[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.
[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.
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.
[0006] These and other advantages and features will become more apparent from the following
description taken in conjunction with the drawings.
[0007] 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:
FIG. 1 is a side perspective view of a compressor section of a gas turbine system;
and
FIG. 2 is a schematic view of a plurality of variable stator vanes of the compressor
section.
[0008] The detailed description explains embodiments of the invention, together with advantages
and features, by way of example with reference to the drawings.
[0009] 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.
[0010] 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.
[0011] 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.
[0012] 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.
[0013] 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.
[0014] 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.
[0015] 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.
[0016] 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.
[0017] Various aspects and embodiments of the present invention are defined by the following
numbered clauses:
- 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 clause 1, wherein the first actuation mechanism is hydraulically
actuated.
- 3. The compressor of clause 1 or clause 2, wherein at least one of the first actuation
mechanism and the second actuation mechanism is driven by an electric motor.
- 4. The compressor of any preceding clause, 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 any preceding clause, 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 any preceding clause, wherein the plurality of stator rows are
operably coupled together.
- 7. The compressor of any preceding clause, wherein the linkage operably couples the
plurality of stator rows together.
- 8. The compressor of any preceding clause, 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 any preceding clause, 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 any preceding clause, wherein the first actuation mechanism
is electrically actuated.
- 12. The compressor of any preceding clause, wherein the second actuation mechanism
comprises a screw driven by an electric motor.
- 13. The compressor of any preceding clause, further comprising at least one inlet
row having a plurality of inlet vanes.
- 14. The compressor of any preceding clause, wherein the plurality of rows is positionally
variable with respect to at least one inlet row.
- 15. The compressor of any preceding clause, 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 any preceding clause, 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 any preceding clause, 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 any preceding clause, wherein the plurality of stator rows is
positionally variable with respect to the at least one inlet row.
- 20. The compressor of any preceding clause, 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.
1. A compressor (12) of a gas turbine system comprising:
at least one inlet row (24) having a plurality of inlet guide vanes (26);
at least one stator row (14) having a plurality of stator vanes;
a first actuation mechanism (32) 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 (34) 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 (32) is hydraulically
actuated.
3. The compressor of claim 1 or claim 2, wherein at least one of the first actuation
mechanism and the second actuation mechanism is driven by an electric motor.
4. The compressor of any preceding claim, 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 any preceding claim, 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 any preceding claim, wherein the plurality of stator rows are operably
coupled together.
7. The compressor of any preceding claim, wherein the linkage operably couples the plurality
of stator rows together.
8. The compressor of any preceding claim, 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 any preceding claim, 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 any preceding claim, wherein the first actuation mechanism is electrically
actuated.
12. The compressor of any preceding claim, wherein the second actuation mechanism comprises
a screw driven by an electric motor.
13. The compressor of any preceding claim, comprising:
a plurality of stator rows, each of the plurality of stator rows having a plurality
of stator vanes; wherein
the first actuation mechanism includes 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
the second actuation mechanism includes 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.
14. The compressor of any preceding claim, wherein the plurality of stator rows is positionally
variable with respect to the at least one inlet row.
15. The compressor of any preceding claim, 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.