U.S. patent application number 10/104626 was filed with the patent office on 2002-10-17 for turbine.
Invention is credited to Bolms, Hans-Thomas.
Application Number | 20020150469 10/104626 |
Document ID | / |
Family ID | 8176908 |
Filed Date | 2002-10-17 |
United States Patent
Application |
20020150469 |
Kind Code |
A1 |
Bolms, Hans-Thomas |
October 17, 2002 |
Turbine
Abstract
The present invention relates to a turbine having a housing (11)
and a rotor (12), the housing (11) being provided with a plurality
of rows of guide vanes (13) and the rotor (12) being provided with
a plurality of rows of rotor blades (14). On the housing (11),
there is a guide ring (18) which is provided axially between in
each case two rows of guide vanes (13), which guide ring, together
with the associated row of rotor blades (14), delimits a gap (21).
According to the invention, the guide ring (18) is adjustable in
order to change the gap (21). The size of the gap (21) can then be
predetermined by adjusting the guide ring (18) and can be optimized
according to the specific application.
Inventors: |
Bolms, Hans-Thomas;
(Muelheim A.D. Ruhr, DE) |
Correspondence
Address: |
SIEMENS CORPORATION
INTELLECTUAL PROPERTY DEPT.
186 WOOD AVENUE SOUTH
ISELIN
NJ
08830
US
|
Family ID: |
8176908 |
Appl. No.: |
10/104626 |
Filed: |
March 21, 2002 |
Current U.S.
Class: |
415/115 ;
415/173.2; 415/173.3 |
Current CPC
Class: |
F05D 2260/56 20130101;
F01D 11/22 20130101 |
Class at
Publication: |
415/115 ;
415/173.2; 415/173.3 |
International
Class: |
F01D 011/22; F01D
005/20 |
Foreign Application Data
Date |
Code |
Application Number |
Mar 23, 2001 |
EP |
01107256.8 |
Claims
What is claimed is:
1. A turbine comprising a housing and a rotor, the housing being
provided with a plurality of rows of guide vanes and the rotor
being provided with a plurality of rows of rotor blades, and a
guide ring being provided on the housing in the axial direction
between in each case two rows of guide vanes, the guide ring
together with the associated row of rotor blades delimiting a gap
characterized in that the guide ring can be adjusted in order to
change the gap.
2. The turbine as claimed in claim 1, wherein the guide ring can be
adjusted in the axial direction of the turbine.
3. The turbine as claimed in claim 2, wherein the guide ring has at
least one guide face, which runs parallel to an axis of rotation of
the rotor and is in contact with at least one stationary supporting
surface.
4. The turbine as claimed in claim 3, wherein the at least one
supporting surface is formed on platforms of the guide vanes which
adjoin the guide ring.
5. The turbine as claimed in claim 1, wherein the guide ring is
arranged on a guide-ring carrier, which can be adjusted with
respect to the housing.
6. The turbine as claimed in claim 5, wherein the guide-ring
carrier has at least one groove, into which an eccentric which can
be driven rotatably engages for adjustment purposes.
7. The turbine as claimed in claim 5, wherein a cooling chamber for
cooling the guide ring is provided between the guide ring and the
guide-ring carrier.
8. The turbine as claimed in claim 1, characterized in that the
guide ring is sealed with respect to the housing by at least one
seal in order to minimize losses of cooling medium.
9. The turbine as claimed in claim 8, wherein the seal is designed
as a labyrinth seal or as an elastically deformable seal.
10. The turbine as claimed in claim 8, wherein the guide ring is
accommodated in an insert and is sealed with respect to this
insert.
11. A turbine adapted for use in a land-based power generation
plant, comprising: a housing having a plurality of rows of guide
vanes; a rotor having a plurality of rows of rotor blades; and a
guide ring provided on the housing in the axial direction between
two rows of guide vanes, the guide ring and the associated row of
rotor blades forming a gap wherein the guide ring can be adjusted
in order to change the size of the gap.
12. The turbine as claimed in claim 11, wherein the guide ring can
be adjusted in the axial direction of the turbine.
13. The turbine as claimed in claim 12, wherein the guide ring has
at least one guide face, which runs parallel to an axis of rotation
of the rotor and is in contact with at least one stationary
supporting surface.
