Description
GUIDE VANE SYSTEM FOR A TURBOMACHINE HAVING SEGMENTED GUIDE VANE
CARRIERS
The invention refers to a turbine stator blade carrier,
especially for a stationary gas turbine.
Gas turbines are used in many fields for driving generators or
driven machines. In this case, the energy content of a fuel is
used for producing a rotational movement of a turbine shaft. To
this end, the fuel is combusted in a combustion chamber, wherein
compressed air is supplied from an air compressor. The
operating medium, which is produced in the combustion chamber as
a result of combustion of the fuel, is directed in this case
under high pressure and under high temperature via a turbine
unit, which is connected downstream to the combustion chamber,
where it is expanded, performing work.
For producing the rotational movement of the turbine shaft, in
this case a number of rotor blades, which are customarily
assembled into blade groups or blade rows, are arranged on this
and drive the turbine shaft via an impulse transfer from the
operating medium. For flow guiding of the operating medium,
moreover, stator blades, which are connected to the turbine
casing and assembled to form stator blade rows, are customarily
arranged between adjacent rotor blade rows. These stator blades
are fastened via a blade root on a customarily hollow
cylindrical or hollow conical stator blade carrier and on their
side facing the turbine axis are fastened via a blade tip on an
inner ring which is common to the respective stator blade row.
In the case of stationary gas turbines, this inner ring
frequently consists of an upper and a lower half which are
interconnected via flanges.

In the design of such gas turbines, in addition to the
achievable power, a particularly high efficiency is customarily
a design aim. An increase of the efficiency can basically be
achieved in this case, for thermodynamic reasons,

by an increase of the discharge temperature at which the
operating medium flows out of the combustion chamber and flows
into the turbine unit. In this case, temperatures of about
1200° C to 1500° C are aimed at, and also achieved, for such
gas turbines.
Such high temperatures of the operating medium, however, lie
far above the melting temperature of the component materials
which are used in the discharge region of the combustion
chamber, for example, so that the critical components have to
be intensely cooled and protected with complex coating systems
for ensuring the necessary function of the gas turbine. In
this case, it cannot be excluded occasionally that despite
application of these highly developed and frequently tested
technologies for cooling and coating the blades a premature
exchange of stator blades becomes necessary since the blade
function, as result of partial loss of the coating or closing
off of cooling air holes, for example, is impermissibly
impaired. In the case of large stationary gas turbines, such
an exchange measure can last at best several days, but on
average about two weeks, so that as a result an undesired and
expensive interruption of the operation of the gas turbine or
of a gas and steam turbine power plant, in which the gas
turbine is used, is brought about.
A stator blade ring for a turbomachine is known from US
3,300,180. The stator blade ring comprises a stator blade
carrier which consists of two clamping rings which in each case
are assembled from two 180° large segments. Stator blade
segments are clamped between the two clamping rings, forming a
stator blade ring. In this case, the stator blade segments are
further stabilized on their inner end by means of an inner
ring.

It is disadvantageous, however, that for removal of a stator
blade segment which is to be exchanged the one or both
segment (s) of one of the two clamping rings has or have to be
completely removed. This is associated with increased time
consumption and greater space requirement.
Furthermore, a turbine stator blade carrier, which extends over
the entire axial length of the turbine unit, is known from US
2005/0132707 A1. This is then of a multiply segmented
construction in the circumferential direction.
The invention is therefore based on the object of disclosing a
turbine stator blade carrier, especially for a gas turbine,
which while maintaining particularly high efficiency, also
enables a particularly simple exchange of individual stator
blades and therefore is designed for a particularly short
repair duration.
This object is achieved according to the invention by the
turbine stator blade carrier being designed according to the
features of claim 1.

