U.S. patent application number 14/359330 was filed with the patent office on 2014-10-23 for eccentric diaphragm adjusting pins for a gas turbine engine.
This patent application is currently assigned to SIEMENS AKTIENGESELLSCHAFT. The applicant listed for this patent is Siemens Aktiengesellschaft. Invention is credited to Paul Jenkinson, Mike McKenna.
Application Number | 20140314550 14/359330 |
Document ID | / |
Family ID | 47115881 |
Filed Date | 2014-10-23 |
United States Patent
Application |
20140314550 |
Kind Code |
A1 |
Jenkinson; Paul ; et
al. |
October 23, 2014 |
ECCENTRIC DIAPHRAGM ADJUSTING PINS FOR A GAS TURBINE ENGINE
Abstract
The present invention relates to a stator stage (100) for a gas
turbine and a method of adjusting a relative position between a
vane segment (110) and a centre section (101) of the stator stage.
A groove (102) is formed between a first rim (103) and a second rim
(104) of a radially outer edge of the centre section, wherein the
groove, the first rim and the second rim run along a
circumferential direction (131). The vane segment comprises a
radially inner shroud (111) from which a protrusion (112) protrudes
radially inwards. The protrusion is inserted into the groove. An
adjusting pin (120) comprises a first end section (121), a second
end section (122) and an eccentric section (123) which runs between
the first end section and the second end section. The first end
section is coupled to the first rim, the second end section is
coupled to the second rim and the eccentric section is coupled to
the protrusion such that by pivoting the adjusting pin the relative
position between the vane segment and the centre section is
adjustable.
Inventors: |
Jenkinson; Paul; (Lincoln,
GB) ; McKenna; Mike; (Newark, GB) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Siemens Aktiengesellschaft |
Munich |
|
DE |
|
|
Assignee: |
SIEMENS AKTIENGESELLSCHAFT
Munich
DE
|
Family ID: |
47115881 |
Appl. No.: |
14/359330 |
Filed: |
October 23, 2012 |
PCT Filed: |
October 23, 2012 |
PCT NO: |
PCT/EP2012/070941 |
371 Date: |
May 20, 2014 |
Current U.S.
Class: |
415/148 ;
29/889.21 |
Current CPC
Class: |
F01D 9/042 20130101;
F01D 17/167 20130101; Y10T 29/49321 20150115; F01D 25/246 20130101;
F05D 2230/644 20130101; F01D 11/025 20130101 |
Class at
Publication: |
415/148 ;
29/889.21 |
International
Class: |
F01D 17/16 20060101
F01D017/16 |
Foreign Application Data
Date |
Code |
Application Number |
Nov 21, 2011 |
EP |
11189936.5 |
Claims
1. Stator stage (100) for a gas turbine, the stator stage (100)
comprising a centre section (101) comprising a centre hole in which
a turbine shaft of the gas turbine is insertable, wherein a groove
(102) is formed between a first rim (103) and a second rim (104) of
a radially outer edge of the centre section (101), and wherein the
groove (102), the first rim (103) and the second rim (104) run
along a circumferential direction (131), a vane segment (110) which
is mountable to a housing (200) of the gas turbine, wherein the
vane segment (110) comprises a radially inner shroud (111) from
which a protrusion (112) protrudes radially inwards, wherein the
protrusion (112) is inserted into the groove (102), and an
adjusting pin (120), wherein the adjusting pin (120) comprises a
first end section (121), a second end section (122) and an
eccentric section (123) formed between the first end section (121)
and the second end section (122), wherein the eccentric section
(123) is eccentric with respect to a symmetry axis of both the
first end section (121) and the second end section (122), and
wherein the first end section (121) is coupled to the first rim
(103), the second end section (122) is coupled to the second rim
(104) and the eccentric section (123) is coupled to the protrusion
(112) such that by pivoting the adjusting pin (120) a relative
position between the vane segment (110) and the centre section
(101) is adjustable.
2. Stator stage (100) according to claim 1, wherein the protrusion
(112) comprises a bore hole in which the adjusting pin (120) is
insertable in such a way that the vane segment (110) is coupled to
the eccentric section (123) of the adjusting pin (120).
3. Stator stage (100) according to claim 1, wherein the protrusion
(112) comprises a slot (113) in which the adjusting pin (120) is
insertable in such a way that the vane segment (110) is coupled to
the eccentric section (123) of the adjusting pin (120).
4. Stator stage (100) according to claim 1, wherein the first rim
(103) and/or the second rim (104) comprise a further slot in which
the adjusting pin (120) is insertable in such a way that the
respective first end section (121) and/or the respective second end
section (122) is coupled to the respective first rim (103) and/or
the respective second rim (104) of the centre section (101).
