U.S. patent number 3,708,242 [Application Number 05/093,655] was granted by the patent office on 1973-01-02 for supporting structure for the blades of turbomachines.
This patent grant is currently assigned to Societe Nationale D'Etude et de Construction de Moteurs D'Aviation. Invention is credited to Henri Bruneau, Gerhard Langner, Marcel Joseph Tournere.
United States Patent |
3,708,242 |
Bruneau , et al. |
January 2, 1973 |
SUPPORTING STRUCTURE FOR THE BLADES OF TURBOMACHINES
Abstract
In and for a fluid handling turbomachine having a relatively
rotatable bld stator and rotor, a blade supporting structure
comprising at least one corrugated annular element coaxial with the
axis of the machine and perforated with openings in each of which a
blade is fitted or embedded at one of its ends in order that the
blade body is disposed obliquely in relation to the general
direction of the corrugations in said corrugated element.
Inventors: |
Bruneau; Henri
(L'Hay-les-Roses, FR), Langner; Gerhard
(Dammarie-les-Lys, FR), Tournere; Marcel Joseph
(Paris, FR) |
Assignee: |
Societe Nationale D'Etude et de
Construction de Moteurs D'Aviation (Paris, FR)
|
Family
ID: |
9043899 |
Appl.
No.: |
05/093,655 |
Filed: |
November 30, 1970 |
Foreign Application Priority Data
Current U.S.
Class: |
415/209.4;
415/200 |
Current CPC
Class: |
F01D
9/044 (20130101); Y02T 50/60 (20130101); Y02T
50/672 (20130101) |
Current International
Class: |
F01D
9/04 (20060101); F04d 029/40 (); F04d 019/02 () |
Field of
Search: |
;415/53,190,191,193,216,217,218,219,172,214 |
References Cited
[Referenced By]
U.S. Patent Documents
|
|
|
3291382 |
December 1966 |
Blackhurst et al. |
3303998 |
February 1967 |
Koff et al. |
2724546 |
November 1955 |
Barrett, Jr. et al. |
|
Foreign Patent Documents
|
|
|
|
|
|
|
154,605 |
|
Jan 1954 |
|
CA |
|
1,028,444 |
|
May 1966 |
|
GB |
|
994,568 |
|
Jun 1965 |
|
GB |
|
Primary Examiner: Raduazo; Henry F.
Claims
We claim:
1. A turbomachine comprising at least one corrugated annular
support element which extends coaxially with the axis of the
machine, said corrugated element being perforated with a plurality
of elongated openings each of which extends lengthwise in a
direction oblique to the general direction of the corrugations in
said corrugated element and passes through at least two successive
corrugations, and a plurality of blades each having one of its ends
shaped to and fixedly fitted in a corresponding elongated opening
and secured to a plurality of said corrugations.
2. A turbomachine according to claim 1 wherein the general
direction of the corrugations in the corrugated element is
substantially parallel to the axis of the machine.
3. A turbomachine according to claim 1 wherein the general
direction of the corrugations in the corrugated element is
substantially circumferential.
4. A turbomachine according to claim 1 further comprising two skins
between which said corrugated element is located, whereby to form a
sandwich structure.
5. A turbomachine according to claim 1 comprising two corrugated
annular elements arranged in radially spaced concentric coaxial
relation to the axis of the machine, each such element being
perforated with a plurality of elongated openings, each opening in
a corrugated element extending lengthwise in a direction oblique to
the general direction of the corrugations in said corrugated
element and passing through at least two corrugations in said
element, each opening in one of said corrugated elements being in
radial registration with an opening in the other corrugated
element; and a plurality of blades each having its opposite ends
fitting in a corresponding pair of radially spaced registering
openings.
6. A turbomachine according to claim 5 wherein the corrugations in
the two concentric corrugated elements extend in the same general
direction.
7. A turbomachine according to claim 6 wherein the peaks of said
corrugations in each of said elements are generally uniformly
spaced apart and the spacing of the corrugations of the two
elements is different.
8. A turbomachine according to claim 6 wherein the corrugations in
the two respective corrugated elements are each generally of the
shape of a regular sinuous curve and the curves of the two elements
are out of phase.
9. A turbomachine according to claim 5 wherein the corrections in
the two corrugated elements respectively extend at right angles to
one another.
10. A turbomachine according to claim 1 wherein said annular
corrugated element comprises at least two annular sections arranged
in axial succeeding relation.