The invention in this case is based on the consideration that a
curtailed repair duration would be possible as a result of a
particularly simple exchangeability of the stator blades if
their installation and removal could be simplified. At present,
specifically on account of the constructional circumstances in
modern stationary annular combustion chamber machines, the
turbine has to be opened up in order to enable access to its
stator blades. In this case, the stator blades lie within the
stator blade carrier which in the case of stationary gas
turbines consists of an upper and a lower solid cast part, and
therefore also has to be disassembled for exchange of the stator
blades. In order to avoid this opening up and lifting the upper
cast part of the stator blade carrier, the stator blade carrier
should therefore be multiply segmented in at least one section.
By the use of more than two segments in this section, these are
smaller than the remaining segments. As a result, just by
lifting individual segments it is possible to reach the region
which is surrounded by them. In order to also ensure
reachability of the stator blades in the process one segment
should extend in this case over the entire radial extent of the
stator blade carrier and the connection of the respective
segment to the remaining stator blade carrier should be
releasable. Therefore, for a repair or an exchange of an
individual stator blade of the first turbine stage the upper
cast part of the stator blade carrier no longer has to be lifted
but only the connection of the respective segment to the
remaining section of the stator blade carrier and to
circumferentially adjacent segments is released, as a result of
which - since the segment in question extends over the entire
radial extent of the stator blade carrier - a direct reaching of
the radially further inwardly disposed stator blades and their
exchange is possible after removal of the respective segment.
The highest temperatures in the gas turbine exist at the exit of
the combustion chamber. Therefore, the stator blade of the
first turbine stage, i.e. the stator blade which lies closest

to the combustion chamber, is exposed to these extremely high
temperatures and is subjected to the greatest wear.
Accordingly, a premature exchange as a result of damage due to
blockage of the cooling air holes (for example as a result of
cooling air holes oxidizing up on the inside) is particularly to
be expected in the case of this turbine stator blade. In order
to also simplify in particular the exchange of these stator
blades individually, the stator blade carrier should therefore
advantageously be multiply segmented in the section of the
stator blade row which lies closest to a combustion chamber of
the gas turbine. In other words, the inflow-side section of the
turbine stator blade carrier should have more segments than the
remaining section of the turbine stator blade carrier.
In order to achieve a.reachability of all the stator blades of a
stator blade row, provision should be made for such a number of
segments that each segment can be handled by one or, in the
worst case, two fitters. Therefore, in each circumferential
section an exchange of stator blades can be carried out by only
the respective segment radially outside the affected stator
blade being removed. In this case, the accurate geometric design
of the segmentation should be adapted in a practical manner to
the handling of the machine.
In a further advantageous development, the respective connection
between axially adjacent segments is a screwed connection and/or
a tongue-in-groove connection. By screws, a particularly simple
releasable connection of segments to each other and/or to the
remaining stator blade carrier is possible. As a result of the
circular arrangement of the segments around the entire
circumference, however, a hook-in fastening in the style of a
tongue-in-groove connection is also possible, in which the
individual segments are only screwed to each other and only
hooked into the rest of the stator blade carrier. In this way,
a particularly simple removal and installation of the individual
segments is possible.

In order to further simplify the removal of the stator blades
which can now be reached as a result of the segmentation of the
stator blade carrier, the stator blade fixing of a gas turbine
should be provided in a practical manner in such a way that an
uninterrupted removal of any segment lying on the circumference
is ensured so that depending upon the position of the blade which
is to be replaced only the affected, radially further outwardly
disposed segment has to be removed. To this end, in an
advantageous development the stator blade of the respective
stator blade row is releasably connected to one of the segments
of the remaining section. Consequently, after removal of the
affected segment the stator blade can be withdrawn by releasing
the connection to the segment of the section. The segments which
are located in the inflow-side section therefore do not serve for
the fastening of stator blades but only for establishing or
maintaining the integrity of the gas turbine and, if applicable,
for the separation of chambers for cooling air at different
pressures and/or temperatures.
In order to enable a simple removal of the stator blade in a gas
turbine not only on the blade root side but also on the blade tip
side of the respective stator blade, the stator blade of the
respective stator blade row, on its side facing the turbine axis,
is advantageously releasably connected in the radial direction to
an inner ring. Therefore, a radial removal of the stator blade
is possible. This allows a particularly simple exchange as a
result.
A particularly simple exchange of the stator blade is possible by
the fixing of the stator blade on the inner ring being designed
as a simple push-in connection. To this end, the respective
stator blade advantageously includes a tongue which can be pushed
into a groove of the inner ring in the radial direction. As a
result, for exchanging the respective stator blade the blade
root-side connection of the stator blade to the remaining stator
blade carrier can simply be released and the respective stator
blade can simply be withdrawn from the turbine in