5. Stator stage (100) according to claim 1, wherein the first rim
(103) and/or the second rim (104) comprise a through hole (104;
105) in which the adjusting pin (120) is insertable in such a way
that the respective first end section (121) and/or the respective
second end section (122) is coupled to the respective first rim
(103) and/or the respective second rim (104) of the centre section
(101).
6. Stator stage (100) according to claim 5, wherein the first end
section (121) and/or the second end section (122) form a press fit
connection with the respective through hole (104; 105) of the
respective first rim (103) and/or the respective second rim
(104).
7. Stator stage (100) according to claim 1, wherein the first end
section (121) and/or the second end section (122) comprise a
coupling section, in particular a screw slot (401), for coupling an
adjusting tool to the adjusting pin (120).
8. Stator stage (100) according to claim 1, further comprising a
safety element, in particular a split pin (501), for securing the
adjusting pin (120) against unintentional readjusting, wherein the
first end section (121) and/or the second end section (122)
comprise a through hole (301) into which the safety element is
insertable.
9. Stator stage (100) according to claim 1, further comprising a
further adjusting pin (620), wherein a further protrusion (112)
protrudes radially inwards from the inner shroud (111), wherein the
further protrusion (112) is spaced along the circumferential
direction (131) from the protrusion (112), wherein the further
protrusion (112) is inserted into the groove (102), wherein the
further adjusting pin (620) comprises a further first end section
(121), a further second end section (122) and a further eccentric
section (123) formed between the first end section (121) and the
second end section (122), wherein the further eccentric section
(123) is eccentric with respect to a further symmetry axis of both,
the further first end section (121) and the further second end
section (122), and wherein the further first end section (121) is
coupled to the first rim (103), the further second end section
(122) is coupled to the second rim (104) and the further eccentric
section (123) is coupled to the further protrusion (112) such that
by pivoting the further adjusting pin (620) a relative position
between the vane segment (110) and the centre section (101) is
adjustable.
10. Stator stage (100) according to claim 9, further comprising a
plurality of further adjusting pins (620) wherein a plurality of
further protrusions (112) protrudes radially inwards from the inner
shroud (111), wherein the further protrusions (112) are spaced from
each other along the circumferential direction (131), wherein to
each of the plurality of further protrusions (112) a respective one
of the plurality of adjusting pins (120) is coupleable.
11. Method of adjusting a vane segment (110) of a stator stage
(100) for a gas turbine with respect to a centre section (101) of
the stator stage (100), the method comprising inserting a
protrusion (112) of the vane segment (110) into a groove (102) of
the centre section (101), wherein the centre section (101)
comprises a centre hole in which a turbine shaft of the gas turbine
is insertable, wherein the groove (102) is formed between a first
rim (103) and a second rim (104) of a radially outer edge of the
centre section (101), and wherein the groove (102), the first rim
(103) and the second rim (104) run along a circumferential
direction (131), wherein the vane segment (110) is mountable to a
housing (200) of the turbine, wherein the vane segment (110)
comprises a radially inner shroud (111) from which the protrusion
(112) protrudes radially inwards, and adjusting a relative position
between the vane segment (110) and the centre section (101) by
pivoting an adjusting pin (120), wherein the adjusting pin (120)
comprises a first end section (121), a second end section (122) and
an eccentric section (123) formed between the first end section
(121) and the second end section (122), wherein the eccentric
section (123) is eccentric with respect to a symmetry axis of both,
the first end section (121) and the second end section (122), and
wherein the first end section (121) is coupled to the first rim
(103), the second end section (122) is coupled to the second rim
(104) and the eccentric section (123) is coupled to the protrusion
(112).
12. Method according to claim 11, wherein the method further
comprises, at first, coupling the first end section (121) of the
adjusting pin (120) to the first rim (103) and the second end
section (122) of the adjusting pin (120) to the second rim (104),
subsequently inserting the protrusion (112) of the vane segment
(110) into the groove (102) of the centre section (101), and
further subsequently adjusting the relative position between the
vane segment (110) and the centre section (101) by pivoting the
adjusting pin (120).
Description
FIELD OF INVENTION
[0001] The present invention relates to a stator stage for a gas
turbine and to a method of adjusting a vane segment of a stator
stage for a gas turbine with respect to a centre section of the
stator stage.
