U.S. patent application number 12/096759 was filed with the patent office on 2009-01-29 for turbomachine having axial rotor blade securing.
This patent application is currently assigned to MTU Aero Engines GmbH. Invention is credited to Wilfried Weidmann, Moritz Wirth.
Application Number | 20090028712 12/096759 |
Document ID | / |
Family ID | 37887331 |
Filed Date | 2009-01-29 |
United States Patent
Application |
20090028712 |
Kind Code |
A1 |
Weidmann; Wilfried ; et
al. |
January 29, 2009 |
TURBOMACHINE HAVING AXIAL ROTOR BLADE SECURING
Abstract
A rotor of a turbine machine having several rotor blade rings
positioned in succession in the axial direction, is disclosed. Each
rotor blade ring has a rotor base body with several rotor blades
anchored by blade footings in axial grooves of the rotor base body
that extend essentially in the axial direction and, in their
anchored position in the rotor base body, are secured against
displacement in the axial direction. The rotor blades of at least
one rotor blade ring have hook-like securing elements, which, in
the anchored position on a low-pressure side of the rotor blade
ring, abut the rotor base body. The hook-like securing elements,
between the rotor base body and a sealing element, which extends
between the rotor base body and a rotor base body of a rotor blade
ring that connects on the low-pressure side, are fixed in the axial
direction on both sides.
Inventors: |
Weidmann; Wilfried; (Erdweg,
DE) ; Wirth; Moritz; (Berlin, DE) |
Correspondence
Address: |
CROWELL & MORING LLP;INTELLECTUAL PROPERTY GROUP
P.O. BOX 14300
WASHINGTON
DC
20044-4300
US
|
Assignee: |
MTU Aero Engines GmbH
Munich
DE
|
Family ID: |
37887331 |
Appl. No.: |
12/096759 |
Filed: |
December 5, 2006 |
PCT Filed: |
December 5, 2006 |
PCT NO: |
PCT/DE2006/002150 |
371 Date: |
October 6, 2008 |
Current U.S.
Class: |
416/220R |
Current CPC
Class: |
F05D 2240/56 20130101;
F01D 11/001 20130101; F01D 5/3007 20130101; F05D 2240/55
20130101 |
Class at
Publication: |
416/220.R |
International
Class: |
F01D 5/30 20060101
F01D005/30; F01D 11/00 20060101 F01D011/00 |
Foreign Application Data
Date |
Code |
Application Number |
Dec 10, 2005 |
DE |
10 2005 059 084.5 |
Claims
1-7. (canceled)
8. A turbomachine having several rotor blade rings positioned in
succession in an axial direction that are assigned to a turbine or
a compressor, wherein each rotor blade ring has a rotor base body
with several rotor blades, and wherein the rotor blades of a rotor
blade ring are anchored by respective blade footings in axial
grooves of a rotor base body of the rotor blade ring that extend in
the axial direction and, in an anchored position in the rotor base
body, are secured against displacement in the axial direction, and
wherein the rotor blades of at least one rotor blade ring have a
hook-like securing element, which, in the anchored position on a
low-pressure side of the rotor blade ring, abut the rotor base
body, wherein the hook-like securing element between the rotor base
body of the rotor blade ring and a sealing element, which extends
between the rotor base body and a rotor base body of a rotor blade
ring that connects on the low-pressure side, are fixed in the axial
direction on both sides.
9. The turbomachine according to claim 8, wherein the hook-like
securing element between the rotor base body of the rotor blade
ring and the sealing element is clamped in the axial direction on
both sides.
10. The turbomachine according to claim 8, wherein the sealing
element is fastened bayonet-like via a section adjacent to the
hook-like securing element on the rotor base body of the rotor
blade ring.
11. The turbomachine according to claim 10, wherein the section of
the sealing element fixes the hook-like securing element of the
rotor blade in the axial direction on both sides.
12. The turbomachine according to claim 10, wherein the section of
the sealing element has a projection, which is insertable via an
opening into a groove of the rotor base body in the axial
direction, wherein the sealing element is rotatable in a
circumferential direction following the bayonet-like fastening of
same.
13. The turbomachine according to claim 8, wherein the sealing
element is fastened via a projection between a flange of the rotor
base body and a flange of the rotor base body of the rotor blade
ring that connects on the low-pressure side.
