U.S. patent application number 12/733382 was filed with the patent office on 2010-08-12 for multilayer shielding ring for a flight driving mechanism.
This patent application is currently assigned to MTU Aero Engines GmbH. Invention is credited to Wilfried Weidmann.
Application Number | 20100202872 12/733382 |
Document ID | / |
Family ID | 40221258 |
Filed Date | 2010-08-12 |
United States Patent
Application |
20100202872 |
Kind Code |
A1 |
Weidmann; Wilfried |
August 12, 2010 |
MULTILAYER SHIELDING RING FOR A FLIGHT DRIVING MECHANISM
Abstract
A shielding (6) of a turbine housing (3) of an aircraft engine
against radial escape of blade fragments, especially for a
high-speed low-pressure turbine, is characterized in that the
shielding (6) is embodied as a rigid ring-shaped component of
several layers (8). Through the decoupling of the containment
function from the design of the turbine exhaust gas channel, which
is fabricated as a cast part, the disadvantages of the prior art
are avoided. Particularly, the design of the turbine exhaust gas
channel can be carried out in a cost- and weight-optimized
manner.
Inventors: |
Weidmann; Wilfried; (Erdweg,
DE) |
Correspondence
Address: |
FASSE PATENT ATTORNEYS, P.A.
P.O. BOX 726
HAMPDEN
ME
04444-0726
US
|
Assignee: |
MTU Aero Engines GmbH
Muenchen
DE
|
Family ID: |
40221258 |
Appl. No.: |
12/733382 |
Filed: |
August 27, 2008 |
PCT Filed: |
August 27, 2008 |
PCT NO: |
PCT/DE2008/001417 |
371 Date: |
February 24, 2010 |
Current U.S.
Class: |
415/9 |
Current CPC
Class: |
F05D 2240/14 20130101;
F01D 21/045 20130101 |
Class at
Publication: |
415/9 |
International
Class: |
F01D 25/24 20060101
F01D025/24 |
Foreign Application Data
Date |
Code |
Application Number |
Sep 7, 2007 |
DE |
10 2007 042 767.2 |
Claims
1. Shielding (6) of a turbine housing (3) of an aircraft engine
against radial escape of blade fragments, especially for a
high-speed low-pressure turbine (1), characterized in that the
shielding (6) is embodied as a rigid ring-shaped component of
several layers (8).
2. Shielding (6) according to patent claim 1, characterized in that
the shielding is arranged on the turbine exhaust gas channel.
3. Shielding (6) according to patent claim 1, characterized in that
the shielding (6) is embodied as a forged component.
4. Shielding (6) according to patent claim 1, characterized in that
the shielding (6) is arranged within the turbine housing (3).
5. Shielding (6) according to patent claim 1, characterized in that
the shielding (6) is embodied as a flow guiding element.
6. Shielding (6) according to patent claim 1, characterized in that
the shielding (6) is embodied as a heat shield.
7. Shielding (6) according to patent claim 1, characterized in that
the layers (8) are made of different materials.
8. Shielding (6) according to patent claim 1, characterized in that
the layers (8) comprise different thicknesses and/or numbers.
9-10. (canceled)
11. Shielding (6) according to patent claim 1, characterized in
that the layers (8) are tuned to one another in a
vibration-optimized manner.
12. Shielding (6) according to patent claim 1, characterized in
that the shielding (6) comprises a mounting frame (7) for different
functional layers.
Description
[0001] The invention relates to a shielding of a turbine housing or
casing of an aircraft engine against the radial escape of blade
fragments according to the preamble of the patent claim 1.
[0002] In conventional low-speed low-pressure turbines, the
so-called containment protection, i.e. the shielding of the housing
or casing against possible radially outwardly ejected blade parts
or blade fragments, is to be examined in connection with the
designing of the housing. Especially for the connection of the
low-pressure turbine (LPT) onto the turbine exhaust gas housing or
casing (Turbine Exhaust Case TEC), which is generally embodied as a
cast part, often only an examination of the wall thickness is
necessary. This examination generally determines that the wall
thickness of the connection LPT/TEC is sufficiently strongly
dimensioned also as a containment protection.
[0003] Such a shielding from the prior art is shown in a cutaway
portion view in FIG. 2. Thereby the low-pressure turbine 1 is shown
with turbine blades 2, which are arranged within a turbine housing
or casing 3. Thereby the turbine blades are arranged axially after
a compressor that is not shown and a combustion chamber that is not
shown, and are located on a turbine disk that rotates about the
engine axis. The turbine housing 3 is connected via a flange 5 with
the turbine exhaust gas channel 10. The turbine exhaust gas channel
10 of the prior art is embodied as a cast part, which also
comprises a containment function due to the existing material
thickness. That is to say, in the unlikely case of an engine damage
with loss of turbine blades or blade parts, the turbine exhaust gas
channel with containment function serves to prevent the escape of
the blade parts out of the engine housing and thereby to avoid
possible damages of the aircraft airframe. In FIG. 2, the impact
area that is determinative for the design is identified by the
straight lines enclosing an angle .alpha..