ART BACKGROUND
[0002] A gas turbine comprises stator stages and rotor stages. The
stator stages are located adjacent to rotor stages. In order to
provide a proper sealing of the stator stage between a high
pressure side and a low pressure side which are divided by the
stator stage, the central section, in particular the static
diaphragm, of the stator stage should accurately be located
relative to the rotating components, i.e. the turbine shaft and the
adjacent rotor stages. Moreover, the supporting elements of the
central section should also allow a relative radial expansion while
maintaining an accurate circumferential location. Furthermore, a
proper balancing of the axial loads caused by the pressure
differential across the stator stage should be achieved.
[0003] The central section of a stator stage may be adjusted by key
blocks and dowels that are drilled and fixed to the stator stage
assembly. First of all, the central section is aligned to a vane
section of a stator stage and after aligning a through hole is
drilled through key blocks at the overlapping portions of the
central section and the vane section. Next, a dowel is fixed into
the through hole in order to fix the relative position between the
central section and the vane section.
[0004] U.S. Pat. No. 3,647,311 discloses a turbine interstage seal
assembly. In order to adjust welded segments of a vane section an
eccentric bushing is fixed to a radial slot, wherein a cylindrical
bold may be inserted in the eccentric bushing for adjusting the
welded segments.
[0005] U.S. Pat. No. 3,529,904 discloses a diaphragm sealed
structure. A sealed support arrangement for a bladed diaphragm of a
gas turbine comprises a seal housing ring which is supported from
diaphragm segments by radially movable keys for permitting a
relative radial motion between the diaphragm segments and the seal
assembly while maintaining the seal concentric with a shaft of the
gas turbine. Centering of the seal housing ring is accomplished by
utilizing integral guided keys and pins together with an adjustable
eccentric bushing.
[0006] U.S. Pat. No. 4,863,342 discloses a gas turbine with a fixed
guide vane ring and a sealing ring which cooperates with a sealing
member of a turbine rotor. The sealing ring is connected to the
guide vane ring through a number of links which are suitable
orientated in a substantially tangential direction. By the
attachment of the sealing ring with link means, a centering of the
sealing ring relative to the rotor is achieved, in particular if
the guide vane ring expands relative to the sealing ring.
[0007] U.S. Pat. No. 4,890,978 discloses a method and an apparatus
for a vane segment support and alignment in a combustion turbine. A
vane segment alignment device comprises a rotatable eccentric
bushing and a pin which is inserted into a slot of the vane
segment. The eccentric bushing further comprises a cover plate
which is peen to the cover plate thus holding the eccentric bushing
in place against the vane segment but allowing an adjustment of the
vane segments.
[0008] U.S. Pat. No. 5,141,394 discloses an apparatus and a method
for supporting a vane segment in a gas turbine. The vane segments
are mounted to an inner cylinder of the gas turbine. A plate
comprising threaded holes is fixed to the inner cylinder. A
threaded plug having an eccentric hole is threaded into each
threaded hole in the plate. A pin is inserted into the eccentric
hole in the plug.
[0009] U.S. Pat. No. 5,921,749 discloses a vane segment support and
alignment assembly for supporting and aligning a vane segment. A
plate defines an opening for receiving an eccentric pin and a
locking end member for receiving a lock socket member.
[0010] U.S. Pat. No. 5,772,401 discloses a diaphragm construction
for a turbo machinery, wherein a particular method of manufacturing
a split diaphragm for use in turbo machinery is described.
SUMMARY OF THE INVENTION
[0011] It may be an objective of the present invention to provide a
more effective adjustment of a diaphragm to a stator stage with
respect to a rotary axis of the gas turbine.
[0012] This objective is solved by a stator stage for a gas turbine
and by a method of adjusting a vane segment of a stator stage for a
gas turbine with respect to a centre section of the stator stage
according to the independent claims.
[0013] According to a first aspect of the present invention a
stator stage for a gas turbine is presented. The stator stage
comprises a centre section, a vane segment and at least an
adjusting pin. The centre section comprises a center hole in which
a rotary axis of the gas turbine is inserted. A groove is formed
between a first rim and a second rim of a radial outer edge of the
centre section. The groove, the first rim and the second rim run
along the circumferential direction.
[0014] The vane segment is mountable to a housing of the turbine.
The vane segment comprises a radially inner shroud from which a
protrusion protrudes radially inwards. The protrusion is inserted
into the groove.
[0015] The adjusting pin comprises a first end section, a second
end section and an eccentric section formed between the first end
section and the second end section. The eccentric section is
eccentric with respect to a symmetry line of both, the first end
section and the second end section. The first end section is
coupled to the first rim, the second end section is coupled to the
second rim and the eccentric section is coupled to the protrusion
such that a relative position between the vane segment and the
centre section is adjustable by pivoting the adjusting pin.
