 300 allows
the cooling fluid to cool the stationary component 190 from within.
The nozzle cooling circuit 300 receives the cooling fluid,
illustrated in the FIGS by the arrows. The currently known circuit
300 includes a path that may direct the cooling fluid to discharge
on an upstream side of the stationary component 190. After exiting
the stationary component 190, the cooling fluid may flow downstream
through the seal system components 140 and then engage a downstream
side of the stationary component 190.
[0034] FIG. 4 illustrates a schematic view of a stationary
component of FIG. 2 having a nozzle cooling circuit, in accordance
with an embodiment of the present invention. The stationary
component 190 comprises a nozzle cooling circuit 400 that is
located internally. The nozzle cooling circuit 400 allows the
cooling fluid to cool the stationary component 190 in a more
controlled and efficient way. The nozzle cooling circuit 400
receives the cooling fluid which is illustrated in the FIGS by the
arrows. By comparing FIG. 3 and FIG. 4, the benefits of embodiments
of the present invention are shown. Here, the cooling fluid flows
from a primary passage 405 to a header 410; which allows the
cooling fluid to discharge from the stationary component 190 in
both upstream and downstream directions. This allows for a more
efficient cooling of the downstream end of the stationary component
190.
[0035] FIG. 5 illustrates an exploded schematic view of the
stationary component of FIG. 4, in accordance with an embodiment of
the present invention. An embodiment of the nozzle cooling circuit
400 may comprise a primary passage 405, a header 410, a port 415,
and a tuning plug 420.
[0036] An embodiment of the primary passage 405 may comprise a
first end and a second end. The first end may be positioned to
receive the cooling fluid. The second end located at an opposite
end of the primary passage 405. The second end may be connected to
the header 410 in a manner that allows the cooling fluid to enter.
In an embodiment of the present invention the nozzle cooling
circuit 400 may comprise one primary passage 405. In an alternate
embodiment of the present invention, the nozzle cooling circuit 400
may comprise multiple primary passages 405. Here, each primary
passage 405 may comprise a dedicated header 410.
[0037] An embodiment of the header 410 may have the form of a
through-hole, or the like. Each end of the header 410 may be
enclosed via a cap 425, as illustrated, for example, in FIG. 5. The
cap 425 may be connected to the header 410, via welding, threaded
connections, or other connection means.
[0038] Located upstream of the end of the header 410 are an
upstream port 415 and a downstream port 415, as illustrated in FIG.
6. The ports 415 may be considered an angled passage. The ports 415
are angularly positioned relative to the header 410. This angle 430
may induce a pre-swirl on the cooling fluid exiting each port 415
and entering the wheelspace area 195. In an embodiment of the
present invention, the angle 430 may comprise a range of from about
0 degrees to about 100 degrees, depending on the physical
constraints associated with the associated components. The
pre-swirl allows the cooling fluid to flow in nearly the same
direction and orientation as the rotating components 185 and the
working fluid. This may improve the mixing of the cooling fluid
with the working fluid, increasing the cooling efficiency.
[0039] The upstream ports 415 allows the cooling fluid to discharge
the near an upstream end of the stationary component 190. The
downstream port 415 allows the cooling fluid to discharge near a
downstream end of the stationary component 190. The tuning plug 420
allows a user to control the flow of the cooling fluid exiting a
designated port 415. The tuning plug 420 comprises a through hole,
or the like, which allows the cooling fluid to flow from the header
410 and discharge via a port 415. The tuning plug 420 may assist
the port 415 with directing the cooling fluid toward an outer
surface of the stationary component 190. The tuning plug 420 may
adjust the mechanical properties of the cooling fluid exiting the
nozzle cooling circuit 400. These properties may include, but are
not limited to: velocity, flowrate, and pressure.
[0040] An embodiment of the tuning plug 420 may comprise a threaded
connection that allows mating with the portion of the port 415. An
alternate embodiment of the tuning plug 420 may be press fit into
the port 415. Another alternate embodiment of the tuning plug 420
may comprise a variable internal diameter through which the cooling
fluid discharges from the header 410, providing more control over
the aforementioned properties.
[0041] FIG. 6 illustrates a schematic view of the stationary
component 190 of FIG. 4 in use, in accordance with an embodiment of
the present invention. In use, an embodiment of the present
invention may function as follows. The nozzle cooling circuit 400
receives the cooling fluid, represented in FIG. 4 by the arrows.
Next, the cooling fluid may flow through the primary passage 405.
Next the cooling fluid may enter the header 410. Here, the flow of
the cooling fluid may diverge. A portion may flow towards the
upstream port 415, discharging via the connected tuning plug 420.
The remaining portion may flow towards the downstream port 415,
discharging via the connected tuning plug 420.
[0042] Although specific embodiments have been illustrated and
described herein, those of ordinary skill in the art appreciate
that any arrangement, which is calculated to achieve the same
purpose, may be substituted for the specific embodiments shown and
that the invention has other applications in other environments.
This application is intended to cover any adaptations or variations
of the present invention. The following claims are in no way
intended to limit the scope of the invention to the specific
embodiments described herein.
[0043] As one of ordinary skill in the art will appreciate, the
many varying features and configurations described above in
relation to the several embodiments may be further selectively
applied to form other possible embodiments of the present
invention. Those in the art will further understand that all
possible iterations of the present invention are not provided or
discussed in detail, even though all combinations and possible
embodiments embraced by the several claims below or otherwise are
intended to be part of the instant application. In addition, from
the above description of several embodiments of the invention,
those skilled in the art will perceive improvements, changes, and
modifications. Such improvements, changes, and modifications within
the skill of the art are also intended to be covered by the
appended claims. Further, it should be apparent that the foregoing
relates only to the described embodiments of the present
application and that numerous changes and modifications may be made
herein without departing from the spirit and scope of the
application as defined by the following claims and the equivalents
thereof.
* * * * *