U.S. patent application number 13/455781 was filed with the patent office on 2013-10-31 for compressor of a gas turbine system.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is Harry McFarland Jarrett, JR., Brian Allen Rittenhouse, Daniel Richard Waugh. Invention is credited to Harry McFarland Jarrett, JR., Brian Allen Rittenhouse, Daniel Richard Waugh.
Application Number | 20130287550 13/455781 |
Document ID | / |
Family ID | 48182783 |
Filed Date | 2013-10-31 |
United States Patent
Application |
20130287550 |
Kind Code |
A1 |
Rittenhouse; Brian Allen ;
et al. |
October 31, 2013 |
COMPRESSOR OF A GAS TURBINE SYSTEM
Abstract
A compressor of a gas turbine system includes at least one inlet
row having a plurality of inlet guide vanes. Also included is at
least one stator row having a plurality of stator vanes. Further
included is a first actuation mechanism operably connected to the
at least one stator row, wherein the first actuation mechanism is
configured to positionally manipulate the at least one stator row.
Yet further included is a second actuation mechanism operably
connected to the at least one stator row, wherein the second
actuation mechanism is configured to positionally manipulate the at
least one stator row.
Inventors: |
Rittenhouse; Brian Allen;
(Simpsonville, SC) ; Jarrett, JR.; Harry McFarland;
(Simpsonville, SC) ; Waugh; Daniel Richard;
(Simpsonville, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Rittenhouse; Brian Allen
Jarrett, JR.; Harry McFarland
Waugh; Daniel Richard |
Simpsonville
Simpsonville
Simpsonville |
SC
SC
SC |
US
US
US |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
48182783 |
Appl. No.: |
13/455781 |
Filed: |
April 25, 2012 |
Current U.S.
Class: |
415/162 |
Current CPC
Class: |
F01D 17/14 20130101;
F01D 17/162 20130101; F01D 17/167 20130101; F04D 27/0246 20130101;
F04D 29/563 20130101; F05D 2220/3217 20130101; F05D 2260/76
20130101 |
Class at
Publication: |
415/162 |
International
Class: |
F01D 9/04 20060101
F01D009/04; F01D 17/12 20060101 F01D017/12 |
Claims
1. A compressor of a gas turbine system comprising: at least one
inlet row having a plurality of inlet guide vanes; at least one
stator row having a plurality of stator vanes; a first actuation
mechanism operably connected to the at least one stator row,
wherein the first actuation mechanism is configured to positionally
manipulate the at least one stator row; and a second actuation
mechanism operably connected to the at least one stator row,
wherein the second actuation mechanism is configured to
positionally manipulate the at least one stator row.
2. The compressor of claim 1, wherein the first actuation mechanism
is hydraulically actuated.
3. The compressor of claim 1, wherein at least one of the first
actuation mechanism and the second actuation mechanism is driven by
an electric motor.
4. The compressor of claim 1, further comprising: a plurality of
stator rows, each of the plurality of stator rows having the
plurality of stator vanes; a linkage operably connecting the first
actuation mechanism to the plurality of stator rows; and a
plurality of second actuation mechanisms, each of the plurality of
second actuation mechanisms operably connected to one of the
plurality of stator rows.
5. The compressor of claim 4, wherein each of the plurality of
second actuation mechanisms is configured to independently
positionally manipulate each of the plurality of stator rows.
6. The compressor of claim 4, wherein the plurality of stator rows
are operably coupled together.
7. The compressor of claim 6, wherein the linkage operably couples
the plurality of stator rows together.
8. The compressor of claim 1, wherein the second actuation
mechanism positionally manipulates the at least one stator row with
greater precision than the first actuation mechanism.
9. The compressor of claim 1, wherein the at least one stator row
is positionally variable with respect to the at least one inlet
row.
10. A compressor of a gas turbine system comprising: a plurality of
rows, each of the plurality of rows having a plurality of stator
vanes; a first actuation mechanism operably connected to the
plurality of rows, wherein the first actuation mechanism is
configured to positionally manipulate the plurality of rows; and a
second actuation mechanism operably connected to at least one row
of the plurality of rows, wherein the second actuation mechanism is
configured to positionally manipulate the at least one row.
11. The compressor of claim 10, wherein the first actuation
mechanism is electrically actuated.
12. The compressor of claim 10, wherein the second actuation
mechanism comprises a screw driven by an electric motor.