the radial direction by releasing the push-in connection. In
this case, as a result of the blade root-side fixing of the
stator blade on the stator blade carrier, adequate security is
also ensured during operation.
In the previous type of construction, the stator blades of a
stator blade row were fixed on the inner ring via a connection
secured with pins so that for disassembly the entire inner ring
had to be removed and the stator blades could then be withdrawn.
With a releasable connection, for example in the. style of a
simple push-in connection of the stator blades to the inner
ring, the inner ring should therefore be fixed to the combustion
chamber hub, i.e. to a component which is connected to the
combustion chamber and therefore to the static part of the gas
turbine. To this end, the inner ring is advantageously
connected to a combustion chamber hub. This can be carried out
by a fixing by welding, clamping, or the like, for example. In
the case of the new construction of a gas turbine, the inner
ring can also be produced directly as a component part of the
combustion chamber hub.
Between the individual stator blades, provision is made both on
the blade root and on the blade tip in the previous type of
construction for grooves in which sealing plates are arranged
between the stator blades in the circumferential direction. If,
however, the stator blades are to be removed individually, the
sealing plates which lie in the grooves of stator blade root and
stator blade tip block the stator blades, however, and can
therefore possibly hinder the removal. Therefore, the fixing of
the sealing plates should be modified in such a way that their
removal is possible and therefore removal of individual stator
blades is simplified. For this purpose, stepped edges, in which
the sealing plate is fixed by means of a clamping element, are
advantageously introduced on the sides of the blade root and/or
blade tip facing the adjacent stator blade in each case. Before
removal of the stator blades, therefore, the clamping element
can be released and the sealing plate can be removed

so that a particularly simple removal of the stator blade is
possible.
In an advantageous development, such a turbine stator blade
carrier is used in a gas turbine. In order to enable a
particularly simple reachability of the stator blade for
exchanging individual stator blades, an outer casing of the gas
turbine in this case advantageously includes a manhole through
which simple access to the segments of the stator blade carrier
for service personnel is possible.
A gas and steam turbine power plant advantageously comprises
such a gas turbine.
The advantages which are achieved with the invention are
especially that as a result of the different segmentation of the
stator blade carrier in the inflow-side section and in at least
one remaining section, those stator blades which are encompassed
by the inflow-side segments and supported by the remaining
section in the process can be released after removing a
respective inflow-side segment from the remaining stator blade
carrier. As a result, a particularly simple exchange of stator
blades of a stator blade row becomes possible since the outer
casing of the turbine and the upper cast half of the turbine
stator blade carrier do not have to be lifted from the rest of
the gas turbine during such an exchange. The fitters who carry
out the exchange of the stator blades can therefore exchange the
stator blades in the gas turbine with the outer casing closed,
which significantly reduces the cost for exchanging the stator
blades and can considerably reduce the necessary downtime of the
gas turbine. Such a simplified exchange especially of the first
stator blade stage directly downstream of the combustion chamber
also enables an increase of the exit temperature in conjunction
with an increase of the efficiency of the gas turbine since as a
result of the simplified exchangeability of the stator blades
less consideration has to be made for their durability. In this
case,

variable exchange concepts are conceivable during operation.
Furthermore, such a construction, as result of the simplified
exchange, enables a comparatively quicker test of new prototypes
of stator blades, for example with new types of coating or new
cooling concepts, in research and development.
An exemplary embodiment of the invention is explained in more
detail with reference to a drawing. In the drawing:
FIG 1 shows a stator blade system, with hook-in fastened
segments, in longitudinal section,
FIG 2 shows a stator blade system, with screwed segments, in
longitudinal section,
FIG 3 shows a cross section through the segments
perpendicularly to the turbine axis,
FIG 4 shows a combustion chamber hub of an annular combustion
chamber,
FIG 5 shows the blade tip-side fixing of the stator blade
according to the prior art,
FIG 6 shows the blade tip-side fixing of the stator blade with
a push-in connection,
FIG 7 shows a combustion chamber hub with the inner ring as a
component part,
FIG 8 shows a cross section through two adjacent stator blades
perpendicularly to the turbine axis with sealing elements
fixed in grooves, according to the prior art,
FIG 9 shows a section through two adjacent stator blades
perpendicularly to the turbine axis with sealing elements
fixed by clamping elements, and

