U.S. patent application number 14/425016 was filed with the patent office on 2015-09-03 for method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor.
This patent application is currently assigned to Siemens Aktiengesellschaft. The applicant listed for this patent is Siemens Aktiengesellschaft. Invention is credited to Karin Costamagna, Sascha Dungs, Harald Hoell, Henrik Hull, Karsten Kolk, Ulf Laudage, Harald Nimptsch, Peter Schroder, Vyacheslav Veitsman.
Application Number | 20150247406 14/425016 |
Document ID | / |
Family ID | 49182221 |
Filed Date | 2015-09-03 |
United States Patent
Application |
20150247406 |
Kind Code |
A1 |
Costamagna; Karin ; et
al. |
September 3, 2015 |
METHOD FOR ASSEMBLING AND DISASSEMBLING A ROTOR HAVING A NUMBER OF
ROTOR COMPONENTS OF AN AXIAL FLOW TURBOMACHINE AND SUCH A ROTOR
Abstract
A method for assembling and disassembling a rotor having a
number of rotor components of an axial flow turbomachine and such a
rotor is provided. The rotor has a number of a plurality of
disc-shaped or drum-shaped rotor components and at least one
pin-shaped tie-rod extending through the rotor components, wherein
a counter-bearing is screwed onto each of the projecting ends of
said tie-rod for axially bracing the rotor components arranged
therebetween. In order to achieve shorter service intervals, a
connector is screwed onto the tie-rod between both
counter-bearings, wherein, after the release of one of the two
counter-bearings, the rotor components arranged between the
connector and the other of the two counter-bearings are braced with
each other by the connector.
Inventors: |
Costamagna; Karin; (Mulheim
a.d.Ruhr, DE) ; Dungs; Sascha; (Wesel, DE) ;
Hoell; Harald; (Wachtersbach, DE) ; Hull; Henrik;
(Norrkoping, SE) ; Kolk; Karsten; (Mulheim a.d.
Ruhr, DE) ; Laudage; Ulf; (Essen, DE) ;
Nimptsch; Harald; (Essen, DE) ; Schroder; Peter;
(Essen, DE) ; Veitsman; Vyacheslav;
(Gelsenkirchen, DE) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Siemens Aktiengesellschaft |
Munich |
|
DE |
|
|
Assignee: |
Siemens Aktiengesellschaft
Munich
DE
|
Family ID: |
49182221 |
Appl. No.: |
14/425016 |
Filed: |
September 6, 2013 |
PCT Filed: |
September 6, 2013 |
PCT NO: |
PCT/EP2013/068507 |
371 Date: |
February 28, 2015 |
Current U.S.
Class: |
416/204A ;
29/889.1; 29/889.21 |
Current CPC
Class: |
F05D 2260/31 20130101;
Y10T 29/49318 20150115; F01D 5/066 20130101; Y10T 29/49321
20150115 |
International
Class: |
F01D 5/06 20060101
F01D005/06 |
Foreign Application Data
Date |
Code |
Application Number |
Sep 7, 2012 |
DE |
10 2012 215 886.3 |
Claims
1. A method for assembling a rotor, comprising a number of rotor
components, of an axial flow turbomachine, in which first
disk-shaped or drum-shaped rotor components in a first rotor
section are clamped between a first counter-bearing and a connector
by screwing the first counter-bearing and the connector onto a
tie-rod, the method comprising: clamping the first and the second
rotor components in a second rotor section between the first
counter-bearing and a second counter-bearing by screwing the second
counter-bearing onto the tie-rod, wherein, during clamping of the
second rotor section, the clamping of the connector is
released.
2. A method for partially dismantling a rotor, comprising clamped
disk-shaped or drum-shaped rotor components, of an axial flow
turbomachine, the method comprising when releasing a clamping of a
second rotor section with second disk-shaped rotor components by
releasing a second counter-bearing screwed onto a tie-rod, first
rotor components of a first rotor section are clamped between a
first counter-bearing and a connector screwed onto the tie-rod.
3. A rotor for an axial flow turbomachine, comprising a number of
disk-shaped or drum-shaped rotor components, at least one tie-rod
extending through the rotor components, with a counter-bearing
being screwed onto each of the projecting ends of this tie-rod in
order to axially clamp the rotor components arranged therebetween,
wherein a connector is screwed onto the tie-rod between the two
counter-bearings, which connector, in the case of rotor components
clamped by the two counter-bearings, participates only slightly or
not at all in clamping the rotor components, and wherein once one
of the two counter-bearings has been released, those rotor
Components arranged between the connector and the other of the two
counter-bearings are clamped by the connector and the other
counter-bearing.