[0004] For achieving the required specifications, future engine
concepts need low-pressure turbines with high AN.sup.2, high
turbine inlet temperatures, and a compact short structure.
[0005] In high-speed low-pressure turbines for such modern engine
concepts, the containment protection is, however, a particular
design criterium, because the regular cast part thickness of the
turbine exhaust gas channel is no longer sufficient to prevent a
possible through-penetration of loose blade parts due to the higher
momentum of the blade parts. Therefore, according to the present
state, no material-, cost- and weight-optimized low-pressure
turbine/turbine exhaust gas channel (LPT/TEC) connection is
possible. Rather, the material selection and material thickness of
the LPT/TEC connection is determined by the required containment
thickness and not by the optimized LPT/TEC connection. The material
selection is also determined by the higher requirements for the
cast material in the containment area and is thereby made more
expensive.
[0006] Nonetheless, a containment solution in the area of the
low-pressure turbine is known from the U.S. Pat. No. 5,328,324.
Therein a glass fiber woven hose is proposed, which is laid onto a
carrier element in a multiply-folded configuration, quasi as a
collar, whereby the carrier element is located on the outer side of
the turbine housing above the low-pressure turbine. In that regard,
the glass fiber woven material is produced from a continuous fiber
and is heat resistant. The intactness of the continuous fiber is
decisive for the functioning of this containment protection. The
glass fiber woven hose is thereby dimensioned so that it lies
tightly on the carrier element. However, here no special solution
for the low-pressure turbine/turbine exhaust gas channel connection
is presented. Disadvantageous in this solution, on the one hand, is
the unfixed construction of the collar, which is highly sensitive
to external influences, for example mechanical influences,
moisture, etc. It is a further disadvantage that damages of the
continuous fiber of the glass fiber woven hose are not easily
noticed and can lead to a total failure of the containment
protection in case of need.
[0007] Therefore, it is the underlying object of the invention to
avoid the disadvantages of the known solutions of the prior art,
and to make available an improved solution for a containment
protection on the LPT/TEC connection especially of high-speed
low-pressure turbines.
[0008] This object is achieved according to the invention by a
multilayer shielding for an aircraft engine with features of the
patent claim 1. Advantageous embodiments and further developments
of the invention are set forth in the dependent claims.
[0009] The inventive shielding of a turbine housing of an aircraft
engine against radial escape of blade fragments, especially for a
high-speed low-pressure turbine, is characterized in that the
shielding is embodied as a rigid ring-shaped component of several
layers. Thereby the ring-shaped shielding can be arranged radially
within or outside of the turbine housing. In connection with
mounting on the turbine housing, the shielding can also direct
cooling air, for example from the fan stream flow, in a targeted
manner onto the outer skin of the housing. It is further possible
that the ring-shaped shielding consists of several segments,
whereby production and assembly are simplified. Due to the stiff
embodiment, the shielding is protected against external influences,
and can be embodied in a self-supporting manner.
[0010] An advantageous embodiment of the inventive shielding
provides that the shielding is arranged on the turbine exhaust gas
channel. By the decoupling of the containment function from the
design of the turbine exhaust gas channel, which is fabricated as a
cast part, the disadvantages of the prior art are avoided.
Especially the design of the turbine exhaust gas channel can be
carried out in a cost- and weight-optimized manner, i.e.
more-economical materials and material thicknesses can be utilized
here, in comparison to what would be the case with an integrated
containment function. The containment function is then exercised
alone by the ring-shaped multilayer shielding.
[0011] An advantageous embodiment of the inventive shielding
provides that the shielding is embodied as a forged component. This
makes possible a multilayer construction with selection of suitable
material layers. In that regard, on the one hand the strength is a
defining factor, as well as the temperatures present in the area of
the low-pressure turbine on the housing or on the LPT/TEC
connection. In that regard, the possibility of the temperature
expansion is to be taken into account for a shielding ring having
multiple parts in the circumferential direction.
[0012] A further advantageous embodiment of the inventive shielding
provides that the shielding is arranged within the turbine housing.
On the one hand this avoids interfering additional structural
components outside of the turbine housing, and on the other hand it
is hereby prevented that the housing or the LPT/TEC connection is
penetrated through in the case of a blade damage, whereby the costs
of an engine failure rise further.