13. The compressor of claim 10, further comprising at least one
inlet row having a plurality of inlet vanes.
14. The compressor of claim 13, wherein the plurality of rows is
positionally variable with respect to at least one inlet row.
15. The compressor of claim 10, further comprising: a linkage
operably connecting the first actuation mechanism to the plurality
of rows; and a plurality of second actuation mechanisms, each of
the plurality of second actuation mechanisms operably connected to
one of the plurality of rows.
16. The compressor of claim 15, wherein each of the plurality of
second actuation mechanisms is configured to independently
positionally manipulate each of the plurality of rows.
17. The compressor of claim 15, wherein the linkage operably
couples the plurality of rows together.
18. A compressor of a gas turbine system comprising: at least one
inlet row having a plurality of inlet guide vanes; a plurality of
stator rows, each of the plurality of stator rows having a
plurality of stator vanes; an electric actuator operably connected
to the plurality of stator rows, wherein the hydraulic actuator is
configured to positionally manipulate the plurality of stator rows;
and an electrically driven screw actuator operably connected to at
least one stator row of the plurality of stator rows, wherein the
electrically driven screw actuator is configured to positionally
manipulate the at least one stator row.
19. The compressor of claim 18, wherein the plurality of stator
rows is positionally variable with respect to the at least one
inlet row.
20. The compressor of claim 18, further comprising a plurality of
second actuation mechanisms, each of the plurality of second
actuation mechanisms operably connected to one of the plurality of
stator rows for independently positionally manipulating each of the
plurality of stator rows.
Description
BACKGROUND OF THE INVENTION
[0001] The subject matter disclosed herein relates to compressors
of gas turbine systems, and more particularly to positional control
of inlet guide and/or stator vanes.
[0002] Gas turbine systems often include multiple rows or stages,
where a rotor is turned at a high speed, such that air is drawn
into the compressor and accelerated by rotating blades that
transfer air downstream and onto or past an adjacent row of stator
vanes. The pressure of the air flowing through the compressor is
increased through each row or stage of the compressor, thereby
forming a compressed gas.
[0003] In an effort to increase the efficiency of gas turbine
systems, and more specifically compressors of such systems,
variable stator vanes may be employed to impart an effect on the
air flowing through the compressor in such a manner as to control
the effect of the angle of flow to the adjacent downstream row or
stage. Although efficiency improvements may be seen at all
operating conditions, variable stator vanes are particularly useful
at relatively low rotational speeds and during turndown.
BRIEF DESCRIPTION OF THE INVENTION
[0004] According to one aspect of the invention, a compressor of a
gas turbine system includes at least one inlet row having a
plurality of inlet guide vanes. Also included is at least one
stator row having a plurality of stator vanes. Further included is
a first actuation mechanism operably connected to the at least one
stator row, wherein the first actuation mechanism is configured to
positionally manipulate the at least one stator row. Yet further
included is a second actuation mechanism operably connected to the
at least one stator row, wherein the second actuation mechanism is
configured to positionally manipulate the at least one stator
row.
[0005] According to another aspect of the invention, a compressor
of a gas turbine system includes a plurality of rows, each of the
plurality of rows having a plurality of stator vanes. Also included
is a first actuation mechanism operably connected to the plurality
of rows, wherein the first actuation mechanism is configured to
positionally manipulate the plurality of rows. Further included is
a second actuation mechanism operably connected to at least one row
of the plurality of rows, wherein the second actuation mechanism is
configured to positionally manipulate the at least one row.
[0006] According to yet another aspect of the invention, a
compressor of a gas turbine system includes at least one inlet row
having a plurality of inlet guide vanes. Also included is a
plurality of stator rows, each of the plurality of stator rows
having a plurality of stator vanes. Further included is an electric
actuator operably connected to the plurality of stator rows,
wherein the hydraulic actuator is configured to positionally
manipulate the plurality of stator rows. Yet further included is an
electrically driven screw actuator operably connected to at least
one stator row of the plurality of stator rows, wherein the
electrically driven screw actuator is configured to positionally
manipulate the at least one stator row.
[0007] These and other advantages and features will become more
apparent from the following description taken in conjunction with
the drawings.
BRIEF DESCRIPTION OF THE DRAWING
[0008] 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:
[0009] FIG. 1 is a side perspective view of a compressor section of
a gas turbine system; and
[0010] FIG. 2 is a schematic view of a plurality of variable stator
vanes of the compressor section.
