U.S. patent application number 10/124428 was filed with the patent office on 2002-12-05 for device for fastening a moving blade to the rotor of a turbomachine.
Invention is credited to Bachofner, Rene, Eschbach, Urban, Mueller, Michael, Regnath, Guenter, Waltke, Ulrich.
Application Number | 20020182081 10/124428 |
Document ID | / |
Family ID | 7682853 |
Filed Date | 2002-12-05 |
United States Patent
Application |
20020182081 |
Kind Code |
A1 |
Bachofner, Rene ; et
al. |
December 5, 2002 |
Device for fastening a moving blade to the rotor of a
turbomachine
Abstract
A device for fastening a moving blade (3) to a rotor (2) of a
thermal turbomachine is described. The moving blade (3) has a blade
root (36), a blade leaf (32) and a platform (31) arranged between
the blade root (36) and the blade leaf (32) and having at least two
side flanks (33, 34). The idea, on which the invention is based, of
avoiding axial forces occurring on the rotor (2) on account of
bearing faces set obliquely to the rotor axis (4) between two
adjacent moving blades (3) is that adjacent moving blades (3) meet
solely at axially oriented bearing faces (52).
Inventors: |
Bachofner, Rene; (Neuenhof,
CH) ; Eschbach, Urban; (Wehr, DE) ; Mueller,
Michael; (Ulm, DE) ; Regnath, Guenter;
(Kuessaberg, DE) ; Waltke, Ulrich; (Muelheim an
der Ruhr, DE) |
Correspondence
Address: |
SHANKS & HERBERT
Intellectual Property Advocates
TransPotomac Plaza
1033 N. Fairfax St., Sute 306
Alexandria
VA
22314
US
|
Family ID: |
7682853 |
Appl. No.: |
10/124428 |
Filed: |
April 18, 2002 |
Current U.S.
Class: |
416/220R |
Current CPC
Class: |
F01D 5/32 20130101; F01D
5/3038 20130101 |
Class at
Publication: |
416/220.00R |
International
Class: |
F04D 029/34 |
Foreign Application Data
Date |
Code |
Application Number |
Apr 26, 2001 |
DE |
101 20 532.5 |
Claims
1. A device for fastening moving blades (3) along a circumferential
groove (1) running within a rotor (2) of a thermal turbomachine, in
which the moving blades (3) have a blade root (36), a blade leaf
(32) and a platform (31) arranged between the blade root (36) and
the blade leaf (32) and having at least two side flanks (33, 34),
the circumferential contour (1) provides an inner contour designed
for receiving the blade roots (36), and the side flanks (33, 34) of
the platform (31) of the moving blades (3) located in the
circumferential groove are inclined obliquely to the rotor axis
(4), characterized in that, in the region of the blade root (36)
extending into the circumferential groove (1), bearing faces (52)
are provided which are actively connected to said blade root and
are oriented parallel to the rotor axis (4), and adjacently
inserted moving blades (3) come into a loose force-exposed
connection directly or indirectly with one another, in each case
within the circumferential groove (1), via the bearing faces (52)
oriented parallel to the rotor axis (4).
2. The device as claimed in claim 1, characterized in that an
intermediate gap (7), in which is introduced a shim (5) having the
bearing faces (52), is provided radially within the circumferential
groove (1) between the blade root (36) and the rotor (2), the shim
(5) extending beyond the two side flanks (33, 34) in the
circumferential direction.
3. The device as claimed in claim 2, characterized in that the shim
(5) has a connection means (6) by which the shim (5) is capable of
being connected releasably firmly to the blade root (36).
4. The device as claimed in claim 3, characterized in that the
connection means (6) is a force-exposed bolt (61) which engages
from the sides of the shim (5) into a recess (64) provided
correspondingly within the blade root (36).
5. The device as claimed in claim 2, characterized in that the shim
(5) is joined firmly to the blade root (36) or is connected in one
piece to the blade root (36).
6. The device as claimed in one of claims 2 to 5, characterized in
that the shim (5) is designed in the manner of an "H", the
connecting limb (51) of which is oriented essentially parallel to
the side flanks (33, 34) of the platform (31) and has four bearing
faces (52) oriented parallel to the rotor axis (4).
7. The device as claimed in one of claims 1 to 6, characterized in
that, in the state in which the moving blade (3) is joined to the
rotor (2), that surface of the platform (31) which is directed
radially to the blade leaf (32) is flush with said rotor.