4. The rotor as claimed in claim 3, wherein the rotor comprises,
along its longitudinal extent, a first rotor end section, at least
a further rotor section and a second rotor end section, wherein the
connector, as seen axially, is arranged in one of the further rotor
sections.
5. The rotor as claimed in claim 3, wherein the connector comprises
a screw nut.
6. The rotor as claimed in claim 4, wherein the connector and one
of the rotor components are designed such that, after the
counter-bearing arranged on the second rotor end section has been
released, the connector adjacent to the second rotor end section,
with the counter-bearing arranged on the first rotor end section,
clamps together the rotor components arranged therebetween.
7. The rotor as claimed in claim 4, wherein the respective
connector has multiple openings for guiding a fluid from one of the
rotor sections through to another of the rotor end sections.
8. The rotor as claimed in claim 7, wherein the respective
connector has a circumferential shaft collar which is arranged on
the circumference and in which are arranged the openings as
throughflow openings.
9. The rotor as claimed in claim 3, wherein the respective
connector bears radially against at least one of the rotor
components.
10. The rotor as claimed in claim 4, wherein the rotor comprises a
gas turbine rotor, the first rotor end section comprises a
compressor rotor, the further rotor section comprises a central
rotor section and the second rotor end section comprises a turbine
rotor.
11. The rotor as claimed in claim 10, wherein the central rotor
section is formed from a hollow shaft or multiple bladeless rotor
disks and the rotor end sections are formed from rotor disks.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application is the US National Stage of International
Application No. PCT/EP2013/068507 filed Sep. 6, 2013, and claims
the benefit thereof. The International Application claims the
benefit of German Application No. DE 102012215886.3 filed Sep. 7,
2012. All of the applications are incorporated by reference herein
in their entirety.
FIELD OF INVENTION
[0002] The invention relates to a rotor for an axial flow
turbomachine, comprising a number of multiple disk-shaped or
drum-shaped rotor components and at least one tie-rod extending
through the rotor components, with a counter-bearing being screwed
onto each of the projecting ends of this tie-rod in order to
axially clamp the rotor components arranged therebetween.
[0003] The invention further relates to a method for assembling and
disassembling such a rotor.
BACKGROUND OF INVENTION
[0004] Such rotors are very well known from the comprehensive
available prior art relating to static gas turbines. For example, a
rotor of the type mentioned in the introduction is shown in the
book "Stationare Gasturbinen" ["Static Gas Turbines"] (Eds
Christoph Lechner and Jorg Seume), on page 629. The rotor is
designed as what is termed a disk construction, wherein the rotor
disks bear blades, either for the compressor or for the turbine
unit of the gas turbine, on their outer circumference. A central
hollow shaft as a drum-shaped component is arranged between the
compressor disks and the turbine disks. A central tie-rod extends
through all the rotor components and, with the aid of two
counter-bearings, the forward hollow shaft and the rear hollow
shaft, clamps together the rotor components arranged between these
two hollow shafts. In that context, the tie-rod is stretched
elastically up to its yield point, thus clamping together the
individual rotor components.
[0005] EP 2 447 471 A2 discloses a gas turbine rotor for an
aircraft engine, in which the compressor disks are clamped by a
first tie-rod section and the turbine disks are clamped separately
by a second tie-rod section, in order to thus pre-clamp the
corresponding rotor sections independently of one another with
different forces.
[0006] EP 2 415 967 A1 discloses the same for a static gas turbine
which likewise comprises a rotor--embodied with a disk
construction--with a compressor section and a turbine section,
whose respective central tie-rods are screwed into a central shaft
connecting the former two to one another. In that context, the
compressor disks are clamped between a first pre-clamping screw
nut--screwed onto the end--and the central shaft, and the turbine
disks are also clamped between the central shaft and a second
pre-clamping screw nut--also screwed onto the end, wherein the
pre-clampings of the compressor section and turbine section are
independent of one another.
[0007] A further disk clamping of a compressor rotor is also known
from DE 10 2005 052 819 A1. According to this teaching, the
multi-part tie-rod comprises two tension sleeves and a compression
sleeve.
[0008] A similar construction is also possible with decentralized
tie-rods, wherein for example twelve tie-rods are arranged evenly
distributed at the same radius.
[0009] It is also known to weld together the disk-shaped or
drum-shaped rotor components. Even combinations of the
aforementioned embodiments, in which for example the compressor
rotor is welded and the rotor components of the turbine unit are
clamped by means of a screwed connection with bolts at the
circumference, are also known.