14. The turbomachine according to claim 13, wherein a section of
the sealing element adjacent to the projection fixes the hook-like
securing element of the rotor blades in the axial direction on both
sides.
15. A turbomachine, comprising: a rotor blade ring having a rotor
blade and a rotor base body, wherein the rotor blade is anchored in
an axial groove of the rotor base body; and wherein the rotor blade
includes a hook-like securing element which is secured between the
rotor base body and a sealing element which extends between the
rotor base body and a second rotor base body of a second rotor
blade ring.
16. The turbomachine according to claim 15, wherein the hook-like
securing element extends in a radially inward direction of the
rotor blade ring.
17. The turbomachine according to claim 15, wherein the hook-like
securing element is disposed on a low-pressure side of the rotor
blade and wherein a portion of the hook-like securing element
extends beyond a radially inner end of the rotor blade.
18. The turbomachine according to claim 15, wherein the sealing
element includes a section that is fastened bayonet-like on the
rotor base body.
19. The turbomachine according to claim 18, wherein the section
abuts the hook-like securing element.
20. The turbomachine according to claim 18, wherein the section has
a projection which is insertable into a groove of the rotor base
body.
21. The turbomachine according to claim 15, wherein the sealing
element includes a projection that is fastened between a flange of
the rotor base body and a flange of the second rotor base body.
22. The turbomachine according to claim 15, further comprising a
guide vane ring disposed between the rotor blade ring and the
second rotor blade ring.
23. The turbomachine according to claim 22, wherein the guide vane
ring includes a seal and wherein the sealing element engages with
the seal.
24. The turbomachine according to claim 23, wherein the seal is a
brush seal.
25. The turbomachine according to claim 23, wherein the seal seals
a radial inner gap defined by the rotor blade rings and the guide
vane ring.
26. The turbomachine according to claim 15, wherein the hook-like
securing element which is secured between the rotor base body and a
sealing element is fixed in an axial direction of the turbomachine.
Description
[0001] This application claims the priority of International
Application No. PCT/DE2006/002150, filed Dec. 5, 2006, and German
Patent Document No. 10 2005 059 084.5, filed Dec. 10, 2005, 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.
[0003] Turbomachines, in particular gas turbines, have several
rotor blade rings positioned in succession in the axial direction
both in the region of a turbine as well as in the region of a
compressor, wherein each rotor blade ring has in particular a
disk-shaped rotor base body and several rotor blades rotating with
the rotor base body. The present invention relates to a
turbomachine, in particular a gas turbine, in which the rotor
blades of the rotor blade rings are fastened by their blade
footings in grooves, which run essentially in the axial direction
of the rotor base body, i.e., in so-called axial grooves. In this
case, the rotor blades of the rotor blade rings must be secured, in
their assembly position or in their anchored position, in the axial
grooves of the rotor base body against displacement in the axial
direction.
[0004] In practice, normally so-called wire securing devices are
used to axially secure the rotor blades of a rotor blade ring that
are fastened in axial grooves of a rotor base body via their blade
footings. In the case of these types of wire securing devices, a
wire-shaped securing element is threaded into a groove, which is
embodied between the blade footings of the rotor blades and the
rotor base body in order to thereby secure the rotor blades against
displacement in the axial direction. A separate wire-shaped
securing element is normally used in this process for each rotor
blade, which results in an intricate assembly of the wire securing
devices. In addition, wire securing devices are subject to
tolerances.
[0005] So-called securing plates, which are also designated as
closing plates or locking plates, are used in the case of another
variation known from the prior art for axially securing rotor
blades. These types of securing plates are guided into a ring
groove of the rotor base body as well as into a ring groove of the
rotor blades anchored in the rotor base body. These types of
securing plates increase the load on the blade footing of the rotor
blades and therefore the boundary stress that occurs.
[0006] Starting herefrom, the present invention is based on the
objective of creating a novel turbomachine.
[0007] According to the invention, the rotor blades of at least one
rotor blade ring have hook-like securing elements, which, in the
anchored position on a low-pressure side of the rotor blade ring,
abut the rotor base body of same, wherein the hook-like securing
elements between the rotor base body of the rotor blade ring and a
sealing element, which extends between the rotor base body and a
rotor base body of a rotor blade ring that connects on the
low-pressure side, are fixed in the axial direction on both
sides.