[0013] Still another advantageous embodiment of the inventive
shielding provides that the shielding is embodied as a flow guide
element. This can be the case both for the application of the
shielding within or outside of the housing. Thereby additional flow
guide elements can be applied on the shielding, or alternatively
the shielding itself is formed or mounted in a flow-advantageous
manner.
[0014] Still a further advantageous embodiment of the inventive
shielding provides that the shielding is embodied as a heat shield.
This is especially necessary for the installation in the flow
channel, i.e. within the turbine housing. However, this can also be
suitable for the purpose for installation on the outer
circumference of the turbine housing, in order to prevent injuries
due to burns on hot engine components during maintenance work.
[0015] An advantageous embodiment of the inventive shielding
provides that the layers are constructed of different materials.
For example, highly heat resistant forgeable alloys come into
consideration as materials. Thereby the strength characteristics,
temperature expansion and weight of the shielding can be influenced
to the desired extent. This is especially expedient in the sense of
a weight- and cost-optimization.
[0016] An advantageous embodiment of the inventive shielding
provides that the layers comprise different thicknesses. Like the
material selection, the strength and the weight of the shielding
can also be optimized by the selection of the layer thickness, and
thereby the costs of the component can be reduced.
[0017] An advantageous embodiment of the inventive shielding
provides that the layers are adapted or tuned to one another in a
vibration-optimized manner. Thereby the layers of the multilayer
shielding ring are connected in a resonance-free manner in the
shielding housing. Hereby both the vibration characteristics of the
shielding alone, as well as the vibration characteristics of the
components coupled with the shielding, can be taken into
consideration. Furthermore, the variation of the vibration
characteristics due to fluid flow thereon and temperature expansion
can be taken into consideration in the design and adaptation or
tuning of the layers.
[0018] Finally an advantageous embodiment of the inventive
shielding provides that the shielding comprises an enclosure or
mounting frame for different functional layers. In that regard,
enclosure or mounting frame can also encompass a shielding housing
with which different layers are connected in a joint-technical
manner. In that regard, the ring-shaped layers can be encased or
enclosed or surrounded quasi from three sides, and if applicable
can also be received in a floating manner in the mounting
frame.
[0019] Further measures improving the invention are explained more
closely in the following together with the description of a
preferred example embodiment of the invention in connection with
the figures. It is shown by:
[0020] FIG. 1 an advantageous embodiment of the present invention,
schematically in a cutaway portion;
[0021] FIG. 2 a schematic partial sectional illustration of a
shielding of the prior art.
[0022] In the depicted figures, the same or similar components are
identified with the same reference numbers. Direction indications
refer to the axes of the aircraft engine.
[0023] FIG. 1 schematically shows in the manner of a cutaway
portion, an advantageous embodiment of an inventive shielding 6 on
a high-speed low-pressure turbine 1. In that regard, the compressor
which is not shown in the drawing and the combustion chamber, as
well as the high- and medium-pressure turbine which is similarly
not shown, are located in the drawing plane on the left hand side,
that is to say upstream with regard to the flow. Thereby the FIG. 1
shows a cutaway portion of a half-section.
[0024] In FIG. 1, a part of a turbine blade 2 is illustrated, which
is arranged within a turbine housing 3 that surrounds the turbine
stage in the circumferential direction. The turbine housing 3 is
connected with the turbine exhaust gas channel 4 or connected
thereto via a material-technically optimized flange connection
5.
[0025] The shielding 6 is arranged on the connection of the
low-pressure turbine 1 to the turbine exhaust gas channel 4 within
the turbine housing 3. A flange 9 protrudes inwardly in the radial
direction on the turbine exhaust gas channel 4, and the shielding 6
or the shielding housing 7 is flange-connected on the flange 9.
[0026] The shielding 6 or the containment ring, which is
illustrated L-shaped in section and is ring-shaped in the
circumferential direction, is embodied as a multilayer forged part
in the present example embodiment. In that regard, the two layers 8
of the shielding 6 are received in a shielding housing 7 and are
connected therewith in a forging-technological manner. Both the
type of the alloy as well as the layer thickness/number of layers
differ from one another in the two layers 8 shown in the example
embodiment. In that regard, the resonance-free shielding 6 in the
present example embodiment also comprises integrated heat-shield
and flow-guiding function in addition to the containment function.
The containment function is presently not integrated in the
connection of low-pressure turbine 1/turbine exhaust gas channel 4,
whereby this connection can be embodied as a weight-optimized cast
part.
[0027] The invention is not limited in its embodiment to the
preferred example embodiment set forth above. Rather, a number of
variants is conceivable, which also makes use of the solution
claimed in the patent claims, also in embodiments of a different
type.
* * * * *