14. The turbine as claimed in claim 13, wherein the at least one
supporting surface is formed on platforms of the guide vanes which
adjoin the guide ring.
15. The turbine as claimed in claim 11, wherein the guide ring is
arranged on a guide-ring carrier, which can be adjusted with
respect to the housing.
16. The turbine as claimed in claim 15, wherein the guide-ring
carrier has at least one groove, into which an eccentric which can
be driven rotatably engages for adjustment purposes.
17. The turbine as claimed in claim 15, wherein a cooling chamber
for cooling the guide ring is provided between the guide ring and
the guide-ring carrier.
18. The turbine as claimed in claim 11, characterized in that the
guide ring is sealed with respect to the housing by at least one
seal in order to minimize losses of cooling medium.
19. The turbine as claimed in claim 18, wherein the seal is
designed as a labyrinth seal or as an elastically deformable
seal.
20. A turbine adapted for use in a land-based power generation
plant, comprising: a housing having a plurality of rows of guide
vanes; a rotor in operative association with the guide vanes; a
guide ring provided on the housing between two rows of guide vanes,
the guide ring and the associated row of rotor blades forming an
adjustable gap.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application claims priority to EP/01107256.8, filed
Mar. 23, 2001 under the European Patent Convention and which is
incorporated by reference herein in its entirety.
FIELD OF THE INVENTION
[0002] The present invention relates to a turbine having a housing
and a rotor, the housing being provided with a plurality of rows of
guide vanes and the rotor being provided with a plurality of rows
of rotor blades, and a guide ring being provided on the housing, in
the axial direction between in each case two rows of guide vanes,
which guide ring, together with the associated row of rotor blades,
delimits a gap.
BACKGROUND OF THE INVENTION
[0003] In known turbines, the gap or its size is thermally
regulated. For this purpose, the housing is cooled to a
considerably greater extent than necessary in the region of the
rotor blades. This intensified cooling contracts the housing, so
that the gap is reduced. The cooling medium, generally cooling air,
is taken from a compressor assigned to the turbine. It can then no
longer be utilized for combustion. For this reason, both the output
and efficiency of the turbine fall.
[0004] Therefore, it is an object of the present invention to allow
the gap to be changed by simple means without the output and
efficiency being impaired.
[0005] According to the invention, this object is achieved, in a
turbine of the type described in the introduction, by the fact that
the guide ring can be adjusted in order to change the gap.
[0006] In view of the mechanical adjustability of the guide ring,
thermal regulation is no longer required. Therefore, the
consumption of cooling medium can be drastically reduced. The guide
ring is adjusted in order to change the gap. Since, in general, the
guide ring is designed as a separate component, which is provided
between in each case two rows of guide vanes, the increased
structural outlay required is very low. The adjustment can take
place highly accurately and with a minimal time delay. Therefore,
the gap can be adapted even to rapidly changing boundary conditions
without any difficulty.
[0007] Advantageous configurations and refinements of the invention
will emerge from the dependent claims.
[0008] According to a first advantageous configuration, the guide
ring can be adjusted in the axial direction of the turbine. Since
the housing of the turbine is generally conical, the adjustment in
the axial direction achieves the desired change in the gap. There
is no need to change the circumference of the guide ring. However,
according to a second advantageous configuration, the guide ring
may also be designed to be adjustable in the radial direction.
[0009] In the first configuration, the guide ring advantageously
has at least one guide face, which runs parallel to an axis of
rotation of the rotor. This guide face is in contact with at least
one stationary supporting surface. The supporting surface may in
this case be provided directly on the housing or on a component
which is secured to the housing. The supporting surface also runs
parallel to the axis of rotation of the rotor. The guide ring
advantageously has two guide faces of this type, which are in
contact with associated supporting surfaces. It is ensured that the
guide ring is adjustable only in the axial direction parallel to
the axis of rotation of the rotor. Unintended radial adjustment of
the guide ring is reliably avoided.
[0010] The supporting surface may be formed in particular on
platforms of the guide vanes which adjoin the guide ring. There is
then no need to additionally machine the housing.