FIG 10 shows a half-section through a gas turbine.
Like components are provided with the same designations in all
the figures.
FIG 1 shows a turbine stator blade carrier 1 - also just called
a stator blade carrier - in detail in the region of the first
two stator blade rows which follow a combustion chamber 2 in the
hot gas direction. The view shows in this case a half-section
through the upper half 4 of a conically formed stator blade
carrier and also the stator blades 6 of the first turbine stage
and stator blades 8 of the second turbine stage which are
arranged in each case at the apex of the stator blade ring.
The stator blades 6, 8 in this case each comprise a blade root
10, 12 and also a blade tip 14, 16, via which their fastening on
the remaining components is carried out. The stator blades 6, 8
of the first and second turbine stage in this case are fastened
by their blade roots 10, 12 on the stator blade carrier 1 and by
their respective blade tips 14, 16 are fixed on inner rings 18,
20. In this case, both the inner ring 20 and the stator blade
carrier 1 comprise a large number of cooling systems 22 which
ensure a cooling air feed to the stator blade carrier 1, to the
stator blades 6, 8 and to the inner ring 22 in order to
adequately cool these components on account of the high hot gas
temperatures.
The highest temperatures occur in this case at the exit of the
combustion chamber 2 which is why the stator blades 6 of the
first stator blade row are exposed to the highest temperatures.
As a result, despite all the cooling measures, damage to the
stator blades 6, and a premature exchange of these stator blades
6 which is necessary as a result, cannot be excluded. In order
to now enable a particularly simple exchange of the stator
blades 6, the stator blade carrier 1 is multiply segmented in
the region of the first stator blade row.

The stator blade carrier 1, in an inflow-side section 23,
comprises a number (in this case 12 pieces, cf. FIG 3) of
segments 24, and in a remaining section 25 comprises a stator
blade carrier 1 which is segmented only into two halves 26. All
the segments 24, 26 are releasably interconnected. In FIG 1,
the connection between the segments 24 of the inflow-side
section 23 and the segments 26 of the remaining section 25 is
realized in this case via a hook-in fastening by means of
grooves 28 and tongues 30 which are introduced into the segments
24 and the segments 26. An exactly identical connection of the
segments 24 to the combustion chamber wall 32 is provided in
order to separate a radially further outwardly lying chamber
from the stator blades 6 and to enable the connection between
combustion chamber 2 and remaining segments 26 which is
necessary for the stability and rigidity of the gas turbine.
An upper and a lower half of a stator blade carrier, which is
annular in cross section, as is already known in the- case of
statically installed gas turbines, is understood as the
remaining stator blade carrier. In this case, two segments 26
are provided in the remaining section 25 of the stator blade
carrier 1. In this respect, more segments 24 are always
provided in sections for the circumference than remaining
segments 26.
As a result of the hook-in fastening, the connection of the
respective segments 24 to the remaining segment 2 6 can be
released and the segment 24 can be withdrawn in the radial
direction. Therefore, the stator blades 6 of the first turbine
stage can be reached from the outside without complete opening
up of the entire turbine. The stator blade 6 of the first
turbine stage is releasably fastened via the blade root 10 on
the remaining segment 26 by means of a fastening device 34.
After removal of the segment 24, this connection can be released
and the stator blade 6 can be withdrawn in the radial direction.
The blade tip 14 of the stator blade 6 of the first turbine
stage in this case includes a tongue 36 which is pushed in a

groove 38 of the inner ring 18. The fastening on the inner
ring 18 is therefore designed simply as a push-in connection

so that the stator blade 6 can be simply withdrawn outwards
after releasing the fastening device 34.
FIG 2 also shows the stator blade system 1 as in FIG 1, but - in
this case the releasable connection of the segment 24 on the
remaining segment 26 is realized via a screw 40. The hook-in
fastening of the segment 24 to the combustion chamber wall 32
via grooves 28 and tongues 30 is unaltered in this case. Such
a connection with a screw 40 may be desirable depending upon
rigidity requirements or geometric requirements in the stator
blade carrier 1.
FIG 3 now shows a section, lying perpendicularly to the turbine
axis 1, through the stator blade carrier 1 at the level of the
segments 24. In the depicted example, provision is made for
altogether twelve segments 24 which via flanges 52 are
connected by a screwed connection, for example. As a result, a
secure retention of the multiply segmented section 23 of the
stator blade carrier 1 is ensured, even if the individual
segments 24 are connected only via a hook-in fastening to the
remaining segment 26, as shown in FIG 1. The segmentation can
also be created in another way, however, and can be
correspondingly adapted to the handling of the machine.
FIG 4 shows the combustion chamber hub 54 of a gas turbine.
This includes a groove 56 into which is inserted the inner ring
18 which is shown in FIGS 1 and 2. Furthermore, provision is
made for a groove 58 in which a sealing plate is provided for
sealing the gap between blade root 14 of the stator blade 6 of
the first turbine stage and the combustion chamber hub 54.
FIG 5 shows a known fastening of the stator blade root 14 on
the combustion chamber hub 54 of the gas turbine in detail. In
this case, the blade root 14 includes a tongue 36 which is
inserted into a groove 38 of the inner ring 18. The stator
blade 6 of the first turbine stage is fixed there by means of a

