U.S. patent application number 13/390304 was filed with the patent office on 2012-06-07 for turbomachine.
This patent application is currently assigned to MTU AERO ENGINES GMBH. Invention is credited to Wilfried Weidmann.
Application Number | 20120141253 13/390304 |
Document ID | / |
Family ID | 43448339 |
Filed Date | 2012-06-07 |
United States Patent
Application |
20120141253 |
Kind Code |
A1 |
Weidmann; Wilfried |
June 7, 2012 |
TURBOMACHINE
Abstract
A turbomachine is disclosed. The turbomachine includes a housing
and a guide blade ring. An outer shroud of the guide blade ring is
divided into segments by joints, where the outer shroud is fastened
to the housing by a first fastening element for absorbing axial
force and a second fastening element independent of the first
fastening element for absorbing circumferential force. The first
fastening element and the second fastening elements enable play in
a radial direction for the segments of the outer shroud.
Inventors: |
Weidmann; Wilfried; (Erdweg,
DE) |
Assignee: |
MTU AERO ENGINES GMBH
Munich
DE
|
Family ID: |
43448339 |
Appl. No.: |
13/390304 |
Filed: |
August 5, 2010 |
PCT Filed: |
August 5, 2010 |
PCT NO: |
PCT/DE10/00927 |
371 Date: |
February 13, 2012 |
Current U.S.
Class: |
415/1 ;
415/182.1 |
Current CPC
Class: |
F01D 5/225 20130101;
F05D 2240/80 20130101; F01D 25/246 20130101; F05D 2260/30 20130101;
F01D 9/042 20130101 |
Class at
Publication: |
415/1 ;
415/182.1 |
International
Class: |
F01D 25/04 20060101
F01D025/04; F01D 25/24 20060101 F01D025/24 |
Foreign Application Data
Date |
Code |
Application Number |
Aug 14, 2009 |
DE |
10 2009 037 620.8 |
Claims
1.-11. (canceled)
12. A turbomachine, comprising: a housing; a guide blade ring,
wherein an outer shroud of the guide blade ring is divided into
segments by respective joints; a first fastening element; and a
second fastening element; wherein the outer shroud is fastened to
the housing by the first fastening element and the second fastening
element; wherein an axial force is absorbable by the first
fastening element, wherein a circumferential force is absorbable by
the second fastening element, and wherein a movement in a radial
direction for a segment of the outer shroud is enableable by the
first fastening element and the second fastening element.
13. The turbomachine according to claim 12, wherein the second
fastening element is an annular housing component that projects
radially inwardly, wherein the housing component includes a first
slot and/or a first nose which meshes with a second nose and/or a
second slot, respectively, in a component of the outer shroud that
projects radially outwardly.
14. The turbomachine according to claim 12, wherein the first
fastening element is disposed in a direction of axial force behind
a component of the outer shroud that transmits axial force.
15. The turbomachine according to claim 14, wherein the axial force
is transmitted by the component by several separate contact
surfaces disposed between the guide blade ring and the first
fastening element.
16. The turbomachine according to claim 12, wherein the first
fastening element is annular and is positively connected with the
housing.
17. The turbomachine according to claim 16, wherein a groove in the
annular first fastening element is positively connected with a
mounting extension on the housing.
18. The turbomachine according to claim 17, wherein an inside
radius of the mounting extension is larger than an outside radius
of the outer shroud.
19. The turbomachine according to claim 12, wherein the first
fastening element is disposed in a direction of axial force in
front of a component of the guide blade ring that transmits axial
force.
20. The turbomachine according to claim 19, wherein the first
fastening element is radially elastic.
21. The turbomachine according to claim 19, wherein the first
fastening element is positively fastened to the housing and to the
guide blade ring.
22. The turbomachine according to claim 16, wherein the positive
connection is secured by a safety wire.
23. The turbomachine according to claim 12, wherein the
turbomachine is a gas turbine.
24. The turbomachine according to claim 12, wherein a movement of
the guide blade ring in an axial direction is enableable by the
second fastening element.
25. A method for absorbing forces in a turbomachine, wherein the
turbomachine comprises: a housing; a guide blade ring, wherein an
outer shroud of the guide blade ring is divided into segments by
respective joints; a first fastening element; and a second
fastening element; wherein the outer shroud is fastened to the
housing by the first fastening element and the second fastening
element; and comprising the steps of; absorbing an axial force by
the first fastening element; absorbing a circumferential force by
the second fastening element; and radially moving a segment of the
outer shroud.