[0016] According to a further aspect, the method of adjusting a
vane segment of a stator stage for a gas turbine with respect to a
centre section of the stator stage is presented. According to the
method, a protrusion of the vane segment is inserted into a groove
of the centre section. The centre section comprises a center hole
in which a rotary shaft of the gas turbine is insertable. The
groove is formed between a first rim and a second rim of a radially
outer edge of the centre section. The groove, the first rim and the
second rim run along a circumferential direction, wherein the vane
segment is mountable to a housing of the turbine. The vane segment
comprises a radially inner shroud from which the protrusion
protrudes radially inwards.
[0017] Furthermore, according to the method, a relative position
between the vane segment and the centre section is adjusted by
pivoting an adjusting pin. The adjusting pin comprises a first end
section, a second end section and an eccentric section formed
between the first end section and the second end section. The
eccentric section is eccentric with respect to a symmetry axis of
both, the first end section and the second end section. The first
end section is coupled to the first rim, the second end section is
coupled to the second rim and the eccentric section is coupled to
the protrusion.
[0018] In the following, an axial direction describes a direction
which is parallel to a rotary axis of the turbine shaft of the gas
turbine. A radial direction describes a direction which runs
through a center point of the rotary axis of the turbine shaft and
which is perpendicular to the rotary axis. The circumferential
direction describes the direction running around the rotary axis,
wherein at a crossing of the circumferential direction with the
radial direction, the circumferential direction is perpendicular to
the radial direction.
[0019] The stator stage is generally located at a downstream
location of a rotary stage of the gas turbine. The rotor stage
comprises rotating blades, wherein the stator stage comprises
vanes, which guides a fluid streaming along a main flow direction
of the gas turbine. The vane segment may comprise one, two or a
plurality of vanes. Along the circumferential direction, a
plurality of sub vane sections may be attached adjacent to each
other and form together the annular vane segment of the stator
stage.
[0020] The centre section (diaphragm section), the turbine shaft of
the gas turbine and the inner shroud of the vane segment separate
an upstream region of the gas turbine (comprising a higher
pressure) from a downstream region of the gas turbine (comprising a
lower pressure). Alternatively, the centre section (diaphragm
section), the turbine shaft of the gas turbine and the inner shroud
of the vane segment separate an upstream region of a compressor
section of the gas turbine (comprising a lower pressure) from a
downstream region of the compressor section of the gas turbine
(comprising a higher pressure). The centre section comprises the
center hole. The turbine shaft of the gas turbine is insertable
through the center hole. The radially inner surface of the center
hole is either in slidable contact with the turbine shaft or
comprises sealing elements which seals a gap between the radially
inner surface and the turbine shaft for sealing purposes. In order
to provide a proper sealing, the centre section has to be adjusted
properly with respect to the turbine shaft. Preferably, the centre
section is aligned with respect to the turbine shaft in such a way
that a center point of the center hole is located onto the rotary
axis of the turbine shaft. In other words, the centre section is
adjusted preferably in such a way that the centre section is
concentric with the rotary axis of the turbine shaft. The centre
section is supported and fixed to the vane segment which is again
fixed to the housing of the gas turbine.
[0021] Specifically, the centre section is supported and fixed to
the vane segment by the adjusting pin.
[0022] Hence, the relative position between the turbine shaft and
the centre section is adjusted by adjusting the relative position
between the centre section and the vane segment by the adjusting
pin.
[0023] Summarizing, the concentricity of the centre section with
respect to the rotary axis of the turbine shaft is achievable
and/or a relative radial and tangential/circumferential position of
the centre section is adjustable by pivoting the adjusting pin,
because the end sections of the adjusting pin are coupled to the
centre section and the eccentric section of the adjusting pin is
coupled to the protrusion of the vane segment. The centre section
may thus be moved relative to the vane segment along a radial
and/or circumferential direction by adjusting the adjusting
pin.
[0024] Respective holes or slots are formed in the centre section
and/or in the protrusion such that a respective supporting force is
transferrable by the adjusting pin between the centre section and
the vane segment. For example, the protrusion of the vane segment
comprises a slot and thus rests onto the eccentric section of the
adjusting pin. Hence, a plurality of adjusting pins which are
located spaced apart along the circumferential direction and onto
which respective protrusions of the vane segment(s) may support and
hold the centre section and vice versa. The adjusting pin mounts in
other words the centre section to the vane segment(s). The centre
section is supported specifically by a plurality of adjusting
pins.