pin 60. The inner ring 18 is then inserted into the groove 56
of the combustion chamber hub 54. At the same time, the blade
root 14 includes

a groove 62 for accommodating a sealing plate 64 which also
lies in the groove 58 of the combustion chamber hub 54.
Since the pin 60 extends parallel to the turbine axis, a
complete removal of the inner ring 18 has been necessary up to
now for removal of the stator blade 6 of the first turbine
stage. Only after removal of the inner ring can the pin 60 be
removed and the stator blade 6 withdrawn. Therefore, the
connection of the stator blade 6 to the combustion chamber hub
54 is now realized as shown in FIG 6:
The tongue 36 of the blade root 14 is now no longer connected
via a pin to the inner ring 18 in its groove 38 but is only
pushed onto the inner ring 18. Instead, the inner ring 18 is
fastened on the combustion chamber hub 54 by means of a pin 66
or a screw. As a result, the stator blades 6 can also be
removed individually without disassembling the inner ring 18.
A secure retention of the stator blades 6 is still ensured in
this case via the fastening device 34, as shown in FIGS 1 and
2.
In such an embodiment, it is also possible to produce the inner
ring 18 directly as a component part of the combustion chamber
hub 54. As a result, separate parts are no longer necessary.
Such a development is shown in FIG 7.
FIG 8 shows a section perpendicularly to the turbine axis
through two adjacent stator blades 6 of the first turbine
stage, as customary according to the prior art. In this case,
grooves 68 are introduced into the blade roots 10 and blade
tips 14 on the face pointing to the adjacent stator blade 6 in
each case, into which grooves are inserted sealing plates 70
which close off the gaps between the blade roots 10 and blade
tips 14. These sealing plates 70, however, can be a hindrance
during a radial withdrawal of individual stator blades 6.

Consequently, a plurality of stator blades 6 are first to be
unlocked and shifted in the circumferential direction so that
one stator

blade 6 disengages from the sealing plates 70 and can be
removed in the radial direction.
In order to avoid this, as shown in FIG 9, the grooves 68 are
replaced by stepped edges 72. The sealing plates 70 are now
inserted into the stepped edges 72 and secured there by means
of clamping elements 74. For removal of an individual stator
blade 6, the clamping element 74 can now be released first and
the sealing element 70 can be removed. The stator blade 6 can
then be withdrawn in the radial direction. Therefore, an
exchange of individual stator blades is made significantly
easier.
Such a stator blade system 1 which is described here is
advantageously used in a gas turbine 101.
A gas turbine 101, as shown in FIG 10, has a compressor 102 for
combustion air, a combustion chamber 2 and also a turbine unit
106 for driving the compressor 102 and for driving a generator
or a driven machine, which is not shown. To this end, the
turbine unit 106 and the compressor 102 are arranged on a
common turbine shaft 108 which is also referred to as a turbine
rotor to which the generator or the driven machine is also
connected, and which is rotatably mounted around its center
axis 109. The combustion chamber 2 which is constructed in the
style of an annular combustion chamber is equipped with a
number of burners 110 for combusting a liquid or gaseous fuel.
The turbine unit 106 has a number of rotatable rotor blades 112
which are connected to the turbine shaft 108. The rotor blades
112 are arranged on the turbine shaft 108 in a ring-like manner
and therefore form a number of rotor blade rows. Furthermore,
the turbine unit 106 comprises a number of fixed stator blades
6, 8, 114 which are also fastened in a ring-like manner on a
stator blade carrier 1 of the turbine unit 106, forming stator
blade rows.

The rotor blades 112 in this case serve for driving the turbine
shaft 108 as a result of impulse transfer from the operating
medium M which flows through the turbine unit 106. The stator
blades 6, 8, 114 on the other hand serve for flow guiding of
the operating medium M between two consecutive rotor blade rows
or rotor blade rings in each case, as seen in the flow
direction of the operating medium M. A consecutive pair,
consisting of a ring of stator blades 114 or a stator blade row
and a ring of rotor blades 112 or a rotor blade row, in this
case is also referred to as a turbine stage.
Each stator blade 114 has a blade root 118 which, for fixing of
the respective stator blade 114 on a stator blade carrier 1 of
the turbine unit 106, is arranged as a wall element. Each
rotor blade 112 is fastened in a similar way on the turbine
shaft 108 via a blade root 119.
Between the platforms 118 - which are arranged in a spaced
apart manner - of the stator blades 114 of two adjacent stator
blade rows, a ring segment 121 is arranged in each case on the
stator blade carrier 1 of the turbine unit 106. The outer
surface of each ring segment 121 in this case is at a distance
in the radial direction from the outer end of the rotor blades
112 lying opposite it by means of a gap. The ring segments 121
which are arranged between adjacent stator blade rows in this
case especially serve as cover elements which protect the inner
casing in the stator blade carrier 1 or other installed
components of the casing against thermal overstress as a result
of the hot operating medium M which flows through the turbine
106.
The combustion chamber 2 in the exemplary embodiment is
designed as a so-called annular combustion chamber in which a
multiplicity of burners 110, which are arranged around the
turbine shaft 108 in the circumferential direction, lead into a
common combustion chamber space. For this, the combustion