[0008] In terms of the invention at hand, the rotor blades that
must be secured in their axial position have hook-like securing
elements, which are fixed between the rotor base body of the
respective rotor blade ring and the sealing element by clamping on
both sides. This provides for completely novel securing of the
rotor blades that are guided into axial grooves against unintended
displacement in the axial direction, which is characterized by
simple assembly and disassembly, and with whose assistance leakage
flows in the radially inner region of the rotor blade rings can
also be minimized. In addition, the inventive axial securing of the
rotor blades does not increase the stress acting on the blade
footings of same.
[0009] The sealing element is preferably fastened bayonet-like via
a section adjacent to the hook-like securing elements on the rotor
base body of the rotor blade ring, whose rotor blades must be
secured against displacement in the axial direction, wherein this
section of the sealing element fixes the hook-like securing
elements of the rotor blades in the axial direction on both
sides.
BRIEF DESCRIPTION OF THE DRAWINGS
[0010] Preferred developments of the invention are yielded from the
following description. Without being limited hereto, exemplary
embodiments of the invention are explained in greater detail on the
basis of the drawings. The drawings show:
[0011] FIG. 1 is a section of an inventive gas turbine according to
a first exemplary embodiment of the invention; and
[0012] FIG. 2 is a section of an inventive gas turbine according to
a second exemplary embodiment of the invention.
DETAILED DESCRIPTION OF THE DRAWINGS
[0013] FIG. 1 depicts a section of a turbine 10 of an inventive gas
turbine, namely of a gas turbine aircraft engine, in the region of
two rotating rotor blade rings 11, 12 arranged in succession in the
axial direction, wherein a stationary guide vane ring 13 is
arranged between the two depicted rotor blade rings 11, 12. The
turbine 10 is flowed through in the axial direction in the
direction of the arrow 14 depicted in FIG. 1.
[0014] Each of the two rotor blade rings 11, 12 depicted in FIG. 1
has a preferably disk-shaped rotor base body 15 or 16, wherein
rotor blades 17 or 18 of the rotor blade rings 11 or 12 are
fastened or anchored by blade footings 19 or 20 in so-called axial
grooves of the respective rotor base body 15 or 16. The axial
grooves of the rotor base bodies 15 or 16, in which the rotor
blades 17 or 18 are anchored via their blade footings 19 or 20, run
essentially in the axial direction of the turbine 10. Blade pans
21, 22 attach radially outside to the blade footings 19, 20 of the
rotor blades 17, 18, wherein blade footing platforms 23, 24 are
embodied between the blade footings 19, 20 and blade pans 21, 22 of
the rotor blades 17, 18.
[0015] The guide vane ring 13 positioned between the two rotor
blade rings 11, 12 is comprised of several stationary guide vanes
25, wherein a platform 27 is embodied on a radial inner end of the
blade pans 26 of the stationary guide vanes 25, on which platform a
seal 28 in the form of a brush seal is fastened in the exemplary
embodiment in FIG. 1, wherein other seal types can also be used.
According to FIG. 1, the stator-side seal 28 cooperates with a
rotor-side sealing element 29 positioned between the two rotor
blade rings 11, 12 in order to thereby seal a radial inner gap
between the rotating rotor blade rings 11, 12 and the stationary
guide vane ring 13.
[0016] To secure the rotor blades 17 of the rotor blade ring 11 in
their anchored position in the axial grooves of the corresponding
rotor base body 15 and consequently to secure the same against
undesired displacement in the axial direction, the rotor blades 17
of the rotor blade ring 11 are assigned hook-like securing elements
30, which, in the anchored position on a low-pressure side of the
rotor blade ring 11, abut the rotor base body 15 of same. As FIG. 1
shows, the securing elements 30 are assigned to the blade footings
19 of the rotor blades 17 and abut the rotor base body 15 of the
rotor blade ring 11 with a radially inner section 31.
[0017] The hook-like securing elements 30 for axially securing the
rotor blades 11 between the rotor base body 15 of the rotor blade
ring 11 and the sealing element 29, which extends between the rotor
base body 15 of the rotor blade ring 11 and the rotor base body 16
of a rotor blade ring 12 that connects on the low-pressure side,
are fixed in the axial direction on both sides. According to FIG.