11. A turbomachine according to claim 1 further comprising a rigid
external housing, and means fixing said annular corrugated element
to the interior of said external housing.
12. A turbomachine according to claim 1 comprising at least two
corrugated annular elements arranged in radially adjacent
concentric coaxial relation to the axis of the machine, each such
element being perforated with a plurality of elongated openings,
each opening in a corrugated element extending lengthwise in a
direction oblique to the general direction of the corrugations in
said corrugated element and passing through at least two
corrugations in said element, each opening in one of said
corrugated elements being in radial registration with an opening in
at least one other corrugated element; and a plurality of blades
each having one of its ends fitting into at least two corresponding
registering openings in such radially adjacent corrugated
elements.
13. A turbomachine according to claim 12 wherein the corrugations
in the two concentric corrugated elements extend in the same
general direction.
14. A turbomachine according to claim 13 wherein the peaks of said
corrugations in each of said elements are generally uniformly
spaced apart and the spacing of the corrugations in the two
elements is different.
15. A turbomachine according to claim 13 wherein the corrugations
in the two respective corrugated elements are each generally of the
shape of a regular sinuous curve and the curves of the two elements
are out of phase.
16. A turbomachine according to claim 12 wherein the corrugations
in the two corrugated elements respectively extend at right angles
to one another.
Description
This invention relates to a supporting structure for blades, for
example, stator blades, in a fluid handling machine having a
relatively rotatable stator and rotor, hereinafter referred to as a
turbomachine, such as a compressor, a turbine or a pump.
A structure of this kind is often designed to withstand the key
stresses, in particular bending, to which the machine is subjected
and must, consequently, have a high stiffness.
Known structures employed for this purpose generally comprise an
external structure made up, for example, of a set of cylindrical or
frusto-conical casings assembled together axially, or again two
half-shells joined to one another along an axial plane. The stator
blades are fixed, at one of their ends, to said external structure,
in order to form one or more successive blade rows. It is often
advantageous, where the attainment of rigidity in the assembly is
concerned, to make this a rigid attachment, for example by
effecting the same by brazing or welding, so that it consequently
represents an embedded or restrained attachment. Equally, it is
possible to provide an internal structure to which the blades are
fixed by their other ends.
Because of their stiffness, the supporting structures thus far
known exhibit the drawback, in particular in the case where the
blades are fixed to them in embedded fashion, that they do not
provide adequate damping of the vibrations to which the blades are
subjected in operation and this makes for increased risk of fatigue
failure on the part of the blades. These structures are,
furthermore, relatively heavy and this is a particular drawback
where the turbomachine is designed for part of a gas-turbine power
plant for aviation applications.
The object of the invention is simultaneously to overcome these two
drawbacks.
In accordance with the invention, therefore, a blade-supporting
structure is designed to comprise at least one corrugated or
undulating annular element disposed coaxially relative to the axis
of the machine, said element being formed with openings in which
each of the blades is fitted at one of its ends, each of said
openings extending in a direction oblique to the general directions
of the folds or corrugations in said corrugated element and passing
through at least two successive corrugations. Preferably, said
corrugated element will be located between two skins or liners, so
as to form the core of a sandwich structure.
This structure, in the application with which the invention is
concerned, has the essential advantage of combining two apparently
contradictory qualities, namely a high structural rigidity, thus
enabling the supporting structure which it forms to withstand at
least some of the main stresses to which the machine is subjected,
and, on the other hand, a local flexibility which makes it possible
to damp the vibrations developing in the blades which are fixed to
said structure. This structure is, furthermore, much lighter than
the conventional supporting structures whilst having the same or
even better stiffness.
The corrugated element doing duty as the core of the structure can
be assembled so that the general direction of its folds or
corrugations is substantially parallel to the axis of the
turbomachine, this, in particular, making for high transverse
stiffness. Equally, however, it can be assembled in such a manner,
and in particular in the case where the supporting structure does
not have to withstand any substantial bending stresses, that the
general direction of its folds or corrugations is substantially
circumferential.
In accordance with one advantageous embodiment, the core of the
sandwich structure may comprise at least two generally concentric
corrugated elements, whose folds or corrugations extend either in
the same direction (advantageously with different or with a certain
difference in phase), or in two mutually perpendicular directions.
In this manner, simultaneously both the stiffness of the supporting
structure and its capacity to damp blade vibrations, are
improved.