8. The device as claimed in one of claims 1 to 7, characterized in
that an intermediate piece which is flush with the rotor (2) is
inserted between two adjacent moving blades (3) into the
circumferential groove (1) and fits snugly, essentially free of
force, against the side flanks (33, 34) of the platform (31) of the
two adjacent moving blades (3).
9. The device as claimed in one of claims 1 to 8, characterized in
that the platform (31) has a rhombically designed shape in which
the side flanks (33, 34) extend along the width of the blade leaf
(32).
10. The device as claimed in one of claims 1 to 9, characterized in
that at least one intermediate piece is inserted between two
adjacent moving blades (3) within the circumferential groove (1)
and has a blade root (36) and also a platform (31) which is flush
with the rotor (2) and with the platforms (31) of two adjacent
moving blades (3).
Description
TECHNICAL FIELD
[0001] The invention relates to a device for fastening a moving
blade to the rotor of a thermal turbomachine according to the
preamble of claim 1.
PRIOR ART
[0002] Moving blades which are fastened in circumferential grooves
on rotors of turbomachines are to be positioned in a suitable way
as a function of the respective flow conditions, but, in
particular, are to be secured reliably against coming loose from
the circumferential groove completely while the turbomachines are
in operation as a result of maladjustments which may possibly
occur.
[0003] There is the risk of individual moving blades coming loose
completely from the respective fastening measures when the moving
blades inserted within the circumferential grooves and fastened in
a way known per se are capable of being displaced unevenly along
the circumferential groove on the rotor in the circumferential
direction within the respective assembly play. Owing to peripheral
maladjustments of this kind in the case of a multiplicity of moving
blades inserted along the circumferential groove, a considerable
gap may be established between two adjacent moving blades, such a
gap being sufficiently large for a moving blade to be capable of
coming loose from the circumferential groove as a result of radial
twisting, thus causing considerable damage to the entire
turbomachine plant.
[0004] Securing measures, known per se, against individual moving
blades coming loose independently from the circumferential groove
are concerned, in general, with reducing the play between two
adjacent blade roots within the circumferential groove in the
circumferential direction. Use is made, for this purpose, of
special intermediate pieces which can fill the play which has
remained in a circumferential direction from assembly, the
intermediate pieces having to be installed very closely together in
the remaining intermediate gap.
[0005] The use of specially shaped intermediate pieces, which
reduce the assembly-related play in the circumferential direction
to an amount which is very much smaller than would be necessary for
the free thermal expansion of the individual moving blades along
the circumferential groove, gives rise, when the turbomachine is in
operation, to thermally induced constraints which are brought about
at least longitudinally in the circumferential direction between
the individual adjacent moving blades. If the blade roots of the
individual moving blades or the platforms provided, as a rule,
between the blade roots and blade leaves are designed to be
contoured obliquely in such a way that two adjacent moving blades
come into contact via oblique bearing faces oriented with respect
to the rotor axis, the abovementioned thermally induced mechanical
constraints lead, within the bearing faces oriented obliquely to
the rotor axis, to additional axial forces which lead to a
distortion of the rotor and consequently to vibrations.
[0006] Irrespective of the design of the platforms of respective
moving blades, it is also conceivable that two blade roots arranged
adjacently within the circumferential groove have blade-root flanks
running obliquely to the rotor axis and are contiguous with one
another, the vibration phenomena explained above occurring in the
same way.
[0007] U.S. Pat. No. 4,684,325 describes generic turbine moving
blades which, in a multiplicity lined up with one another along the
circumferential groove, are directly contiguous with one another
via the side flanks of rhombically designed platforms. The rhombic
design of the platforms, on the one hand, is due to the oblique
position of the respective turbine leaf in relation to the
throughflow direction and, on the other hand, is motivated by an
increase in the packing density of moving blades to be arranged
along the circumferential groove. If, then, due to the operating
conditions prevailing in a turbomachine, turbine moving blades
designed in this way come into force-exposed active connection via
the bearing faces not oriented parallel to the axis of rotation,
the axial forces arising along the individual bearing faces between
the adjacent moving blades lead to unavoidable vibrations within
the rotor arrangement, due to which corresponding bearings
supporting the rotor arrangement are subjected to considerable
load. It is expedient to counteract effectively this very situation
by means of appropriate measures.
PRESENTATION OF THE INVENTION
[0008] The object on which the invention is based is to develop a
device for fastening a moving blade of the generic type described
above, in such a way that axial forces on the rotor which occur due
to thermal distortions within the moving blades are to be avoided
completely. Care is to be taken, at the same time, to show that a
coming loose of individual moving blades on account of gap
interspaces which may possibly be formed can be ruled out
completely. The measures to be taken are not to require any
structurally complicated work or precautions and, in particular,
are to allow retrofitting in the case of already existing rotor
arrangements.