Description
[0001] This application claims the priority of International
Application No. PCT/DE2010/000927, filed Aug. 5, 2010, and German
Patent Document No. 10 2009 037 620.8, filed Aug. 14, 2009, the
disclosures of which are expressly incorporated by reference
herein.
BACKGROUND AND SUMMARY OF THE INVENTION
[0002] The invention relates to a turbomachine, in particular a gas
turbine, comprising a housing and at least one guide blade ring,
the outer shroud of which is divided into segments by joints.
[0003] Such a turbomachine is known from German Patent Document No.
DE 198 07 247 C2 for example. The guide blade rings are fastened to
the housing of the turbomachine with mounting pegs in the region of
its outer shroud, wherein the segments of the guide blade ring are
radially freely moveable in the region of the outer shroud. This
type of mounting is also designated as spoke centering. In the
process, the mounting pegs absorb all the forces transmitted by the
guide blade ring onto the housing, in particular in the
circumferential direction and axial direction.
[0004] The object of the invention is creating an improved
fastening of a guide blade ring on the housing of the turbomachine,
which enables a radial movability of the guide blade ring segments
with a simultaneously lower load for the fastening elements.
[0005] According to the invention, a turbomachine of the type
described at the outset is provided, wherein the outer shroud of
the guide blade ring is fastened to the housing by means of a first
fastening element for absorbing axial force and a second fastening
element independent of the first fastening element for absorbing
circumferential force and wherein the first and the second
fastening elements enable play in the radial direction for the
segments of the outer shroud.
[0006] In this way the axial force and the circumferential force
are absorbed by means of separate, independent fastening elements.
The load of the fastening elements is thereby reduced, and the
fastening elements may be designed optimally for their respective
functions. The axial force and circumferential force are orthogonal
to each other, thereby enabling an independent absorption of the
force, while, at the same time, forces in the radial direction are
not absorbed by the fastening elements, thereby enabling play in
the radial direction for the guide blade ring.
[0007] According to a preferred embodiment, the fastening element
for absorbing circumferential force is formed by an essentially
annular housing component that projects radially inwardly, wherein
first slots and/or first noses are provided in the housing
component, which mesh with second noses or second slots in a
component of the outer shroud that projects radially outwardly and
transmits circumferential force, such that the guide blade ring is
fixed in the circumferential direction and the second nose or the
second slot has play in the radial direction. This enables a simple
geometry of the components transmitting circumferential force and
therewith the smallest possible required installation space.
Because of a symmetrical or asymmetrical arrangement of the noses
and slots in the circumferential direction, the installation
position of the guide blade ring can be determined.
[0008] It is possible for the fastening element for absorbing axial
force to be arranged in the direction of force behind a component
of the outer shroud that transmits axial force. This makes it
possible to transmit compressive forces to the fastening
element.
[0009] The axial force is preferably transmitted by means of
several separate contact surfaces between the guide blade ring and
the fastening element for absorbing axial force. In this way, it is
possible to reduce the friction between the fastening element for
absorbing axial force and the guide blade ring.
[0010] The fastening element for absorbing axial force is
preferably annular and forms a positive connection with the
housing. This enables, for example, a rotationally symmetrical
embodiment of the fastening element for absorbing axial force.
[0011] The positive connection may be formed by a mounting
extension on the housing and a groove in the annular fastening
element for absorbing axial force.
[0012] The inside radius of the mounting extension is preferably
larger than the outside radius of the outer shroud. This enables an
assembly of the turbomachine in the axial direction.
[0013] According to another preferred embodiment, several fastening
elements for absorbing axial force are provided, which are arranged
in the direction of force in front of a component of the guide
blade ring that transmits axial force. In this way, the axial force
is transmitted by the guide blade ring by means of tensile forces
to the fastening elements.
[0014] The fastening elements for absorbing axial force are
preferably radially elastic elements. This guarantees the
movability of the guide blade ring segments in the radial
direction.
[0015] The fastening elements for absorbing axial force may be
positively fastened to the housing and to the guide blade ring.