In accordance with another arrangement of the invention, applicable
in particular to situations where considerations of weight are of
relatively minor importance, the supporting sandwich structure can
be fixed to the interior of a conventional rigid external housing
casing.
The description which now follows in relation to the accompanying
drawing will indicate how the invention may be carried into
practice.
IN THE DRAWINGS:
FIG. 1 is a schematic view, in section on an axial plane, of a part
of the stator of a turbomachine comprising a stator blade
supporting structure in accordance with the invention;
FIGS. 2 to 11 are schematic views relating to different embodiments
of said supporting structure or to its assembly;
FIGS. 1a, 2a and 5a are sectional views on the lines Ia-Ia, IIa-IIa
and Va-Va respectively, of the structures respectively illustrated
in FIGS. 1, 2 and 5;
FIGS. 12, 13 and 14 are explanatory diagrams relating to the
vibratory phenomena occurring in the turbomachine during
operation.
In FIGS. 1 and 1a, part of the stator of a turbomachine, such as an
axial-flow compressor for a turbojet engine, has been shown, and
indeed, more specifically, a supporting structure for a row of
stator blades 1. This structure comprises an external casing
section 2 and a internal casing section 3 each constituted, in part
at least, by a body of sandwich structure. Each of these sections
comprises an annular corrugated element 2a or 3a forming the core,
between two "skins" 3b, 3c or 3b, 3c. In this example, the general
direction of the folds or corrugations in the elements 2a and 3a is
substantially circumferential.
In order to enable an external casing section 2 to be assembled to
the next adjacent casing (not shown), there is fixed to each end of
the casing section, for example by welding and after previous local
pinching of the sandwich structure, a ring 4 formed with a groove
4a or with a tongue so that sealed attachment to an adjacent
complementary ring, belonging to the next casing section, can be
effected.
The sandwich structure of the internal casings 3 is likewise
pinched at its edges and bent in order to enable the attachment,
for example by welding or brazing, of sealing rings 5. These latter
operate in a manner known per se with labyrinth arrangements
carried by the rotor of the machine and shown in FIG. 11.
The external casing section 2 and the internal casing section 3 are
punched to fit the shape and setting angle of the blades 1. Thus,
elongated openings are formed each of which extends lengthwise in a
direction oblique to the general direction of the corrugations in
the corrugated elements 2a and 3a and passes through or across at
least two successive corrugations. In these elongated openings the
respective ends of the blades are fitted either by simply
press-fitting them in position, or by securing them by some other
method such as welding, brazing, diffusion or bonding. FIGs. 2 and
2a relate to a variant embodiment in accordance with which the
general direction of the folds or corrugations in the corrugated
elements 2a, 3a, is substantially parallel to the axis of the
turbomachine. In addition, the rings 4 of FIG. 1 are replaced by
flanges 6 attached, for example by welding, to the two previously
pinched ends of the casing section 2. The adjacent flanges of two
successive casing sections are advantageously assembled together by
bolts.
FIG. 3 relates to a variant embodiment in accordance with which the
external supporting structure comprises a plurality of casing
sections 2, cylindrical or frusto-conical in form, assembled
together axially. At least at one of its ends, the structure
terminates in an attached flange 7 similar (with the exception of a
shoulder 7a ) to the flanges 6 described in respect of FIG. 2. The
fixing together of the casing sections 2, on the other hand, is
effected by flanges 8 which are produced by pinching and folding
the sandwich structure itself, said flanges being bolted together
at 9.
FIG. 4 illustrates a variant embodiment which differs from the
arrangement shown in FIG. 1 simply by the fact that the tongued and
grooved rings 4 are replaced by rings 10 with interlocking teeth 11
so that the casing sections are centered and prevented from
rotating in relation to one another.
FIGS. 5 and 5a relate to a variant embodiment of the arrangement
shown in FIGS. 2 and 2a, in accordance with which the folds or
corrugations in the corrugated elements 2a and 3a extend
respectively in circumferential and axial directions. FIG. 5
likewise illustrates the fixing together of the successive flanges,
by bolts 12.
FIGS. 6 and 7 relate to variant embodiments of the invention in
which the core of the sandwich structure is made up of at least two
concentric corrugated annular elements 12a, 22a, separated from one
another by an intermediate "skin" 2d. In accordance with the
embodiment shown in FIG. 6, the folds or corrugations in said
elements extend in two mutually perpendicular directions, namely
circumferentially in the case of the element 12a and axially in the
case of the element 22a. In the embodiment shown in FIG. 7, these
folds extend in the same direction, for example circumferentially.