SUMMARY OF INVENTION
[0010] The invention has an object of proposing an alternative
construction of rotors for an axial flow turbomachine. The
invention has a further object of providing the methods for
assembling and for dismantling such a rotor necessary therefor.
[0011] The object relating to the methods is achieved with the
methods according to the features of the independent claims. The
object relating to the rotor is achieved with a rotor according to
the features of the independent claims. Advantageous configurations
and refinements are indicated in the dependent claims.
[0012] The invention first proposes, when assembling the rotor,
clamping the rotor components of a modular rotor of a turbomachine
in multiple steps. First, those rotor components which are arranged
in a first rotor section--hereinafter called the first rotor
components--are clamped between a first counter-bearing and a
connector. To that end, the counter-bearing and the connector are
screwed onto a tie-rod until all the first rotor components
arranged therebetween are pressed securely against one another by
these two. In a second step, those rotor components which are to be
assigned to a second rotor section--hereinafter referred to as
second rotor components--are then threaded onto the connector side
of the tie-rod. A second counter-bearing is then screwed onto the
free end of the tie-rod, with the aid of which counter-bearing the
second rotor components and also the first rotor components are
clamped between the two counter-bearings. When clamping the second
counter-bearing, the clamping between the first counter-bearing and
the connector is then released, such that once the rotor is
assembled the connector participates only slightly or not at all in
clamping. All of the rotor components are then clamped by the two
counter-bearings, in conjunction with the tie-rod, in the manner of
brackets.
[0013] When dismantling the rotor, the method steps are then of
course carried out in reverse order such that, in order to
dismantle the rotor, of an axial flow turbomachine, comprising
clamped disk-shaped rotor components, a second rotor section having
second disk-shaped rotor components is first declamped by releasing
the second counter-bearing screwed onto the tie-rod, wherein in the
process the first disk-shaped rotor components of the first rotor
section are clamped between the first counter-bearing and a
connector screwed onto the tie-rod.
[0014] Consequently, the rotor comprises a number of disk-shaped or
drum-shaped rotor components and at least one tie-rod extending
through the rotor components, with a counter-bearing being screwed
onto each of the projecting ends of this tie-rod in order to
axially clamp the rotor components arranged therebetween, wherein a
connector is screwed onto the tie-rod between the two
counter-bearings such that, once one of the two counter-bearings
has been released, those rotor components arranged between the
connector and the other of the two counter-bearings are clamped by
the connector and the other counter-bearing.
[0015] Advantageously, the rotor comprises, along its longitudinal
extent, a first rotor end section, at least a further rotor section
and a second rotor end section, wherein the connector, as seen
axially, is arranged in one of the further rotor sections. The
first rotor section, defined for the method, encompasses the first
rotor end section and the further rotor section, whereas the second
rotor section corresponds to the second rotor end section.
Particular advantages can be realized in the configuration in which
the connector and one of the rotor components are configured such
that, after the counter-bearing arranged on the second rotor end
section has been released, the connector adjacent to the second
rotor end section, with the counter-bearing arranged on the first
rotor end section, clamps together the rotor components arranged
therebetween. A particular advantage of this configuration is that,
in a first assembly step, those rotor components which are threaded
onto the first tie-rod element can already be clamped by one of the
two counter-bearings and the connector, although the rotor is not
yet completely stocked with rotor components. Only after this are
the further disk-shaped or drum-shaped rotor components to be
threaded onto the tie-rod on the side of the connector, after which
the second counter-bearing can then be screwed onto the end of the
tie-rod, whereby all the disk-shaped or drum-shaped rotor
components of the rotor can finally be clamped together. According
to the invention, it is provided in that context that the clamping
which acts in the interim from one of the two counter-bearings and
the connection element on a part of the disk-shaped or drum-shaped
rotor components is then released again. In this respect, the
temporary and final clampings are matched to each other such that,
with the rotor components being finally clamped between the two
counter-bearings, the initial clamping of the counter-bearing and
the connection element is at least partially--or
entirely--released. This is of particular interest for gas turbine
installations in which, instead of a welded compressor rotor, a
modular rotor having a disk construction should be used, which
modular rotor should further also be clamped to the turbine rotor
and with the aid of tie-rods. This improves the handling of the
rotor during maintenance work of an operationally stressed gas
turbine and reduces the time necessary for carrying out the
maintenance work, since it is not necessary to unstack the entire
rotor but only the turbine-side rotor section. Particularly, the
connector may be designed as a screw nut. Instead, it is of course
also conceivable for the connector to be connected in one piece
with the tie-rod.
[0016] According to a first advantageous refinement, the connector
has multiple openings for guiding a fluid from one of the rotor
(end) sections through to another of the rotor (end) sections.