[0011] The guide ring is advantageously arranged on a guide-ring
carrier, which can be adjusted with respect to the housing. The
guide-ring carrier ensures that the guide ring is held reliably.
Undefined movements of the guide ring are reliably ruled out. The
guide-ring carrier may simply be inserted into a corresponding
recess in the housing and for its part may be suitably guided in
this recess. It can therefore both be provided from the outset in
new turbines and be retrofitted to existing turbines.
[0012] According to an advantageous refinement, the guide-ring
carrier has at least one groove, into which an eccentric which can
be driven rotatably engages for adjustment purposes. Suitable
selection of the materials for the guide-ring carrier and the
eccentric makes it possible to dispense with lubrication. The
adjustment can then be designed for high temperatures. It operates
rapidly and reliably and is easy to produce.
[0013] In an advantageous refinement, a cooling chamber for cooling
the guide ring is provided between the guide ring and the
guide-ring carrier. The cooling chamber is acted on by a cooling
medium via suitable connections. Therefore, the guide ring can be
used even at high temperatures.
[0014] The guide ring is advantageously sealed with respect to the
housing by at least one seal, in order to minimize or completely
prevent losses of cooling medium. As was stated in the
introduction, the cooling medium is taken from the compressor. The
more cooling medium is removed, the lower the efficiency becomes.
The at least one seal can therefore minimize the consumption of
coolant and therefore produce a higher efficiency.
[0015] The seal may in this case be designed as a labyrinth seal or
as an elastically deformable seal. When an elastically deformable
seal is used, the seal advantageously consists of a metallic
material which is suitable for high temperatures.
[0016] The guide ring is advantageously accommodated in an insert
and sealed with respect to this insert. The seals then run between
the insert and the guide ring. The insert can be preassembled with
the seals and the guide ring and inserted into the recess in the
housing. Therefore, the design, production and assembly can be made
simple even when using seals.
BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The invention is explained in more detail below with
reference to exemplary embodiments, which are diagrammatically
illustrated in the drawing. Throughout the description, identical
reference symbols are used for similar and functionally identical
components. In the drawing:
[0018] FIG. 1 shows a diagrammatic longitudinal section through a
turbine;
[0019] FIG. 2 shows an enlarged illustration of detail X from FIG.
1;
[0020] FIGS. 3 and 4 show different positions of the guide ring in
a view which is similar to that shown in FIG. 2;
[0021] FIG. 5 diagrammatically depicts the adjustability of the
guide ring in longitudinal section;
[0022] FIG. 6 shows an enlarged illustration of detail Y from FIG.
5;
[0023] FIG. 7 shows an enlarged illustration of detail Z from FIG.
5;
[0024] FIG. 8 shows a plan view of a guide ring in the direction
indicated by arrow VIII in FIG. 5; and
[0025] FIG. 9 illustrates a further exemplary embodiment, in a view
similar to that shown in FIG. 5.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
[0026] FIG. 1 shows a diagrammatic longitudinal section through a
gas turbine 10 having a housing 11 and a rotor 12. The housing 11
is provided with guide vanes 13, and the rotor 12 is provided with
rotor blades 14. Hot gas flows through the gas turbine 10 in the
direction indicated by arrow 15, causing the rotor 12 to rotate
about its axis of rotation 16, in the direction indicated by arrow
17. Both the guide vanes 13 and the rotor blades 14 are arranged in
rows. A guide ring 18 is arranged between in each case two rows of
guide vanes 13. The guide ring 18 is advantageously of multipart
design.
[0027] FIG. 2 shows an enlarged illustration of the detail X from
FIG. 1, and FIGS. 3 and 4 show different positions of the guide
ring 18. The housing 11 widens in the direction indicated by arrow
15. Therefore, by adjusting the guide ring 18 in the axial
direction in accordance with the directions indicated by arrows 19,
20, it is possible to change the size of a gap 21 between the guide
ring 18 and the free end of the rotor blades 14. Adjustment to the
left, in the direction indicated by arrow 19, into position 18'
leads to an enlarged gap 21'. This adjustment is illustrated in
FIG. 3. If, by contrast, the guide ring is displaced in the
direction indicated by arrow 20, into its position 18" illustrated
in FIG. 4, the size of the gap 21" is reduced. There is no need to
change the diameter of the guide ring. This is diagrammatically
indicated by a dashed line 22, connecting FIGS. 3 and 4.