In this case, the spacing or the phase of the corrugations 12a will
advantageously be made different to that of the corrugations 22a,
this increasing the transverse rigidity of the supporting structure
assembly.
FIG. 8 illustrates a variant embodiment of the invention in
accordance with which the core of the sandwich structure comprises
three concentric corrugated annular elements 102a 112a, 122a,
separated from one another by intermediate skins 2e, 2f. As in the
case of FIG. 7, the spacing of the corrugations 112a differs from
that of those 102a and 122a, and these latter can themselves be so
arranged in relation to one another as to give a certain difference
in phase which is beneficial in increasing the stiffness of the
supporting structure assembly.
FIG. 9 relates to a variant embodiment of the invention in
accordance with which the corrugations of the element 2a, instead
of being simple as in the preceding cases, have a complex periodic
profile.
FIGS. 10 and 11 relate to two variant embodiments of the invention
in accordance with which the supporting structures 2 (sandwich
structures), for the stator blades, are fixed to the interior of a
conventional rigid housing constituted, for example, by a stack of
rings such as those marked 20.
In accordance with FIG. 10, the supporting structures 2 present
flanges 21, 22 fixed by bolts 23 to the housing rings 20.
In accordance with FIG. 11, the supporting structures 2 are fixed
to the housing on the one hand in the circumferential direction by
a system of splines 24, and on the other hand, in the axial
direction, by the axial stacking of said structures and the fitting
of retainer rings 25. This figure also shows the relative
arrangement of two rows of stator blades 1 and a row of rotor
blades 26 carried by a disc 27. Assembled on the latter there are
labyrinth arrangements 28 cooperating with the sealing rings 5.
FIGS. 12, 13 and 14 provide a highly schematic illustration of the
vibratory phenomena to which reference has been made
hereinbefore.
As those skilled in the art will realize, the stator blades 1,
exposed to vibrations of aerodynamic nature in the fluid flowing
through the turbomachine, themselves experience mechanical
vibrations for example in the fundamental mode 1a or at a harmonic,
for example the second harmonic 1b. The amplitudes of these
vibrations, illustrated in FIG. 12, have been exaggerated simply in
order to clarify the drawing. As FIGS. 13 and 14 show, the
elongations e are along the large axis B--B of the blade
profile.
The blades 1 are embedded at their respective ends in the
supporting structures 2, 3, namely the sandwich structures
described hereinbefore. FIG. 13 corresponds to the case in which
the corrugations in the material are axially disposed; this
material then has a high radial rigidity and, by contrast, a
certain degree of circumferential flexibility. FIG. 14 relates to
the case in which the corrugations in the material extend
circumferentially; its rigidity and flexibility are then
respectively circumferential and axial. In both cases and by virtue
of the substantially oblique disposition of the blades 1 in
relation to the axis of the turbomachine, there is at least one
component x or y, of the vibratory movement, in respect of which
the restrained end of the blade cooperates with an elastic
structure constituted by corrugated element 2a. GIven appropriate
dimensioning and assembly of said element, it can be arranged that
its resonance frequency is at all times far below that of the blade
with the result that, as those skilled in the art will appreciate,
the vibrations of the latter damped.
In the case where the sandwich structure utilized has two mutually
perpendicular corrugation directions as shown for example in FIG.
6, or again in the case where the directions of the corrugations in
external and internal supporting structures 2 and 3 respectively,
are at right-angles to one another (as shown for example in FIG.
5), the vibration-damping effect just referred to is still more
pronounced.
The main stresses to which the turbomachine is subjected being
generally axial and radial, it may be a useful feature to use for
the external supporting structure a sandwich material incorporating
at least one element with axial corrugations, as shown in FIGS. 2
and 6, at any rate in the case where it is necessary to take into
account the internal arrangement of the corrugations in order to
achieve a stiff stator assembly. On the other hand, where said
stiffness is provided anyway by a conventional external casing, as
shown in FIGS. 10 and 11, the choice of the type of corrugations
depends essentially upon its anti-vibration properties.
It will be apparent that the embodiments described are open to
modification in various ways without departing from the scope of
the invention as defined in the appended claims. Thus, in
particular, the stator blades supporting structures which have been
illustrated in the form of casing sections designed for axial
assembly, could be replaced by half-shells or shell segments
assembled together along axial lines.
* * * * *