chamber 2. in its entirety is designed as an annular structure
which is positioned around the turbine shaft 108.

By using a turbine stator blade carrier 1 of the design which
is specified above in such a gas turbine 101, a considerably
simplified repair can be achieved with high efficiency of the
gas turbine 101 at the same time as a result of a significantly
simpler exchangeability of individual stator blades 6,
especially of the first turbine stage.

1. A turbine stator blade carrier (1), especially for a
stationary gas turbine (101),
comprising a number of segments (24, 26),
wherein one segment (24) extends over the entire radial extent
of the turbine stator blade carrier (1) and the connection of
the respective segment (24) to adjacent segments (24, 26) is
releasable,
characterized in that
the turbine stator blade carrier (1) comprises at least two
interconnected sections (23, 25) along its axial extent, which
have a different number of segments (24, 26).
2. The turbine stator blade carrier (1) as claimed in claim 1,
which has an inflow-side section (23) and at least one
remaining section (25), wherein the inflow-side section (23)
has a greater number of segments (24) than the at least one
remaining section (25).
3. The turbine stator blade carrier (1) as claimed in claim 1
or 2,
in which the connection between axially adjacent segments (24,
26) is a screwed connection and/or a tongue-in-groove
connection.
4. The turbine stator blade carrier (1) as claimed in one of
claims 2 and 3,
in which the at least one remaining section (25), on its side
facing the inflow-side section (23), has a radially outwardly
protruding projection in such a way that this is encompassed by
the segments (24) of the inflow-side section (23) in the radial
direction.

5. A gas turbine with a turbine stator blade carrier (1) as
claimed in one of claims 1 to 4,
having a row of stator blades (6) which are releasably fastened
on the segments (26) of the at least one remaining section
(25) .
6. The gas turbine as claimed in claim 5 having a turbine
stator blade carrier as claimed in claim 4,
in which the stator blades (6) are fastened on the projection.
7. The gas turbine as claimed in claim 5 or 6,
in which a stator blade (6) of the respective stator blade row,
on its side facing the turbine axis (109), is releasably
connected to an inner ring (20).
8. The gas turbine as claimed in claim 7,
in which the respective stator blade (6) includes a tongue (36)
which can be pushed into a groove (38) of the inner ring (20)
in the radial direction.
9. The gas turbine as claimed in one of claims 7 and 8,
in which the inner ring (18) is connected to a combustion
chamber hub (54) .
10. The gas turbine as claimed in one of claims 5 to 9,
in which the segments (24) which are provided in the inflow-
side section (23) are connected to a combustion chamber wall
(32).
11. The gas turbine as claimed in one of claims 5 to 10,
in which a sealing plate (70) is provided between adjacent
stator blades (6) of the respective stator blade row, wherein
stepped edges (72), in which the sealing plate (70) is fixed by
means of a clamping element (74), are introduced on the sides
of blade root (10) and/or blade tip (14) facing the adjacent
SLator blade (6) in each case.

12. The gas turbine (101) as claimed in one of claims 5 to 11,
in which a manhole is introduced into an outer casing of the
gas turbine (101) .
A turbine guide vane system (1), in particular for a gas turbine (101),
having a number of guide vane row and a guide vane carrier (1), is to
enable particularly simple replacement of guide vanes, while maintaining
a particularly high degree of efficiency, and thus designed for particularly
short repair durations. For this purpose, the guide vane carrier (1) has a
number of segments (24, 26), wherein a segment (24, 26) extends over
the entire radial extension of the guide vane carrier (1) and the
connection of the remaining segments (26) can be detached, and wherein
the turbine guide vane carrier (1) has at least two sections (23, 25) along
the axial extension thereof that are connected to one another and have a
different number of segments (24, 26).