Particular advantages can be realized in the configuration in which
the respective connector has a circumferential shaft collar which
is arranged on the circumference and in which are arranged the
openings as throughflow openings for cooling fluid. When the rotor
is used in a gas turbine, it is then for example possible to feed
compressor air--bled from the compressor--into the interior of the
rotor and to guide this air through the connector into a turbine
rotor, where the cooling air can be used for cooling purposes. By
using a shaft collar at the circumference of the connector, it is
possible to arrange the throughflow openings, which are necessary
for feeding through the fluid, on a larger radius. It is thus
possible to create larger throughflow cross sections and
accordingly to feed through a greater cooling air mass flow rate
with low pressure losses.
[0017] Further, the connector can also be used to create a support
for the tie-rod in order to reduce vibrations when the turbomachine
is in operation. To that end, only a radial support for at least
one of the rotor components at the relevant connector is
necessary.
[0018] Particular advantages can be realized in the configuration
in which the rotor is designed as a gas turbine rotor, the first
rotor end section is designed as a compressor rotor, the further
rotor section is designed as a central rotor section and the second
rotor end section is designed as a turbine rotor. In that context,
the central rotor section can be formed solely from a hollow shaft
or from multiple bladeless rotor disks and the rotor end sections
from rotor disks.
BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The invention will be explained in more detail with
reference to exemplary embodiments in the figures. In that context,
further features and advantages are indicated in the description of
the figures, in which:
[0020] FIG. 1 shows a partial longitudinal section through a rotor
according to the invention for a static axial flow
turbomachine;
[0021] FIG. 2 shows a detail from the longitudinal section of FIG.
1, in the region of the connector;
[0022] FIG. 3 shows the same detail of FIG. 2, according to an
alternative exemplary embodiment;
[0023] FIG. 4 shows a connection element with a shaft collar
arranged at the circumference;
[0024] FIG. 5 shows, in a perspective representation, the
connection element of FIG. 4 and
[0025] FIG. 6 shows a connection element bearing radially against
the rotor component, in the longitudinal section of FIG. 2.
[0026] In all figures, identical features are provided with
identical reference signs.
DETAILED DESCRIPTION OF INVENTION
[0027] FIG. 1 shows a partial longitudinal section through the
rotor 10 of an axial flow turbomachine. In the exemplary embodiment
shown, the rotor 10 is configured as a gas turbine rotor, wherein
the remaining constituents of the gas turbine are not represented
in more detail here. The construction of the rotor 10 is
fundamentally modular and is to be termed disk construction.
[0028] Consequently, the rotor 10 comprises a number of rotor disks
12, which in this case are also termed disk-shaped rotor components
14. In addition, the rotor 10 further comprises a drum-shaped rotor
component 16 which in the exemplary embodiment is termed central
hollow shaft 18. In addition to the central hollow shaft 18, there
is also a forward hollow shaft 22, screwed onto the end of a
tie-rod 20, and a rear hollow shaft 24, screwed on at the opposite
end. In this case, the forward hollow shaft 22 is also termed first
counter-bearing 26 and the rear hollow shaft 24 is termed second
counter-bearing 28. The two counter-bearings 26, 28, with the aid
of the tie-rod 20, clamp the rotor components 14, 16 together and
press them securely against one another. In order to achieve this,
the tie-rod 20 is stretched elastically by the two counter-bearings
26, 28.
[0029] According to the invention, it is provided that a connection
34 formed as a screw nut 35 is screwed onto the tie-rod 20 within
the rotor 10 in order to clamp, only while the rotor is being
assembled or dismantled, the rotor components 14, 16 arranged in a
section of the rotor 10.