[0009] According to the invention, the device for fastening a
moving blade according to the preamble of claim 1 is designed such
that, in the region of the blade root extending into the
circumferential groove, bearing faces are provided which are
actively connected to said blade root and are oriented parallel to
the rotor axis, and adjacently inserted moving blades come into a
loose force-exposed connection directly or indirectly with one
another, in each case within the circumferential groove, via the
bearing faces oriented parallel to the rotor axis.
[0010] The idea, on which the invention is based, of avoiding axial
forces occurring on the rotor due to bearing faces set obliquely to
the rotor axis between two adjacent moving blades is the avoidance
of those very oblique bearing faces. The idea of the invention is
therefore of particular importance especially in the case of moving
blades with a large angle of incidence in relation to the
throughflow direction in turbomachines, especially since the
platforms of moving blades of this kind have, not least for reasons
of space and weight, obliquely running side flanks, via which the
directly adjacent moving blades or similarly configured
intermediate pieces, inserted, as a rule, within the
circumferential groove, are contiguous with one another.
[0011] To avoid those very contact faces oriented obliquely to the
rotor axis, there is in a particularly advantageous way, for each
individual moving blade, a shim which is introduced radially
between the blade root and the rotor within the circumferential
groove and which makes at least one releasably firm active
connection with the respective blade root. The shim has bearing
faces which are oriented parallel to the rotor axis and which
project beyond the side flanks of the platform of the moving blade
in the circumferential direction of the rotor. What is achieved
thereby is that two adjacent moving blades butt against one another
solely via the bearing faces, assigned to them, of the respective
shims, said bearing faces being oriented parallel to the rotor
axis. By virtue of the geometric design of the shims, during
operation, only stresses in the circumferential direction occur on
account of differences in thermal expansion between the rotor and
the shims arranged in the circumferential direction within the
circumferential groove, but said stresses are entirely uncritical
for the rotational behavior of the rotor. Any axial forces directed
onto the rotor can be avoided because of the axial or parallel
orientation of the bearing faces in relation to the rotor axis.
[0012] The releasably firm active connection between the individual
moving-blade roots and the shims assigned to them is made from the
sides of the shim preferably by means of a force-exposed bolt,
preferably a spring-force-exposed bolt, which engages into a
corresponding recess within the blade root, as a result of which,
on the one hand, movement-free fixing of the moving blade in the
circumferential direction is ensured, but, on the other hand, there
is sufficient play between the rotor and the blade root, so that
the blade root can thermally expand essentially freely within the
circumferential groove. Thermal distortions within the blade root
seated in the circumferential groove can thereby be largely
avoided.
BRIEF DESCRIPTION OF THE INVENTION
[0013] The invention is described by way of example below, without
the general idea of the invention being restricted, by means of
exemplary embodiments, with reference to the drawings in which:
[0014] FIG. 1 shows a top view of a moving blade inserted into a
circumferential groove, with two adjacently arranged shims,
[0015] FIG. 2 shows a cross-sectional illustration along the
sectional line in FIG. 1, and
[0016] FIG. 3 shows an illustration of a detail regarding the
connection between shim and blade root.
[0017] Only the elements essential for the invention are
illustrated. Like elements are designated identically in the
various figures.
EMBODIMENTS OF THE INVENTION, COMMERCIAL PRACTICABILITY
[0018] FIG. 1 shows a top view of the circumferential groove 1 of a
rotor 2 of a thermal turbomachine, such as a compressor or a gas or
steam turbine. For the sake of greater clarity in the illustration,
only one moving blade 3 (middle position) with a rhombically
designed platform 31 and with a blade leaf 32 set at an angle
.alpha. is illustrated within the circumferential groove 2. In the
exemplary embodiment illustrated, the side flanks 33, 34 of the
platform 31 are directed essentially parallel to one another and
form the same angle of incidence .alpha. with respect to the
coparallel, marked by broken lines, to the axis of rotation 4. It
may be pointed out, merely for the sake of completeness, that the
blade leaf 32 has a wrenched design in its radial extent, that is
to say the blade tip 35 has a larger angle of incidence .alpha.
than the blade-leaf region near the platform 31.