[0025] The vane segment is mountable in particular with the
radially outer edge to the housing of the gas turbine. At the
radially inner end of the vane segment, the inner shroud is formed
which runs in particular along the circumferential direction. The
protrusion, such as a plug or tenon, extends radially inwards along
the radial direction from the inner shroud.
[0026] At a radially outer end of the centre section the radially
outer edge is formed which comprises a first rim and a second rim
between of which a groove is formed. Between the first rim and the
second rim, the protrusion of the vane segment is fited.
[0027] The adjusting pin comprises the first end section and the
second end section, wherein the first and second end sections may
comprise a larger diameter than the eccentric section. The first
end section and the second end section comprise a first symmetry
axis, wherein the eccentric section comprises a second symmetry
axis. The first symmetry axis and the second symmetry axis are
substantially parallel, wherein the first symmetry axis and the
second symmetry axis are spaced about from each other by a
predefined distance i.e. along the radial direction.
[0028] Hence, by rotating the adjusting pin, the vane segment which
is supported by the eccentric section, is relocated with respect to
the centre section at which the first end section and the second
end section are supported. By supporting the first end section and
the second end section within both, the first rim and the second
rim of the centre segment, a very robust adjusting pin is provided,
e.g. in comparison to an eccentric pin which comprises a free end
along its rotational axis. Hence, an adjustable and robust
connection between the centre section and the vane segment is
achieved. Hence, due to the robust adjusting pin, further
supporting elements, such as keys inside the groove for supporting
the adjusting pin, may be obsolete. Hence, an easier assembly and a
proper adjusting of a centre section with respect to the vane
segment is achieved.
[0029] Furthermore, the use of the above described eccentric
adjusting pin allows an adjustment of the centre section along its
radial and circumferential location i.e. its radial and
circumferential direction, if the centre section is already mounted
to the vane segment. For example, in contrary to conventional
approaches, it is not longer necessary to compensate manufacturing
tolerances by machining the components when the centre section is
already mounted to the vane segment. Hence, there is no need to
clean the assembled stator stage in order to remove debris.
Additionally, this also allows assembling and installing the stator
stage inside a clean room environment. Moreover, because the need
of key blocks inside the groove is obsolete, the amount of parts is
also reduced and thus the overall weight and the overall costs.
[0030] According to a further aspect of the present invention, the
protrusion comprises a further through hole in which the adjusting
pin is insertable in such a way that the vane segment rests onto
the eccentric section of the adjusting pin.
[0031] According to a further exemplary embodiment, the protrusion
comprises a slot in which the adjusting pin is insertable in such a
way that the vane segment rests onto the eccentric section of the
adjusting pin. The through hole or the slot may be formed with
respect to the eccentric section in such a way that e.g. a form
fitting, in particular a press fitting or a closure fitting
connection, may be provided. Alternatively, the through hole or the
slots may be formed with respect to the eccentric section such that
a play is provided. Hence, manufacturing tolerances may be
cleared.
[0032] According to a further exemplary embodiment, the first rim
and/or the second rim comprise(s) a further slot in which the
adjusting pin is insertable in such a way that the respective first
end section and/or the respective second end section rests onto the
respective first rim and/or the respective second rim of the centre
section.
[0033] According to a further exemplary embodiment, the first rim
and/or the second rim comprise(s) a through hole in which the
adjusting pin is insertable in such a way that the respective first
end section and/or the respective second end section rest(s) onto
the respective first rim and/or the respective second rim of the
centre section.
[0034] In particular, according to a further exemplary embodiment,
the first end section and/or the second end section form(s) a press
fit connection or transition fit connection with the respective
through hole of the respective first rim and/or the respective
second rim.
[0035] Hence, by providing a press fit connection of the respective
end sections of the adjusting pin with the respective through holes
or slots of the respective rims, a fixation and a locking of the
adjusting pin against e.g. unintended readjusting is provided.
[0036] Alternatively, a closure fit of the respective end sections
of the adjusting pin with the respective through hole or slots of
the respective rims may be provided, so that manufacturing
tolerances of the vane segment and/or the centre section may be
cleared.
[0037] In particular, the bore hole and/or the further slot of the
protrusion and/or the slot or the through hole of the first and
second rim may comprise an extending direction of its symmetry
lines which is generally parallel with the axial direction.
[0038] Additionally or alternatively, the first end section and/or
the second end section may form at the respective first and second
rim a screw connection.