[0030] The rotor 10 can theoretically be split axially into a first
rotor end section 38, a further rotor section 40 and a second rotor
end section 42, wherein the connector 34, seen axially, is arranged
in the further rotor section 40. In the shown gas turbine rotor 10,
the first rotor end section 38 is designed as a compressor rotor
44, and the second rotor end section 42 is designed as a turbine
rotor 48. In the region of the further rotor section 40, a
combustion chamber of the gas turbine is arranged radially outside
the rotor 10. In order, when servicing the gas turbine, to release
where relevant only the rotor disks 12 of the turbine rotor 48,
without at the same time the central hollow shaft 18 and the rotor
disks 12 arranged in the compressor rotor 44 releasing, it is
provided that, after the counter-bearing 28 arranged on the second
rotor end section 42 has been released, the connector 34 adjacent
to the second rotor end section 42, with the counter-bearing 26
arranged on the first rotor end section 38, clamps together the
rotor components 14, 16 arranged therebetween. In order to achieve
this, multiple exemplary embodiments are conceivable. To that end,
FIGS. 2, 3 and 4 show various exemplary embodiments. FIGS. 2 to 4
show, in longitudinal section, a detail from the transition region
between the further rotor section 40 and the second rotor end
section 42. As connector 34, the screw nut 35 is screwed onto the
tie-rod 20. The central hollow shaft 18 is arranged radially
adjacent to the screw nut 35. The screw nut 35 has a conical face
50 whose gradient matches an inward-oriented face 52 of the central
hollow shaft 18. In addition, a smaller shaft collar 54 is provided
centrally between the two screw openings 37 of the screw nut 35,
the side face 56 of which collar bears against a side face
58--parallel thereto--of the central hollow shaft 18. During
assembly of the rotor 10, the first counter-bearing 26 is first
screwed onto the end of the tie-rod 20. This subassembly is then
set upright such that the individual disk-shaped or drum-shaped
rotor components 14, 16 can be placed onto the first
counter-bearing 26 from above. Then, the screw nut 35 is screwed
onto that end of the tie-rod element 30 which has been left free,
until the rotor components 14, 16 located between the screw nut 35
and the first counter-bearing 26 are clamped together. The rotor
disks 12 provided for the turbine rotor 48 are then threaded on and
placed onto the turbine-side end of the tie-rod 20 from above.
Finally, the second counter-bearing 28 is screwed onto that end of
the tie-rod 20 which has been left free. In so doing, the entire
tie-rod 20 is stretched elastically such that the clamping of the
screw nut 35 or, as the case may be, of the connector 34 and the
first counter-bearing 26 is released.
[0031] According to the exemplary embodiment of FIG. 2, axial bores
60 can be provided both in the central hollow shaft 18 and in the
screw nut 35, by means of which bores a cooling device can be
guided from one rotor (end) section to another rotor (end)
section.
[0032] FIG. 3 shows the same detail as FIG. 2, but in which the
construction for axially clamping in the region of the screw nut 35
and of the central hollow shaft 18 is slightly modified in
comparison with the construction of FIG. 2. The radial overlap
between the screw nut 35 and the central hollow shaft 18, required
in order to establish the axial clamping, is achieved here with the
use of a sleeve 62 which is arranged therebetween and is provided
with a flange.
[0033] FIG. 4 shows a further exemplary embodiment for clamping the
rotor components 14, 16 between a first counter-bearing (not shown
in FIG. 4) and the connector 34. The connector 34 is again
configured as a screw nut 35 with two mutually opposite screw
openings 37. A larger shaft collar 54 is provided on the outer
circumference, centrally between the screw openings 37, in which
collar are provided, distributed evenly about the circumference,
openings 64 for guiding through a cooling fluid. The two parallel
side faces 56 of the shaft collar 54 transition, via a radius, into
curved, tapered flanks 57 which end at the screw openings 37. FIG.
5 shows this screw nut 35 with the screw opening 37 and four evenly
distributed throughflow openings 64 in a perspective
representation.
[0034] In order to avoid radial vibrations of the tie-rod 20 in
operation, it is possible to provide, on the casing-side face of
the shaft collar 54, a circumferential groove 66 with a support
wire 68 therein, with the aid of which the tie-rod 20 is supported
radially on one of the rotor components, according to FIG. 6 on the
central hollow shaft 18.
[0035] The exemplary embodiments of FIGS. 2 to 6 all show gas
turbine rotors 10 in which the second counter-bearing 28 is not yet
screwed onto the second tie-rod element 32, such that only those
rotor components 14, 16 depicted to the left of the screw nut 35 in
FIGS. 2 to 6 are clamped with the first counter-bearing 26 and
those rotor components 14, 16 depicted to the right thereof are
not.
[0036] Overall, the invention thus relates to a rotor 10 for an
axial flow turbomachine, comprising a number of multiple
disk-shaped or drum-shaped rotor components 14, 16 and at least one
pin-shaped tie-rod 20 extending through the rotor components 14,
16, with a counter-bearing 26, 28 being screwed onto each of the
projecting ends of this tie-rod in order to axially clamp the rotor
components 14, 16 arranged therebetween.
[0037] In order to provide a rotor 10 by means of which shorter
service interval times can be achieved, it is provided that a
connector 34 is screwed onto the tie-rod 20 between the two
counter-bearings 26, 28, by means of which connector 34, after one
of the two counter-bearings 28 has been released, those rotor
components 14, 16 arranged between the connector 34 and the other
of the two counter-bearings 26 are clamped together.
* * * * *