1, the hook-like securing elements 30 between the rotor base body
15 of the rotor blade ring 11, which secures the rotor blades 17
with respect to their axial position, and the rotor-side sealing
element 29 are clamped on both sides.
[0018] In the exemplary embodiment in FIG. 1, the rotor-side
sealing element 29 is fastened bayonet-like via a section 32, which
is positioned adjacent to the hook-like securing elements 30 of the
rotor blades 17, on the rotor base body 15 of the rotor blade ring
11. The section 32 of the sealing element 29 has a nose-like
projection 33, which can be inserted via an opening (not shown)
into a groove 34 of the rotor base body 15 in the axial direction.
After inserting the projection 33 of the sealing element 29 via the
opening into the groove 34 of the rotor base body 15, the sealing
element 29 can be rotated in the circumferential direction in order
to thereby fasten the bayonet-like fastening of the sealing element
29 on the rotor base body 15 of the rotor blade ring 11, whose
rotor blades 17 must be secured against displacement in the axial
direction. When rotating in the circumferential direction for the
bayonet-like fastening of the sealing element 29 on the rotor base
body 15 of the rotor blade ring 11, the hook-like securing elements
30 between the rotor base body 15 and the sealing element 29 are
clamped in order to thereby fix the rotor blades 17 and 18 on both
sides. The section 32 of the sealing element 29, which is used for
the bayonet-like fastening of the sealing element 29 on the rotor
base body 15 of the rotor blade ring 11, fixes the rotor blades 11
via the hook-like securing elements 30 in the axial direction on
both sides.
[0019] FIG. 2 shows another exemplary embodiment of an inventive
gas turbine, wherein the exemplary embodiment in FIG. 2 also
depicts a section of a turbine 35. The exemplary embodiment in FIG.
2 corresponds in terms of many details to the exemplary embodiment
in FIG. 1. As a result, in order to avoid unnecessary repetition,
the same reference numerals are used for the same components. In
the following, only the details of the exemplary embodiment in FIG.
2 that differ from the exemplary embodiment in FIG. 1 will be
addressed.
[0020] In the exemplary embodiment in FIG. 2, the rotor blades 17
have hook-like securing elements 30 just like the exemplary
embodiment in FIG. 1, which, in the anchored position on a
low-pressure side of the rotor blade ring 11 abut the rotor base
body 15 of same. The hook-like securing elements 30 in this case
are again fixed between the rotor base body 15 of the rotor blade
ring 11 and the sealing element 29 in the axial direction on both
sides, wherein the sealing element 29 extends between the rotor
base body 15 of the rotor blade ring 11, whose rotor blades must be
secured against displacement in the axial direction, and the rotor
base body 16 of a rotor blade ring 12 that connects on the
low-pressure side.
[0021] In the exemplary embodiment in FIG. 2, the sealing element
29 is not connected bayonet-like to the rotor base body 15 of the
rotor blade ring 11 as in the exemplary embodiment in FIG. 1,
rather a projection 36 of the sealing element 29 is fastened via
screws between two flanges 37 and 38 of the rotor base bodies 15
and 16 that are positioned in succession in the axial direction. A
section 39 of the sealing element 29 that connects to the
projection 36 is used for fixing the hook-like securing elements 30
on both sides between the rotor base body 15 and the sealing
element 29 in order to thereby prevent unintended displacement of
the rotor blades 17 of the rotor blade ring 11 in the axial
direction.
[0022] In terms of the present invention, rotor blades of rotor
blade rings inserted into axial grooves are secured against
undesired axial displacement in that hook-like securing elements
assigned to the blade footings of the rotor blades are fixed
between the rotor base body of the rotor blade ring and a
rotor-side sealing element of a so-called inner-air seal, namely in
the axial direction on both sides, wherein all blades of two
adjacent rotor blade rings 11 and 12 are secured axially by a
component 29. In the process, the sealing element is fastened
preferably bayonet-like on the corresponding rotor base body. The
advantage of the invention is that the rotor blades can be
assembled or disassembled relatively simply from the rotor base
body. All rotor blades of a rotor blade ring in this case can be
fixed jointly via a sealing element in the axial direction.
* * * * *