[0039] For example, the respective through hole may comprise a
thread and the first and/or second end section may comprise an
external male screw thread which fits into the thread of the
respective through hole. In a further exemplary embodiment, the
bore hole of the protrusion may comprise an inner thread and the
eccentric section may comprise a screw thread which may fit into
the thread of the bore hole.
[0040] According to a further exemplary embodiment, the first end
section and/or the second end section comprises a coupling section,
in particular a screw slot, for coupling an adjusting tool to the
adjusting pin. The coupling section may comprise a screw slot, a
cross slot or a square drive, for example. The coupling section may
preferably be formed at a front face of the adjusting pin, wherein
the front face runs along a plane which normal is parallel to a
rotating axis of the adjusting pin.
[0041] The adjusting tool may be for instance a screw driver which
comprises an engaging section that fits into the respective
coupling section. Hence, by screwing and thus pivoting the
adjusting pin, the relative position between the centre section and
the vane segment is adjusted.
[0042] According to a further exemplary embodiment, the stator
stage comprises a safety element, in particular a safety screw or a
split pin, for securing the adjusting pin against unintentional
adjusting. The first end section and/or the second end section
comprise a through hole into which the safety element is
insertable.
[0043] The safety element is for example a split pin which may be
inserted into a through hole of the respective first end section
and/or second end section. The safety element extends from the
respective first end section and second end section and blocks the
adjusting pin from being pulled off from the centre section. If a
removing of the adjusting pin is intended, the safety element has
to be removed in order to unblock a movement of the adjusting pin
through the through holes or slots of the respective first and
second rim.
[0044] According to a further exemplary embodiment, the stator
stage comprises a further adjusting pin. Furthermore, a further
protrusion protrudes radially inwards from the inner shroud. The
further protrusion is spaced along the circumferential direction
from the protrusion, wherein the further protrusion is inserted
into the groove. The further adjusting pin comprise a further first
end section, a further second end section and a further eccentric
section formed between the first end section and the second end
section. The further eccentric section is eccentrically in respect
to the first end section and the further second end section. The
further first end section is coupled to the first rim, the further
second end section is coupled to the second rim and the further
eccentric section is coupled to the further protrusion such that by
pivoting the further adjusting pin a relative position between the
vane segment and the centre section is adjustable.
[0045] In particular, according to a further exemplary embodiment,
the plurality of further adjusting pins are comprised by a stator
stage. Furthermore, a plurality of further protrusions may protrude
radially inward from the inner shroud, wherein the further
protrusions are spaced from each other along the circumferential
direction. A respective one of the plurality of adjusting pins is
coupled to a respective one of the plurality of further
protrusions.
[0046] By the above described exemplary embodiment, a stator stage
is presented by which the relative position between the centre
section and the vane segment is adjustable by the plurality of
adjusting pins that are distributed along the circumferential
direction.
[0047] In particular, each adjusting pin defines a radial line
which runs between the adjusting pin and the center point of the
turbine shaft. Such a radial line between an adjusting pin and the
centre point comprises for example an angle to an adjacent radial
line between an adjacent adjusting pin and the centre point of
approximately 90.degree. degree. Alternatively, each radial line
may comprise an angle to an adjacent radial line for example of
45.degree., 30.degree. or 60.degree. degree. With other words,
along an annual run of the groove of the central section 2, 4, 6,
8, 10, 12 or more through holes in the respective rims and
respective protrusions formed at the inner shroud are provided,
wherein respectively fixable adjusting pins may be attached.
[0048] According to a further exemplary embodiment of the method,
as a first step the first end section of the adjusting pin and the
second end section of the adjusting pin are coupled to the
respective first rim and the respective second rim. Subsequently,
the protrusion of the vane segment (e.g. which comprises a
respective slot) is coupled to and/or inserted into the groove of
the centre section. Further subsequently, the relative position
between the vane segment and the centre section is adjusted by
pivoting the adjusting pin. Hence, only a few steps are necessary
to mount and adjust a centre section to a vane section, or vice
versa. Hence, an efficient mounting and adjusting method for
assembling a turbine may be achieved.
[0049] Summarizing, by the present invention, the centre section is
supported and adjusted by e.g. an array of adjusting pins, which
couples the vane segment with the centre section. For example, at
least three adjusting pins are mountable at annular spaced
locations to the respective first and second rims of the central
section and to the respective protrusions in order to control the
required degrees of freedom. Additionally, more than three
adjusting pins may be applied, for example for structural purposes.
Additionally, a plurality of concentric pins may be mounted to the
respective rims of the centre section and respective protrusions of
the vane segment between the adjusting pins to improve the
structural stability of the connection between the centre section
and the vane segment.