[0011] The detailed description explains embodiments of the
invention, together with advantages and features, by way of example
with reference to the drawings.
DETAILED DESCRIPTION OF THE INVENTION
[0012] Referring to FIGS. 1 and 2, a gas turbine system 10 includes
an axial flow compressor 12 having a plurality of stages or stator
rows 14. Each stator row 14 comprises at least one, but typically a
plurality of, circumferentially spaced variable stator vanes 16
that are positioned upstream of a row of circumferentially spaced
rotor blades (not shown) that are operably connected to, and extend
radially away from, a rotor (not shown). The rotor is configured to
rotate about a central axis. The rotor blades are constrained to
rotate about the axis and within a compressor casing (not
illustrated). Additionally, the compressor 12 includes at least one
inlet guide row 24 that comprises at least one, but typically a
plurality of, inlet guide vanes 26, which may be variable as well.
The inlet guide row 24 is positioned at the entry to the compressor
12.
[0013] In operation, air flows into the compressor 12 and is
compressed into a high pressure gas. The high pressure gas is
supplied to a combustor assembly (not illustrated) and mixed with
fuel, for example natural gas and/or liquid fuel.
[0014] A linkage 28 is operably coupled to at least one of the
stator rows 14, and therefore the variable stator vanes 16. The
linkage 28 is typically operably coupled to a plurality of the
stator rows 14, as is the case in the illustrated embodiment, where
the linkage 28 is coupled to three such stator rows 14. The linkage
28 includes a torque shaft 30 and a first actuator mechanism 32
that is configured to drive the linkage 28. The first actuator
mechanism 32 is typically an electric actuator or a hydraulic
actuator, but it is contemplated that several other actuator types
may be employed to successfully drive the linkage 28 and therefore
the stator rows 14. As described above, the first actuator
mechanism 32 is operably coupled to a plurality of the stator rows
14 and thereby achieves relatively fast adjustment of the stator
rows 14 and the variable stator vanes 16. Relatively fast
adjustment is beneficial during transitioning of the gas turbine
system 10, and specifically the compressor 12, between various
operating conditions. The first actuator mechanism 32 may be
disposed within the compressor 12 in a number of ways, including
but not limited to direct or indirect attachment to the compressor
casing or stable structures within the compressor casing. Such
mounting may include the use of mechanical fasteners for
establishing a secure relationship between the first actuator
mechanism 32 and an associated structure within the compressor
12.
[0015] In order to establish more control precision over adjustment
of the stator rows 14, and therefore the variable stator vanes 16,
a second actuator mechanism 34 is associated with an individual
stator row 14. The second actuator mechanism 34 is configured to
enhance the precision of the adjustment for each stator row 14.
Furthermore, the second actuator mechanism 34 functions to provide
independent control over each stator row 14, such that the number
of achievable positional combinations of the stator rows 14 is
increased greatly. A number of actuator types may be employed as
the second actuator mechanism 34, with one type being a screw type
actuator electrically driven by a motor, such as a trimmer motor.
Typically, the compressor 12 will house a plurality of second
actuator mechanisms 34, with the precise number of second actuator
mechanisms 34 being determined by how many stator rows 14 are
desired to be controlled.
[0016] The inlet guide row 24 may also be positionally adjusted
with an operable connection to an inlet row actuator 36. The inlet
row actuator 36 may be of the hydraulic type, electrically driven,
or any other suitable alternative.
[0017] In operation, the variable stator vanes 16 and/or the inlet
guide vanes 26 correct the deflection given to air flowing through
the compressor 12 by upstream rotor blades and presenting the air
at a correct angle to the next row of rotor blades. In addition to
this base load function, the variable stator vanes 16 and/or the
inlet guide vanes 26 may be adjusted to enhance performance during
transitions of the gas turbine system 10, such as turndown
transitioning. The first actuator mechanism 32 provides the ability
to respond quickly to adjustment requirements and the second
actuator mechanism 34 maintains a slower, but more precise
adjustment capability of each independent stator row 14 and/or
inlet guide row 24.
[0018] Advantageously, the primary and secondary adjustment of the
stator rows 14 by the first actuator mechanism 32 and the second
actuator mechanism 34, respectively, improve base load performance
through enhanced control of the relationship between the variable
stator vanes 16 and/or the inlet guide vanes 26, as well as
improved performance during turn down. The dual adjustment also
allows for improved efficiency at a greater number of operating and
flow conditions.
[0019] 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.
* * * * *