[0016] The preferably positive connection between the fastening
element for absorbing axial force and the housing may be secured by
a safety wire. In this way, it is possible to prevent an
inadvertent detachment of the connection between the fastening
element for absorbing axial force and the housing.
[0017] Additional features and advantages of the invention are
disclosed in the following description and the following drawings
to which reference is made.
BRIEF DESCRIPTION OF THE DRAWINGS
[0018] FIG. 1 illustrates a guide blade ring;
[0019] FIG. 2 is a sectional view of a turbomachine with two guide
blades and one rotor blade;
[0020] FIG. 3 is a sectional view of a turbomachine with a radially
movable guide blade;
[0021] FIG. 4 is a sectional view of a turbomachine according to a
first embodiment of the invention;
[0022] FIG. 5 is a guide blade ring segment of the turbomachine
according to FIG. 4; and
[0023] FIG. 6 is a turbomachine according to a second embodiment of
the invention in a sectional view.
DETAILED DESCRIPTION OF THE DRAWINGS
[0024] FIGS. 1 to 3 depict a turbomachine 10 having a guide blade
ring 12. The guide blade ring has an outer shroud 16, which is
divided into individual segments 14 by joints. As indicated in FIG.
1 and FIG. 3 by the double-sided arrows, the segments 14 of the
outer shroud 16 may move in the radial direction.
[0025] FIG. 2 shows a section of turbomachine 10 with two guide
blade rings 12 and a rotor blade 18. The two guide blade rings 12
are connected by a honeycomb carrier 20.
[0026] FIG. 3 depicts a guide blade ring 12 between two rotor
blades 18. The guide blade ring 12 and the honeycomb carrier 20
connected therewith are fastened in a housing 22 of the
turbomachine 10, wherein the fastening (not shown in FIG. 3) for
the segments 14 of the outer shroud 16 of the guide blade ring 12
enables play in the radial direction for the spoke-centered
fastening. The outer shroud 16 of the guide blade ring 12 may move
in this case in the radial direction between the radially inward
and outward positions shown with dashed lines.
[0027] The various guide blades are preferably integrally connected
to the inner shroud 17 of the guide blade ring 12.
[0028] FIG. 4 depicts a first embodiment of the fastening of the
guide blade ring 12 on the housing 22 of the turbomachine 10. A
fastening element 24 for absorbing circumferential force is an
essentially annular housing component 26 that projects radially
inwardly in which several slots are provided. The guide blade ring
12 has a component 28 that projects radially outwardly in the
region of the outer shroud 16, which forms noses, which are
positively connected to the slots in the housing component 26 and
fix the guide blade ring 12 in the circumferential direction.
Naturally, it is also possible for the housing component 26 to have
noses which engage in slots in the component 28 of the guide blade
ring 12 or for noses and slots to be provided both on the housing
component 26 as well as on the component 28 of the guide blade ring
12, which mutually mesh to produce the positive connection.
[0029] A force acting on the guide blade ring 12 in the
circumferential direction is transmitted by the component 28 by
means of the meshing noses and slots to the housing component 26,
which absorbs the circumferential force and thereby fixes the guide
blade ring 12 in the housing 22 of the turbomachine 10 in the
circumferential direction.
[0030] Forces acting in the axial direction are not absorbed by the
fastening element 24 for absorbing circumferential force. The
fastening element 24 for absorbing circumferential force allows on
its own a movement of the guide blade ring 12 in one or both axial
directions.
[0031] A fastening element 30 for absorbing axial force is arranged
in the direction of force behind a component 32 of the guide blade
ring 12 that transmits axial force. The direction of the axial
force points from left to right in the depicted embodiment. In this
arrangement, the axial force is transmitted as compressive force
from the guide blade ring 12 by means of the component 32 that
transmits axial force to the fastening element 30 for absorbing
axial force.
[0032] The component 32 transmitting axial force has several
separate contact surfaces 34, via which the axial force is
transmitted between the guide blade ring 12 and the fastening
element 30 for absorbing axial force. FIG. 5 shows a segment 14 of
the shroud 16 of the guide blade ring 12, which has a contact
surface 34 on each of its ends lying in the circumferential
direction. Naturally, it is also possible for the contact surface
34 to extend over the entire circumference of the guide blade ring
12.