[0050] It has to be noted that embodiments of the invention have
been described with reference to different subject matters. In
particular, some embodiments have been described with reference to
apparatus type claims whereas other embodiments have been described
with reference to method type claims. However, a person skilled in
the art will gather from the above and the following description
that, unless otherwise notified, in addition to any combination of
features belonging to one type of subject matter also any
combination between features relating to different subject matters,
in particular between features of the apparatus type claims and
features of the method type claims is considered as to be disclosed
with this application.
BRIEF DESCRIPTION OF THE DRAWINGS
[0051] The aspects defined above and further aspects of the present
invention are apparent from the examples of embodiment to be
described hereinafter and are explained with reference to the
examples of embodiment. The invention will be described in more
detail hereinafter with reference to examples of embodiment but to
which the invention is not limited.
[0052] FIG. 1 shows a schematical view of a stator stage for a gas
turbine and of a method of adjusting a vane segment to a centre
section according to an exemplary embodiment of the present
invention;
[0053] FIG. 2 shows a schematical view of the stator stage
according to an exemplary embodiment of the present invention;
[0054] FIG. 3 shows a schematical view of the adjusting pin
according to an exemplary embodiment of the present invention;
[0055] FIG. 4 shows a schematical view of the adjusting pin
comprising a coupling section according to an exemplary embodiment
of the present invention;
[0056] FIG. 5 shows a schematical view of a stator stage comprising
the adjusting pin which is secured by a split pin, according to an
exemplary embodiment of the present invention; and
[0057] FIG. 6 shows a front view of the stator stage according to
an exemplary embodiment of the present invention.
DETAILED DESCRIPTION
[0058] The illustrations in the drawings are schematical. It is
noted that in different figures, similar or identical elements are
provided with the same reference signs.
[0059] FIG. 1 shows a stator stage 100 for a gas turbine. The
stator stage 100 comprises a centre section 101, a vane segment 110
and an adjusting pin 120.
[0060] The centre section 101 comprises a center hole in which a
turbine shaft 601 (shown in FIG. 6) of the gas turbine is
insertable. A groove 102 is formed between the first rim 103 and
the second rim 104 of a radially outer edge of the centre section
101. The groove 102, the first rim 103 and the second rim 104 run
along a circumferential direction 131.
[0061] The vane segment 110 is mountable to a housing 200 (shown in
FIG. 2) of the gas turbine. The vane segment 110 comprises a
radially inner shroud 111--or an inner platform of the vane segment
110--from which a protrusion 112 protrudes radially inwards. The
protrusion 112 is inserted into the groove 102.
[0062] The adjusting pin 120 comprises a first end section 121, a
second end section 122 and an eccentric section 123 which run(s)
between the first end section 121 and the second end section 122.
The eccentric section 123 is eccentric with respect to the first
end section 121 and the second end section 122.
[0063] The first end section 121 is coupled to the first rim 103,
the second end section 122 is coupled to the second rim 104 and the
eccentric section 123 is coupled to the protrusion 112, such that
the relative position between the vane segment 110 and the centre
section 101 is adjustable by pivoting the adjusting pin 120.
[0064] The inner shroud 111 may be a radially inner band or ground
plate which runs along the circumferential direction 131, wherein
from the inner shroud 111 the protrusion 112 of the vane segment
110 extends along a radially inwardly directed radial direction
132.
[0065] As shown in FIG. 1, the protrusion 112 comprises a slot 113,
wherein the slot is formed through the protrusion 112 along the
axial direction 130 of the turbine shaft.
[0066] The adjusting pin 120 is fixed with a first end section 121
to a first through hole 105 of the first rim 103 and with a second
end section 122 to a second through hole 106 of the second rim 104.
The first through hole 105 and the second through hole 106 are
concentrically along the axial direction 130. The center axis
(symmetry axis) of the eccentric section 123 is parallel but spaced
from a centre axis (symmetry axis) of the first end section 121 and
the second end section 122. The first end section 121 and the
second end section 122 are fixed to the respective through holes
105, 106 e.g. by a press fit connection or a clearance fit
connection.
[0067] Furthermore as shown in FIG. 1, the method of adjusting the
vane segment 110 of the stator stage 100 to the centre section 101
of the stator stage 100 is shown. As indicated by the bold arrows,
first of all the first end section 121 of the adjusting pin 120 is
coupled to the first rim 103 and the second end section 122 of the
adjusting pin 120 is coupled to the second rim 104.
[0068] Subsequently, the vane segment 110 is inserted with its
protrusion 112 into the groove 102 of the centre section 101.
Hence, the centre section 101 is supported by the adjusting pin
120.