[0028] FIG. 5 diagrammatically depicts the adjustability of the
guide ring 18 in longitudinal section. The guide ring 18 is secured
to a guide-ring carrier 23, which is accommodated in a recess 24 in
a guide-vane carrier 30, and is supported on platforms 33 of
adjacent guide vanes 13. The guide-vane carrier 30 is connected to
the housing 11 in a suitable manner which is not illustrated in
more detail. To adjust the guide-ring carrier 23, a shaft 25, which
can be driven rotatably, in a bore 32 and an eccentric 26 are
provided. As soon as the shaft 25 is rotated in the direction
indicated by arrow 31, the eccentric 26 causes the guide-ring
carrier 23 to be displaced in the directions indicated by arrows
19, 20. In this case, the eccentric 26 is supported on lateral
projections 37, 38 of the guide-ring carrier 23.
[0029] With the adjustability which is provided according to the
invention, there is also provision for the guide ring 18 to be
cooled. A cooling medium, for example cooling air which has been
taken from a compressor, is passed through the housing 11 and the
guide-vane carrier 30, via a bore 27, into the recess 24. For its
part, the guide-ring carrier 23 has a bore 28 into which the
cooling medium can pass. The bore 28 leads to a chamber 29 which,
toward the rotor 12, is delimited by the guide ring 18. Therefore,
effective cooling of the guide ring 18 is achieved by applying the
cooling medium to the chamber 29. Details of the adjustment of the
guide ring 18 are illustrated in FIGS. 6 to 8. In this case, FIGS.
6 and 7 show an enlarged illustration of the details Y, Z from FIG.
5. The guide ring 18 has guide faces 34 which run parallel to the
axis of rotation 16 of the rotor. These guide faces are in contact
with associated supporting surfaces 35 on the platforms 33. The
supporting surfaces 35 also run parallel to the axis of rotation
16. This ensures that the guide ring 18 is reliably guided in the
axial direction and adjustment takes place only in the directions
indicated by arrows 19, 20. There is no possibility of an
unintended radial displacement of the guide ring 18. The adjustment
is effected by rotation of the eccentrics 26, which engage in a
groove 36 between the projections 37, 38 on the top side of the
guide-ring carrier 23. The bores 28 used for cooling are arranged
between the eccentrics 26.
[0030] FIG. 9 shows a further exemplary embodiment of the
invention, in a view which is similar to that shown in FIG. 5. An
insert 40 with side parts 41, 42 is inserted into the recess 24. In
the exemplary embodiment illustrated, a ring 43 with an opening 44,
to which the side parts 41, 42 are secured, is additionally
provided. The insert 40 can therefore be preassembled and then
fixed in the recess 24. As well as the three-part design
illustrated, a single-part design of the insert 40 is also
possible.
[0031] The guide-ring carrier 23 is accommodated in the insert 40
and can be displaced in the directions indicated by arrows 19, 20
by means of the shaft 25 and the eccentrics 26. It is guided by
means of elements which are not illustrated in more detail.
[0032] To prevent losses of cooling medium, the guide-ring carrier
23 is sealed by means of seals 45, 46. The seals 45, 46 are
arranged between the guide-ring carrier 23 and the side parts 41 of
the insert 40. The seal 45 is in this case designed as a labyrinth
seal. The seal 46 is elastically deformable. It consists of an
elastic material which is designed for the temperatures which occur
during operation of the turbine 10.
[0033] For production, the guide ring 18 is secured to the
guide-ring carrier 23. Then, the seals 45, 46 are prefitted and the
insert 40 is put in place. Then, the guide-ring carrier 23 is
inserted, together with the insert 40 and the seals 45, 46, into
the recess 24.
[0034] The subject matter of the present invention makes it
possible to change the gap 21 easily and without complications by
adjusting the guide ring 18. This adjustment arrangement can also
be retrofitted to existing turbines 10. Changing the gap 21 results
in optimum matching to the prevailing operating conditions. There
is no need for increased consumption of the cooling medium, as has
been the case in previous solutions. Therefore, the efficiency of
the turbine 10 is considerably improved.
* * * * *