[0033] A special surface structure or a special coating, for
example an armoring, may be provided for the contact surfaces 34 in
order to keep the friction between guide blade ring 12 and the
fastening element 30 for absorbing axial force as low as
possible.
[0034] The fastening element 30 for absorbing axial force, which is
slotted for mounting on the circumference, is annular and has a
groove running in the circumferential direction on its outside
radius, the groove being used to positively connect it to a
mounting extension 36, which is formed on the housing 22. The
inside radius of the mounting extension 36 is larger than the
outside radius of the guide blade ring 12. In this way, the guide
blade ring 12 is inserted in the axial direction into the closed
housing 22 during assembly of the turbomachine 10.
[0035] During assembly of the turbomachine 10, after insertion of
the guide blade ring 12 into the housing 22, the annular fastening
element 30 for absorbing axial force, which is slotted for mounting
on the circumference, is inserted on the mounting extension 36 of
the housing 22, wherein the mounting extension 36 positively
engages in the groove of the fastening element 30.
[0036] The inside radius of the fastening element 30 for absorbing
axial force is smaller than the outside radius of the guide blade
ring 12. In this way, the guide blade ring 12 is adjacent with the
contact surfaces 34 to the fastening element 30 for absorbing axial
force and the guide blade ring 12 is fixed in its axial position by
means of the fastening element 30.
[0037] In the depicted embodiment, the component 32 that transmits
axial force in the direction opposite from the axial force is
adjacent to the fastening element 24 for absorbing circumferential
force. In this way, the axial position of the guide blade ring 12
is exactly defined by the two fastening elements 24, 30 for
absorbing circumferential force and for absorbing axial force,
wherein, because of the direction of the axial force acting during
normal operation of the turbomachine, the axial force is absorbed
only by the fastening element 30 for absorbing axial force.
[0038] The two fastening elements 24, 30 for absorbing
circumferential force and for absorbing axial force together form a
guide for the components 28, 32 of the segment 14 of the outer
shroud 16 of the guide blade ring 12, which enables a movement of
the segment 14 in the radial direction.
[0039] The positive connection between the fastening element 30 for
absorbing axial force and the mounting extension 36 of the housing
22 is secured by a safety wire 38. It is also possible for the
fastening element 30 for absorbing axial force to be secured
directly on the housing 22 by means of the safety wire 38.
[0040] A second embodiment of the fastening element 30 for
absorbing axial force is depicted in FIG. 6. The fastening element
30 for absorbing axial force in this embodiment is arranged in the
direction of force in front of a component 32 of the guide blade
ring 12 that transmits axial force, whereby tensile forces may be
transmitted between the component 32 transmitting axial force and
the fastening element 30 for absorbing axial force.
[0041] One or more fastening elements 30 for absorbing axial force
are provided for each segment 14 of the outer shroud of the guide
blade ring 12. The fastening elements 30 are positively fastened to
the housing 22 and to the guide blade ring 12. The positive
connection to the fastening element 30 is secured on the housing 22
by means of a safety wire 38. The positive connection between the
fastening element 30 and the guide blade ring 12 is secured by a
clamp 40, which may be part of the honeycomb carrier 20 or a
separate part.
[0042] The fastening elements 30 for absorbing axial force are
radially elastic elements. The end of the fastening element 30 for
absorbing axial force that is fastened to the guide blade ring 12
may move along a circular path around the end of the fastening
element 30 fastened to the housing 22, wherein, in the case of
small angles, the movement takes place in the radial direction in
an approximately linear manner.
[0043] It is possible for the fastening elements 30 for absorbing
axial force to be completely separate components. Alternatively,
several and in particular all fastening elements 30 may be
connected with one another on the end fastened to the housing 22,
thereby forming an essentially annular fastening element 30 having
several radially elastic extensions, each of which is fastened on
its end to the guide blade ring 12.
[0044] In this embodiment, an essentially frictionless radial
movement of the segments 14 of the guide blade ring 12 is possible
independent of the axial force. Because no fastening elements 24,
30 are arranged in the direction of force behind the guide blade
ring, a simple assembly in the axial direction is possible.
[0045] The housing component 26 that projects radially inwardly,
which forms the fastening element 24 for absorbing circumferential
force, as well as the component 28 of the guide blade ring 12 that
transmits circumferential force is analogous in terms of design and
function to the embodiment described in FIG. 4.
* * * * *