[0019] Furthermore, the blade root, not illustrated, which is
completely covered by the platform 31 in the illustration of a top
view according to FIG. 1, is in engagement with a holding contour
which is incorporated within the circumferential groove 1 and may
be gathered in detail from the cross-sectional illustration
according to the FIG. 2, which will also be dealt with in
detail.
[0020] Provided radially below the moving blade 3, within the
circumferential groove 1, is a shim 5, a multiplicity of which are
arranged, distributed in the circumferential direction, in each
case directly contiguously with one another. The shims 5 have in
each case bearing faces 52 oriented parallel to the rotor axis 4.
For the sake of clearer illustration, the associated moving blade 3
is depicted merely in terms of the middle shim 5 in FIG. 1, said
moving blade being connected via a connection means at least
releasably firmly to the shim 5 associated with it. The connection
means 6 is connected such that the moving blade 3 is fixed securely
in the circumferential direction longitudinally in relation to the
circumferential groove 1. A special design of the connection means
4 will be dealt with below in FIG. 3.
[0021] In the exemplary embodiment according to FIG. 1, the shims 5
connectable in each case to a moving blade 3 are designed
preferably in the manner of an obliquely set "H" and have a middle
connecting web 51, in which the corresponding connection means 6
can be integrated. The side limbs directed in the circumferential
direction in relation to the circumferential groove 1 terminate in
each case in the regions having the bearing faces 52 which are
oriented parallel to the rotor axis 4 and which all project beyond
the moving blade 3 in radial projection, thus ensuring that two
moving blades arranged adjacently in the circumferential groove 1
are in force-exposed contact preferably solely in each case via the
bearing faces 52. In particular, as a result of the very high
temperatures prevailing when a turbomachine is in operation, even
the shims 5 expand in relation to the rotor material, thus giving
rise, however, to only mechanical constraints in the
circumferential direction between the individual shims 5, whereas
any axial forces on the rotor are avoided owing to the parallel
orientation of the bearing faces in relation to the rotor axis.
[0022] The idea, on which the invention is based, of avoiding axial
forces occurring on the rotor 2 due to bearing faces set obliquely
to the rotor axis 4 between two adjacent moving blades 3 is, in
general, that adjacent moving blades 3 meet only at axially
oriented bearing faces 52, irrespective of whether these bearing
faces 52 are fastened to a shim 5 or directly to the blade root 36
or are connected in another active way to the blade root 36. The
bearing faces is oriented parallel to the rotor axis project beyond
the side flanks 33, 34 of the platform 31 of the moving blade 3 in
the circumferential direction of the rotor for the inventive
purpose.
[0023] FIG. 2 illustrates a sectional diagram along the sectional
line A-A according to FIG. 1. This shim 5 assigned to the moving
blade 3 is located in an intermediate gap 7 between the blade root
36 and the rotor 2. The platform 31, the top side of which is flush
with the rotor top side, may likewise be gathered from the
cross-sectional illustration according to FIG. 2. A
spring-force-exposed bolt 7, by means of which the moving blade 3
is fixed in relation to the shim 5, is provided centrally in
relation to the blade root 36 as a connection means 6.
[0024] FIG. 3 illustrates a corresponding cross-sectional
illustration of the connection means 6. Here, the shim 5 has a
press fit by means of a sleeve 62, within which is provided a
spring element 63 which can drive a bolt 61 vertically upwards. The
bolt 61 and the sleeve 62 project, in association with the moving
blade 3, into a corresponding recess 64 within the blade root
36.
[0025] As indicated diagrammatically in FIG. 1 below the moving
blade 3, at least one intermediate piece 8 may be inserted within
the circumferential groove 1 between two moving blades 3, as a
spacer piece which has a blade root as fastening element and also a
platform which is flush with the rotor 2 and with the platforms 31
of two adjacent moving blades 3.
[0026] The measure according to the invention is suitable in a
particularly advantageous way as a retrofit set in the case of
turbomachines which are already in operation. It is expedient
merely to enlarge the axial and, if appropriate, circumferential
play in the region of the blade roots by remachining, for example
by regrinding, in order to provide sufficient space for inserting
the shims.
1 List of reference symbols 1 Circumferential groove 2 Rotor 3
Moving blade 31 Platform 32 Blade leaf 33, 34 Side flanks 35 Blade
leaf tip 36 Blade root 4 Rotor axis 5 Shim 51 Connecting web 52
Bearing faces 6 Connection means 61 Bolt 62 Sleeve 63 Spring
element 64 Recess 7 Intermediate gap 8 Intermediate piece
* * * * *