[0069] Finally, the relative position between the vane segment 110
and the centre section 101 is adjusted by pivoting/rotating the
adjusting pin 120.
[0070] FIG. 2 shows the stator stage 100. As shown in FIG. 2, the
vane segment 110 is fixed to the housing 200 of the gas turbine.
The centre section 101 is fixed to the vane segment 110 by the
adjusting pin 120. Besides the adjusting pin 120 further
concentrical pins may be additionally added to the stator stage 100
in order to restrain the support of the centre section 101 to the
vane segment 110.
[0071] FIG. 3 shows a more detailed view of the adjusting pin 120.
The adjusting pin 120 comprises the first end section 121, the
second end section 122 and the eccentric section 123. As shown in
FIG. 3, the first end section 121 and the second end section 122
comprise a common center axis 302 (symmetry axis). The eccentric
section 123 comprises a further center axis 303 (symmetry axis)
which is parallel to the center axis 302 of the first and second
end sections 121, 122, wherein the further center axis 303 is
spaced by a predefined distance e from the center axis 302. Hence,
because the centre section 101 is coupled to the end sections 121,
122 and the vane segment 110 is coupled to the eccentric section
123, a pivoting of the adjusting pin 120 adjusts the relative
position between the centre section 101 and the vane segment
110.
[0072] Moreover, as shown in FIG. 3, the adjusting pin 120 is
formed in a dumbbell shape, i.e. the diameters of the first end
section 121 and the second end section 122 are larger than the
diameter of the eccentric section 123. Furthermore, to the first
end section 121 through holes 301 are formed through which a safety
element, such as a split pin 501 (as shown in FIG. 5) may be
installed in order to safe the adjusting pin 120 against
unintentional adjusting or removing.
[0073] A coupling section, such as a screw slot 401 (as shown in
FIG. 4), may be formed to a front surface 304 of the second end
section 122.
[0074] FIG. 4 shows the coupling section which is formed by a screw
slot 401 inside the front surface 304. An adjusting tool, such as a
screw driver, may be coupled to the screw slot 401 in order to
pivot the adjusting pin 120.
[0075] FIG. 5 shows a further view of the stator stage 100, wherein
the adjusting pin 120 is shown in an assembled and adjusted state.
The adjusting pin 120 is fixed by its first and second end sections
121, 122 to the centre section 101. The vane segment 110 is coupled
to the eccentric section 123 of the adjusting pin 120. In order to
prevent an unintentional adjustment and pivoting of the adjusting
pin 120, a split pin 501 as safety element is inserted into a
further through hole 301 at the first end section 121. Hence, the
adjusting pin 120 is secured from being unintentionally removed
from the stator stage 100. Furthermore, in order to prevent an
unintentionally pivoting of the adjusting pin 120, the split pin
501 is inserted additionally in a further through hole which is
formed into the first rim 103, for example. Hence, a relative
pivoting between the adjusting pin 120 and the centre section 101
and hence with respect to the vane segment 110 is prevented.
[0076] FIG. 6 shows a front view of the stator stage 100. In
particular, the centre hole of the centre section 101 is shown in
FIG. 6, through which centre hole the turbine shaft 601 is guided.
The turbine shaft 601 defines the rotary axis 130. The centre
section 101 and/or the vane segment 110 may be separated into two
half sections or into four quarter sections, for example. The vane
segment 110 may comprise an annular shape and runs along the
circumferential direction 131 all around the centre section 101.
Furthermore, the vane segment 110 may be built by a plurality of
sub vane segments which forms together the annular vane segment 110
as shown in FIG. 6.
[0077] Generally as shown in FIG. 6, the stator stage 100 may be
formed of an upper half and a lower half. Each half comprises three
adjusting pins 120, 601. By applying at least three adjusting pins
120, 601 to each half of the stator segment 100, each half is
adjustable along the required degrees of freedom (as indicated by
the arrows). For example each half of the stator stage 100 may be
adjusted along e.g. the radial direction 132 and the
circumferential direction 131, i.e. along the vertical and a
horizontal direction as indicated by the arrows in FIG. 6.
[0078] After adjusting the relative position of the centre section
101 with respect to the vane segment 110, a plurality of
concentrical pins 602 may be attached in order to fix and support
the centre section 101 to the vane segment 110.
[0079] It should be noted that the term "comprising" does not
exclude other elements or steps and "a" or "an" does not exclude a
plurality. Also elements described in association with different
embodiments may be combined. It should also be noted that reference
signs in the claims should not be construed as limiting the scope
of the claims.
* * * * *